EP2657608B1 - A Combustor - Google Patents
A Combustor Download PDFInfo
- Publication number
- EP2657608B1 EP2657608B1 EP13156623.4A EP13156623A EP2657608B1 EP 2657608 B1 EP2657608 B1 EP 2657608B1 EP 13156623 A EP13156623 A EP 13156623A EP 2657608 B1 EP2657608 B1 EP 2657608B1
- Authority
- EP
- European Patent Office
- Prior art keywords
- combustor
- fuel
- end cap
- tubes
- downstream
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
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Links
- 239000000446 fuel Substances 0.000 claims description 78
- 239000012530 fluid Substances 0.000 claims description 50
- 230000007704 transition Effects 0.000 claims description 41
- 238000002485 combustion reaction Methods 0.000 claims description 32
- 238000011144 upstream manufacturing Methods 0.000 claims description 20
- 238000004891 communication Methods 0.000 claims description 11
- 239000000567 combustion gas Substances 0.000 description 31
- 239000003570 air Substances 0.000 description 15
- 239000007789 gas Substances 0.000 description 13
- 239000000203 mixture Substances 0.000 description 7
- MWUXSHHQAYIFBG-UHFFFAOYSA-N nitrogen oxide Inorganic materials O=[N] MWUXSHHQAYIFBG-UHFFFAOYSA-N 0.000 description 7
- 238000013461 design Methods 0.000 description 6
- 230000004888 barrier function Effects 0.000 description 4
- 238000001816 cooling Methods 0.000 description 3
- 238000000034 method Methods 0.000 description 3
- ATUOYWHBWRKTHZ-UHFFFAOYSA-N Propane Chemical compound CCC ATUOYWHBWRKTHZ-UHFFFAOYSA-N 0.000 description 2
- 239000012080 ambient air Substances 0.000 description 2
- 230000008901 benefit Effects 0.000 description 2
- 230000005611 electricity Effects 0.000 description 2
- 230000002708 enhancing effect Effects 0.000 description 2
- 239000003949 liquefied natural gas Substances 0.000 description 2
- 238000004519 manufacturing process Methods 0.000 description 2
- VNWKTOKETHGBQD-UHFFFAOYSA-N methane Chemical compound C VNWKTOKETHGBQD-UHFFFAOYSA-N 0.000 description 2
- IJGRMHOSHXDMSA-UHFFFAOYSA-N Atomic nitrogen Chemical compound N#N IJGRMHOSHXDMSA-UHFFFAOYSA-N 0.000 description 1
- UGFAIRIUMAVXCW-UHFFFAOYSA-N Carbon monoxide Chemical compound [O+]#[C-] UGFAIRIUMAVXCW-UHFFFAOYSA-N 0.000 description 1
- 230000002411 adverse Effects 0.000 description 1
- 229910002091 carbon monoxide Inorganic materials 0.000 description 1
- 238000006243 chemical reaction Methods 0.000 description 1
- 239000000571 coke Substances 0.000 description 1
- 239000012141 concentrate Substances 0.000 description 1
- 229930195733 hydrocarbon Natural products 0.000 description 1
- 150000002430 hydrocarbons Chemical class 0.000 description 1
- 239000001257 hydrogen Substances 0.000 description 1
- 229910052739 hydrogen Inorganic materials 0.000 description 1
- 125000004435 hydrogen atom Chemical class [H]* 0.000 description 1
- 230000003116 impacting effect Effects 0.000 description 1
- 239000003345 natural gas Substances 0.000 description 1
- 230000037361 pathway Effects 0.000 description 1
- 238000010248 power generation Methods 0.000 description 1
- 230000008569 process Effects 0.000 description 1
- 239000001294 propane Substances 0.000 description 1
- 230000001681 protective effect Effects 0.000 description 1
- 238000012552 review Methods 0.000 description 1
- 238000012546 transfer Methods 0.000 description 1
Images
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
- F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
- F23R3/28—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
- F23R3/286—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply having fuel-air premixing devices
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
- F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
- F23R3/42—Continuous combustion chambers using liquid or gaseous fuel characterised by the arrangement or form of the flame tubes or combustion chambers
- F23R3/425—Combustion chambers comprising a tangential or helicoidal arrangement of the flame tubes
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
- F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
- F23R3/42—Continuous combustion chambers using liquid or gaseous fuel characterised by the arrangement or form of the flame tubes or combustion chambers
- F23R3/46—Combustion chambers comprising an annular arrangement of several essentially tubular flame tubes within a common annular casing or within individual casings
Definitions
- the present invention generally involves a combustor.
- the combustor may be incorporated into a gas turbine or other turbo- machine.
- Combustors are commonly used in industrial and power generation operations to ignite fuel to produce combustion gases having a high temperature and pressure.
- gas turbines typically include one or more combustors to generate power or thrust.
- a typical gas turbine used to generate electrical power includes an axial compressor at the front, one or more combustors around the middle, and a turbine at the rear.
- Ambient air may be supplied to the compressor, and rotating blades and stationary vanes in the compressor progressively impart kinetic energy to the working fluid (air) to produce a compressed working fluid at a highly energized state.
- the compressed working fluid exits the compressor and flows through one or more fuel nozzles in the combustor where the compressed working fluid mixes with fuel and ignites in a combustion chamber to generate combustion gases having a high temperature and pressure.
- the combustion gases flow through a transition piece to the turbine where alternating stages of stationary nozzles and rotating buckets redirect, accelerate, and expand the combustion gases to generate work.
- expansion of the combustion gases in the turbine may rotate a shaft connected to a generator to produce
- thermodynamic efficiency of the combustor generally improves the thermodynamic efficiency of the combustor.
- higher combustion gas temperatures also promote flame holding conditions in which the combustion flame migrates towards the fuel being supplied by the nozzles, possibly causing accelerated damage to the nozzles in a relatively short amount of time.
- higher combustion gas temperatures generally increase the disassociation rate of diatomic nitrogen, increasing the production of nitrogen oxides (NO x ).
- a lower combustion gas temperature associated with reduced fuel flow and/or part load operation (turndown) generally reduces the chemical reaction rates of the combustion gases, increasing the production of carbon monoxide and unburned hydrocarbons.
