U.S. patent application number 14/913056 was filed with the patent office on 2016-07-14 for dual fuel nozzle system and apparatus.
The applicant listed for this patent is UNITED TECHNOLOGIES CORPORATION. Invention is credited to Zhongtao Dai, Kristin Kopp-Vaughan, Randolph J Smith, Timothy S Snyder.
Application Number | 20160201897 14/913056 |
Document ID | / |
Family ID | 52484086 |
Filed Date | 2016-07-14 |
United States Patent
Application |
20160201897 |
Kind Code |
A1 |
Snyder; Timothy S ; et
al. |
July 14, 2016 |
DUAL FUEL NOZZLE SYSTEM AND APPARATUS
Abstract
In various embodiments, a dual fuel nozzle (200) for use in a
gas 200 turbine engine is provided. The nozzle may be configured to
supply and gas and a liquid. The dual fuel nozzle (200) may include
an interior wall (217). The interior wall (217) may include a
shoulder (219). The shoulder (219) may include one or more gas
ports (216). Gas may be discharged through the gas ports (216) and
penetrate a mixing zone.
Inventors: |
Snyder; Timothy S;
(Glastonbury, CT) ; Dai; Zhongtao; (Manchester,
CT) ; Smith; Randolph J; (Ellington, CT) ;
Kopp-Vaughan; Kristin; (East Hartford, CT) |
|
Applicant: |
Name |
City |
State |
Country |
Type |
UNITED TECHNOLOGIES CORPORATION |
Hartford |
CT |
US |
|
|
Family ID: |
52484086 |
Appl. No.: |
14/913056 |
Filed: |
August 19, 2014 |
PCT Filed: |
August 19, 2014 |
PCT NO: |
PCT/US2014/051582 |
371 Date: |
February 19, 2016 |
Related U.S. Patent Documents
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Application
Number |
Filing Date |
Patent Number |
|
|
61867869 |
Aug 20, 2013 |
|
|
|
Current U.S.
Class: |
239/418 |
Current CPC
Class: |
F23R 3/36 20130101; F23D
2900/11101 20130101; F23R 3/286 20130101; F23D 14/48 20130101; F23C
1/08 20130101 |
International
Class: |
F23C 1/08 20060101
F23C001/08; F23D 14/48 20060101 F23D014/48 |
Claims
1. A gas turbine fuel nozzle, comprising: a housing, defining a
mixing chamber including a transition zone, the housing comprising,
an interior wall comprising a shoulder and defining a fuel port in
the shoulder, the fuel port configured to conduct a fuel into the
mixing chamber, wherein the fuel propagates across a volume of the
mixing chamber prior to reaching the transition zone.
2. The gas turbine fuel nozzle of claim 1, further comprising a
liquid supply.
3. The gas turbine fuel nozzle of claim 2, wherein the liquid
supply is configured to conduct a liquid to the transition
zone.
4. The gas turbine fuel nozzle of claim 3, wherein the liquid is at
least one of a liquid fuel and water.
5. The gas turbine fuel nozzle of claim 1, wherein the shoulder
defines a plurality of fuel ports.
6. The gas turbine fuel nozzle of claim 1, wherein the fuel port
has a diameter of approximately 0.090 inches to approximately 0.110
inches.
7. The gas turbine fuel nozzle of claim 1, wherein the fuel
propagates away from the interior wall.
8. A dual fuel nozzle, comprising: a gas supply; an interior wall
comprising a shoulder, the shoulder defining a gas port; a housing
defining a gas discharge zone configured to receive a gas from the
gas port, the gas discharge zone comprising a transition zone; a
liquid supply; and a liquid supply channel configured to conduct a
liquid into the transition zone.
9. The dual fuel nozzle of claim 8, wherein the liquid is a liquid
fuel.
10. The dual fuel nozzle of claim 8, wherein the liquid is water
and is supplied to reduce emissions.
11. The dual fuel nozzle of claim 8, wherein the shoulder defines a
plurality of gas ports.
12. The dual fuel nozzle of claim 8, wherein the gas penetrates a
volume of the gas discharge zone.
13. The dual fuel nozzle of claim 8, wherein the gas propagates
away from the interior way.
14. The dual fuel nozzle of claim 8, wherein the gas and the liquid
mix in the transition zone.
15. The dual fuel nozzle of claim 8, further comprising an air
channel configured to conduct air to the transition zone, wherein
the air is mixed with the liquid and the gas.
16. A dual fuel distribution system, comprising: a gas fuel supply;
a housing comprising an interior wall defining a shoulder, the
shoulder defining a plurality of gas ports, wherein gas from the
gas fuel supply is conducted through the plurality of gas ports in
a mixing chamber; a liquid supply; and a liquid distribution
channel defined in the housing and configured to conduct a liquid
from the liquid supply to a transition zone, wherein the transition
zone is a portion of the mixing chamber.
