U.S. patent application number 13/131416 was filed with the patent office on 2011-09-22 for combustion methods, apparatuses and systems.
Invention is credited to Nikolai Novikov, Norman Salansky.
Application Number | 20110229834 13/131416 |
Document ID | / |
Family ID | 42225174 |
Filed Date | 2011-09-22 |
United States Patent
Application |
20110229834 |
Kind Code |
A1 |
Salansky; Norman ; et
al. |
September 22, 2011 |
Combustion Methods, Apparatuses and Systems
Abstract
Fuel combustion and waste conversion can be achieved by passing
an axial vortex stream in a combustion chamber in a first linear
direction, and passing a peripheral vortex stream as a counterflow
to the axial vortex stream in a direction generally opposing the
first linear direction. The peripheral and axial vortex streams can
be merged so that a first fuel and oxidant in the streams at least
partially combust to form a product stream, the product stream
moving in the first linear direction to an outlet at the second end
of the combustion chamber. Vortices can be generated by
tangentially introducing fluid streams into the one or more
chambers. A primary chamber, a main chamber, and an afterburner
chamber can be connected in series. Second fuel and pre-chambers
can be used to stabilize and enhance combustion. Reagents can be
introduced to refine gaseous streams including pollutants.
Inventors: |
Salansky; Norman; (Toronto,
CA) ; Novikov; Nikolai; (Jaroslavskaya Province,
RU) |
Family ID: |
42225174 |
Appl. No.: |
13/131416 |
Filed: |
November 26, 2009 |
PCT Filed: |
November 26, 2009 |
PCT NO: |
PCT/CA09/01717 |
371 Date: |
May 26, 2011 |
Related U.S. Patent Documents
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Application
Number |
Filing Date |
Patent Number |
|
|
61118300 |
Nov 26, 2008 |
|
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|
Current U.S.
Class: |
431/10 ;
431/185 |
Current CPC
Class: |
F23G 5/16 20130101; F23D
2900/14241 20130101; F23C 6/04 20130101; F23G 2201/303 20130101;
F23C 3/006 20130101; F23G 5/32 20130101; F23G 7/065 20130101; Y02E
20/12 20130101; F23D 14/62 20130101; F23G 5/0276 20130101; F23G
2201/701 20130101 |
Class at
Publication: |
431/10 ;
431/185 |
International
Class: |
F23K 5/00 20060101
F23K005/00 |
Claims
1-92. (canceled)
93. A combustion method comprising: a) generating an axial vortex
stream, and passing the axial vortex stream between a first end and
a second end of a main chamber in a first linear direction; b)
generating a peripheral vortex stream, and passing the peripheral
vortex stream as a counterflow to the axial vortex stream in a
direction generally opposing the first linear direction; and c)
merging the peripheral vortex stream with the axial vortex stream
to form a product stream, the product stream moving in the first
linear direction to an outlet at the second end of the main
chamber.
94. The method of claim 93, wherein the axial vortex stream
includes a first fuel and the peripheral vortex stream includes a
first oxidant, and the first fuel of the axial vortex stream and
the first oxidant of the peripheral vortex stream at least
partially combust to form the product stream.
95. The method of claim 94, wherein the axial and peripheral vortex
streams are generated having the same rotational polarity.
96. The method of claim 95, wherein, in step (c), the peripheral
vortex stream is merged with the axial vortex stream proximate to
the first end of the combustion chamber.
97. The method of claim 96, wherein, in step (b), the peripheral
vortex stream is generated by tangentially introducing a first
stream to the combustion chamber.
98. The method of claim 97, wherein the first stream is introduced
to form the peripheral vortex stream proximate to the second end of
the combustion chamber.
99. The method of claim 98, wherein the first stream includes the
oxidant.
100. The method of claim 99, wherein the first stream includes a
second fuel.
101. The method of claim 96, wherein the first stream includes a
first pre-chamber product stream from at least one first
pre-chamber, the at least one first pre-chamber including a source
of a second fuel, a source of the oxidant, and an ignition source,
wherein the second fuel and the oxidant have at least partially
combusted in the at least one first pre-chamber to form the first
pre-chamber product stream.
102. The method of claim 101, wherein the second fuel has a higher
heat of combustion than the first fuel.
103. The method of claim 94, wherein the axial vortex stream is
formed upstream from an inlet at the first end of the main chamber,
and the axial vortex stream is passed through the inlet.
104. The method of claim 103, wherein, in step (a), the axial
vortex stream is generated by passing a second stream, and
tangentially introducing a third stream to combine with the second
stream.
105. The method of claim 104, wherein the second stream includes
the first fuel and the third stream includes the oxidant.
106. The method of claim 105, wherein the third stream includes a
second pre-chamber product stream from at least one second
pre-chamber, the at least one second pre-chamber including a source
of a second fuel, a source of the oxidant, and an ignition source,
wherein the second fuel and the oxidant have at least partially
combusted in the at least one second pre-chamber to form the second
pre-chamber product stream.
107. The method of claim 106, wherein the second fuel has a higher
heat of combustion than the first fuel.
108. The method of claim 93, further comprising cooling the product
stream to avoid recombination of molecules.
109. The method of claim 108, wherein a fourth gas stream is
introduced to the product stream downstream from the outlet to cool
the product stream.
110. The method of claim 109, wherein the fourth gas stream is
tangentially introduced to the product stream.
111. The method of claim 94, wherein velocities of the axial and
peripheral vortex streams are controlled to provide substantially
full combustion of the first fuel and the oxidant.
112. The method of claim 111, wherein compositions of the axial and
peripheral vortex streams are controlled so as to provide a
stoichiometric excess of oxidant relative to the first and second
fuels.
113. The method of claim 112, further comprising monitoring
combustion data representing at least one of temperature, fuel
quantity, air quantity, and pressure, and using the data as
feedback to control the axial and peripheral vortex streams.
114. The method of claim 113, wherein the data is gathered using a
microprocessor, and the microprocessor calculates optimum control
parameters using a mathematical combustion model.
115. An apparatus comprising a housing including interior
sidewalls, the sidewalls defining a main chamber, the main chamber
including an inlet, an outlet, and first and second ends, the inlet
for passing an axial vortex stream to the first end, the axial
vortex stream including a first fuel, the second end including an
outlet for expelling a product stream, the main chamber including
at least one first channel disposed between the first and second
ends, the at least one first channel for introducing fluid into the
main chamber to form a peripheral vortex stream including an
oxidant as a counterflow to the axial vortex stream.
116. The apparatus of claim 115, wherein the interior walls of the
main chamber are generally cylindrical and converge in a flow
direction of the axial vortex stream from the first end to the
second end.
117. The apparatus of claim 116, further comprising a merging
surface within the main chamber for merging the peripheral and
axial vortex streams.
118. The apparatus of claim 117, wherein the merging surface is
located along the sidewalls of the main chamber at the first end
thereof.
119. The apparatus of claim 118, wherein the merging surface is
frusto-toroidal in shape.
120. The apparatus of claim 115, wherein the inlet comprises a
cylindrical sleeve extending into the main chamber, the sleeve for
directing flow of the axial vortex stream into the main
chamber.
121. The apparatus of claim 120, wherein the sleeve is
frusto-conical in shape.
122. The apparatus of claim 121, wherein the sleeve includes a
plurality of apertures.
123. The apparatus of claim 115, further comprising a first
injection zone for producing a first stream, the first injection
zone in fluid communication with the at least one first channel for
providing the first stream to the main chamber, the first stream
forming the peripheral vortex stream.
124. The apparatus of claim 123, wherein the first injection zone
is generally annular in shape and extends radially around a
circumference of the main chamber.
125. The apparatus of claim 124, wherein the first injection zone
includes a plurality of swirl vanes for directing rotational fluid
flow.
126. The apparatus of claim 123, wherein the first injection zone
includes an oxidant source for injecting an oxidant to form at
least a portion of the first stream.
127. The apparatus of claim 126, wherein the oxidant source is
tangentially aligned within the first injection zone.
128. The apparatus of claim 123, wherein the first injection zone
includes a fuel source for injecting a second fuel to form at least
a portion of the first stream.
129. The apparatus of claim 128, wherein the fuel source is
tangentially aligned within the first injection zone.
130. The apparatus of claim 123, wherein the first injection zone
includes at least one pre-chamber, the at least one pre-chamber
including a fuel source for supplying a second fuel, an oxidant
source for supplying an oxidant, an igniter, and an outlet for
exhausting a second pre-chamber product stream.
131. The apparatus of claim 130, wherein the outlet of the at least
one pre-chamber is tangentially aligned within the first injection
zone.
132. The apparatus of claim 115, further comprising a primary
chamber in fluid communication with the inlet of the main chamber,
the primary chamber including a primary inlet for receiving a
second stream, and at least one second channel for supplying a
third stream, the second and third streams mixing in the primary
chamber to form the axial vortex stream.
133. The apparatus of claim 132, wherein the primary inlet is
connected to a source of the first fuel, the first fuel forming at
least a portion of the second stream.
134. The apparatus of claim 133, further comprising a second
injection zone for producing the third stream, the second injection
zone in communication with the at least one second channel for
providing the third stream to the primary chamber.
135. The apparatus of claim 134, wherein the second injection zone
is generally annular in shape and extends radially around a
circumference of the primary chamber.
136. The apparatus of claim 135, wherein the second injection zone
includes a plurality of swirl vanes for directing rotational fluid
flow.
137. The apparatus of claim 134, wherein the second injection zone
includes an oxidant source for injecting an oxidant to form at
least a portion of the third stream.
138. The apparatus of claim 137, wherein the oxidant source is
tangentially aligned within the second injection zone.
139. The apparatus of claim 134, wherein the second injection zone
includes at least one pre-chamber, the at least one pre-chamber
including a fuel source for supplying a second fuel, an oxidant
source for supplying an oxidant, an igniter, and a pre-chamber
outlet for exhausting a second pre-chamber product stream.
140. The apparatus of claim 139, wherein the pre-chamber outlet of
the at least one second pre-chamber is tangentially aligned within
the second injection zone.
141. The apparatus of claim 115, further comprising an afterburner
chamber in fluid communication with the outlet of the main chamber,
the afterburner chamber for receiving the product stream and
cooling the product stream.
142. The apparatus of claim 141, wherein the afterburner chamber
includes at least one third channel for introducing a fourth stream
to the product stream, the fourth stream comprising a coolant
fluid.
143. The apparatus of claim 142, further comprising a third
injection zone for producing the fourth stream, the third injection
zone in fluid communication with the at least one third channel for
providing the fourth stream to the afterburner chamber.
144. The apparatus of claim 143, wherein the third injection zone
is generally annular in shape and extends radially around a
circumference of the afterburner chamber.
145. The apparatus of claim 144, wherein the third injection zone
includes a plurality of swirl vanes for directing rotational fluid
flow.
146. A method of gas refinement, comprising: d) providing an axial
stream, and passing the axial stream in a main chamber in a first
linear direction from a first end towards a second end, the axial
stream including at least one pollutant; e) generating a first
peripheral vortex stream, the peripheral vortex stream including at
least one reagent; and f) merging the first peripheral vortex
stream with the axial stream to form a product stream, the at least
one pollutant and the at least one reagent at least partially
reacting in the product stream, the product stream moving in the
first linear direction to an outlet at the second end of the main
chamber.
147. The method of claim 146, wherein the at least one pollutant is
selected from the group consisting of SO.sub.2, NO.sub.x and
CO.sub.2.
148. The method of claim 147, wherein the at least one first
reagent is selected from the group consisting of NH.sub.3,
CO(NH.sub.2).sub.2, C, H.sub.2O and CaO.
149. The method of claim 146, wherein the at least one pollutant is
selected from the group consisting of SO.sub.2 and NO.sub.2, and
the at least one reagent is selected from the group consisting of
NH.sub.3 and CO(NH.sub.2).sub.2.
150. The method of claim 149, wherein the peripheral vortex stream
further comprises at least one second reagent selected from the
group consisting of NaHCO.sub.3, CaCO.sub.3, CaO and
Ca(OH).sub.2.
151. The method of claim 146, wherein the at least one pollutant
comprises CO.sub.2, and the at least one reagent is selected from
the group consisting of NH.sub.3, C, H.sub.2O and CaO.
152. The method of claim 146, wherein, prior to step (c), the
peripheral vortex stream is passed as a counterflow to the axial
vortex stream in a direction generally opposing the first linear
direction.
153. The method of claim 152 wherein, in step (c), the peripheral
vortex stream is merged with the axial vortex stream proximate to
the first end of the main chamber.
