U.S. patent application number 15/390052 was filed with the patent office on 2018-06-28 for turbine engine assembly including a rotating detonation combustor.
The applicant listed for this patent is General Electric Company. Invention is credited to Anthony John Dean, Thomas Michael Lavertu, Jr., Andrew Maxwell Peter, James Albert Tallman, Venkat Eswarlu Tangirala.
Application Number | 20180180289 15/390052 |
Document ID | / |
Family ID | 62629567 |
Filed Date | 2018-06-28 |
United States Patent
Application |
20180180289 |
Kind Code |
A1 |
Lavertu, Jr.; Thomas Michael ;
et al. |
June 28, 2018 |
TURBINE ENGINE ASSEMBLY INCLUDING A ROTATING DETONATION
COMBUSTOR
Abstract
A turbine engine assembly including a rotating detonation
combustor configured to combust a fuel-air mixture. The rotating
detonation combustor includes a radially inner side wall, a
radially outer side wall extending about the radially inner side
wall such that an annular combustion chamber is at least partially
defined therebetween, and a cooling conduit extending along at
least one of the radially inner side wall or the radially outer
side wall. The assembly also includes a first compressor configured
to discharge a flow of cooling air towards the rotating detonation
combustor, and to channel the flow of cooling air through the
cooling conduit.
Inventors: |
Lavertu, Jr.; Thomas Michael;
(Clifton Park, NY) ; Peter; Andrew Maxwell;
(Saratoga Springs, NY) ; Tangirala; Venkat Eswarlu;
(Niskayuna, NY) ; Tallman; James Albert;
(Glenville, NY) ; Dean; Anthony John; (Scotia,
NY) |
|
Applicant: |
Name |
City |
State |
Country |
Type |
General Electric Company |
Schenectady |
NY |
US |
|
|
Family ID: |
62629567 |
Appl. No.: |
15/390052 |
Filed: |
December 23, 2016 |
Current U.S.
Class: |
1/1 |
Current CPC
Class: |
F23R 2900/03041
20130101; F23R 3/16 20130101; F23R 3/56 20130101; F02C 5/02
20130101; F23R 7/00 20130101 |
International
Class: |
F23R 7/00 20060101
F23R007/00 |
Claims
1. A turbine engine assembly comprising: a rotating detonation
combustor configured to combust a fuel-air mixture, wherein said
rotating detonation combustor comprises: a radially inner side
wall; a radially outer side wall extending about said radially
inner side wall such that an annular combustion chamber is at least
partially defined therebetween; and a cooling conduit extending
along at least one of said radially inner side wall or said
radially outer side wall; and a first compressor configured to
discharge a flow of cooling air towards said rotating detonation
combustor and configured to channel the flow of cooling air through
said cooling conduit.
2. The turbine engine assembly in accordance with claim 1, wherein
said rotating detonation combustor further comprises an annular
jacket radially spaced from at least one of said radially inner
side wall or said radially outer side wall, said annular jacket at
least partially defining said cooling conduit.
3. The turbine engine assembly in accordance with claim 1, wherein
said rotating detonation combustor is configured to channel the
fuel-air mixture in a first direction within said annular
combustion chamber, said first compressor coupled in flow
communication with said rotating detonation combustor such that the
flow of cooling air is channeled in a second direction, opposite
from the first direction, within said cooling conduit.
4. The turbine engine assembly in accordance with claim 1, wherein
said cooling conduit extends along said radially inner side wall,
wherein said rotating detonation combustor is configured to channel
the fuel-air mixture in a first direction within said annular
combustion chamber, and wherein said first compressor is coupled in
flow communication with said rotating detonation combustor such
that the flow of cooling air is channeled in the first direction
within said cooling conduit.
5. The turbine engine assembly in accordance with claim 1, wherein
said rotating detonation combustor further comprises a fuel-air
mixer configured to receive fuel and air to form the fuel-air
mixture, said cooling conduit oriented such that the flow of
cooling air channeled therethrough is further channeled towards
said fuel-air mixer such that the fuel-air mixture is formed from
the cooling air.
6. The turbine engine assembly in accordance with claim 5, wherein
said cooling conduit and said fuel-air mixer are coupled in flow
communication such that the air in the fuel-air mixture is derived
entirely from the flow of cooling air.