17. The dual fuel distribution system of claim 16, wherein the gas
fuel and the liquid are mixed in the transition zone.
18. The dual fuel distribution system of claim 16, wherein the
housing further comprises an air supply that is configured to
conduct air to the transition zone.
19. The dual fuel distribution system of claim 16, wherein the
plurality of gas ports is 12 gas ports.
20. The dual fuel distribution system of claim 16, wherein the
liquid is at least one of water and a liquid fuel.
Description
CROSS REFERENCE TO RELATED APPLICATION
[0001] This application claims the benefit of provisional
application Ser. No. 61/867,869, filed Aug. 20, 2013.
FIELD
[0002] The present disclosure relates to radial fuel injection in
fuel nozzles, and more specifically, to radial fuel injection in
dual fuel nozzle to improve gaseous fuel dispersion and/or
penetration.
BACKGROUND
[0003] A gas turbine may generally include a fuel nozzle that is
configured to supply one or more fuels to the combustor. This fuel
may be mixed with air and/or pollution mitigation substances such
as, for example, water. Dual fuel nozzles used in propulsion and
energy production applications may comprise a radial fuel port.
Dispersion and/or penetration of gas fuel may be affected by the
location of the radial fuel port. Greater dispersion and/or
penetration of gaseous fuel may increase the operating efficiency
of a gas turbine.
SUMMARY
[0004] In various embodiments, a gas turbine fuel nozzle may
comprise a housing. The housing may define a mixing chamber
including a transition zone. The housing may comprise an interior
wall. The interior wall may comprise a shoulder. A fuel port may be
defined in the shoulder. The fuel port may be configured to conduct
a fuel into the mixing chamber. The fuel may propagate across a
volume of the mixing chamber prior to reaching the transition
zone.
[0005] In various embodiments, a dual fuel nozzle may comprise a
gas supply, an interior wall, a housing, a liquid supply and a
liquid supply channel. The interior wall may comprise a shoulder.
The shoulder may include a gas port. The housing may define a gas
discharge zone configured to receive a gas from the gas port. The
gas discharge zone may comprise a transition zone. The liquid
supply channel may be configured to conduct a liquid to the
transition zone.
[0006] In various embodiments, a dual fuel distribution system may
comprise a gas fuel supply, a housing, a liquid fuel supply, and a
liquid distribution channel. The housing may comprise an interior
wall defining a shoulder. The shoulder may define a plurality of
gas ports. Gaseous fuel from the gas fuel supply may be conducted
through the gas ports into a mixing chamber. The liquid
distribution channel may be defined in the housing. The liquid
distribution channel may be configured to conduct a liquid fuel
from the liquid fuel supply to a transition zone. The transition
zone may be a portion of the mixing chamber.
BRIEF DESCRIPTION OF THE DRAWINGS
[0007] The subject matter of the present disclosure is particularly
pointed out and distinctly claimed in the concluding portion of the
specification. A more complete understanding of the present
disclosure, however, may best be obtained by referring to the
detailed description and claims when considered in connection with
the drawing figures, wherein like numerals denote like
elements.
[0008] FIG. 1A illustrates a perspective cross sectional view of a
prior art dual fuel nozzle.
[0009] FIG. 1B illustrates a gas fuel dispersion and/or penetration
of a prior art dual fuel nozzle.
[0010] FIG. 2A illustrates a perspective cross sectional view of a
dual fuel nozzle, in accordance with various embodiments.
[0011] FIG. 2B illustrates a gaseous fuel dispersion and/or
penetration of a dual fuel nozzle, in accordance with various
embodiments.
[0012] FIG. 2C illustrates a perspective cross sectional view of a
portion of a dual fuel nozzle, in accordance with various
embodiments.
DETAILED DESCRIPTION
[0013] The detailed description of exemplary embodiments herein
makes reference to the accompanying drawings, which show exemplary
embodiments by way of illustration and their best mode. While these
exemplary embodiments are described in sufficient detail to enable
those skilled in the art to practice the inventions, it should be
understood that other embodiments may be realized and that logical,
chemical and mechanical changes may be made without departing from
the spirit and scope of the disclosure. Thus, the detailed
description herein is presented for purposes of illustration only
and not of limitation. For example, the steps recited in any of the
method or process descriptions may be executed in any order and are
not necessarily limited to the order presented.
[0014] Furthermore, any reference to singular includes plural
embodiments, and any reference to more than one component or step
may include a singular embodiment or step. Also, any reference to
attached, fixed, connected or the like may include permanent,
removable, temporary, partial, full and/or any other possible
attachment option. Additionally, any reference to without contact
(or similar phrases) may also include reduced contact or minimal
contact.