154. The method of claim 146, wherein, in step (b), the peripheral
vortex stream is generated by tangentially introducing a first
stream to the combustion chamber, the first stream including the at
least one first reagent.
155. The method of claim 154, wherein, in step (b), the first
stream is tangentially introduced proximate to a source of the at
least one first reagent.
156. The method of claim 155, wherein the first stream comprises an
oxidant.
157. The method of claim 156, further comprising introducing a fuel
to the first stream.
158. The method of claim 146, wherein, in step (b), the first
peripheral vortex stream is generated at least in part by
tangentially introducing a first pre-chamber product stream from at
least one first pre-chamber, the at least one first pre-chamber
including a source of a fuel, a source of the oxidant, and an
ignition source, the fuel and the oxidant at least partially
combusting in the at least one first pre-chamber to form the first
pre-chamber product stream.
159. The method of claim 146, further comprising cooling the
product stream to avoid recombination of molecules.
160. An apparatus for gas refinement, comprising: g) a housing
including interior sidewalls, the sidewalls defining a main
chamber, the main chamber including first and second ends and an
inlet for introducing an axial stream that passes in a first linear
direction from the first end to the second end of the main chamber,
the axial stream including at least one pollutant, the second end
including an outlet for expelling a product stream; h) at least one
first channel disposed between the first and second ends of the
main chamber; and i) a first injection zone for producing a first
stream, the first injection zone including a source of at least one
first reagent, the first injection zone in fluid communication with
the at least one first channel for providing the first stream to
the main chamber to form a peripheral vortex stream, the at least
one pollutant in the axial stream and the at least one reagent in
the peripheral vortex stream at least partially reacting in the
product stream.
161. The apparatus of claim 160, wherein the at least one pollutant
is selected from the group consisting of SO.sub.2 and NO.sub.2, and
the at least one reagent is selected from the group consisting of
NH.sub.3 and CO(NH.sub.2).sub.2.
162. The apparatus of claim 160, wherein the at least one pollutant
is CO.sub.2, and the at least one reagent is selected from the
group consisting of NH.sub.3, C, H.sub.2O and CaO.
163. The apparatus of claim 160, wherein the first injection zone
is generally annular in shape and extends radially around a
circumference of the main chamber.
164. The apparatus of claim 163, wherein the first injection zone
includes a plurality of swirl vanes for directing rotational fluid
flow.
165. The apparatus of claim 164, wherein the first injection zone
includes an oxidant source for injecting an oxidant to form at
least a portion of the first stream.
166. The apparatus of claim 165, wherein the oxidant source is
tangentially aligned within the first injection zone.
167. The apparatus of claim 166, wherein the oxidant source is
proximate to the source of the at least one first reagent.
168. The apparatus of claim 160, wherein the first injection zone
includes a fuel source for injecting a fuel to form at least a
portion of the first stream.
169. The apparatus of claim 160, wherein the first injection zone
includes at least one pre-chamber, the at least one pre-chamber
including a fuel source for supplying a second fuel, an oxidant
source for supplying an oxidant, an igniter, and an outlet for
exhausting a second pre-chamber product stream.
170. The apparatus of claim 160, further comprising an afterburner
chamber in fluid communication with the outlet of the main chamber,
the afterburner chamber for receiving the product stream and
cooling the product stream.
Description
CROSS REFERENCE TO RELATED APPLICATIONS
[0001] This application claims the benefit of U.S. Provisional
Application No. 61/118,300 filed Nov. 26, 2008, which is hereby
incorporated by reference in its entirety.
FIELD
[0002] This specification relates generally to apparatuses, systems
and methods for fuel combustion. This specification also relates
generally to apparatuses, systems and methods for waste conversion,
pollution control and gas refinement.
BACKGROUND
[0003] The following paragraphs are not an admission that anything
discussed in them is prior art or part of the knowledge of persons
skilled in the art.
[0004] U.S. Pat. No. 3,630,651 to Fay et al. discloses a dual
vortex gaseous burner having a vortex tube, a separator tube, a
pair of vortex chambers and an igniter. An oxidizer is injected
tangentially through a jet in one of the vortex chambers forming a
primary vortex between the separator tube and the vortex tube wall,
while a fuel is injected tangentially through a jet in the other
vortex chamber forming a secondary vortex between the igniter and
the separator tube. An electric spark from the igniter produces
ignition of the oxidizer and fuel at the boundary between the two
vortices.
[0005] U.S. Pat. No. 5,055,030 to Schirmer discloses a method and
apparatus for recovering hydrocarbons in which a first toroidal
vortex of fuel and a combustion supporting gas is created with its
center adjacent the axis of an elongated combustor; a second
toroidal vortex of combustion supporting gas is generated between
the first toroidal vortex; the fuel is burned in the presence of
the combustion supporting gas to produce a fuel gas at the
downstream end of the combustor; water is introduced into the flue
gas adjacent the downstream end of the combustion to produce a
mixture of flue gas and water; a major portion of the water is
vaporized in a vaporizor to produce a mixture of flue gas and
steam; and the mixture of flue gas and steam is injected into a
hydrocarbon bearing formation.
INTRODUCTION
[0006] The following introduction is intended to introduce the
reader to this specification. One or more inventions may reside in
a combination or sub-combination of the apparatus elements or
method steps described below or in other parts of this document.
The applicant(s) does not waive or disclaim rights to any invention
or inventions disclosed in this specification merely by not
describing such other invention or inventions in the claims.
[0007] In an aspect of this specification, a combustion method
comprises: generating an axial vortex stream, and passing the axial
vortex stream between a first end and a second end of a main
chamber in a first linear direction; generating a peripheral vortex
stream, and passing the peripheral vortex stream as a counterflow
to the axial vortex stream in a direction generally opposing the
first linear direction; and merging the peripheral vortex stream
with the axial vortex stream to form a product stream, the product
stream moving in the first linear direction to an outlet at the
second end of the main chamber.
[0008] The axial vortex stream can include a first fuel and the
peripheral vortex stream can include a first oxidant. The first
fuel of the axial vortex stream and the first oxidant of the
peripheral vortex stream can at least partially combust to form the
product stream. The axial and peripheral vortex streams can be
generated having the same rotational polarity. The peripheral
vortex stream can be merged with the axial vortex stream proximate
to the first end of the combustion chamber.
[0009] The peripheral vortex stream can be generated by
tangentially introducing a first stream to the combustion chamber.
The first stream can be introduced to form the peripheral vortex
stream proximate to the second end of the combustion chamber. The
first stream can include the oxidant. The first stream can include
a second fuel. The first stream can include a first pre-chamber
product stream from at least one first pre-chamber. The at least
one first pre-chamber can include a source of a second fuel, a
source of the oxidant, and an ignition source. The second fuel and
the oxidant can have at least partially combusted in the at least
one first pre-chamber to form the first pre-chamber product stream.
The second fuel can have a higher heat of combustion than the first
fuel.
[0010] The axial vortex stream can be formed upstream from an inlet
at the first end of the main chamber, and the axial vortex stream
can be passed through the inlet. The axial vortex stream can be
generated by passing a second stream, and tangentially introducing
a third stream to combine with the second stream. The second stream
can include the first fuel and the third stream includes the
oxidant. The third stream can include a second pre-chamber product
stream from at least one second pre-chamber. The at least one
second pre-chamber can include a source of a second fuel, a source
of the oxidant, and an ignition source. The second fuel and the
oxidant can have at least partially combusted in the at least one
second pre-chamber to form the second pre-chamber product stream.
The second fuel can have a higher heat of combustion than the first
fuel.
[0011] The method can further comprise cooling the product stream
to avoid recombination of molecules. A fourth gas stream can be
introduced to the product stream downstream from the outlet to cool
the product stream. The fourth gas stream can be tangentially
introduced to the product stream.
[0012] Velocities of the axial and peripheral vortex streams can be
controlled to provide substantially full combustion of the first
fuel and the oxidant. Compositions of the axial and peripheral
vortex streams can be controlled so as to provide a stoichiometric
excess of oxidant relative to the first and second fuels. The
method can further comprise monitoring combustion data representing
at least one of temperature, fuel quantity, air quantity, and
pressure, and using the data as feedback to control the axial and
peripheral vortex streams. The data can be gathered using a
microprocessor, and the microprocessor can calculate optimum
control parameters using a mathematical combustion model.
[0013] In another aspect of this specification, an apparatus
comprises a housing including interior sidewalls, the sidewalls
defining a main chamber, the main chamber including an inlet, an
outlet, and first and second ends, the inlet for passing an axial
vortex stream to the first end, the axial vortex stream including a
first fuel, the second end including an outlet for expelling a
product stream, the main chamber including at least one first
channel disposed between the first and second ends, the at least
one first channel for introducing fluid into the main chamber to
form a peripheral vortex stream including an oxidant as a
counterflow to the axial vortex stream.
[0014] The interior walls of the main chamber can be generally
cylindrical and converge in a flow direction of the axial vortex
stream from the first end to the second end. The apparatus can
further comprise a merging surface within the main chamber for
merging the peripheral and axial vortex streams. The merging
surface can be located along the sidewalls of the main chamber at
the first end thereof. The merging surface can be frusto-toroidal
in shape. The inlet can comprise a cylindrical sleeve extending
into the main chamber, the sleeve for directing flow of the axial
vortex stream into the main chamber. The sleeve can be
frusto-conical in shape. The sleeve can include a plurality of
apertures.
[0015] The apparatus can further comprise a first injection zone
for producing a first stream, the first injection zone in fluid
communication with the at least one first channel for providing the
first stream to the main chamber, the first stream forming the
peripheral vortex stream. The first injection zone can be generally
annular in shape and extend radially around a circumference of the
main chamber. The first injection zone can include a plurality of
swirl vanes for directing rotational fluid flow. The first
injection zone can include an oxidant source for injecting an
oxidant to form at least a portion of the first stream. The oxidant
source can be tangentially aligned within the first injection zone.
The first injection zone can include a fuel source for injecting a
second fuel to form at least a portion of the first stream. The
fuel source can be tangentially aligned within the first injection
zone. The first injection zone can include at least one
pre-chamber, the at least one pre-chamber including a fuel source
for supplying a second fuel, an oxidant source for supplying an
oxidant, an igniter, and an outlet for exhausting a second
pre-chamber product stream. The outlet of the at least one
pre-chamber can be tangentially aligned within the first injection
zone.
[0016] The apparatus can further comprise a primary chamber in
fluid communication with the inlet of the main chamber. The primary
chamber can include a primary inlet for receiving a second stream,
and at least one second channel for supplying a third stream, the
second and third streams mixing in the primary chamber to form the
axial vortex stream. The primary inlet can be connected to a source
of the first fuel, the first fuel forming at least a portion of the
second stream. The apparatus can further comprise a second
injection zone for producing the third stream, the second injection
zone in communication with the at least one second channel for
providing the third stream to the primary chamber. The second
injection zone can be generally annular in shape and extend
radially around a circumference of the primary chamber. The second
injection zone can include a plurality of swirl vanes for directing
rotational fluid flow. The second injection zone can include an
oxidant source for injecting an oxidant to form at least a portion
of the third stream. The oxidant source can be tangentially aligned
within the second injection zone. The second injection zone can
include at least one pre-chamber. The at least one pre-chamber can
include a fuel source for supplying a second fuel, an oxidant
source for supplying an oxidant, an igniter, and a pre-chamber
outlet for exhausting a second pre-chamber product stream. The
pre-chamber outlet of the at least one second pre-chamber can be
tangentially aligned within the second injection zone.
[0017] The apparatus can further comprise an afterburner chamber in
fluid communication with the outlet of the main chamber, the
afterburner chamber for receiving the product stream and cooling
the product stream. The afterburner chamber can include at least
one third channel for introducing a fourth stream to the product
stream, the fourth stream comprising a coolant fluid. The apparatus
can further comprise a third injection zone for producing the
fourth stream, the third injection zone in fluid communication with
the at least one third channel for providing the fourth stream to
the afterburner chamber. The third injection zone can be generally
annular in shape and extend radially around a circumference of the
afterburner chamber. The third injection zone can include a
plurality of swirl vanes for directing rotational fluid flow.