- One solution for balancing the thermodynamic efficiency of the combustor, accelerated damage, and/or undesirable emissions over a wide range of combustor operating levels is to enhance mixing between the fuel and compressed working fluid to produce a lean fuel-working fluid mixture for combustion.
- the enhanced mixing between the fuel and compressed working fluid is often accomplished by various combinations of injecting, atomizing, and/or swirling the fuel and/or working fluid prior to combustion to reduce localized hot spots in the combustion chamber.
- the stationary nozzles in the first stage of the turbine include rounded leading edges with large radii to accommodate swirling combustion gases impacting the first stage nozzles at various angles of incidence.
- the first stage of stationary nozzles may be replaced with transition ducts between each combustor and the turbine. The transition ducts accelerate and redirect the combustion gases flowing into the turbine in place of the first stage nozzles. Although effective at enhancing turbine output and/or efficiency, excessive swirling in the combustion gases reduces the effectiveness of the transition ducts.
- US 2010/115953 which shows a combustor according to the preamble of claim 1, describes an integrated combustor and stage one nozzle in a gas turbine including a combustion chamber that receives premixed fuel and air from at least one fuel nozzle group at separate axial locations.
- the combustion chamber includes a liner and a transition piece that deliver hot combustion gas to the turbine.
- the stage one nozzle, the liner and the transition piece are integrated into a single part.
- At least one of the axial locations of the one or more fuel nozzle groups includes a plurality of small scale mixing devices that concentrate heat release and reduce flame length.
- EP 2213944 describes a system including a fuel nozzle that includes a fuel injector configured to output a fuel flow and a premixer tube disposed about the fuel flow output from the fuel injector.
- the premixer tube includes a perforated portion and a non-perforated portion downstream of the perforated portion.
- US 2010/300102 describes a method including receiving fuel and air into a cup of a turbine fuel nozzle, mixing the fuel and air at least partially within the cup, directing a fuel air mixture toward a turbine combustor and shielding an inner wall of the cup with a blanket of a protective fluid flow to reduce the possibility of flame holding along the inner wall.
- a combustor that may be incorporated, for example, into a gas turbine or other turbo-machine.
- the combustor generally includes a plurality of premixer tubes that allow a fuel to be mixed with a compressed working fluid to produce a lean fuel-working fluid mixture with reduced amounts of swirl compared to conventional fuel nozzles.
- the lean fuel-working fluid mixture flows into a combustion chamber where it ignites to produce combustion gases having a high temperature and pressure.
- the combustion gases flow through a transition duct that accelerates and/or directs the combustion gases onto a first stage of rotating blades where the combustion gases expand and transfer energy to the rotating blades to produce work.
- Fig. 1 provides a simplified cross-section view of an exemplary gas turbine 10 that may incorporate various embodiments of the present invention.
- the gas turbine 10 may generally include a compressor 12 at the front, one or more combustors 14 radially disposed around the middle, and a turbine 16 at the rear.
- the compressor 12 and the turbine 16 may share a common rotor 18 connected to a generator 20 to produce electricity.
- the compressor 12 may be an axial flow compressor in which a working fluid 22, such as ambient air, enters the compressor 12 and passes through alternating stages of stationary vanes 24 and rotating blades 26.
- a compressor casing 28 contains the working fluid 22 as the stationary vanes 24 and rotating blades 26 accelerate and redirect the working fluid 22 to produce a continuous flow of compressed working fluid 22.
- the majority of the compressed working fluid 22 flows through a compressor discharge plenum 30 to the combustor 14.
- the combustor 14 may be any type of combustor known in the art.
- a combustor casing 32 may circumferentially surround some or all of the combustor 14 to contain the compressed working fluid 22 flowing from the compressor 12.
- One or more fuel nozzles 34 may be radially arranged in an end cover 36 to supply fuel to a combustion chamber 38 downstream from the fuel nozzles 34.
- Possible fuels include, for example, one or more of blast furnace gas, coke oven gas, natural gas, vaporized liquefied natural gas (LNG), hydrogen, and propane.
- the compressed working fluid 22 may flow from the compressor discharge passage 30 along the outside of the combustion chamber 38 before reaching the end cover 36 and reversing direction to flow through the fuel nozzles 34 to mix with the fuel.
- the mixture of fuel and compressed working fluid 22 flows into the combustion chamber 38 where it ignites to generate combustion gases having a high temperature and pressure.
- a transition duct 40 circumferentially surrounds at least a portion of the combustion chamber 38, and the combustion gases flow through the transition duct 40 to the turbine 16.
- the turbine 16 may include alternating stages of rotating buckets 42 and stationary vanes 44.
- the transition duct 40 redirects and focuses the combustion gases onto the first stage of rotating buckets 42.
- the combustion gases expand, causing the rotating buckets 42 and rotor 18 to rotate.
- the combustion gases then flow to the next stage of stationary vanes 44 which redirect the combustion gases to the next stage of rotating buckets 42, and the process repeats for the following stages.
- Fig. 2 shows a simplified cross-section view of the exemplary combustor 14 shown in Fig. 1 according to one embodiment of the present invention.
- the combustor casing 32 and end cover 36 may surround the combustor 14 to contain the working fluid 22 flowing from the compressor 12.
- An impingement sleeve 46 may surround the transition duct 40, and the working fluid 22 may pass through flow holes 48 in the impingement sleeve 46 to flow along the outside of the transition duct 40 to provide convective cooling to the transition duct 40.
- the working fluid 22 When the working fluid 22 reaches the end cover 36, the working fluid 22 reverses direction to flow through one or more fuel nozzles 34 and/or tubes 50 and into the combustion chamber 38.
- Fig. 3 provides an enlarged cross-section view of a portion of the combustor 14 shown in Figs. 1 and 2 according to one embodiment of the present invention.
- the one or more fuel nozzles 34 and tubes 50 may be radially arranged in an end cap 52 upstream from the combustion chamber 38.
- Various embodiments of the combustor 14 may include different numbers and arrangements of fuel nozzles 34 and tubes 50.
- the combustor 14 includes a single fuel nozzle 34 aligned with an axial centerline 54 of the combustor 14, and the tubes 50 are radially arranged around the single fuel nozzle 34 in the end cap 52.