7. The turbine engine assembly in accordance with claim 1 further
comprising a second compressor configured to receive a flow of
bleed air from said first compressor, and configured to discharge a
flow of boosted cooling air towards said rotating detonation
combustor such that the fuel-air mixture is formed from a mixed
flow of cooling air and boosted cooling air.
8. The turbine engine assembly in accordance with claim 7 further
comprising a cooling device positioned between said first
compressor and said second compressor, said cooling device
configured to cool the flow of bleed air before being channeled
towards said second compressor.
9. A rotating detonation combustor comprising: a radially inner
side wall; a radially outer side wall extending about said radially
inner side wall such that an annular combustion chamber is at least
partially defined therebetween; and a cooling conduit configured to
channel cooling air therethrough, said cooling conduit extending
along at least one of said radially inner side wall or said
radially outer side wall.
10. The rotating detonation combustor in accordance with claim 9
further comprising a plurality of thermally conductive projection
members extending into an interior of said cooling conduit from at
least one of said radially inner side wall or said radially outer
side wall.
11. The rotating detonation combustor in accordance with claim 9
further comprising: a first end plate coupled to said radially
inner side wall and said radially outer side wall, said first end
plate at least partially defining said annular combustion chamber,
wherein said first end plate comprises an air inlet defined
therein; and a second end plate spaced from said first end plate
and at least partially defining said cooling conduit such that the
cooling air channeled therethrough is further channeled towards
said air inlet.
12. The rotating detonation combustor in accordance with claim 9
further comprising a first annular jacket radially spaced from said
radially outer side wall such that said cooling conduit is defined
between said radially outer side wall and said first annular
jacket.
13. The rotating detonation combustor in accordance with claim 9
further comprising a second annular jacket radially spaced from
said radially inner side wall such that said cooling conduit is
defined between said radially inner side wall and said second
annular jacket.
14. The rotating detonation combustor in accordance with claim 9,
wherein said cooling conduit extends within a portion of at least
one of said radially inner side wall or said radially outer side
wall.
15. The rotating detonation combustor in accordance with claim 14,
wherein at least a portion of said at least one of said radially
inner side wall or said radially outer side wall is recessed
relative to an interior of said annular combustion chamber such
that a stepped side wall portion is formed, said stepped side wall
portion defining an air pocket within said annular combustion
chamber, and said stepped side wall portion comprising an opening
defined therein that couples said cooling conduit in flow
communication with said air pocket.
16. A turbine engine assembly comprising: a rotating detonation
combustor configured to combust a fuel-air mixture, wherein said
rotating detonation combustor comprises: a radially inner side
wall; a radially outer side wall extending about said radially
inner side wall such that an annular combustion chamber is at least
partially defined therebetween; and a cooling conduit extending
along at least one of said radially inner side wall or said
radially outer side wall; and a source of cooling fluid coupled in
flow communication with said rotating detonation combustor, said
source of cooling fluid configured to discharge a flow of cooling
fluid towards said rotating detonation combustor, and configured to
channel the flow of cooling fluid through said cooling conduit,
wherein the cooling fluid includes at least one of steam, water, or
fuel.
17. The turbine engine assembly in accordance with claim 16,
wherein said source of cooling fluid is configured to channel steam
or water through said cooling conduit such that heated steam or
heated water is formed, said turbine engine assembly further
comprising a steam turbine configured to receive a flow of heated
steam or heated water from said cooling conduit.
18. The turbine engine assembly in accordance with claim 16,
wherein said source of cooling fluid is configured to channel fuel
through said cooling conduit, wherein at least one of said radially
inner side wall or said radially outer side wall comprises at least
one fuel inlet defined therein, said at least one fuel inlet
configured to inject the fuel into said annular combustion
chamber.
19. The turbine engine assembly in accordance with claim 18,
wherein said at least one fuel inlet comprises a plurality of fuel
inlets spaced axially from each other relative to a centerline of
said rotating detonation combustor.
20. The turbine engine assembly in accordance with claim 18,
wherein said rotating detonation combustor further comprises a
fuel-air mixer positioned within said annular combustion chamber
upstream from said at least one fuel inlet relative to a flow
direction of the fuel-air mixture.
Description
BACKGROUND
[0001] The present disclosure relates generally to rotating
detonation combustion systems and, more specifically, to systems
and methods of cooling a rotating detonation combustor.