[0018] In another aspect of this specification, a combustion system
comprises: a source of a first fuel; a primary chamber connected to
the source of the first fuel, the primary chamber receiving a
second stream including the first fuel, the primary chamber adapted
to tangentially introduce a third stream into the second stream to
generate an axial vortex stream; and a main chamber connected to
the primary chamber, the main chamber including an inlet for
receiving the axial vortex stream from the primary chamber, the
main chamber adapted to tangentially introduce a first stream to
generate a peripheral vortex stream, the peripheral vortex stream
moving as a counterflow to the axial vortex stream, the first
stream including an oxidant, the first fuel in the axial vortex
stream and the oxidant in the peripheral vortex stream at least
partially combusting to form a product stream, the main chamber
including an outlet for expelling the product stream.
[0019] In the main chamber, the first stream can be introduced
adjacent to the outlet. At least a portion of the peripheral vortex
stream can flow along a substantial length of the main chamber from
the outlet to the inlet. The first stream can include the oxidant.
The first stream can include a second fuel. The first stream can
include a first pre-chamber product stream. The first pre-chamber
product stream can include a second fuel, the second fuel at least
partially combusted in the first pre-chamber product stream. The
third stream can include the oxidant. The third stream can include
a second fuel. The third stream can include a second pre-chamber
product stream. The second pre-chamber product stream can include a
second fuel, the second fuel at least partially combusted in the
second pre-chamber product stream. The second fuel can have a
higher heat of combustion than the first fuel.
[0020] The system can further comprise an afterburner chamber in
fluid communication with the outlet of the main chamber, the
afterburner chamber adapted to inject a fourth stream into the
product stream, the fourth stream including a coolant fluid.
[0021] The system can further comprise a plurality of sensors for
monitoring combustion data representing at least one of
temperature, fuel quantity, air quantity, and pressure. The system
can further comprise a microprocessor for collecting the data, the
microprocessor adapted to use the data as feedback to control the
axial and peripheral vortex streams. The microprocessor can be
adapted to calculate optimum control parameters using a
mathematical combustion model.
[0022] In another aspect of this specification, a method of gas
refinement comprises: providing an axial stream, and passing the
axial stream in a main chamber in a first linear direction from a
first end towards a second end, the axial stream including at least
one pollutant; generating a first peripheral vortex stream, the
peripheral vortex stream including at least one reagent; and
merging the first peripheral vortex stream with the axial stream to
form a product stream, the at least one pollutant and the at least
one reagent at least partially reacting in the product stream, the
product stream moving in the first linear direction to an outlet at
the second end of the main chamber.
[0023] The at least one pollutant can be selected from the group
consisting of SO.sub.2, NO.sub.x and CO.sub.2. The at least one
first reagent can be selected from the group consisting of
NH.sub.3, CO(NH.sub.2).sub.2, C, H.sub.2O and CaO. The at least one
pollutant is selected from the group consisting of SO.sub.2 and
NO.sub.2, and the at least one reagent is selected from the group
consisting of NH.sub.3 and CO(NH.sub.2).sub.2. The at least one
pollutant comprises CO.sub.2, and the at least one reagent is
selected from the group consisting of NH.sub.3, C, H.sub.2O and
CaO. The peripheral vortex stream further comprises at least one
second reagent selected from the group consisting of NaHCO.sub.3,
CaCO.sub.3, CaO and Ca(OH).sub.2.
[0024] The peripheral vortex stream can be passed as a counterflow
to the axial vortex stream in a direction generally opposing the
first linear direction. The peripheral vortex stream can be merged
with the axial vortex stream proximate to the first end of the main
chamber. The peripheral vortex stream can be generated by
tangentially introducing a first stream to the combustion chamber,
the first stream including the at least one first reagent. The
first stream can be tangentially introduced proximate to a source
of the at least one first reagent. The first stream can comprise an
oxidant. The method can further comprise introducing a fuel to the
first stream. The first peripheral vortex stream can be generated
at least in part by tangentially introducing a first pre-chamber
product stream from at least one first pre-chamber. The at least
one first pre-chamber can include a source of a fuel, a source of
the oxidant, and an ignition source, the fuel and the oxidant at
least partially combusting in the at least one first pre-chamber to
form the first pre-chamber product stream. The method can further
comprise cooling the product stream to avoid recombination of
molecules.
[0025] In yet another aspect of this specification, an apparatus
for gas refinement comprises: a housing including interior
sidewalls, the sidewalls defining a main chamber, the main chamber
including first and second ends and an inlet for introducing an
axial stream that passes in a first linear direction from the first
end to the second end of the main chamber, the axial stream
including at least one pollutant, the second end including an
outlet for expelling a product stream; at least one first channel
disposed between the first and second ends of the main chamber; and
a first injection zone for producing a first stream, the first
injection zone including a source of at least one first reagent,
the first injection zone in fluid communication with the at least
one first channel for providing the first stream to the main
chamber to form a peripheral vortex stream, the at least one
pollutant in the axial stream and the at least one reagent in the
peripheral vortex stream at least partially reacting in the product
stream.
[0026] The at least one pollutant can be selected from the group
consisting of SO.sub.2 and NO.sub.2, and the at least one reagent
can be selected from the group consisting of NH.sub.3 and
CO(NH.sub.2).sub.2. The at least one pollutant can be CO.sub.2, and
the at least one reagent can be selected from the group consisting
of NH.sub.3, C, H.sub.2O and CaO.
[0027] The first injection zone can be generally annular in shape
and extend radially around a circumference of the main chamber. The
third injection zone can include a plurality of swirl vanes for
directing rotational fluid flow. The first injection zone can
include an oxidant source for injecting an oxidant to form at least
a portion of the first stream. The oxidant source can be
tangentially aligned within the first injection zone. The oxidant
source can be proximate to the source of the at least one first
reagent. The first injection zone can include a fuel source for
injecting a fuel to form at least a portion of the first stream.
The first injection zone can include at least one pre-chamber. The
at least one pre-chamber can include a fuel source for supplying a
second fuel, an oxidant source for supplying an oxidant, an
igniter, and an outlet for exhausting a second pre-chamber product
stream.
[0028] The apparatus can further comprise an afterburner chamber in
fluid communication with the outlet of the main chamber, the
afterburner chamber for receiving the product stream and cooling
the product stream.
DRAWINGS
[0029] The skilled person in the art will understand that the
drawings, described below, are for illustration purposes only. The
drawings are not intended to limit the scope of the applicant's
teachings in any way.
[0030] FIG. 1 is a schematic diagram of an apparatus according to a
first example;
[0031] FIG. 2 is a sectional diagram of the apparatus of FIG.
1;
[0032] FIGS. 3 and 4 are sectional diagrams of the apparatus of
FIG. 2 along lines A-A and B-B, respectively;
[0033] FIGS. 5 and 6 are sectional diagrams of the apparatus of
FIG. 2 illustrating velocities of fluid flow;
[0034] FIGS. 7A, 7B and 7C are graphs of temperature, pressure and
tangential velocity of fluid flow, respectively, of the apparatus
of FIGS. 5 and 6 along lines a-a, b-b, c-c, d-d and g-g;
[0035] FIG. 8 is a schematic diagram of an apparatus according to a
second example;
[0036] FIG. 9 is a sectional diagram of the apparatus of FIG.
8;
[0037] FIGS. 10 and 11 are sectional diagrams of the apparatus of
FIG. 9 along lines A-A and B-B, respectively;
[0038] FIG. 12 is a schematic diagram of an apparatus according to
a third example;
[0039] FIG. 13 is a sectional diagram of the apparatus of FIG.
12;
[0040] FIGS. 14 and 15 are sectional diagrams of the apparatus of
FIG. 13 along lines A-A and B-B, respectively;
[0041] FIG. 16 is a schematic diagram of an apparatus according to
a fourth example;
[0042] FIG. 17 is a sectional diagram of the apparatus of FIG.
16;
[0043] FIGS. 18 and 19 are sectional diagrams of the apparatus of
FIG. 17 along lines A-A and B-B, respectively;
[0044] FIG. 20 is a schematic diagram of an apparatus according to
a fifth example;
[0045] FIG. 21 is a sectional diagram of the apparatus of FIG.
20;
[0046] FIGS. 22 and 23 are sectional diagrams of the apparatus of
FIG. 21 along lines A-A and B-B, respectively;
[0047] FIG. 24 is a schematic diagram of an apparatus according to
a sixth example;
[0048] FIG. 25 is a sectional diagram of the apparatus of FIG.
24;
[0049] FIGS. 26 and 27 are sectional diagrams of the apparatus of
FIG. 25 along lines A-A and B-B, respectively;
[0050] FIG. 28 is a schematic diagram of an apparatus according to
a seventh example;
[0051] FIG. 29 is a sectional diagram of the apparatus of FIG.
28;
[0052] FIGS. 30 and 31 are sectional diagrams of the apparatus of
FIG. 29 along lines A-A and B-B, respectively;
[0053] FIG. 32 is a schematic diagram of an apparatus according to
a eighth example;
[0054] FIG. 33 is a sectional diagram of the apparatus of FIG.
32;
[0055] FIG. 34 is a sectional diagram of the apparatus of FIG. 33
along line A-A;
[0056] FIG. 35 is a schematic diagram of an apparatus according to
a ninth example;
[0057] FIG. 36 is a sectional diagram of the apparatus of FIG.
35;
[0058] FIG. 37 is a sectional diagram of the apparatus of FIG. 36
along line A-A;
[0059] FIG. 38 is a schematic diagram of an apparatus according to
a tenth example;
[0060] FIG. 39 is a sectional diagram of the apparatus of FIG.
38;
[0061] FIG. 40 is a sectional diagram of the apparatus of FIG. 39
along line A-A;
[0062] FIGS. 41, 42 and 43 are schematic diagrams;
[0063] FIG. 44 is a schematic diagram of an apparatus according to
an eleventh example;
[0064] FIG. 45 is a sectional diagram of the apparatus of FIG.
44;
[0065] FIGS. 46, 47 and 48 are sectional diagrams of the apparatus
of FIG. 45 along lines A-A, B-B and C-C, respectively;
[0066] FIG. 49 is a schematic diagram of an apparatus according to
a twelfth example;
[0067] FIG. 50 is a sectional diagram of the apparatus of FIG.
49;
[0068] FIGS. 51 and 52 are sectional diagrams of the apparatus of
FIG. 50 along lines A-A and B-B, respectively;
[0069] FIG. 53 is a schematic diagram of an apparatus according to
a thirteenth example;
[0070] FIG. 54 is a sectional diagram of the apparatus of FIG. 53;
and
[0071] FIGS. 55 and 56 are sectional diagrams of the apparatus of
FIG. 54 along lines A-A and B-B, respectively.
DESCRIPTION OF VARIOUS EMBODIMENTS
[0072] Various apparatuses or methods will be described below to
provide an example of an embodiment of each claimed invention. No
embodiment described below limits any claimed invention and any
claimed invention may cover apparatuses or methods that are not
described below. The claimed inventions are not limited to
apparatuses or methods having all of the features of any one
apparatus or method described below or to features common to
multiple or all of the apparatuses described below. It is possible
that an apparatus or method described below is not an embodiment of
any claimed invention. The applicant(s), inventor(s) and/or
owner(s) reserve all rights in any invention disclosed in an
apparatus or method described below that is not claimed in this
document and do not abandon, disclaim or dedicate to the public any
such invention by its disclosure in this document.
[0073] Applicant's teachings relate to the use of at least one
combustion chamber in which an axial vortex stream is passed in a
first linear direction, and a peripheral vortex stream is passed as
a counterflow to the axial vortex stream in a direction generally
opposing the first linear direction. The peripheral and axial
vortex streams are merged to form a product stream, the product
stream moving in the first linear direction to an outlet of the
chamber.
[0074] Applicant's teachings can be directed to a variety of
application areas, including but not limited to: thermochemical
processing and utilization of solid domestic, industrial, medical
and biological waste; production of artificial fuels (for example,
methanol dimethyl-ether, biodiesel, benzene); reducing the presence
of airborne pollutants and/or greenhouse gases from emission
sources, e.g., industrial plants, coal-fired electricity generating
stations, incinerators, cars, trucks, ships, etc.; burning of
gaseous waste with low thermal coefficients with stable composition
and non-stationary parameters; burning of liquid waste with high
and low thermal coefficients; combustion of liquid and gaseous fuel
mixes (including waste); acceleration of different thermochemical
reactions; utilization in diesel generators and boilers; heat
generations, for example, combustion systems of airplanes and
ships; etc.
[0075] Applicant's teachings can be implemented as a retrofit to
existing industrial apparatuses to reduce the presence of airborne
pollutants and/or greenhouse gases from existing emission sources,
and can be scalable depending on energy and waste conversion
demands of a particular application. The combustion process can be
computer-controlled, whereby feedback data can be monitored and
adjustments can be made to operating parameters.