- the fuel nozzle 34 may extend through the end cap 52 to provide fluid communication through the end cap 52 to the combustion chamber 38.
- the fuel nozzle 34 may include any suitable structure known to one of ordinary skill in the art for mixing fuel with the working fluid 22 prior to entry into the combustion chamber 38, and the present invention is not limited to any particular structure or design unless specifically recited in the claims.
- the fuel nozzle 34 may include a center body 56 and a bellmouth opening 58.
- the center body 56 provides fluid communication for fuel to flow from the end cover 36, through the center body 56, and into the combustion chamber 38.
- the bellmouth opening 58 surrounds at least a portion of the center body 56 to define an annular passage 60 between the center body 56 and the bellmouth opening 58.
- the working fluid 22 may flow through the annular passage 60 to mix with the fuel from the center body 56 prior to reaching the combustion chamber 38.
- the fuel nozzle 34 may further include one or more swirler vanes 62 that extend radially between the center body 56 and the bellmouth opening 58 to impart swirl to the fuel-working fluid mixture prior to reaching the combustion chamber 38.
- the end cap 52 extends radially across at least a portion of the combustor 14 and generally includes an upstream surface 64 axially separated from a downstream surface 66.
- the tubes 50 generally extend axially from the upstream surface 64 through the downstream surface 66 of the end cap 52 to provide fluid communication for the working fluid 22 to flow through the end cap 52 and into the combustion chamber 38.
- the cross-section of the tubes 50 may be any geometric shape, and the present invention is not limited to any particular cross-section unless specifically recited in the claims.
- a shroud 68 circumferentially surrounds at least a portion of the end cap 52 to partially define a fuel plenum 70 between the upstream and downstream surfaces 64, 66.
- a fuel conduit 72 may extend from the end cover 36 through the upstream surface 64 of the end cap 52 to provide fluid communication for fuel to flow from the end cover 36, through the fuel conduit 72, and into the fuel plenum 70.
- One or more of the tubes 50 may include a fuel port 74 that provides fluid communication from the fuel plenum 70 into one or more of the tubes 50.
- the fuel ports 74 may be angled radially, axially, and/or azimuthally to project and/or impart swirl to the fuel flowing through the fuel ports 74 and into the tubes 50.
- the working fluid 22 may flow into the tubes 50, and fuel from the fuel conduit 72 may flow around the tubes 50 in the fuel plenum 70 to provide convective cooling to the tubes 50 before flowing through the fuel ports 74 and into the tubes 50 to mix with the working fluid 22.
- the fuel-working fluid mixture may then flow through the tubes 50 and into the combustion chamber 38.
- Fig. 4 provides an enlarged cross-section view of a portion of the combustor 14 shown in Fig. 1 according to an alternate embodiment of the present invention
- Fig. 5 provides a partial perspective view of the end cap 52 portion of the combustor 14 shown in Fig. 4
- the end cap 52 may again include the upstream surface 64, downstream surface 66, shroud 68, and fuel plenum 70 as previously described with respect to the embodiment shown in Fig. 3
- the end cap 52 may include a generally horizontal barrier 74 that extends radially between the upstream surface 64 and the downstream surface 66 to axially separate the fuel plenum 70 from an air plenum 76.
- one or more generally vertical baffles 78 may extend axially from the upstream surface 64 to the barrier 74 or completely through the end cap 52 to the downstream surface 66 to radially separate the tubes 50 into a plurality of groups or bundles 80 in the end cap 52.
- the baffles 78 allow each bundle 80 of tubes 50 to have a dedicated fuel plenum 70 and/or air plenum 76, allowing different fuels and/or fuel flow rates to be supplied to each bundle 80 of tubes 50.
- the baffles 78 may include flow holes 82 or other perforations to facilitate the flow of fuel between the fuel plenums 70 associated with each bundle 80 of tubes 50.
- the shroud 68 may include a plurality of air ports 84 that provide fluid communication for the working fluid 22 to flow through the shroud 68 and into the air plenum 76.
- an air passage 86 between one or more tubes 50 and the downstream surface 66 may provide fluid communication from the air plenum 76, through the downstream surface 66, and into the combustion chamber 38. In this manner, a portion of the working fluid 22 may flow through the air ports 84 in the shroud 68 and into the air plenum 76 to provide convective cooling around the lower portion of the tubes 50 before flowing through the air passages 86 and into the combustion chamber 38.
- combustor 14 may include different numbers and arrangements of fuel nozzles 34 and tubes 50, and Figs. 6-8 provide downstream axial views of the end cap 52 illustrating various arrangements within the scope of the present invention.
- the tubes 50 are radially arranged across the end cap 52, and fuel and working fluid 22 may be supplied through the tubes 50 to the combustion chamber 38.
- the generally vertical baffles 78 may separate the tubes 50 into generally circular tube bundles 80 radially arranged around a center circular tube bundle 80.
- Fig. 6 for example, the tubes 50 are radially arranged across the end cap 52, and fuel and working fluid 22 may be supplied through the tubes 50 to the combustion chamber 38.
- the generally vertical baffles 78 may separate the tubes 50 into generally circular tube bundles 80 radially arranged around a center circular tube bundle 80.
- the generally vertical baffles 78 may separate the tubes 50 into triangular or pie-shaped tube bundles 80 radially arranged around a center fuel nozzle 34.
- the particular embodiments of the present invention are not limited to any particular arrangement, shape, or number of fuel nozzles 34, tubes 50, and/or tube bundles 80 unless specifically recited in the claims.
- Fig. 9 provides a perspective view of the transition duct 40 and impingement sleeve 46 shown in Fig. 2
- Fig. 10 provides a perspective view of multiple transition ducts 40 radially circumferentially arranged around the gas turbine 10 shown in Fig. 1 .
- the transition duct 40 generally surrounds at least a portion of the combustion chamber 38 and extends each end cap 52 and the turbine 16. In this manner, each transition duct 40 provides a path that conditions the flow of combustion gases from each combustor 14 to the turbine 16.