[0002] In rotating detonation engines and, more specifically, in
rotating detonation combustors, a mixture of fuel and an oxidizer
is ignited such that combustion products are formed. For example,
the combustion process begins when the fuel-oxidizer mixture in a
tube or a pipe structure is ignited via a spark or another suitable
ignition source to generate a compression wave. The compression
wave is followed by a chemical reaction that transitions the
compression wave to a detonation wave. The detonation wave enters a
combustion chamber of the rotating detonation combustor and travels
along the combustion chamber. Air and fuel are separately fed into
the rotating detonation combustion chamber and are consumed by the
detonation wave. As the detonation wave consumes air and fuel,
combustion products traveling along the combustion chamber
accelerate and are discharged from the combustion chamber. However,
rotating detonation combustors generally operate at high local
combustion temperatures greater than the temperature limit of
materials used to form at least some portions of the rotating
detonation combustor.
BRIEF DESCRIPTION
[0003] In one aspect, a turbine engine assembly is provided. The
assembly includes a rotating detonation combustor configured to
combust a fuel-air mixture. The rotating detonation combustor
includes a radially inner side wall, a radially outer side wall
extending about the radially inner side wall such that an annular
combustion chamber is at least partially defined therebetween, and
a cooling conduit extending along at least one of the radially
inner side wall or the radially outer side wall. The assembly also
includes a first compressor configured to discharge a flow of
cooling air towards the rotating detonation combustor, and to
channel the flow of cooling air through the cooling conduit.
[0004] In another aspect, a rotating detonation combustor is
provided. The combustor includes a radially inner side wall, a
radially outer side wall extending about the radially inner side
wall such that an annular combustion chamber is at least partially
defined therebetween, and a cooling conduit configured to channel
cooling air therethrough. The cooling conduit extends along at
least one of the radially inner side wall or the radially outer
side wall.
[0005] In yet another aspect, a turbine engine assembly is
provided. The assembly includes a rotating detonation combustor
configured to combust a fuel-air mixture. The rotating detonation
combustor includes a radially inner side wall, a radially outer
side wall extending about the radially inner side wall such that an
annular combustion chamber is at least partially defined
therebetween, and a cooling conduit extending along at least one of
the radially inner side wall or the radially outer side wall. The
assembly further includes a source of cooling fluid coupled in flow
communication with the rotating detonation combustor. The source of
cooling fluid is configured to discharge a flow of cooling fluid
towards the rotating detonation combustor, and to channel the flow
of cooling fluid through the cooling conduit. The cooling fluid
includes at least one of steam, water, or fuel.
DRAWINGS
[0006] These and other features, aspects, and advantages of the
present disclosure will become better understood when the following
detailed description is read with reference to the accompanying
drawings in which like characters represent like parts throughout
the drawings, wherein:
[0007] FIG. 1 is a schematic illustration of an exemplary combined
cycle power generation system;
[0008] FIG. 2 is a schematic illustration of an exemplary rotating
detonation combustor that may be used in the gas turbine engine
assembly shown in FIG. 1;
[0009] FIG. 3 is a schematic illustration of the rotating
detonation combustor shown in FIG. 2, in accordance with a second
embodiment of the disclosure;
[0010] FIG. 4 is an enlarged cross-sectional view of a portion of
the rotating detonation combustor shown in FIG. 2, taken along Area
4;
[0011] FIG. 5 is an enlarged cross-sectional view of a portion of
the rotating detonation combustor shown in FIG. 2, taken along Area
5;
[0012] FIG. 6 is a schematic illustration of an exemplary rotating
detonation combustion system that may be used in the combined cycle
power generation system shown in FIG. 1;
[0013] FIG. 7 is a schematic illustration of an alternative
rotating detonation combustion system that may be used in the
combined cycle power generation system shown in FIG. 1;
[0014] FIG. 8 is an enlarged cross-sectional view of a portion of
the rotating detonation combustor shown in FIG. 7, taken along Area
8; and
[0015] FIG. 9 is a further alternative rotating detonation
combustion system that may be used in the combined cycle power
generation system shown in FIG. 1.
[0016] Unless otherwise indicated, the drawings provided herein are
meant to illustrate features of embodiments of the disclosure.
These features are believed to be applicable in a wide variety of
systems comprising one or more embodiments of the disclosure. As
such, the drawings are not meant to include all conventional
features known by those of ordinary skill in the art to be required
for the practice of the embodiments disclosed herein.