[0076] FIG. 1 shows a combustion apparatus 100 according to a first
example described in this specification. The apparatus 100 includes
a first or primary combustion chamber 102. The primary combustion
chamber 102 is in fluid connection with a second or main combustion
chamber 104. The term "primary" as used herein to describe chamber
102 refers to the fact that chamber 102 can be connected upstream
from the main chamber 104, and can be the first in a series of
chambers of apparatus 100. At least partially combusted products
exiting the main combustion chamber 104 are passed to an
afterburner chamber 106. One or more first pre-chambers 110 can be
provided as fluid inputs (e.g., for injection of liquid or gaseous
fuels, air, oxygen, or various combinations thereof) to the main
combustion chamber 104. One or more second pre-chambers 108 can be
provided as fluid inputs to the primary combustion chamber 102.
[0077] The apparatus 100 can be used for the combustion and
decomposition of gaseous fuels or waste having relatively low heats
of combustion, unstable parameters and non-standard characteristics
(e.g., pressure and temperature characteristics). For example, the
apparatus 100 can be implemented for: thermochemical processing and
utilization of solid domestic and industrial residue; processing of
medical and biological residue; or production of artificial fuels
(for example but not limited to methanol, dimethyl-ether,
bio-diesel, benzene). In a specific example, the apparatus 100 can
be used to combust pyrolysis gas resulting from the burning of
solid waste in the thermochemical reactor, the pyrolysis gas having
a relatively low heat of combustion (e.g., 4-12 MJ/kg) and unstable
components due to different burning products and non-stationary
parameters of the gaseous quantity.
[0078] The primary combustion chamber 102 includes a fuel source
112 for delivering a stream to the primary combustion chamber 102
comprising a first fuel. The primary combustion chamber 102 can
include an air or oxidant source 114. The main combustion chamber
104 can include a fuel source 116 and an air or oxidant source 118.
The second pre-chamber 108 can include an air or oxidant source 120
and fuel source 122, and the first pre-chamber 110 can include an
air or oxidant source 124 and a fuel source 126.
[0079] Formation and burning of a fuel-air mix can take place in
the primary and main combustion chambers 102, 104. The
multiple-stage combustion can take place in sequence, providing an
increase in fuel burning completeness. Use of the pre-chambers 108,
110 to the primary and main combustion chambers 102, 104 can
stabilize the combustion process and reduce or eliminate flame
interruption during non-steady fuel supply from the fuel source 112
to the primary combustion chamber 102, which can increase
reliability and stability of the combustion process.
[0080] Referring to FIGS. 2 to 4, the main combustion chamber 104
includes a generally cylindrical housing 128. Interior sidewalls
130 of the housing 128 can be sloped according to an angle of
contraction such that the radial area of the main combustion
chamber 104 decreases along the longitudinal or axial direction of
the apparatus 100. The angle of contraction serves to maintain
static pressure within the main chamber 104. In some examples, the
interior sidewalls 130 of the main chamber 104 can converge in a
flow direction according to an angle of contraction of about 5 to
15 degrees.
[0081] In some examples, the main chamber 104 includes an inlet
132, an outlet 134, and first and second ends 136, 138. The inlet
132 can be proximate to the first end 136 and receives an axial
vortex stream 140. The outlet 134 can be proximate to the second
end 138 and receives a product stream 142, and passes the product
stream to the afterburner chamber 106. The main chamber 104 can
include at least one first channel 144 disposed between the first
and second ends 136, 138, the at least one channel 144 for
introducing fluid into the main chamber 104 to form a peripheral
vortex stream 146 as a counterflow to the axial vortex stream 140.
The peripheral and axial vortex streams 146, 140 have the same
rotational polarity.
[0082] In some examples, and with reference to FIG. 2 and FIG. 3 (a
sectional view along line A-A in FIG. 2), the main chamber 104 of
the apparatus 100 can include a first injection zone 148 for
producing a first fluid stream 150 to form the peripheral vortex
stream 146. The first injection zone 148 is in fluid communication
with the at least one first channel 144 and delivers the first
stream 150 to the main chamber 104. The first injection zone 148
can be generally annular in shape and extend radially around a
circumference of the main chamber 104. The first injection zone 148
can include a plurality of swirl vanes 152 for directing rotational
fluid flow.
[0083] The first injection zone 148 can include an oxidant source
118 for injecting an oxidant to form at least a portion of the
first stream 150. The oxidant source 118 can be tangentially
aligned within the first injection zone 148 for directing
rotational fluid flow. The oxidant source 118 can be for example
but not limited to, an air ejector.
[0084] The first injection zone 148 can also include one or more
fuel sources 116A, 1168 for injecting a second fuel to form at
least a portion of the first stream 150. The second fuel can be
richer than the first fuel, i.e. the second fuel can have a higher
heat of combustion than the first fuel. In some examples, the fuel
sources 116A, 116B can direct a liquid fuel into the first
injection zone 148, the liquid fuel having a relatively high heat
of combustion. The fuel sources 116A, 116B can be tangentially
aligned within the first injection zone 148 for directing
rotational fluid flow. Fuel sources 116A, 116B need not be
identical.
[0085] The first injection zone 148 can also include one or more
first pre-chambers 110A, 110B. Each of the one or more first
pre-chambers 110A, 110B can include respective air or oxidant
sources 124A, 124B for supplying an oxidant, fuel sources 126A,
126B for supplying a second fuel, ignition sources or igniters
154A, 154B, and outlets 156A, 156B for exhausting a first
pre-chamber product stream into the first injection zone 148. The
first pre-chamber outlets 156A, 156B can also be tangentially
aligned within the first injection zone 148 for directing
rotational fluid flow. The first pre-chambers 110A, 1106 and
associated components need not be identical.
[0086] A maximum burning temperature of the product stream 142 in
the main chamber 104 can be reached due to the injection of second
fuel entering the main chamber 104 by way of the fuel source 116
and pre-chambers 110 (via the peripheral vortex stream 146). The
extra supply of fuel to the main chamber 104 can provide for the
near stoichiometric condition to provide complete combustion of
first fuel from the fuel source 112 having relatively low heat of
combustion.
[0087] Referring to FIG. 2, the main chamber 104 can further
comprise a merging surface 158 for merging the peripheral and axial
vortex streams 146, 140. The merging surface 158 can be located
along the interior sidewalls 130 of the main chamber 104 proximate
to the first end 136. The merging surface 158 can be
frusto-toroidal in shape. The inlet 132 at the first end 136 can
include a cylindrical sleeve 160 extending into the main chamber
104, the sleeve 160 for directing flow of the axial vortex stream
140 into the main chamber 104. The sleeve 160 can be frusto-conical
in shape, and can include a plurality of apertures 162 allowing for
migration of fluid from the peripheral vortex stream 146 into the
axial vortex stream 140 near the first end 136.
[0088] With reference to FIG. 2, the primary chamber 102 can
include a primary inlet 164 for directing the gaseous fuel from the
fuel source 112 towards the main chamber 104. In some examples,
first fuel from the fuel source 112 and oxidant can be mixed in the
primary chamber 102 and form the axial vortex stream 140. The first
fuel from the fuel source 112 and oxidant can at least partially
combust in the primary chamber 102, prior to entering the main
chamber 104 as the axial vortex stream 140. In particular, the
primary chamber 102 can be in fluid communication with the inlet
132 of the main chamber 104. The primary chamber 102 can include
the primary inlet 164 for receiving a second stream 166, with the
first fuel from the fuel source 112 forming at least a portion of
the second stream 166. The primary chamber 102 can further include
at least one second channel 168 for supplying a third stream 170,
the second and third streams 166, 170 mixing in the primary chamber
102 to form the axial vortex stream 140.
[0089] In some examples, and with reference to FIGS. 2 and 4 (a
sectional view along line B-B in FIG. 2), the primary chamber 102
of the apparatus 100 can include a second injection zone 172 for
producing the third stream 170. The second injection zone 172 can
be in fluid communication with the at least one second channel 168
for directing the third stream 170 to the primary chamber 102 to
mix with the second stream 166. The second injection zone 172 can
be generally annular in shape and extend radially around a
circumference of the primary chamber 102. The second injection zone
172 can include a plurality of swirl vanes 152 for directing
rotational fluid flow.
[0090] The second injection zone 172 can include an oxidant source
114 for injecting an oxidant to form at least a portion of the
third stream 170. The oxidant source 114 can be tangentially
aligned within the second injection zone 172 for directing
rotational fluid flow.
[0091] The second injection zone 172 can also include one or more
second pre-chambers 108A, 108B. Each of the one or more second
pre-chambers 108A, 108B can include respective fuel sources 122A,
122B for supplying a second fuel, oxidant sources 120A, 120B for
supplying an oxidant, ignition sources or igniters 154A, 154B, and
second pre-chamber outlets 174A, 174B for exhausting a second
pre-chamber product stream into the second injection zone 172. The
second pre-chamber outlets 174A, 174B can be tangentially aligned
within the second injection zone 172 for directing rotational fluid
flow. The second pre-chambers 108A, 108B and associated components
need not be identical.
[0092] The use of one or more pre-chambers 108A, 108B can provide
an increase in fluid velocity in the second injection zone 172
which can lead to an increase in radial and axial static pressure
gradients within the primary combustion chamber 102. An increase in
static pressure gradients can serve to draw in first fuel from the
fuel source 112, and lead to a temperature increase within the
primary chamber 102, which can stabilize the burning process of the
incoming first fuel if the first fuel is unstable with
non-stationary parameters.
[0093] The exit of the product stream 142 from the main chamber 104
and the entrance of the first fluid stream 150 (which forms the
peripheral vortex stream 146) can be provided at roughly the same
cross-sectional position within the main chamber 104 in a direction
orthogonal to the longitudinal axis of the main chamber 104.
Consequently, the peripheral vortex stream 146 serves to cover
substantially the entire length of the main chamber 104 and thus
shield the interior sidewalls 130 from the axial vortex and product
streams 140, 142, which can be of relatively high temperature. The
sidewalls 130, therefore, can be fabricated to tolerate lower
temperatures. In other words, although temperatures along the
center axis of the main chamber 104 can reach relatively high
values, the temperature at the sidewalls 130 can remain
substantially cooler during steady state combustion as a result of
the peripheral vortex stream 146. In some examples, the temperature
in the axial vortex stream 140 could reach more than 2,000 degrees
Celsius, whereas the temperature at the internal walls of the main
combustion chamber heat pipe does not exceed 400 to 500 degrees
Celsius, resulting in improved reliability and longer lifespan of
the main chamber 104.
[0094] With continued reference to FIG. 2, the apparatus 100 can
further comprise an afterburner chamber 106 in fluid communication
with the outlet 134 of the main chamber 104, the afterburner
chamber 106 for receiving the product stream 142 and cooling the
product stream 142. The afterburner chamber 106 can include at
least one third channel 176 for introducing a fourth stream 178 to
the product stream 142. The fourth stream 172 can include a coolant
fluid for reducing the temperature of the product stream upon
exiting the main chamber 104. In some examples, the coolant fluid
can be air or an inert gas. A third injection zone (not shown) can
be provided for producing the fourth stream 178, the third
injection zone being in fluid communication with the at least one
third channel 176 for directing the fourth stream 178 to the
afterburner chamber 106. Similar to the injection zones 148, 172,
the third injection zone can be generally annular in shape and
extend radially around a circumference of the afterburner chamber
106.
[0095] In the afterburner chamber 106, the product stream can be
cooled to prevent or reduce recombination of molecules. In
particular, the afterburner chamber 106 can provide for finalizing
of the fuel burning and accordingly decreasing of emissions by
mixing, dilution and cooling of the burned products. Also, the use
of the kinetic energy of the product stream 142 from the main
chamber 104 can require less reliance on external air or oxidant
sources. The afterburner chamber 106 can expel the cooled product
stream 142 through the afterburner outlet 180.
[0096] FIG. 5 illustrates the distribution of tangential component,
w.sub..phi., of fluid flow velocity within the main chamber 104 at
various cross-sections. FIG. 6 illustrates the distribution of
axial component, w.sub.z, of fluid flow velocity within the main
chamber 104 at various cross-sections. The w.sub..phi. and w.sub.z
profiles illustrate the mixing of the axial and peripheral vortex
streams 140, 146 within the main chamber 104.