- the orientation and/or cross-section of the transition ducts 40 may replace or eliminate the need for stationary vanes 44 immediately upstream from the first stage of rotating buckets 42, thus increasing the efficiency and/or output of the turbine 16.
- each transition duct 40 generally includes an inlet 90 and an outlet 92 downstream from the inlet 90.
- the cross-section of the inlet 90 generally conforms to the radial cross-section of the combustion chamber 38 proximate to the end cap 52, and the cross-section of the transition duct 40 may progressively narrow proximate to the outlet 92 to accelerate the combustion gases into the turbine 16.
- the transition duct 40 may curve between the inlet 90 and outlet 92 to enhance the angle at which the combustion gases flow into the turbine 16. For example, as shown in Figs.
- longitudinal, tangential, and radial axes 94, 96, 98 superimposed over the transition ducts 40 illustrate that the transition ducts 40 may curve transversely, tangentially, and/or radially from the longitudinal axis 94.
- the radial and tangential axes 96, 98 are defined individually for each transition duct 40 with respect to a circumference defined by the annular array of transition ducts 40, as shown in Fig. 10 , and that the radial and tangential axes 96, 98 vary for each transition duct 40 about the circumference based on the number of transition ducts 40 disposed in the annular array about the longitudinal axis 94. As shown in Figs.
- the outlet 92 of the transition duct 40 may be displaced or offset from the inlet 90 along both the longitudinal and tangential axes 94, 98.
- the transition ducts 40 may also curve radially from the longitudinal axis 94 to enhance the impact angle of the combustion gases against the rotating buckets 42.
- the outlet 92 of the transition duct 40 may be displaced or offset from the inlet 90 along the radial axis 96, as shown most clearly in Fig. 10 .
- the combination of the tangential and/or radial offset of the outlet 92 with respect to the inlet 90 may obviate the need for stationary vanes 44 upstream from the first stage of rotating buckets 42.
- combustors often include fuel nozzles designed to swirl the fuel and working fluid to enhance mixing prior to combustion.
- a first stage of stationary vanes is often included between the combustor and the turbine upstream from the first stage of rotating buckets to redirect the resulting swirling combustion gases onto the first stage of rotating buckets.
- the transition duct incorporated into various embodiments of the present invention obviates the need for the first stage of stationary vanes, leading to enhanced efficiency of the turbine.
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- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
- Combustion Of Fluid Fuel (AREA)
- Pre-Mixing And Non-Premixing Gas Burner (AREA)
Description
- The present invention generally involves a combustor. In particular embodiments of the present invention, the combustor may be incorporated into a gas turbine or other turbo- machine.
- Combustors are commonly used in industrial and power generation operations to ignite fuel to produce combustion gases having a high temperature and pressure. For example, gas turbines typically include one or more combustors to generate power or thrust. A typical gas turbine used to generate electrical power includes an axial compressor at the front, one or more combustors around the middle, and a turbine at the rear. Ambient air may be supplied to the compressor, and rotating blades and stationary vanes in the compressor progressively impart kinetic energy to the working fluid (air) to produce a compressed working fluid at a highly energized state. The compressed working fluid exits the compressor and flows through one or more fuel nozzles in the combustor where the compressed working fluid mixes with fuel and ignites in a combustion chamber to generate combustion gases having a high temperature and pressure. The combustion gases flow through a transition piece to the turbine where alternating stages of stationary nozzles and rotating buckets redirect, accelerate, and expand the combustion gases to generate work. For example, expansion of the combustion gases in the turbine may rotate a shaft connected to a generator to produce electricity.
- Various design and operating parameters influence the design and operation of combustors. For example, higher combustion gas temperatures generally improve the thermodynamic efficiency of the combustor. However, higher combustion gas temperatures also promote flame holding conditions in which the combustion flame migrates towards the fuel being supplied by the nozzles, possibly causing accelerated damage to the nozzles in a relatively short amount of time. In addition, higher combustion gas temperatures generally increase the disassociation rate of diatomic nitrogen, increasing the production of nitrogen oxides (NOx). Conversely, a lower combustion gas temperature associated with reduced fuel flow and/or part load operation (turndown) generally reduces the chemical reaction rates of the combustion gases, increasing the production of carbon monoxide and unburned hydrocarbons. One solution for balancing the thermodynamic efficiency of the combustor, accelerated damage, and/or undesirable emissions over a wide range of combustor operating levels is to enhance mixing between the fuel and compressed working fluid to produce a lean fuel-working fluid mixture for combustion.
- The enhanced mixing between the fuel and compressed working fluid is often accomplished by various combinations of injecting, atomizing, and/or swirling the fuel and/or working fluid prior to combustion to reduce localized hot spots in the combustion chamber. In some turbine designs, the stationary nozzles in the first stage of the turbine include rounded leading edges with large radii to accommodate swirling combustion gases impacting the first stage nozzles at various angles of incidence. In particular turbine designs, however, the first stage of stationary nozzles may be replaced with transition ducts between each combustor and the turbine. The transition ducts accelerate and redirect the combustion gases flowing into the turbine in place of the first stage nozzles. Although effective at enhancing turbine output and/or efficiency, excessive swirling in the combustion gases reduces the effectiveness of the transition ducts.
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US 2010/115953 , which shows a combustor according to the preamble ofclaim 1, describes an integrated combustor and stage one nozzle in a gas turbine including a combustion chamber that receives premixed fuel and air from at least one fuel nozzle group at separate axial locations. The combustion chamber includes a liner and a transition piece that deliver hot combustion gas to the turbine. The stage one nozzle, the liner and the transition piece are integrated into a single part. At least one of the axial locations of the one or more fuel nozzle groups includes a plurality of small scale mixing devices that concentrate heat release and reduce flame length.EP 2213944 describes a system including a fuel nozzle that includes a fuel injector configured to output a fuel flow and a premixer tube disposed about the fuel flow output from the fuel injector. The premixer tube includes a perforated portion and a non-perforated portion downstream of the perforated portion.US 2010/300102 describes a method including receiving fuel and air into a cup of a turbine fuel nozzle, mixing the fuel and air at least partially within the cup, directing a fuel air mixture toward a turbine combustor and shielding an inner wall of the cup with a blanket of a protective fluid flow to reduce the possibility of flame holding along the inner wall. - As a result, an improved combustor design that enhances mixing between the fuel and working fluid without increasing swirling in the combustion gases would be useful to enhancing combustor performance without adversely affecting emissions.