DETAILED DESCRIPTION
[0017] In the following specification and the claims, reference
will be made to a number of terms, which shall be defined to have
the following meanings.
[0018] The singular forms "a", "an", and "the" include plural
references unless the context clearly dictates otherwise.
[0019] "Optional" or "optionally" means that the subsequently
described event or circumstance may or may not occur, and that the
description includes instances where the event occurs and instances
where it does not.
[0020] Approximating language, as used herein throughout the
specification and claims, may be applied to modify any quantitative
representation that could permissibly vary without resulting in a
change in the basic function to which it is related. Accordingly, a
value modified by a term or terms, such as "about",
"approximately", and "substantially", are not to be limited to the
precise value specified. In at least some instances, the
approximating language may correspond to the precision of an
instrument for measuring the value. Here and throughout the
specification and claims, range limitations may be combined and/or
interchanged. Such ranges are identified and include all the
sub-ranges contained therein unless context or language indicates
otherwise.
[0021] Embodiments of the present disclosure relate to systems and
methods of cooling a rotating detonation combustor. More
specifically, the systems described herein include a rotating
detonation combustor including an annular combustion chamber
defined by a radially inner side wall and a radially outer side
wall, and at least one cooling conduit positioned for cooling one
or both of the radially inner side wall or the radially outer side
wall. The cooling conduit described herein cools the side walls by
channeling a cooling fluid therethrough, such as cooling air (i.e.,
an oxidizer), fuel, steam, or water. As such, the rotating
detonation combustor described herein is capable of producing
detonations while still operating within predefined material
temperature limits.
[0022] As used herein, "detonation" and "quasi-detonation" may be
used interchangeably. Typical embodiments of detonation chambers
include a means of igniting a fuel/oxidizer mixture, for example a
fuel/air mixture, and a confining chamber, in which pressure wave
fronts initiated by the ignition process coalesce to produce a
detonation wave. Each detonation or quasi-detonation is initiated
either by external ignition, such as spark discharge or laser
pulse, or by gas dynamic processes, such as shock focusing,
autoignition or by another detonation via cross-firing. The
geometry of the detonation chamber is such that the pressure rise
of the detonation wave expels combustion products out the
detonation chamber exhaust to produce a thrust force. In addition,
rotating detonation combustors are designed such that a
substantially continuous detonation wave is produced and discharged
therefrom. As known to those skilled in the art, detonation may be
accomplished in a number of types of detonation chambers, including
detonation tubes, shock tubes, resonating detonation cavities, and
annular detonation chambers.
[0023] FIG. 1 is a schematic illustration of an exemplary combined
cycle power generation system 100. Power generation system 100
includes a gas turbine engine assembly 102 and a steam turbine
engine assembly 104. Gas turbine engine assembly 102 includes a
compressor 106, a combustor 108, and a first turbine 110 powered by
expanding hot gas produced in combustor 108 for driving an
electrical generator 112. Gas turbine engine assembly 102 may be
used in a stand-alone simple cycle configuration for power
generation or mechanical drive applications. In the exemplary
embodiment, exhaust gas 114 is channeled from first turbine 110
towards a heat recovery steam generator (HRSG) 116 for recovering
waste heat from exhaust gas 114. More specifically, HRSG 116
transfers heat from exhaust gas 114 to water/steam 118 channeled
through HRSG 116 to produce steam 120. Steam turbine engine
assembly 104 includes a second turbine 122 that receives steam 120,
which powers second turbine 122 for further driving electrical
generator 112.
[0024] In operation, air enters gas turbine engine assembly 102
through an intake 121 and is channeled through multiple stages of
compressor 106 towards combustor 108. Compressor 106 compresses the
air and the highly compressed air is channeled from compressor 106
towards combustor 108 and mixed with fuel. The fuel-air mixture is
combusted within combustor 108. High temperature combustion gas
generated by combustor 108 is channeled towards first turbine 110.
Exhaust gas 114 is subsequently discharged from first turbine 110
through an exhaust 123.