[0097] With reference to cross-section a-a in FIGS. 5 and 6, the
second stream 166 including first fuel from the first fuel source
112 (e.g., pyrolysis, synthetic, bio gases, etc.) can be supplied
to the primary chamber 102 at atmospheric pressure or can be
pressurized. The apparatus 100 can achieve refinement of components
of the first fuel, which can contain partially burned hydrocarbons
CH.sub.x, carbon monoxide CO, sulphur dioxide SO.sub.2 and/or
nitrogen oxide NO.sub.x. Between cross-sections a-a and b-b in
FIGS. 5 and 6, the second stream 166 can be accelerated as the
radial cross-sectional area of the primary chamber decreases
towards the primary inlet 164, resulting in a pressure change
between the cross-sections a-a and b-b. The pressure can be modeled
using the following equation:
P * = P + .rho. .omega. 2 2 ( 1 ) , ( Eq . 1 ) ##EQU00001##
where: P* is the complete pressure of the gas stream, [Pa]; P is
the statistical pressure of the gas stream, [Pa];
.rho. .omega. 2 2 ##EQU00002##
is the dynamic pressure of the gas stream or speed pressure, [Pa],
[kg/m.sup.3m.sup.2/s.sup.2]; .rho. is the density of the gas,
[kg/m.sup.3]; w= {square root over
(w.sub.z.sup.2+w.sub..phi..sup.2)} is the total stream speed,
[m/s]; w.sub.z is the axial component of the speed; and w.sub..phi.
is the tangential component of the speed.
[0098] Alternatively, it is possible to use the following equation
to model the pressure:
P * = P ( 1 + k - 1 2 .times. M 2 ) k k - 1 , ( Eq . 2 )
##EQU00003##
where: k is the adiabat constant of the gas
( k = C p C v , ##EQU00004##
where C.sub.p is the isobar thermal capacity of the gas [kJ/kgK]
and C.sub.v is the isochronous thermal capacity of the gas,
[KJ/kgK]); M is the Mach's number in the stream; w is the total
stream speed; a is the acoustic speed of the stream; R is the
constant of the supplied gas (depends on the gas components); and T
is the gas temperature.
[0099] FIGS. 7A, 7B and 7C show qualitative flow structure changes
in the combustion chamber as a function of location, and require
reference to sectional lines a-a, b-b, c-c, d-d and g-g in FIGS. 5
and 6. FIG. 7A shows change of the average full temperature in the
axial (I) and peripheral flows (II) at specific locations. FIG. 7B
shows change of the full pressure P in the peripheral (I) and axial
flows (II); and average values of static pressure P in the
peripheral (III) and axial pressure of the axial flow (IV). FIG. 7C
shows change of maximal tangential velocity w.sub..phi., average
tangential velocity w.sub.z in the peripheral flow (curves I and
II, respectively), and change of axial velocity w.sub.z on the
central axis of the axial flow (III).
[0100] During the movement of the second stream 166 along a-a to
b-b, a temperature drop can be possible. Pressure change between
a-a to b-b without a pressurized supply from fuel source 112 can be
provided by the incoming pressure of the third stream 170 from the
first injection zone 148.
[0101] In the cross-section b-b, relatively high centrifugal forces
can be acting in accordance with the following equation:
F y = m W .PHI. 2 z , ( Eq . 3 ) ##EQU00005##
where: m is the mass of the gas [kg]; W.sub..phi. is the tangential
component of the speed in this cross-section [m/s]; and z is the
radius where the gas element is located [m].
[0102] A high gradient of static pressure can be formed by the
centrifugal forces in cross-section b-b. Therefore, the static
pressure of the fluid decreases along the radius of the
cross-section, and it reaches minimal value on the center axis (see
FIG. 5). The reduction of static pressure leads to the axial
gradient of static pressure formation. Therefore, the axial speed
of the fluid flow, which moves away from the cross-section a-a, is
increasing. The speed reaches its maximum in the cross-section b-b.
The growth of axial fluid component leads to the growth of dynamic
pressure in the stream at constant pressure, which is inflowing
from the source 112 into the cross-section a-a, in accordance with
the Equation (1).
[0103] Between b-b and c-c in the primary chamber 102, the fuel air
mixture is formed, comprising first fuel from source 112, oxidant
from source 114, pre-chamber product stream from pre-chamber 108,
and a portion of the peripheral vortex stream 146 that passes
through the apertures 162 to combine with the axial vortex stream
140.
[0104] The burning process of the fuels between b-b and c-c can
cause the temperature to increase rapidly (see FIG. 7A). The
temperature increase causes a corresponding increase in the volume
consumption of the reactants. Decline of the axial velocity between
b-b and c-c (see FIG. 7B) leads to a static pressure increase. FIG.
7C shows the distribution of tangential w.sub..phi. and axial
w.sub.z speeds in the cross-sections b-b and c-c, with the
tangential speed w.sub..phi. of the peripheral vortex stream being
significantly lower than the tangential speed of the axial vortex
stream. Additionally, the reduction of the pressure due to fluid
entering from the peripheral vortex stream flow 146 into the axial
vortex stream 140 through the apertures 162 contributes to the
reduction of the axial speed of the axial vortex stream 140. This
reduction is offset by the increase in the consumption of reactants
between b-b and c-c.
[0105] At cross-section d-d, the first stream 150 enters the first
channel 144 and forms the peripheral vortex flow 146 with axial
component speed w.sub.z. The distribution of tangential and axial
components of the speed in the cross-section d-d is shown in FIGS.
5 and 6. The maximum value of the tangential component of the speed
is approximately located at the borderline between the peripheral
vortex stream 146 and the product stream 142.
[0106] Between c-c and d-d, the peripheral vortex stream 146 is
losing its tangential speed adjacent to the product stream 142. In
addition, along with a reduction of the axial speed of the
peripheral flow, mass transfer from the peripheral vortex stream
146 to the product stream 140 (moving in generally opposite linear
direction) intensifies due to the formation of anisotropic
turbulence between the streams.
[0107] The temperature changes of the gas in axial (I) and
peripheral (II) streams are shown in FIG. 7A. The temperature of
the burning products continues to grow rapidly starting from
cross-section c-c. It reaches its maximum in the burning zone near
the first end 136 of the main chamber 104, and then it decreases
due to the cooler fluid supply from the peripheral vortex stream,
preventing or reducing recombination of molecules.
[0108] FIG. 7B shows the change of the complete pressure P* of the
peripheral (I) and axial flows (II). The reduction of the complete
pressure P* in the peripheral flow, while it is moving towards the
cross-section b-b, can be explained by hydraulic losses. The
reduction of the complete pressure P* of the axial flow, while it
is moving from the cross-section c-c to the cross-section d-d, can
be explained by transfer of the pressure to heat and hydraulic
losses. In addition, pressure reduction in the peripheral and axial
streams can also be attributed to energy losses in generating
turbulence between counterflows.
[0109] FIGS. 8 to 11 show a combustion apparatus 200 according to a
second example described in this specification. The apparatus 200
is similar to the apparatus 100, with like features identified by
like reference numbers. In particular, the first injection zone 248
does not include a pre-chamber.
[0110] The apparatus 200 can be used for the combustion and
decomposition of gaseous fuels or waste having relatively low heats
of combustion, stable parameters and non-standard pressure and
temperature characteristics. In a particular example, the apparatus
200 could be used for heat production systems (e.g., coal-fired
electricity plants) using after-burning of gaseous substances for
production of specific substances and their regeneration. In some
examples, the apparatus 200 can be utilized for burning pyrolysis
gas produced during the processing of industrial waste, e.g.,
polishing discs, wood waste, etc. The pyrolysis gas obtained in
these processes can have relatively low heats of combustion,
unstable composition, significant amount of hydrocarbons, and
non-stationary consumption parameters. In examples involving
combustion of pyrolysis gas from a thermal-chemical reactor,
negative pressure of the second stream 266 from the fuel source 212
can be desirable to prevent or reduce leakage of pyrolysis gas to
the atmosphere. In such examples, an ejector can be placed at the
inlet to the primary chamber 202 to pressurize the second stream
266, e.g., -5 to 0 mm of water column.
[0111] Stable composition of the gaseous fuels permits the use of
the main chamber 204 without a pre-chamber. Similar to the
apparatus 100, stabilization of the burning process can take place
due to the use of at least one pre-chamber 208 connected to the
second injection zone 272 of the primary chamber 202.
[0112] In contrast with the apparatus 100, thermal stress within
the first injection zone 248 and on the sidewalls 230 of the main
chamber 204 can be reduced due to the absence of burning products
streaming into and out of the first injection zone 248.
Furthermore, the system of air and fuel supply to the first
injection zone 248 of the main chamber 202 can be simplified.
[0113] FIGS. 12 to 15 show a combustion apparatus 300 according to
a third example described in this specification. The apparatus 300
is similar to the apparatuses 100 and 200, with like features
identified by like reference numbers. In particular, the second
injection zone 372 does not include a pre-chamber.
[0114] The apparatus 300 can be used for the combustion and
decomposition of gaseous fuels or waste having relatively low
thermal capacity, stable parameters, stable pressure and
temperature characteristics, but with pressurized supply of the
fuel to the primary chamber 302. In some examples, the apparatus
300 can be used for thermo-chemical waste processing installations
where pressure below atmosphere is not required. In other examples,
the apparatus 300 can be used for afterburning of burned products
of harmful emissions (e.g., car emissions).
[0115] The flow formation within the primary chamber 302 is due to
the use of the oxidant source 314 introduced tangentially within
the second injection zone 372. In some examples, the oxidant source
314 can include an air ejector, with the air from the ejector
mixing with the first fuel to form the axial vortex stream 140.
Similar to the apparatus 100, stabilization of the burning process
can take place due to the use of at least one pre-chamber 310
connected to the first injection zone 348 of the main chamber
304.
[0116] In contrast with the apparatus 100, thermal stress within
the second injection zone 372 and within the primary chamber 302
can be reduced due to the absence of a burning products streaming
into and out of the second injection zone 372. Furthermore, the
radial gradient of static pressure at the entrance of the primary
chamber 302 can be reduced. Moreover, construction of the primary
chamber 302 can be simplified due to the absence of a
pre-chamber.
[0117] FIGS. 16 to 19 show a combustion apparatus 400 according to
a fourth example described in this specification. The apparatus 400
is similar to the apparatuses 100, 200 and 300, with like features
identified by like reference numbers. In particular, the first
injection zone 448 does not include a pre-chamber, and the second
injection zone 472 does not include an oxidant source.
[0118] The apparatus 400 can be used for the combustion and
decomposition of liquid fuels having both low and high heats of
combustion. In particular, the apparatus 400 can be used to achieve
simultaneous burning of liquid waste with high and low heats of
combustion, e.g., simultaneous burning of sewage and oil refinery
waste (benzene, acetone, etc). The apparatus 400 can also be used
in industrial construction devices with sewage and liquids having
high heats of combustion, such as paint industry with sewage and
different chemicals, alcohol production industry with sewage and
alcohol waste, liquids used to wash heating tanks, etc.
[0119] For the burning of liquid fuels with low and high heats of
combustion simultaneously, the fuel with higher heat of combustion
can be provided using one or more fuel sources 416, connected to
the first injection zone 448. The fuel with lower heat of
combustion can be provided through the fuel source 422 of the one
or more pre-chambers 408 connected to the second injection zone
472. Alternatively, the fuel with higher heat of combustion can be
provided through the fuel source 422 of the one or more
pre-chambers 408 connected to the second injection zone 472.
Oxidant or air from the oxidant source 418 and fuel from the fuel
source 416 can mix in the first injection zone 448 and enhance the
quality of burning downstream in the main chamber 404. Similar to
the apparatuses 100 and 200, stabilization of the burning process
can take place due to the use of at least one pre-chamber 408
connected to the second injection zone 472 of the primary chamber
402.
[0120] In contrast with the apparatus 100, thermal stress within
the first injection zone 448 and on the sidewalls 430 of the main
chamber 404 can be reduced due to the absence of a burning products
from a pre-chamber, and thermal stress within the second injection
zone 472 and within the primary chamber 402 can be reduced due to
the fact that the burning process there takes place with reduced
oxidant or air. The construction of the primary and main chambers
402, 404 is also simplified due to the absence of a pre-chambers
and oxidant sources, respectively.
[0121] FIGS. 20 to 23 show a combustion apparatus 500 according to
a fifth example described in this specification. The apparatus 500
is similar to the apparatuses 100, 200, 300 and 400, with like
features identified by like reference numbers. In particular, the
first injection zone 548 does not include an oxidant source
(separate from the pre-chambers 510). Accordingly, all oxidant or
air present in the peripheral vortex stream 546 originates from the
oxidant source 524 of the one or more pre-chambers 510.