- Aspects and advantages of the invention are set forth below in the following description, or may be obvious from the description, or may be learned through practice of the invention.
- The present invention resides in a combustor as defined in the appended claims.
- Those of ordinary skill in the art will better appreciate the features and aspects of such embodiments, and others, upon review of the specification.
- Embodiments of the present invention will now be described, by way of example only, with reference to the accompanying drawings in which:
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Fig. 1 is a simplified side cross-section view of an exemplary gas turbine; -
Fig. 2 is a simplified cross-section view of the exemplary combustor shown inFig. 1 according to one embodiment of the present invention; -
Fig. 3 is an enlarged cross-section view of a portion of the combustor shown inFigs. 1 and2 according to one embodiment of the present invention; -
Fig. 4 is an enlarged cross-section view of a portion of the combustor shown inFig. 1 according to an alternate embodiment of the present invention; -
Fig. 5 is a partial perspective view of the end cap portion of the combustor shown inFig. 4 ; -
Fig. 6 is a downstream axial view of the end cap according to one embodiment of the present invention; -
Fig. 7 is a downstream axial view of the end cap according to an alternate embodiment of the present invention; -
Fig. 8 is a downstream axial view of the end cap according to an alternate embodiment of the present invention; -
Fig. 9 is a perspective view of the transition duct and impingement sleeve shown inFig. 2 ; and -
Fig. 10 is a perspective view of multiple transition ducts circumferentially arranged around the gas turbine shown inFig. 1 . - Reference will now be made in detail to present embodiments of the invention, one or more examples of which are illustrated in the accompanying drawings. The detailed description uses numerical and letter designations to refer to features in the drawings. Like or similar designations in the drawings and description have been used to refer to like or similar parts of the invention. As used herein, the terms "first", "second", and "third" may be used interchangeably to distinguish one component from another and are not intended to signify location or importance of the individual components. In addition, the terms "upstream" and "downstream" refer to the relative location of components in a fluid pathway. For example, component A is upstream from component B if a fluid flows from component A to component B. Conversely, component B is downstream from component A if component B receives a fluid flow from component A.
- Various embodiments of the present invention include a combustor that may be incorporated, for example, into a gas turbine or other turbo-machine. The combustor generally includes a plurality of premixer tubes that allow a fuel to be mixed with a compressed working fluid to produce a lean fuel-working fluid mixture with reduced amounts of swirl compared to conventional fuel nozzles. The lean fuel-working fluid mixture flows into a combustion chamber where it ignites to produce combustion gases having a high temperature and pressure. The combustion gases flow through a transition duct that accelerates and/or directs the combustion gases onto a first stage of rotating blades where the combustion gases expand and transfer energy to the rotating blades to produce work. Although exemplary embodiments of the present invention will be described generally in the context of a combustor incorporated into a gas turbine for purposes of illustration, one of ordinary skill in the art will readily appreciate that embodiments of the present invention may be applied to any combustor and are not limited to a gas turbine combustor unless specifically recited in the claims.
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Fig. 1 provides a simplified cross-section view of anexemplary gas turbine 10 that may incorporate various embodiments of the present invention. As shown, thegas turbine 10 may generally include acompressor 12 at the front, one ormore combustors 14 radially disposed around the middle, and aturbine 16 at the rear. Thecompressor 12 and theturbine 16 may share acommon rotor 18 connected to agenerator 20 to produce electricity. - The
compressor 12 may be an axial flow compressor in which a workingfluid 22, such as ambient air, enters thecompressor 12 and passes through alternating stages ofstationary vanes 24 and rotatingblades 26. Acompressor casing 28 contains the workingfluid 22 as thestationary vanes 24 and rotatingblades 26 accelerate and redirect the workingfluid 22 to produce a continuous flow of compressed workingfluid 22. The majority of the compressed workingfluid 22 flows through acompressor discharge plenum 30 to thecombustor 14. - The
combustor 14 may be any type of combustor known in the art. For example, as shown inFig. 1 , acombustor casing 32 may circumferentially surround some or all of thecombustor 14 to contain the compressed workingfluid 22 flowing from thecompressor 12. One ormore fuel nozzles 34 may be radially arranged in anend cover 36 to supply fuel to acombustion chamber 38 downstream from thefuel nozzles 34. Possible fuels include, for example, one or more of blast furnace gas, coke oven gas, natural gas, vaporized liquefied natural gas (LNG), hydrogen, and propane. The compressed workingfluid 22 may flow from thecompressor discharge passage 30 along the outside of thecombustion chamber 38 before reaching theend cover 36 and reversing direction to flow through thefuel nozzles 34 to mix with the fuel. The mixture of fuel and compressed workingfluid 22 flows into thecombustion chamber 38 where it ignites to generate combustion gases having a high temperature and pressure. Atransition duct 40 circumferentially surrounds at least a portion of thecombustion chamber 38, and the combustion gases flow through thetransition duct 40 to theturbine 16. - The
turbine 16 may include alternating stages of rotatingbuckets 42 andstationary vanes 44. As will be described in more detail, thetransition duct 40 redirects and focuses the combustion gases onto the first stage of rotatingbuckets 42. As the combustion gases pass over the first stage of rotatingbuckets 42, the combustion gases expand, causing therotating buckets 42 androtor 18 to rotate. The combustion gases then flow to the next stage ofstationary vanes 44 which redirect the combustion gases to the next stage of rotatingbuckets 42, and the process repeats for the following stages. -