[0025] FIG. 2 is a schematic illustration of an exemplary rotating
detonation combustor 124 that may be used in gas turbine engine
assembly 102 (shown in FIG. 1). In the exemplary embodiment,
rotating detonation combustor 124 (i.e., combustor 108 (shown in
FIG. 1)) includes a radially outer side wall 126 and a radially
inner side wall 128 that both extend circumferentially relative to
a centerline 130 of rotating detonation combustor 124. As such, an
annular combustion chamber 132 is defined between radially outer
side wall 126 and radially inner side wall 128. In addition,
rotating detonation combustor 124 includes a fuel-air mixer 134
coupled within annular combustion chamber 132. Fuel-air mixer 134
receives fuel 136 and air (not shown), and rotating detonation
combustor 124 combusts a fuel-air mixture 138 discharged from
fuel-air mixer 134. Moreover, rotating detonation combustor 124
channels fuel-air mixture 138 in a first direction 140 within
annular combustion chamber 132. While shown as traveling in an
axial direction along the length of rotating detonation combustor
124, it should be understood that fuel-air mixture 138 also flows
helically within annular combustion chamber 132.
[0026] In further embodiments, annular combustion chamber 132 is
any suitable geometric shape and does not necessarily include an
inner liner and/or center body. For example, in some embodiments,
annular combustion chamber 132 is substantially cylindrical.
[0027] Rotating detonation combustor 124 further includes a cooling
conduit 142 extending along at least one of radially outer side
wall 126 or radially inner side wall 128. For example, rotating
detonation combustor 124 includes at least one annular jacket
radially spaced from at least one of radially outer side wall 126
or radially inner side wall 128 for at least partially defining
cooling conduit 142. More specifically, in one embodiment, a first
annular jacket 144 is spaced from radially outer side wall 126 such
that a first cooling conduit 146 is defined between radially outer
side wall 126 and first annular jacket 144. In addition, a second
annular jacket 148 is spaced from radially inner side wall 128 such
that a second cooling conduit 150 is defined between radially inner
side wall 128 and second annular jacket 148. In an alternative
embodiment, and as applicable to the other embodiments described
herein, cooling is provided to either radially outer side wall 126
or radially inner side wall 128, but not both, with a single
cooling conduit.
[0028] In the exemplary embodiment, compressor 106 (shown in FIG.
1) discharges a flow of cooling air 152 towards rotating detonation
combustor 124 such that the flow of cooling air 152 is channeled
through cooling conduits 142. As such, heat produced by the
combustion of fuel-air mixture 138 is conducted through radially
outer side wall 126 and radially inner side wall 128, and
transferred to cooling air 152 channeled through cooling conduits
142. In one embodiment, compressor 106 is coupled in flow
communication with rotating detonation combustor 124 such that the
flow of cooling air 152 is channeled within first cooling conduit
146 and second cooling conduit 150 in a second direction 154
opposite from first direction 140. In addition, first cooling
conduit 146 and second cooling conduit 150 are oriented such that
the flow of cooling air 152 channeled therethrough is further
channeled towards fuel-air mixer 134 such that fuel-air mixture 138
is formed from cooling air 152. In other words, first cooling
conduit 146 and second cooling conduit 150 are oriented such that
the flow of cooling air 152 is channeled in a direction that
enables cooling air 152 to be combined with fuel 136 and included
in fuel-air mixture 138. More specifically, cooling air 152 enters
rotating detonation combustor 124 at a first end 153 thereof, and
flows in second direction 154 towards towards a second end 155 of
rotating detonation combustor 124. Cooling air 152 is then injected
into annular combustion chamber 132 for mixing with fuel 136.
[0029] Moreover, in one embodiment, cooling conduits 142 and
fuel-air mixer 134 are coupled in flow communication such that the
air in fuel-air mixture 138 is derived entirely from the flow of
cooling air 152, and such that no air from compressor 106 bypasses
annular combustion chamber 132. As such, limiting airflow bypass
facilitates enhancing the pressure gain capability of rotating
detonation combustor 124 such that the efficiency of gas turbine
engine 102 is increased.
[0030] Rotating detonation combustor 124 further includes a first
end plate 156 and a second end plate 158. First end plate 156 is
coupled to radially outer side wall 126 and radially inner side
wall 128 such that annular combustion chamber 132 is at least
partially defined by first end plate 156. First end plate 156
includes an air inlet 160 defined therein. Air inlet 160 is
positioned to couple cooling conduits 142 in flow communication
with annular combustion chamber 132 upstream of fuel-air mixer 134.
Second end plate 158 is spaced from first end plate 156 such that
cooling conduits 142 are at least partially defined therefrom. As
such, cooling air 152 channeled through first cooling conduit 146
and second cooling conduit 150 is channeled towards air inlet 160
for injection into annular combustion chamber 132 and for mixing
with fuel 136 to form fuel-air mixture 138.