[0122] The apparatus 500 can be used for the combustion and
decomposition of gaseous fuels or waste having relatively low heats
of combustion, unstable parameters and non-standard characteristics
simultaneously with gaseous wastes that result from the burning of
liquid waste having high heats of combustion. In some examples, the
apparatus 500 can be used for after-burning of gaseous emissions
containing unburned hydrocarbons for the purpose of controlling
emissions.
[0123] The at least one pre-chamber 510 can be operated such that
the air or oxidant source 524 provides an excess of air for the
burning of second fuel from the fuel source 526, and subsequently
the fuel from fuel source 516. Fuels injected via sources 526 or
516 can be the same or different. Similar to the apparatuses 100
and 300, stabilization of the burning process can take place due to
the use of at least one pre-chamber 510 connected to the first
injection zone 548 of the main chamber 504.
[0124] In contrast with the apparatus 100, the construction of the
main chamber 504 can be simplified as a result of the absence of a
direct oxidant source and necessary connections. Furthermore,
velocity of the peripheral vortex stream 546 in the main chamber
504 can be increased, and accordingly the level of radial and axial
gradients of static pressure can be increased, leading to an
increase in turbulence and intensification of combustion.
[0125] FIGS. 24 to 27 show a combustion apparatus 600 according to
a sixth example described in this specification. The apparatus 600
is similar to the apparatuses 100, 200, 300, 400 and 500, with like
features identified by like reference numbers. In particular, the
second injection zone 672 does not include an oxidant source
(separate from the pre-chambers 608). Accordingly, all oxidant or
air present in the axial vortex stream 640 originates from the
oxidant source 620 of the one or more pre-chambers 608.
[0126] The apparatus 600 can be used for the combustion of gaseous
waste with low heats of combustion, with unstable compositions, and
non-stationary parameters, jointly with gaseous waste that results
from the burning of liquid waste. Additional fuel (i.e. the second
fuel) is provided through the first injection zone 648 to increase
the temperature in the main chamber 604 to a maximum, thus enabling
decomposition and burning of hydrocarbons, resulting in relatively
low emissions in the product stream 642.
[0127] In contrast with apparatus 100, the quality of the mix in
the primary chamber 602 can be increased due to the increase of the
temperature and air consumption which enters with the burning
product stream from the at least one pre-chamber 608. Consumption
of the fuel from the pre-chamber 608 of the primary chamber 602 can
be increased. Accordingly, radial and axial gradients of static
pressure can be increased at the inlet 664 of the primary chamber
602, which can lead to improvement of the injection properties of
the second injection zone 672 and pressure decrease of gaseous and
liquid fuel mix entering the primary chamber 602. Absence of an
oxidant source in the second injection zone 672 simplifies
construction of the primary chamber 602.
[0128] FIGS. 28 to 31 show a combustion apparatus 700 according to
a seventh example described in this specification. The apparatus
700 is similar to the apparatuses 100, 200, 300, 400, 500 and 600,
with like features identified by like reference numbers. In
particular, the first injection zone 748 does not include an
oxidant source (separate from the pre-chambers 710), and the second
injection zone 772 does not include an oxidant source (separate
from the pre-chambers 708). Accordingly, all oxidant or air present
in the axial and peripheral vortex stream 740, 746 originates from
the oxidant sources 720, 724 of the pre-chambers 708, 710.
[0129] The apparatus 700 can be used for the combustion of gaseous
fuel with low heats of combustion, non-stable composition and
non-stationary parameters, jointly with gaseous waste resulting
from the burning of liquid waste with low heats of combustion. The
apparatus 700 is similar to the apparatus 600, with the difference
that the burning process in the main chamber 704 can be more
intense than that of the main chamber 604. The apparatus 700 can be
useful for mobile systems.
[0130] All oxidant or air for the working process in the primary
and main chambers 702, 704 enters from their respective
pre-chambers 708, 710. The maximum temperature in the burning zone
of the main chamber 704 can be achieved due to the burning of fuel
having a relatively high heat of combustion, which enters the main
chamber 704 via source 716. Absence of an oxidant source in the
first or second injection zones 748, 772 simplifies construction of
the primary and main chambers 702, 704.
[0131] FIGS. 32 to 34 show a combustion apparatus 800 according to
an eighth example described in this specification. The apparatus
800 is similar to the apparatuses 100, 200, 300, 400, 500, 600 and
700, with like features identified by like reference numbers. In
particular, the apparatus 800 does not include a primary chamber.
All reactants entering the main chamber 804 are injected via the
first injection zone 848 through the at least one first channel
844, forming the peripheral vortex stream 846. The peripheral
vortex stream 846 travels within the main chamber 804 towards the
first end 836 thereof. A generally spherical end surface 882 causes
the peripheral stream to merge inwardly to form an axial vortex
stream 840. The axial vortex stream 840 acts as a counterflow to
the peripheral vortex stream 846, moving in generally opposite
linear direction. The peripheral and axial vortex streams 846, 840
can have the same rotational polarity.
[0132] The apparatus 800 can be used for the combustion and
decomposition of liquid fuels having a low and high thermal
capacity, with stable parameters. The first liquid fuel is provided
to the main chamber 804 via fuel source 816. In some examples, the
first fuel can be a water emulsion fuel. A second fuel, which can
be gaseous fuel having a higher heat of combustion than the first
fuel, can be provided to the main chamber via fuel source 826.
Oxidant or air is provided to the main chamber via oxidant sources
818, 824. Stabilization of the combustion can be realized by the at
least one pre-chamber 810, that serves to ignite a fuel-air
mixture.
[0133] FIGS. 35 to 37 show a combustion apparatus 900 according to
a ninth example described in this specification. The apparatus 900
is similar to the apparatuses 100, 200, 300, 400, 500, 600, 700 and
800, with like features identified by like reference numbers. In
particular, similar to the apparatus 800, the apparatus 900 does
not include a primary chamber.
[0134] The apparatus 900 can be used for the combustion and
decomposition of liquid and gas fuels having high heat of
combustion with stationary characteristics and stable parameters.
The apparatus 900 is similar to apparatus 800, except that the
liquid or gaseous fuels burned have relatively high heats of
combustion. The apparatus 900 can be utilized for combusting gas,
liquid fuel, or a combination of two or three phase fuels.
[0135] In apparatus 900, the at least one pre-chamber 910 works as
an igniter. The formation of the air-fuel mix begins in the first
injection zone 948 and forms the peripheral vortex stream 946,
which in turn forms the axial vortex stream 940.
[0136] FIGS. 38 to 40 show a combustion apparatus 1000 according to
a tenth example described in this specification. The apparatus 1000
is similar to the apparatuses 100, 200, 300, 400, 500, 600, 700,
800 and 900, with like features identified by like reference
numbers. In particular, similar to the apparatuses 800 and 900, the
apparatus 1000 does not include a primary chamber. In contrast with
apparatuses 800 and 900, the first injection zone 1048 does not
include an oxidant source (separate from the pre-chambers 1010).
The formation of the air-fuel mixture can be intensified due to the
fact that it takes place in the product stream of the at least one
pre-chamber 1010. The burning process in the apparatus 1000 can be
more intense, relative to apparatuses 800 and 900, because of
increasing speed of the air-fuel mixture, high centrifugal forces,
high anisotropic turbulence and acoustic vibration.
[0137] The apparatus 1000 can be used for the combustion and
decomposition of liquid fuels, gaseous fuels, solid fuels,
dust-like fuels, and two and three phase fuels. The apparatus 1000
can be particularly useful for systems where multi-phase fuels are
used, e.g., burning of solid or dust-like fuels such as wood dust,
coal dust, sometimes mixed with liquid fuels (liquid hydrocarbons)
or gaseous fuels (natural gas, black oil, bio-gas, synthetic gas),
etc.
[0138] FIG. 41 illustrates an example of a fuel combustion system
2000 including apparatus 100, and further including various power
and control components. Although the system 2000 is shown in
association with the apparatus 100, it should be appreciated that
other systems are possible and contemplated in association with the
apparatuses 200, 300, 400, 500, 600, 700, 800, 900, 1000.
[0139] With reference to FIG. 41 (and with continued reference to
FIGS. 1 to 4), air from a compressor 2002 passes through valve 2004
and enters one or more pre-chambers 110, and through valve 2006 is
directed to the main chamber 104 via 118 (i.e. to the first
injection zone 148). The amount of air can be controlled by a
variable frequency drive 2008, which in turn controls the
compressor 2002. Airflow to the main chamber 104 is thereby
controlled with valves 2004, 2006. Similarly, air from compressor
2010 flows through valve 2012 to one or more pre-chambers 108, and
through valve 2014 to the primary combustion chamber 102 via 114
(i.e. to the second injection zone 172). The amount of air is
controlled by variable frequency drive 2016, which in turn controls
the compressor 2010. Airflow to the primary chamber 102 is thereby
controlled with valves 2012, 2014. Second fuel from pump 2018
through valves 2020, 2022, 2024 flows to pre-chambers 108, 110 via
122, 124, respectively and directly to the main chamber 104 via
116. The flow of second fuel is thereby controlled by valves 2020,
2022, 2024, and by variable frequency drive 2026. The valves 2020,
2022, 2024 can be, for example but not limited to, adjustable
needle valves with AC/DC drives. The valves 2004, 2006, 2012, 2014
can be, for example but not limited to, pneumatic valves with AC/DC
actuators. In the pre-chambers 108, 110, a mixture of air and
second fuel is formed. The mixture of air and second fuel can be at
least partially combusted in the pre-chambers 108, 110 prior to
being injected into the first and second injection zones in the
form of first and second pre-chamber product streams. The first and
second pre-chamber product streams can accelerate the air that is
introduced into the first and second injection zones 148, 172 by
compressors 2002, 2010. The combination of combustion product
streams and compressed air then feed into first and second
injection zones 148, 172 of the main and primary chambers 104, 102,
thereby generating the axial and peripheral vortex streams 140,
146. The second fuel that enters the main chamber 104 and driven by
the fuel pump 2018 through valve 2022 mixes with the air, and can
at least partially combust. The first fuel enters the primary
chamber 102 from source 112. The product stream 142 formed in the
main chamber 104 enters the afterburner chamber 106, which is
located downstream from the main chamber 104. In the afterburner
chamber 106, the product stream is cooled to prevent or reduce
recombination of molecules before exiting outlet 180.
[0140] The inventors have developed a mathematical model to
establish and control system parameters to optimize combustion
performance. Control of primary parameters using a computer or
microprocessor means can provide for system performance
optimization. Optimization can serve to reduce the energy supply to
the system, improve emission reduction and increase burning
efficacy of a broad range of fuels. The mathematical model can
permit the ability to perform analytical modeling of the combustion
chamber system for different configurations and applications to
obtain the values of combustion parameters and configurations.
[0141] In accordance with the mathematical model, the following
parametric equation consists of the product of several
dimensionless complex parameters:
A.sub.ij.times.F.sub.ij.times.B.sub.ij.times.C.sub.ij.times.G.sub.ji=1
(Eq. 4)
[0142] A.sub.ij, F.sub.ij B.sub.ij, C.sub.ij, and G.sub.ji are the
integral parameters which define the working characteristics and
geometric sizes of components of a given combustion system, where:
A.sub.ij is a thermal parameter and depends on the air excess
coefficient during fuel combustion, temperatures of the fuel
combustion, air and fuel temperature at the entrance to the primary
and main chambers and pre-chambers, and type of first and second
fuels and their chemical composition; F.sub.ij is a geometry
parameter and depends on the geometry of each component of the
apparatus; B.sub.ij is a first hydrodynamic parameter and depends
on the relative speed of incoming and outgoing reactants and
product in each component of the apparatus; C.sub.ij is a second
hydrodynamic parameter and depends on the static pressure of
reactants products in each of the components of the apparatus; and
G.sub.ij is an emission parameter and depends on air consumption in
the main and primary combustion chambers. The indices i and j
correspond with the entrance and exit, respectively, to each
chamber of the apparatus.