Fig. 2 shows a simplified cross-section view of theexemplary combustor 14 shown inFig. 1 according to one embodiment of the present invention. As shown, thecombustor casing 32 and end cover 36 may surround thecombustor 14 to contain the workingfluid 22 flowing from thecompressor 12. Animpingement sleeve 46 may surround thetransition duct 40, and the workingfluid 22 may pass through flow holes 48 in theimpingement sleeve 46 to flow along the outside of thetransition duct 40 to provide convective cooling to thetransition duct 40. When the workingfluid 22 reaches theend cover 36, the workingfluid 22 reverses direction to flow through one ormore fuel nozzles 34 and/ortubes 50 and into thecombustion chamber 38. -
Fig. 3 provides an enlarged cross-section view of a portion of thecombustor 14 shown inFigs. 1 and2 according to one embodiment of the present invention. As shown, the one ormore fuel nozzles 34 andtubes 50 may be radially arranged in anend cap 52 upstream from thecombustion chamber 38. Various embodiments of thecombustor 14 may include different numbers and arrangements offuel nozzles 34 andtubes 50. For example, in the embodiment shown inFigs. 1-3 , thecombustor 14 includes asingle fuel nozzle 34 aligned with anaxial centerline 54 of thecombustor 14, and thetubes 50 are radially arranged around thesingle fuel nozzle 34 in theend cap 52. Thefuel nozzle 34 may extend through theend cap 52 to provide fluid communication through theend cap 52 to thecombustion chamber 38. Thefuel nozzle 34 may include any suitable structure known to one of ordinary skill in the art for mixing fuel with the workingfluid 22 prior to entry into thecombustion chamber 38, and the present invention is not limited to any particular structure or design unless specifically recited in the claims. For example, as shown inFig. 3 , thefuel nozzle 34 may include acenter body 56 and abellmouth opening 58. Thecenter body 56 provides fluid communication for fuel to flow from theend cover 36, through thecenter body 56, and into thecombustion chamber 38. Thebellmouth opening 58 surrounds at least a portion of thecenter body 56 to define anannular passage 60 between thecenter body 56 and thebellmouth opening 58. In this manner, the workingfluid 22 may flow through theannular passage 60 to mix with the fuel from thecenter body 56 prior to reaching thecombustion chamber 38. If desired, thefuel nozzle 34 may further include one ormore swirler vanes 62 that extend radially between thecenter body 56 and thebellmouth opening 58 to impart swirl to the fuel-working fluid mixture prior to reaching thecombustion chamber 38. - As shown in
Fig. 3 , theend cap 52 extends radially across at least a portion of thecombustor 14 and generally includes anupstream surface 64 axially separated from adownstream surface 66. Thetubes 50 generally extend axially from theupstream surface 64 through thedownstream surface 66 of theend cap 52 to provide fluid communication for the workingfluid 22 to flow through theend cap 52 and into thecombustion chamber 38. Although shown as cylindrical tubes, the cross-section of thetubes 50 may be any geometric shape, and the present invention is not limited to any particular cross-section unless specifically recited in the claims. Ashroud 68 circumferentially surrounds at least a portion of theend cap 52 to partially define afuel plenum 70 between the upstream anddownstream surfaces - A
fuel conduit 72 may extend from theend cover 36 through theupstream surface 64 of theend cap 52 to provide fluid communication for fuel to flow from theend cover 36, through thefuel conduit 72, and into thefuel plenum 70. One or more of thetubes 50 may include afuel port 74 that provides fluid communication from thefuel plenum 70 into one or more of thetubes 50. Thefuel ports 74 may be angled radially, axially, and/or azimuthally to project and/or impart swirl to the fuel flowing through thefuel ports 74 and into thetubes 50. In this manner, the workingfluid 22 may flow into thetubes 50, and fuel from thefuel conduit 72 may flow around thetubes 50 in thefuel plenum 70 to provide convective cooling to thetubes 50 before flowing through thefuel ports 74 and into thetubes 50 to mix with the workingfluid 22. The fuel-working fluid mixture may then flow through thetubes 50 and into thecombustion chamber 38. -
Fig. 4 provides an enlarged cross-section view of a portion of thecombustor 14 shown inFig. 1 according to an alternate embodiment of the present invention, andFig. 5 provides a partial perspective view of theend cap 52 portion of thecombustor 14 shown inFig. 4 . As shown inFigs. 4 and5 , theend cap 52 may again include theupstream surface 64,downstream surface 66,shroud 68, andfuel plenum 70 as previously described with respect to the embodiment shown inFig. 3 . In addition, theend cap 52 may include a generallyhorizontal barrier 74 that extends radially between theupstream surface 64 and thedownstream surface 66 to axially separate thefuel plenum 70 from anair plenum 76. In this manner, theupstream surface 64,shroud 68, andbarrier 74 enclose or define thefuel plenum 70 around the upstream portion of thetubes 50, and thedownstream surface 66,shroud 68, andbarrier 74 enclose or define theair plenum 76 around the downstream portion of thetubes 50. In particular embodiments, as shown most clearly inFig. 5 , one or more generallyvertical baffles 78 may extend axially from theupstream surface 64 to thebarrier 74 or completely through theend cap 52 to thedownstream surface 66 to radially separate thetubes 50 into a plurality of groups or bundles 80 in theend cap 52. The baffles 78 (if present) allow eachbundle 80 oftubes 50 to have a dedicatedfuel plenum 70 and/orair plenum 76, allowing different fuels and/or fuel flow rates to be supplied to eachbundle 80 oftubes 50. Alternately, the baffles 78 (if present) may include flow holes 82 or other perforations to facilitate the flow of fuel between thefuel plenums 70 associated with eachbundle 80 oftubes 50. - As shown most clearly in
Figs. 4 and5 , theshroud 68 may include a plurality ofair ports 84 that provide fluid communication for the workingfluid 22 to flow through theshroud 68 and into theair plenum 76. In particular embodiments, as shown most clearly inFig. 4 , anair passage 86 between one ormore tubes 50 and thedownstream surface 66 may provide fluid communication from theair plenum 76, through thedownstream surface 66, and into thecombustion chamber 38. In this manner, a portion of the workingfluid 22 may flow through theair ports 84 in theshroud 68 and into theair plenum 76 to provide convective cooling around the lower portion of thetubes 50 before flowing through theair passages 86 and into thecombustion chamber 38. - Various embodiments of the