[0031] FIG. 3 is a schematic illustration of rotating detonation
combustor 124 in accordance with a second embodiment of the
disclosure. As described above, rotating detonation combustor 124
channels fuel-air mixture 138 in first direction 140 within annular
combustion chamber 132. In the exemplary embodiment, second cooling
conduit 150 extends along radially inner side wall 128, and
compressor 106 (shown in FIG. 1) is coupled in flow communication
with rotating detonation combustor 124 such that the flow of
cooling air 152 within second cooling conduit 150 is likewise
channeled in first direction 140 for discharge towards first
turbine 110 (shown in FIG. 1). In such an embodiment, the air in
fuel-air mixture 138 is derived entirely from the flow of cooling
air 152 channeled through first cooling conduit 146. As such,
channeling cooling air 152 in first direction 140 provides cooling
along radially inner side wall 128 and provides purging and pilot
flame holding capabilities for rotating detonation combustor
124.
[0032] FIG. 4 is an enlarged cross-sectional view of a portion of
rotating detonation combustor 124, taken along Area 4 (shown in
FIG. 2). In the exemplary embodiment, rotating detonation combustor
124 further includes a plurality of thermally conductive projection
members 162 extending into an interior 164 of first cooling conduit
146. Thermally conductive projection member 162 provides a heat
sink for heat produced by combustion of fuel-air mixture 138 (shown
in FIG. 2) and conducted through radially outer side wall 126. As
such, heat dissipation from radially outer side wall 126 is
improved. As shown, thermally conductive projection members 162
extend into interior 164 of first cooling conduit 146 from radially
outer side wall 126. Alternatively, or in addition to thermally
conductive projection members 162 extending from radially outer
side wall 126, thermally conductive projection members 162 extend
into second cooling conduit 150 from radially inner side wall 128
(both shown in FIG. 2). In addition, thermally conductive
projection member 162 acts as a turbulator to facilitate vitiating
the flow of cooling air 152 channeled across radially outer side
wall 126, thereby increasing heat transfer to cooling air 152.
[0033] FIG. 5 is an enlarged cross-sectional view of a portion of
rotating detonation combustor 124, taken along Area 5 (shown in
FIG. 2). In the exemplary embodiment, cooling conduit 142 extends
within a thickness portion of at least one of radially outer side
wall 126 or radially inner side wall 128. As shown, cooling conduit
142 extends within the thickness portion of radially outer side
wall 126. In addition, at least a portion of radially outer side
wall 126 is recessed relative to an interior 166 of annular
combustion chamber 132 such that one or more stepped side wall
portions 168 are formed. Each stepped side wall portion 168 defines
an air pocket 170 within annular combustion chamber 132, and
includes an opening 172 defined therein that couples cooling
conduit 142 in flow communication with air pocket 170. As such, at
least a portion of cooling air 152 channeled within cooling conduit
142 flows into air pocket 170, thereby forming an air isolation
layer 174 within annular combustion chamber 132. As such, air
isolation layer 174 provides cooling and pressure force dampening,
induced by detonative combustion, for radially outer side wall
126.
[0034] FIG. 6 is a schematic illustration of an exemplary rotating
detonation combustion (RDC) system 176 that may be used in combined
cycle power generation system 100 (shown in FIG. 1). In the
exemplary embodiment, RDC system 176 includes rotating detonation
combustor 124 and a source 178 of cooling fluid, such as steam or
water 180. Source 178 of cooling fluid channels cooling fluid, such
as steam or water 180, towards rotating detonation combustor 124,
and channels the flow of cooling fluid through cooling conduits
142. As such, heat produced by the combustion of fuel-air mixture
138 is transferred to steam or water 180 such that heated steam or
water 182 is formed. Rotating detonation combustor 124 then
channels a flow of heated steam or water 182 from cooling conduits
142 towards second turbine 122 (shown in FIG. 1) for use in the
bottoming cycle thereof to facilitate power generation. As such,
cooling is provided to rotating detonation combustor 124 and heat
produced by the combustion of fuel-air mixture 138 is utilized in
an effective and thermally efficient manner.