[0143] The parameter A.sub.ij determines the working regime, based
on the following correlations: coefficients of air excess; fuel
composition; temperature of the reactants and products, which are
supplied into the primary and main combustion chamber and
pre-chambers. The air excess coefficient should be
.alpha..sub.0=.alpha..sub.p=0 for the air, which is supplied
through the injection zones of the primary and main combustion
chambers. Thus:
A.sub.ij=A.sub.ij(.alpha..sub.i,.alpha..sub.j,L.sub.oi,L.sub.oj,H.sub.ui-
,H.sub.uj,T.sub.i.sup.B,T.sub.j.sup.B,T.sub.i.sup.T,T.sub.i.sup.T),
(Eq. 5)
where: .alpha..sub.i, .alpha..sub.j are coefficients of the air
excess; L.sub.oi, L.sub.oj (kg air/kg fuel) are coefficients which
take into consideration the quantity of the air required for the
burning of 1 kg of the fuel; H.sub.ui, H.sub.uj (kJ/kg) are
combustion heat coefficients of 1 kg of the fuel; T.sub.i.sup.B,
T.sub.j.sup.B (K) are air temperatures at the entrance; and
T.sub.i.sup.T, T.sub.j.sup.T(K) are fuel temperatures at the
entrance.
[0144] The geometric parameter F.sub.ij determines the influence of
the geometric sizes of the main components of the primary and main
combustion chambers on the flow path of a given combustion system.
Therefore, the main elements of the flow path include size and
shape of the injection zones of the primary and main chambers,
pre-chamber outlets to the injection zones and location of the
pre-chambers, inlets and outlets of the primary and main chambers,
etc.
[0145] The parameter B.sub.ij determines the influence of the
non-dimensional speed of streams within the chambers, where:
B.sub.ij=B.sub.ij(M.sub.i,M.sub.j), (Eq. 6)
where M.sub.i and M.sub.j are the Mach's numbers of the
corresponding flow cross-section.
[0146] The parameter C.sub.ij determines the influence of static
pressures in the peripheral vortex formation, where:
C.sub.ij=C.sub.ij(P.sub.i,P.sub.i and other), (Eq. 7)
where P.sub.i, P.sub.j are static pressures in the corresponding
cross-section of the flow.
[0147] The parameter G.sub.ji determines the correlation of the
consumption in the related cross-section of the flow, where:
G.sub.ji=G.sub.ji(G.sub.j,G.sub.i), (Eq. 8)
where G.sub.j and G.sub.i reflect air consumption.
[0148] Referring to FIG. 42, an example of a fuel combustion system
3000 is shown schematically including main chamber 104 of apparatus
100 (see FIGS. 1 and 2), and further including a feedback means
based on the mathematical model described above. Second fuel can be
supplied by the fuel tanks/pumps 3026, 3028, 3030 and can be
controlled (velocity and temperature) using valves 3002, 3004, 3006
(or more). An air compressor 3018 and a water supply 3020 can
respectively supply air and water to the combustion chamber using
valves 3008, 3010. The mixers/selectors 3012, 3014 are controllable
and connect the valves 3002, 3004, 3006, 3008, 3010 with the
apparatus 100. The mixers/selector 3012 can provide initial
conditions to the main chamber 104 via valves 3002, 3004, 3006 upon
startup. A heater 3032 can be operably connected to the
mixers/selectors 3012, 3014 to increase temperature of fluids
before delivery to the main chamber 104.
[0149] The microprocessor control unit 3016 can be a small computer
on a single integrated circuit consisting of a relatively simple
CPU combined with support functions such as a crystal oscillator,
timers, watchdog, serial and analog connections, etc. Program
memory in the form of flash or OTPROM can also be included,
typically along with limited read/write memory. In some examples,
the microprocessor control unit 3016 can include a PIC16, PIC18 or
dsPIC30 device. A computer 3022 can be connected to the
microprocessor control unit 3016, for example, via RS-232 through a
DB9 serial connector. An interface 3024 to the microprocessor
control unit 3016 can include a keypad and a display.
[0150] Using feedback means, the temperature in the combustion zone
of the main chamber 104 can be measured and supported at its
maximum value, to provide decomposition and burning of all organic
fuel components by controlling the coefficient of the air excess
and fuel consumption via the main combustion fuel source. For this
purpose, in some examples, to support the maximum temperature the
coefficient of the air excess can be selected between 1.01 and
1.05. At the outlet 134 of the chamber 104, a gas analyzer can
provide measurement of residual contaminant in the product stream
and this information can be fed back to a microprocessor control
unit 3016. The microprocessor control unit 3016 can provide initial
settings of one or more primary parameters. With the feedback from
the gas analyzer, general optimization of primary parameters can be
achieved.
[0151] Referring back to FIGS. 1 to 4, it can be preferable to set
aside a fixed time for the fuels and oxidants to be in the primary
and main chambers 102, 104 at maximum temperature to provide for
full combustion and decomposition of all organic fuel components,
along with the prevention and/or delay of synthesis of harmful
molecules, e.g., NO.sub.x. Residence time can be adjusted by
control of the average velocity of the axial vortex stream 140 and
the total incoming air pressure to the main, primary and
pre-chambers 104, 102, 108, 110. Emission parameters can be
measured at the exit of the afterburner chamber 106 and can be
optimized according to monitoring and adjustment of: coefficient of
air excess, fuel consumption in the primary and main chambers and
pre-chambers, and total air pressure in the primary and main
chambers and pre-chambers. Additional feedback for the optimization
of combustion can be accomplished by measuring various parameters
including: temperature of the inlet and outlet of the primary and
main chambers 102, 104 (e.g., using an optical meter, pyrometer or
other optical spectroscopy means); fluid velocities at various
points (e.g., using a tachometer); fuel emission of the one or more
pre-chambers 108, 110 and first and second fuel sources 112, 116,
122, 126; controlling quantity of air in the primary and main
chambers 102, 104; pressure of the stream comprising first fuel
provided to the primary chamber 102; etc. The data can be used in
addition to the main feedback to obtain greater control on the
combustion process.
[0152] FIG. 43 provides further details of an example
implementation of the system 3000 shown in FIG. 42. The interface
3024 can include a keypad 3034 and a display 3036. The keypad 3034
can connect to the microprocessor control unit 3016, for example,
by an 8-pin connection. The display 3036 can connect to the
microprocessor control unit 3016, for example, via SPC or I2C bus
connection. In some examples, the display 3036 can be an LCD
display. Analog signals from the sensors 3038 in the chamber and
sensors 3040 in or near the outlet of the chamber can be provided
to the microprocessor control unit 3016 by means of
analog-to-digital conversion. The analog-to-digital conversion can
also allow for two-way communication so that the microprocessor
control unit 3016 is capable of sending data to the sensors 3038
and/or the sensors 3040. The microprocessor control unit 3016 can
be connected to the heater 3032 and the valves 3002, 3004, 3006,
3008, 3010 using for example, SPC or I2C bus connections, and can
include a means for digital-to-analog conversion. Actuators of the
heater 3032 and the valves 3002, 3004, 3006, 3008, 3010 can operate
with relatively high AC or DC voltage, so proper drivers or signal
transmitters isolated from any electrical connection, for example,
a photocoupler, can be provided. The microprocessor control unit
3016 can be further connected to a beeper 3042 by chip select
connection. The beeper 3042 can be a piezoelectric device and serve
as an alarm or indicator to provide feedback to an operator. The
system 3000 can be implemented to operate and control the apparatus
100 in substantially real-time. The microprocessor control unit
3016 can work generally independently to calculate various
parameters from the sensors 3038, 3040 and to control the actuators
of the heater 3032 and the valves 3002, 3004, 3006, 3008, 3010. In
addition, some parameters can be modified through RS-232 protocol,
which can also be used to accumulate data for improvement of the
system's performance and statistics.
[0153] Using a prototype model of the apparatus 100, the inventors
ran a verification test to confirm the results of the mathematical
model described above. The test results are provided below in Table
1. The relative low error values indicate reasonable validation of
the model.
TABLE-US-00001 TABLE 1 Version dc = 0.227 dc = 0.273 1 2 3 4 1 2
Absolute air KPa 241 235 248 252 181 181 pressure at main chamber
inlet Air temp at K 300 300 300 300 300 300 main chamber inlet Air
temp at K 340 360 380 400 320 360 first injection zone Main g/s 132
132 132 132 132 132 chamber air consumption Main g/s 7.4 8.0 8.4
9.0 7.2 8.0 chamber fuel consumption Excess air -- 1.209 1.120
1.065 0.994 1.240 1.120 coefficient Average air K 1500 1600 1840
1860 1480 1600 temp at main chamber outlet Mach number -- 0.680
0.758 0.739 0.746 0.902 0.985 in first injection zone Speed in
first m/s 243 263 264 273 304 342 injection zone Mach number --
0.811 0.827 0.877 0.854 0.789 0.786 of stream at main chamber
outlet Average gas m/s 571 602 685 670 552 572 consumption at main
chamber outlet Experimental parametric results A.sub.oc .times.
F.sub.oc .times. B.sub.oc .times. C.sub.oc .times. G.sub.oc = 1
.+-. .DELTA.oc A.sub.oc -- 2.218 2.236 2.340 2.156 2.268 2.236
F.sub.oc -- 0.441 0.305 B.sub.oc -- 0.931 1.026 0.936 0.974 1.195
1.460 C.sub.oc -- 1.079 1.121 1.099 1.127 1.196 1.143 G.sub.oc --
1.056 1.060 1.064 1.068 1.054 1.061 .DELTA.oc -- 0.037 0.202 0.129
0.115 0.043 0.207 .delta.oc % 3.7 20.2 12.9 11.5 4.3 20.7 Version
dc = 0.273 dc = 0.527 3 4 5 1 2 3 Absolute air KPa 201 201 201 161
188 166 pressure at main chamber inlet Air temp at K 300 300 300
300 300 300 main chamber inlet Air temp at K 400 400 330 320 400
325 first injection zone Main g/s 132 132 132 132 132 132 chamber
air consumption Main g/s 8.4 9.0 9.8 7.2 9.0 9.8 chamber fuel
consumption Excess air -- 1.070 0.992 0.913 1.243 0.992 0.909
coefficient Average air K 1830 1860 1460 1480 1860 1420 temp at
main chamber outlet Mach number -- 0.934 0.934 0.823 0.973 0.990
1.000 in first injection zone Speed in first m/s 342 342 274 328
366 330 injection zone Mach number -- 0.832 0.795 0.860 0.300 0.334
0.297 of stream at main chamber outlet Average gas m/s 648 624 597
210 272 204 consumption at main chamber outlet Experimental
parametric results A.sub.oc .times. F.sub.oc .times. B.sub.oc
.times. C.sub.oc .times. G.sub.oc = 1 .+-. .DELTA.oc A.sub.oc --
2.274 2.304 2.259 2.268 2.304 2.246 F.sub.oc -- 0.305 0.0836
B.sub.oc -- 1.289 1.388 1.077 3.920 3.597 4.100 C.sub.oc -- 1.240
1.173 1.418 1.540 1.750 1.540 G.sub.oc -- 1.064 1.068 1.074 1.054
1.068 1.074 .DELTA.oc -- 0.179 0.222 0.130 0.229 0.302 0.273
.delta.oc % 17.9 22.2 13.0 22.9 30.2 27.3
[0154] Applicant's teachings also relate to the use of reagents to
refine gaseous streams containing pollutants. Refinement of flue
gases can be carried out using a multistage vortex counterflow
combustion apparatus, which can be similar to the apparatuses 100,
200, 300, 400, 500, 600, 700, 800, 900 and 1000. Thermochemical
processes in the chamber(s) are taking place in vortex flows of the
mixture of flue gases, water, burning products and/or chemical
reagents. Vortex flows can have unique characteristics, can
intensify thermochemical processes, and can increase refinement
efficiency. Pollutants targeted during the refinement can include
sulfur dioxide SO.sub.2, nitrogen oxides NO.sub.x and/or carbon
dioxide CO.sub.2. During refinement, solid and gaseous components
can be produced. Solid components can be non-toxic and can be
recycled. Gaseous components, for example, N.sub.2, O.sub.2 and
water steam, can be emitted into the atmosphere without the need
for further processing.
[0155] Combustion apparatuses taught herein are appropriate for
implementation as a thermochemical reactor for at least the
following reasons. High temperatures promote relatively high
chemical reaction speeds, since an increase in temperature
generally leads to an increase in the kinetic energy and number of
collisions of chemical particles. Furthermore, the presence of
anisotropic turbulence in a reaction environment can promote more
complete mixing of the reagents, which can also lead to an increase
in reaction speed. The presence of intense acoustic oscillations
can yet also lead to the increase of the chemical reaction speed,
because it can produce a mechanical effect on the reagent
particles. The reagent particles are stirred intensively and
collide with each other, which can lead to the formation of free
radicals on the outer surface of the particles.