combustor 14 may include different numbers and arrangements offuel nozzles 34 andtubes 50, andFigs. 6-8 provide downstream axial views of theend cap 52 illustrating various arrangements within the scope of the present invention. In the particular embodiment shown inFig. 6 , for example, thetubes 50 are radially arranged across theend cap 52, and fuel and workingfluid 22 may be supplied through thetubes 50 to thecombustion chamber 38. In the particular embodiment shown inFig. 7 , the generallyvertical baffles 78 may separate thetubes 50 into generally circular tube bundles 80 radially arranged around a centercircular tube bundle 80. Alternately, as shown inFig. 8 , the generallyvertical baffles 78 may separate thetubes 50 into triangular or pie-shaped tube bundles 80 radially arranged around acenter fuel nozzle 34. One of ordinary skill in the art will readily appreciate based on that teachings herein that the particular embodiments of the present invention are not limited to any particular arrangement, shape, or number offuel nozzles 34,tubes 50, and/or tube bundles 80 unless specifically recited in the claims. -
Fig. 9 provides a perspective view of thetransition duct 40 andimpingement sleeve 46 shown inFig. 2 , andFig. 10 provides a perspective view ofmultiple transition ducts 40 radially circumferentially arranged around thegas turbine 10 shown inFig. 1 . As previously shown, thetransition duct 40 generally surrounds at least a portion of thecombustion chamber 38 and extends eachend cap 52 and theturbine 16. In this manner, eachtransition duct 40 provides a path that conditions the flow of combustion gases from each combustor 14 to theturbine 16. In particular embodiments, the orientation and/or cross-section of thetransition ducts 40 may replace or eliminate the need forstationary vanes 44 immediately upstream from the first stage of rotatingbuckets 42, thus increasing the efficiency and/or output of theturbine 16. - As shown in
Figs. 9 and10 , eachtransition duct 40 generally includes aninlet 90 and anoutlet 92 downstream from theinlet 90. The cross-section of theinlet 90 generally conforms to the radial cross-section of thecombustion chamber 38 proximate to theend cap 52, and the cross-section of thetransition duct 40 may progressively narrow proximate to theoutlet 92 to accelerate the combustion gases into theturbine 16. In addition, thetransition duct 40 may curve between theinlet 90 andoutlet 92 to enhance the angle at which the combustion gases flow into theturbine 16. For example, as shown inFigs. 9 and10 , longitudinal, tangential, andradial axes transition ducts 40 illustrate that thetransition ducts 40 may curve transversely, tangentially, and/or radially from thelongitudinal axis 94. It should be understood that the radial andtangential axes transition duct 40 with respect to a circumference defined by the annular array oftransition ducts 40, as shown inFig. 10 , and that the radial andtangential axes transition duct 40 about the circumference based on the number oftransition ducts 40 disposed in the annular array about thelongitudinal axis 94. As shown inFigs. 9 and10 , theoutlet 92 of thetransition duct 40 may be displaced or offset from theinlet 90 along both the longitudinal andtangential axes transition ducts 40 may also curve radially from thelongitudinal axis 94 to enhance the impact angle of the combustion gases against the rotatingbuckets 42. As a result, theoutlet 92 of thetransition duct 40 may be displaced or offset from theinlet 90 along theradial axis 96, as shown most clearly inFig. 10 . The combination of the tangential and/or radial offset of theoutlet 92 with respect to theinlet 90 may obviate the need forstationary vanes 44 upstream from the first stage of rotatingbuckets 42. - The embodiments described and illustrated in
Figs. 2-10 provide one or more benefits over existing combustors and methods of supplying fuel to combustors. For example, conventional combustors often include fuel nozzles designed to swirl the fuel and working fluid to enhance mixing prior to combustion. Although effective at reducing undesirable NOx emissions, a first stage of stationary vanes is often included between the combustor and the turbine upstream from the first stage of rotating buckets to redirect the resulting swirling combustion gases onto the first stage of rotating buckets. The transition duct incorporated into various embodiments of the present invention obviates the need for the first stage of stationary vanes, leading to enhanced efficiency of the turbine.
Claims (11)
- A combustor (14), comprising:a. an end cap (52) that extends radially across at least a portion of the combustor (14), wherein the end cap (52) comprises an upstream surface (64) axially separated from a downstream surface (66);b. a shroud (68) that circumferentially surrounds at least a portion of the end cap (52), wherein the shroud (68) at least partially defines a fuel plenum (70) between the upstream surface (64) and the downstream surface (66);c. a combustion chamber (38) downstream from the end cap (52), wherein the combustion chamber (38) defines a longitudinal axis (94);d. a plurality of tubes (50) that extend from the upstream surface (64) through the downstream surface (66) of the end cap (52), wherein the plurality of tubes (50) provide fluid communication through the end cap (52) to the combustion chamber (38);e. a transition duct (40) that circumferentially surrounds at least a portion of the combustion chamber (38) downstream from the end cap (52), wherein the transition duct curves (40) tangentially from the longitudinal axis (94); and characterised in that the combustor further comprises:f. a baffle (78) extending axially from the upstream surface (64) to the downstream surface (66), wherein the baffle (78) separates the plurality of tubes (50) into a plurality of tube bundles (80) in the end cap (52).
- The combustor as in claim 1, further comprising a fuel port that provides fluid communication from the fuel plenum (70) into one or more of the plurality of tubes (50).
- The combustor as in claim 1 or 2, further comprising an air plenum (76) between the upstream (64) and downstream (66) surfaces and downstream from the fuel plenum (70).
- The combustor as in claim 3, further comprising one or more air ports (84) that provide fluid communication through the shroud (68) to the air plenum (76).
- The combustor as in any of claims 1 to 4, further comprising a fuel nozzle (34) extending through the end cap (52), wherein the fuel nozzle (34) provides fluid communication through the end cap (52) to the combustion chamber (38).
- The combustor as in claim 5, wherein the plurality of tubes (50) circumferentially surrounds the fuel nozzle (34).
- The combustor of any preceding claim, wherein the transition duct (40) defines a longitudinal axis (94), a tangential axis (96), and a radial axis (98) and wherein an outlet (92) to the transition duct (40) is displaced from an inlet (90) to the transition duct (40) along the longitudinal axis (94) and the tangential axis (96).
- The combustor as in claim 7, wherein the transition duct (40) curves radially from the longitudinal axis (94).
- The combustor as in any preceding claim, further comprising an air passage (86) between one or more of the plurality of tubes (50) and the downstream surface (66) of the end cap (52).