[0015] As used herein, phrases such as "make contact with,"
"coupled to," "touch," "interface with" and "engage" may be used
interchangeably. Different surface shading may be used throughout
the figures to denote different parts but not necessarily to denote
the same or different materials.
[0016] In various embodiments, a gas turbine engine may comprise a
dual fuel nozzle. The fuel nozzle may define one or more channels.
One or more of these channels may be configured to receive a gas
and/or a liquid. These channels may be operatively coupled and/or
may be in fluid communication with one or more components of a gas
turbine engine including, for example, the combustor. The liquid,
gas, and/or air supplied through the one or more channels may be
conducted or carried from the fuel nozzle to the combustor. In this
regard, the nozzle is configured to provide fuel in the form of a
gas or a liquid to the combustor for starting or sustained
operation of the gas turbine. The nozzle is configured to provide
air, and/or water in either gaseous form or liquid form, or
combinations thereof to the combustor for starting or sustained
operation of the gas turbine.
[0017] In various embodiments, the gas turbine may be a gas turbine
configured to provide power and/or a gas turbine configured to
provide propulsion. For example, in an embodiment where the gas
turbine is configured to provide power, the gas turbine may be
installed or operated in a power plant environment where the gas
turbine drives electricity generating devices and supplies power to
a structure and/or a utility provider. In an embodiment where the
gas turbine is configured to provide propulsion, the gas turbine
may be installed on a vehicle such as, for example, an aircraft or
other suitable machinery.
[0018] In various embodiments and with reference to FIGS. 1A and 1B
a gas turbine may comprise a typical dual fuel nozzle comprising a
housing 110, a gas supply channel 112 and a liquid supply channel
118. Housing 110 may define a gas distribution channel 114 and a
liquid distribution channel 120. Housing 110 may also define a
mixing chamber 124. Mixing chamber 124 may be in fluid
communication with gas distribution channel 114.
[0019] Dual fuel nozzle 100 may further comprise a gas port 116
defined in an interior wall 117 of housing 110. Gas port 116 may be
located downstream of a shoulder 119 in interior wall 117
substantially near a transition zone 124' of a mixing chamber 124.
In this regard, gas (e.g., a gaseous fuel) may be conducted through
gas supply channel 112 and gas distribution channel 114. The gas
may be discharged through gas port 116 into mixing chamber 124
adjacent to transition zone 124'.
[0020] In various embodiments, liquid may be supplied through
liquid supply channel 118 and conducted into liquid distribution
channel 120. The liquid may be disbursed through a lip 122. Dual
fuel nozzle 100 may further comprise an impeller 126. Housing 110
may define an air supply channel 128 along a centerline A-A' of
dual fuel nozzle 100. The impeller may be configured to conduct air
through air supply channel 128 into a discharge zone 130. In
various embodiments, the liquid, fuel and air may be mixed in
discharge zone 130.
[0021] In various embodiments, the liquid may be a liquid fuel
and/or water. Where the dual fuel nozzle is installed in a power
generation application, the liquid may be water that is used to
mitigate or minimize carbon monoxide and/or mono-nitrogen oxide
emissions (i.e., NO.sub.x).
[0022] In various embodiments and with specific reference to FIG.
1B, fuel mixing is shown as letter G. Fuel may be discharged
through gas port 116 from fuel distribution channel 114 into mixing
chamber 124. Fuel distribution G generally shows that the fuel does
not mix well into mixing chamber 124, but rather, remains clustered
(e.g., close to) near interior wall 117 as the fuel propagates from
mixing chamber 124 to transition zone 124'. This clustering or lack
of fuel dispersion and/or penetration may result in inefficient
combustion of fuel G. In this regard the fluid velocity in mixing
chamber 124 generally increases at transition zone 124'. This
increase in fluid velocity may minimize fuel distribution G as the
fuel propagates from mixing chamber 124 to transition zone 124'
causing the fuel to cluster along a portion of interior wall 117
adjacent to transition zone 124'.
[0023] In various embodiments and with reference to FIGS. 2A-2C,
adjusting the position of fuel port 216 may increase fuel
penetration (e.g., the distance the fuel travels into the mixing
chamber 224) and dispersion (e.g., the spreading of a mass of fuel
across a volume) . More specifically, moving fuel port 216 forward
(e.g., in the direction associated with reference A of the A-A'
centerline) further away from transition zone 224' may allow fuel
discharged through fuel port 216 to further propagate into mixing
chamber 224. In this regard, the fluid velocity in mixing chamber
224 may be lower upstream of transition zone 224', allowing for
greater fuel penetration in mixing chamber 224.
[0024] In various embodiments, fuel port 216 may be defined by
interior wall 217 at shoulder 219. With specific reference to FIG.