[0156] Various chemical reagents can be used, depending on the
composition of the gaseous stream to be refined and which
pollutants are desired to be removed by the refinement processes.
The following examples are intended to be illustrative but
non-limiting.
[0157] In a first example, an ammoniac method can be implemented to
provide for the simultaneous refinement of flue gases from SO.sub.2
and NO.sub.2 in the combustion apparatus. This method is relatively
simple and can produce finished products that may be recycled. For
the reaction, ammonia NH.sub.3 or carbamide CO(NH.sub.2).sub.2 can
be used as chemical reagents. Solid products can include ammonium
sulfate (NH.sub.4)2.SO.sub.4, which is a mineral fertilizer.
Gaseous products can include nitrogen N.sub.2 and water steam
H.sub.2O. The following chemical reactions can take place:
4NH.sub.3+3NO.sub.2=3.5N.sub.2+6H.sub.2O-1627.07 kJ/mole (Eq.
9)
CO(NH.sub.2).sub.2+H.sub.2O.dbd.CO.sub.2+2NH.sub.3+136.08 kJ/mole
(Eq. 10)
It is noted that flue gases can contain nitrogen oxides NO and
NO.sub.2, but NO typically immediately oxidizes to NO.sub.2, and
therefore only NO.sub.2 is considered. Besides the chemical
reactions involving the interaction of NH.sub.3 with NO.sub.2,
reactions with sulfur dioxide SO.sub.2 may also be taking place in
accordance with the following:
2SO.sub.2+O.sub.2=2SO.sub.3-185.9 kJ/mole (Eq. 11)
SO.sub.3+H.sub.2O.dbd.H.sub.2SO.sub.4-125.2 kJ/mole (Eq. 12)
2NH.sub.3+H.sub.2SO.sub.4.dbd.(NH.sub.4).sub.2SO.sub.4-275.9
kJ/mole (Eq. 13)
[0158] In a second example, simultaneous use of two chemical
reagents can be implemented for the refining of flue gases from
SO.sub.2 and NO.sub.2 in the combustion apparatus. A first one of
the reagents can be NH.sub.3 or CO(NH.sub.2).sub.2. A second one of
the reagents can be powdery sodium bicarbonate, calcium carbonate,
calcium oxide or calcium hydroxide, which can be supplied in
atomized form into the combustion apparatus.
[0159] In a third example, ammonia NH.sub.3 can be used as the
chemical reagent. The following reaction can take place in the
combustion apparatus:
CO.sub.2+2NH.sub.3.dbd.CO(NH.sub.2)ONH.sub.4-2,552.73 kJ/kg
CO.sub.2 (Eq. 14)
where CO(NH.sub.2)ONH.sub.4 is carbamic acidic ammonium, which can
become carbamide, is accordance with the following reaction:
CO(NH.sub.2)ONH.sub.4.dbd.CO(NH.sub.4).sub.2+H.sub.2O+483.3 kJ/kg
CO(NH.sub.2).sub.2 (Eq. 15)
A refined product stream from the combustion apparatus can then
undergo separation procedure to separate solid materials from the
gaseous stream.
[0160] In a fourth example, carbon, water and calcium oxide CaO can
be used as chemical reagents. Chemical reactions in the combustion
apparatus can produce calcium carbonate CaCO.sub.3, which can be
used as a fertilizer. Calcium carbonate CaCO.sub.3 can also be used
for the refinement of flue gases from sulfur dioxide SO.sub.2. The
following chemical reactions can take place in the combustion
apparatus:
CO.sub.2+C=2CO+174.18 kJ/mole or 3,958.64 kJ/kg CO.sub.2 (Eq.
16)
CO+H.sub.2O+CaO.dbd.CaCO.sub.3+H.sub.2-199.3 kJ/mole or -1.993
kJ/kg CaCO.sub.3 (Eq. 17)
[0161] In a fifth example, CO.sub.2 can be reduced or substantially
eliminated from an incoming gaseous stream utilizing the combustion
apparatuses as described herein, with which the following sequence
of reactions can be performed:
CO.sub.2+3H.sub.2(Copper and Aluminum
Catalyst).fwdarw.CH.sub.3OH+H.sub.2O (Eq. 18)
2CH.sub.3OH.fwdarw.C.sub.2H.sub.6O+H.sub.2O (Eq. 19)
C.sub.4H.sub.8O.sub.2+CH.sub.3OH(H.sub.2SO.sub.4 as a
catalyst).fwdarw.C.sub.3H.sub.6O.sub.2+C.sub.2H.sub.5OH (Eq.
20)
Equations 18 and 19 can take place in the main chamber, whereas
Equation 20 can take place in an additional reaction chamber. One
or more separators and/or chemical storage mechanisms can also be
installed downstream from the additional reaction chamber.
[0162] Combustion apparatuses can be tailored for the refinement of
various pollutants from gaseous streams and for the introduction of
various reagents, and are based on vortex counterflow combustion
apparatuses, which can complete thermochemical processes required
for the refinement of gaseous streams with generally high quality,
high speed and high efficiency.
[0163] FIGS. 44 to 48 show an apparatus 1100 according to an
eleventh example described in this specification. The apparatus
1100 is similar to the apparatuses 100, 200, 300, 400, 500, 600,
700, 800, 900 and 1000, with like features identified by like
reference numbers. In particular, the apparatus 1100 includes a
means for introducing at least one reagent to the main chamber
1104, as described in further detail below.
[0164] Referring particularly to FIG. 46, the first injection zone
1148 includes a source of reagents 1186, which can be positioned
next to the air or oxidant source 1118. An external source can
provide air or oxidant to the source 1118 at an elevated pressure.
The source 1186 can introduce reagents tangentially relative to the
direction of fluid flow within the first injection zone 1148.
Furthermore, tangential supply of the reagents via the source 1186
relative to the air or oxidant source 1118 can serve to disperse
the reagents, which may be in the form of a fine powder or
particulate. A first pre-chamber 1110 and a fuel source 1116 can
also be provided as inputs to the first injection zone 1148. The
fuel source 1126 of the first pre-chamber 1110 and the fuel source
1116 can be connected to, for example but not limited to, a feed of
natural gas, propane, or diesel fuel.
[0165] Referring particularly to FIG. 47, the second injection zone
1172 includes a source of reagents 1184, which can be positioned
next to the air or oxidant source 1114. The source 1184 can
introduce reagents tangentially relative to the direction of fluid
flow within the second injection zone 1172. An external source can
provide air or oxidant to the source 1114 at an elevated pressure.
A second pre-chamber 1108 can also be provided as an input to the
second injection zone 1172. The fuel source 1122 of the second
pre-chamber 1108 can be connected to, for example but not limited
to, a feed of natural gas, propane or diesel fuel.
[0166] Referring particularly to FIG. 48, and with continued
reference to FIG. 45, a third injection zone 1194 produces fluid
stream 1178. The third injection zone 1194 is in fluid
communication with the at least one third channel 1176 and delivers
the stream 1178 to the afterburner chamber 1106 proximate to an
inlet 1192 of the afterburner chamber 1106. The third injection
zone 1194 can be generally annular in shape and extend radially
around a circumference of the afterburner chamber 1106. The third
injection zone 1194 can include a plurality of swirl vanes 1152 for
directing rotational fluid flow. The third injection zone 1194
includes a source of reagents 1190 and an air or oxidant source
1188. The source 1190 can introduce reagents tangentially relative
to the direction of fluid flow within the third injection zone
1194. An external source can provide air or oxidant to the source
1188 at an elevated pressure.
[0167] The thermochemical parameters of temperature, static
pressure, ingredients, and the flow structure (temperature fields,
pressures and speeds) can influence the speed of chemical reactions
in the apparatus 1100, and the refinement of the input stream 1112.
Furthermore, concentrations of the chemical reagents and their
distribution among the chambers 1102, 1104, 1106 can influence the
speed of chemical reactions in the apparatus 1100. Supply or
introduction of the one or more reagents to the chambers 1102,
1104, 1106 can be selectively controlled by the sources 1184, 1186,
1190, respectively. Concentrations of chemical reagents and their
distribution among the chambers 1102, 1104, 1106 can be controlled
to enable complete or near complete reactions.
[0168] Different chemical reagents can be supplied into the
apparatus 1100, depending on the components to be refined.
Furthermore, the reagent supplied to source 1184 need not be the
same chemical compound as that supplied at source 1186, and nor
does the reagent supplied to source 1186 need not be the same
chemical compound supplied at source 1190. In some examples, it may
be desirable to introduce reagents at sources 1184, 1186, but not
at source 1190. Various configurations are possible and within the
scope of the applicant's teachings herein.
[0169] FIGS. 49 to 52 show an apparatus 1200 according to a twelfth
example described in this specification. The apparatus 1200 is
similar to the apparatuses 100, 200, 300, 400, 500, 600, 700, 800,
900, 1000 and 1100, with like features identified by like reference
numbers. In particular, and similar to the apparatus 1100, the
apparatus 1200 includes a means for introducing at least one
reagent to the main chamber 1204, as described in further detail
below.
[0170] The apparatus 1200 includes an injection nozzle 1296 for
supplying or introducing a gaseous stream to be refined into the
main chamber 1204. In some examples, the gaseous stream can be
formed upstream of the injection nozzle 1296 by the mixture of flue
gases along with fuel and/or oxidant. The injection nozzle 1296 is
positioned at the first end 1236 generally at a central apex point
of the spherical end surface 1282. The apparatus 1200 does not
include a primary chamber.
[0171] Referring particularly to FIG. 51, the first injection zone
1248 includes a source of reagents 1286 and an air or oxidant
source 1218. An external source can provide air or oxidant to the
source 1218 at an elevated pressure. The source 1286 can introduce
reagents tangentially relative to the direction of fluid flow
within the first injection zone 1248. Referring particularly to
FIG. 52, the third injection zone 1294 includes a source of
reagents 1290 and an air or oxidant source 1288. An external source
can provide air or oxidant to the source 1288 at an elevated
pressure. The source 1290 can introduce reagents tangentially
relative to the direction of fluid flow within the third injection
zone 1294.
[0172] The apparatus 1200 can be implemented in situations where
the flow rate of gaseous stream to be refined is relatively high,
and also either the temperature of the gaseous stream to be refined
is high enough for the desired reactions or the reactions can occur
at relatively low temperature, so heating is not required and thus
no primary chamber is necessary. One limitation to the design of
the apparatus 1200 is that relatively high stress can be put on the
injection nozzle 1296 to provide the required pressure of gaseous
stream being introduced to the main chamber 1204. Another
limitation to the design of the apparatus 1200 is that there is no
second injection zone and thus there is one less source for
supplying reagents.
[0173] FIGS. 53 to 56 show an apparatus 1300 according to a
thirteenth example described in this specification. The apparatus
1300 is similar to the apparatuses 100, 200, 300, 400, 500, 600,
700, 800, 900, 1000, 1100 and 1200, with like features identified
by like reference numbers. In particular, and similar to the
apparatuses 1100 and 1200, the apparatus 1300 includes a means for
introducing at least one reagent to the main chamber 1304, as
described in further detail below.
[0174] A gaseous stream to be refined is introduced to the first
injection zone 1348 via inlet or source 1312. An ignition source or
igniter 1354 is provided within the inlet 1312 to ignite the
incoming stream as it is being tangentially supplied to the first
injection zone 1348. Like apparatus 1200, apparatus 1300 does not
include a primary chamber.
[0175] Referring particularly to FIG. 55, the first injection zone
1348 includes a source of reagents 1386. The source 1386 can
introduce reagents tangentially relative to the direction of fluid
flow within the first injection zone 1348. Referring particularly
to FIG. 56, the third injection zone 1394 includes a source of
reagents 1390 and an air or oxidant source 1388. An external source
can provide air or oxidant to the source 1388 at an elevated
pressure. The source 1390 can introduce reagents tangentially
relative to the direction of fluid flow within the third injection
zone 1394.
[0176] The apparatus 1300 can also be implemented in situations
where the flow rate of gaseous stream to be refined is relatively
high, and also either the temperature of the gaseous stream to be
refined is high enough for the desired reactions or the reactions
can occur at relatively low temperature, so heating is not required
and thus no primary chamber is necessary.
[0177] While the applicant's teachings are described in conjunction
with various embodiments, it is not intended that the applicant's
teachings be limited to such embodiments. The applicant's teachings
encompass various alternatives, modifications, and equivalents, as
will be appreciated by those of skill in the art.
* * * * *