[0035] FIG. 7 is a schematic illustration of an alternative RDC
system 184 that may be used in combined cycle power generation
system 100 (shown in FIG. 1), and FIG. 8 is an enlarged
cross-sectional view of a portion of rotating detonation combustor
124, taken along Area 8 (shown in FIG. 7). In the exemplary
embodiment, RDC system 184 includes rotating detonation combustor
124 and a source 186 of cooling fluid, such as fuel 136. In
operation, source 186 of cooling fluid channels fuel 136 through
cooling conduits 142.
[0036] In addition, referring to FIG. 8, radially outer side wall
126 includes at least one fuel inlet 188 defined therein.
Specifically, a plurality of fuel inlets 188 are spaced axially
from each other relative to centerline 130 (shown in FIG. 2) of
rotating detonation combustor 124. Fuel inlets 188 inject fuel 136,
in the form of fuel jets 190, into annular combustion chamber 132
for mixing with fuel-air mixture 138. Moreover, rotating detonation
combustor 124 includes fuel-air mixer 134, and fuel-air mixer 134
is positioned within annular combustion chamber 132 upstream from
the plurality of fuel inlets 188 relative to a flow direction of
fuel-air mixture 138. As such, staged fuel injection longitudinally
relative to centerline 130 (shown in FIG. 2) facilitates improving
mixing of the fuel and air, and facilitates controlling the
equivalence ratio of the fuel-air mixture along the axial length of
rotating detonation combustor 124. Moreover, staged fuel injection
also facilitates improving the fill length of rotating detonation
combustor 124.
[0037] FIG. 9 is a further alternative RDC system 192 that may be
used in combined cycle power generation system 100 (shown in FIG.
1). In the exemplary embodiment, RDC system 192 includes a second
compressor 194 coupled downstream from and that receives a flow of
bleed air 196 from compressor 106. Second compressor 194 compresses
the flow of bleed air 196, and discharges a flow of boosted cooling
air 198 towards rotating detonation combustor 124 such that
fuel-air mixture 138 (shown in FIG. 2) is formed from a mixed flow
of cooling air 152 (shown in FIG. 2) and boosted cooling air 198.
As such, using boosted cooling air 198 to cool rotating detonation
combustor 124 facilitates improving the cooling effectiveness
provided to rotating detonation combustor 124 from the cooling
fluid.
[0038] In some embodiments, RDC system 192 includes a cooling
device 200 positioned between compressor 106 and second compressor
194. Cooling device 200 cools the flow of bleed air 196 before
being channeled towards second compressor 194. As such, compression
of bleed air 196 within second compressor 194 is provided in a more
cost effective manner relative to compressing uncooled air.
[0039] The systems and methods described herein facilitate
providing cooling to a rotating detonation combustor. The cooling
is provided by channeling a cooling fluid through one or more
cooling conduits that extend along a radially outer side wall or a
radially inner side wall of the rotating detonation combustor. In
addition, the system described herein facilitates using the heat
generated by combustion to improve the thermal efficiency of
related assemblies.
[0040] An exemplary technical effect of the systems and methods
described herein includes at least one of: (a) providing cooling to
a rotating detonation combustor; (b) increasing the efficiency of a
gas turbine engine; and (c) utilizing one or more architectural
cooling concepts to improve the thermal efficiency of a turbine
engine assembly.
[0041] Exemplary embodiments of RDC systems are provided herein.
The systems and methods are not limited to the specific embodiments
described herein, but rather, components of systems and/or steps of
the methods may be utilized independently and separately from other
components and/or steps described herein. For example, the
configuration of components described herein may also be used in
combination with other processes, and is not limited to practice
with only ground-based, combined cycle power generation systems, as
described herein. Rather, the exemplary embodiment can be
implemented and utilized in connection with many applications where
a RDC system may be implemented.
[0042] Although specific features of various embodiments of the
present disclosure may be shown in some drawings and not in others,
this is for convenience only. In accordance with the principles of
embodiments of the present disclosure, any feature of a drawing may
be referenced and/or claimed in combination with any feature of any
other drawing.
[0043] This written description uses examples to disclose the
embodiments of the present disclosure, including the best mode, and
also to enable any person skilled in the art to practice
embodiments of the present disclosure, including making and using
any devices or systems and performing any incorporated methods. The
patentable scope of the embodiments described herein is defined by
the claims, and may include other examples that occur to those
skilled in the art. Such other examples are intended to be within
the scope of the claims if they have structural elements that do
not differ from the literal language of the claims, or if they
include equivalent structural elements with insubstantial
differences from the literal languages of the claims.
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