2B, fuel may be distributed or injected into mixing chamber 224
where the fluid velocity in the chamber is relatively low (e.g.,
the fluid velocity in an upstream portion of mixing chamber 224 may
be lower than the fluid velocity in mixing chamber 224 near
transition zone 224'). The fuel distribution G' demonstrates
greater fuel penetration as compared to fuel distribution G, as
shown in FIG. 1B. In this regard, fuel distribution G' illustrates
that the fuel propagates across the entire volume of mixing chamber
224. This greater penetration provides for lower fuel density, a
more suitable fuel-air mixture, and better ignition efficiency.
[0025] In various embodiments, the fuel distribution G' illustrates
that the fuel may propagate into the volume of mixing chamber 224
as opposed to clustering near interior wall 217. The fuel may be
conducted through the transition zone 224', and mixed with air
supplied through channel 228, and a liquid supplied through channel
220 and lip 222. This air, fuel, and water mixture may be further
supplied to the combustor for ignition. In this regard, the mixture
(gas (e.g., fuel), liquid (e.g., fuel and/or water), and/or air)
may be conducted to the combustor.
[0026] In various embodiments, interior wall 217 may comprise a
plurality of gas ports 216. In various embodiments, interior wall
217 may define 8-14 gas ports 216 around its diameter. In various
embodiments, interior wall 217 may define 12 gas ports 216 around
its diameter. Gas ports 216 may be substantially aligned with one
another around along a diameter of interior wall 217. Moreover, gas
ports 216 may be equally spaced circumferentially around interior
wall 217. The holes may be of any suitable diameter (e.g., 0.090
inches-0.110 inches/0.2286 cm to 0.29784 cm) and/or pitch. The
pitch may be a function of the shape and/or slope of shoulder 219.
In this regard, the geometry of one or more gas ports 216 and/or
number of gas ports may provide a Holdeman Parameter that is
greater than the ratio of pitch to diameter.
[0027] In various embodiments and with reference to FIG. 2C, a
portion of the dual fuel nozzle illustrating particular flow
channels is provided. A liquid B may be supplied through liquid
supply 218 and conducted to channel 220 and discharged through lip
222 as B'. Similarly, a gas A may be supplied to gas distribution
channel 212 through gas distribution channel 214 and out of gas
port 216 into mixing chamber 224 as A'. Air C may be supplied along
channel 228 as C'. At transition zone 224', gas A' and liquid B'
may be mixed and supplied into channel 228 and mixed with air C'.
The mixture is then conducted to a combustor for gas turbine
operation, ignition and/or burning.
[0028] Benefits, other advantages, and solutions to problems have
been described herein with regard to specific embodiments.
Furthermore, the connecting lines shown in the various figures
contained herein are intended to represent exemplary functional
relationships and/or physical couplings between the various
elements. It should be noted that many alternative or additional
functional relationships or physical connections may be present in
a practical system. However, the benefits, advantages, solutions to
problems, and any elements that may cause any benefit, advantage,
or solution to occur or become more pronounced are not to be
construed as critical, required, or essential features or elements
of the inventions. The scope of the inventions is accordingly to be
limited by nothing other than the appended claims, in which
reference to an element in the singular is not intended to mean
"one and only one" unless explicitly so stated, but rather "one or
more." Moreover, where a phrase similar to "at least one of A, B,
or C" is used in the claims, it is intended that the phrase be
interpreted to mean that A alone may be present in an embodiment, B
alone may be present in an embodiment, C alone may be present in an
embodiment, or that any combination of the elements A, B and C may
be present in a single embodiment; for example, A and B, A and C, B
and C, or A and B and C. Different cross-hatching is used
throughout the figures to denote different parts but not
necessarily to denote the same or different materials.
[0029] Systems, methods and apparatus are provided herein. In the
detailed description herein, references to "one embodiment", "an
embodiment", "various embodiments", etc., indicate that the
embodiment described may include a particular feature, structure,
or characteristic, but every embodiment may not necessarily include
the particular feature, structure, or characteristic. Moreover,
such phrases are not necessarily referring to the same embodiment.
Further, when a particular feature, structure, or characteristic is
described in connection with an embodiment, it is submitted that it
is within the knowledge of one skilled in the art to affect such
feature, structure, or characteristic in connection with other
embodiments whether or not explicitly described. After reading the
description, it will be apparent to one skilled in the relevant
art(s) how to implement the disclosure in alternative
embodiments.
[0030] Furthermore, no element, component, or method step in the
present disclosure is intended to be dedicated to the public
regardless of whether the element, component, or method step is
explicitly recited in the claims. No claim element herein is to be
construed under the provisions of 35 U.S.C. 112, sixth paragraph,
unless the element is expressly recited using the phrase "means
for." As used herein, the terms "comprises", "comprising", or any
other variation thereof, are intended to cover a non-exclusive
inclusion, such that a process, method, article, or apparatus that
comprises a list of elements does not include only those elements
but may include other elements not expressly listed or inherent to
such process, method, article, or apparatus.
* * * * *