- The combustor as in any of claims 7 to 9, wherein the outlet (92) to the transition duct (40) is displaced from the inlet (90) along the radial axis (98).
- The combustor as in any of claims 7 to 10, wherein the transition duct (40) curves radially from the longitudinal axis (94).
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US13/457,754 US20130283802A1 (en) | 2012-04-27 | 2012-04-27 | Combustor |
Publications (3)
Publication Number | Publication Date |
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EP2657608A2 EP2657608A2 (en) | 2013-10-30 |
EP2657608A3 EP2657608A3 (en) | 2013-12-11 |
EP2657608B1 true EP2657608B1 (en) | 2015-12-16 |
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EP13156623.4A Active EP2657608B1 (en) | 2012-04-27 | 2013-02-25 | A Combustor |
Country Status (5)
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US (1) | US20130283802A1 (en) |
EP (1) | EP2657608B1 (en) |
JP (1) | JP2013231575A (en) |
CN (1) | CN103375811A (en) |
RU (1) | RU2013108310A (en) |
Families Citing this family (10)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
JP6262616B2 (en) * | 2014-08-05 | 2018-01-17 | 三菱日立パワーシステムズ株式会社 | Gas turbine combustor |
EP3026346A1 (en) * | 2014-11-25 | 2016-06-01 | Alstom Technology Ltd | Combustor liner |
US10519860B2 (en) | 2017-03-07 | 2019-12-31 | General Electric Company | Turbine frame and bearing arrangement for three spool engine |
US10294821B2 (en) | 2017-04-12 | 2019-05-21 | General Electric Company | Interturbine frame for gas turbine engine |
WO2018190926A1 (en) * | 2017-04-13 | 2018-10-18 | General Electric Company | Single cavity trapped vortex combustor |
KR102063169B1 (en) | 2017-07-04 | 2020-01-07 | 두산중공업 주식회사 | Fuel nozzle assembly and combustor and gas turbine having the same |
CN107702144B (en) * | 2017-09-05 | 2020-03-10 | 中国联合重型燃气轮机技术有限公司 | Combustor and gas turbine with same |
KR20190048053A (en) * | 2017-10-30 | 2019-05-09 | 두산중공업 주식회사 | Combustor and gas turbine comprising the same |
US11428160B2 (en) | 2020-12-31 | 2022-08-30 | General Electric Company | Gas turbine engine with interdigitated turbine and gear assembly |
CN112902230A (en) * | 2021-03-11 | 2021-06-04 | 西北工业大学 | Inclined inlet double-head two-stage swirler combustion chamber |
Family Cites Families (18)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US4100733A (en) * | 1976-10-04 | 1978-07-18 | United Technologies Corporation | Premix combustor |
DE2950535A1 (en) * | 1979-11-23 | 1981-06-11 | BBC AG Brown, Boveri & Cie., Baden, Aargau | COMBUSTION CHAMBER OF A GAS TURBINE WITH PRE-MIXING / PRE-EVAPORATING ELEMENTS |
JP2528894B2 (en) * | 1987-09-04 | 1996-08-28 | 株式会社日立製作所 | Gas turbine combustor |
US5361586A (en) * | 1993-04-15 | 1994-11-08 | Westinghouse Electric Corporation | Gas turbine ultra low NOx combustor |
JP3956882B2 (en) * | 2002-08-22 | 2007-08-08 | 株式会社日立製作所 | Gas turbine combustor and gas turbine combustor remodeling method |
US7721547B2 (en) * | 2005-06-27 | 2010-05-25 | Siemens Energy, Inc. | Combustion transition duct providing stage 1 tangential turning for turbine engines |
JP4959620B2 (en) * | 2007-04-26 | 2012-06-27 | 株式会社日立製作所 | Combustor and fuel supply method for combustor |
US9822649B2 (en) * | 2008-11-12 | 2017-11-21 | General Electric Company | Integrated combustor and stage 1 nozzle in a gas turbine and method |
US9140454B2 (en) * | 2009-01-23 | 2015-09-22 | General Electric Company | Bundled multi-tube nozzle for a turbomachine |
US8205452B2 (en) * | 2009-02-02 | 2012-06-26 | General Electric Company | Apparatus for fuel injection in a turbine engine |
US8424311B2 (en) * | 2009-02-27 | 2013-04-23 | General Electric Company | Premixed direct injection disk |
US20100300102A1 (en) * | 2009-05-28 | 2010-12-02 | General Electric Company | Method and apparatus for air and fuel injection in a turbine |
US8616002B2 (en) * | 2009-07-23 | 2013-12-31 | General Electric Company | Gas turbine premixing systems |
JP5103454B2 (en) * | 2009-09-30 | 2012-12-19 | 株式会社日立製作所 | Combustor |
US8276385B2 (en) * | 2009-10-08 | 2012-10-02 | General Electric Company | Staged multi-tube premixing injector |
US20110259015A1 (en) * | 2010-04-27 | 2011-10-27 | David Richard Johns | Tangential Combustor |
US20120058437A1 (en) * | 2010-09-08 | 2012-03-08 | General Electric Company | Apparatus and method for mixing fuel in a gas turbine nozzle |
US8984887B2 (en) * | 2011-09-25 | 2015-03-24 | General Electric Company | Combustor and method for supplying fuel to a combustor |
-
2012
- 2012-04-27 US US13/457,754 patent/US20130283802A1/en not_active Abandoned
-
2013
- 2013-02-20 JP JP2013030522A patent/JP2013231575A/en active Pending
- 2013-02-25 EP EP13156623.4A patent/EP2657608B1/en active Active
- 2013-02-26 RU RU2013108310/06A patent/RU2013108310A/en not_active Application Discontinuation
- 2013-02-27 CN CN2013100614032A patent/CN103375811A/en active Pending
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JP2013231575A (en) | 2013-11-14 |
US20130283802A1 (en) | 2013-10-31 |
EP2657608A2 (en) | 2013-10-30 |
EP2657608A3 (en) | 2013-12-11 |
CN103375811A (en) | 2013-10-30 |
RU2013108310A (en) | 2014-09-10 |
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