EP2515042A2 - Aerodynamic fuel nozzle - Google Patents
Aerodynamic fuel nozzle Download PDFInfo
- Publication number
- EP2515042A2 EP2515042A2 EP12164848A EP12164848A EP2515042A2 EP 2515042 A2 EP2515042 A2 EP 2515042A2 EP 12164848 A EP12164848 A EP 12164848A EP 12164848 A EP12164848 A EP 12164848A EP 2515042 A2 EP2515042 A2 EP 2515042A2
- Authority
- EP
- European Patent Office
- Prior art keywords
- combustor
- fuel
- flow
- stages
- blocks
- 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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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
- F23R3/02—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration
- F23R3/04—Air inlet arrangements
- F23R3/10—Air inlet arrangements for primary air
- F23R3/12—Air inlet arrangements for primary air inducing a vortex
- F23R3/14—Air inlet arrangements for primary air inducing a vortex by using swirl vanes
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- 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
Definitions
- the present application relates generally to gas turbine engines and more particularly relates to an aerodynamic fuel nozzle with a triple stage swirler for late lean injection and turndown.
- Dry Low NO x technology may be applied for emissions control with gaseous fuel combustion in industrial gas turbines using annular can combustion systems and the like.
- These known Dry Low NO x combustion systems provide premixing of the fuel and the air for a generally uniform rate of combustion with relatively constant reaction zone temperatures.
- reaction zone temperatures may be optimized for very low production of nitrogen oxides ("NO x "), carbon monoxide (“CO”), unburned hydrocarbons (“UHC”), and other types of undesirable emissions.
- NO x nitrogen oxides
- CO carbon monoxide
- UHC unburned hydrocarbons
- the modulation of a center premix fuel nozzle may expand the range of operation by allowing the fuel-air ratio and the corresponding reaction rates of the outer nozzles to remain relatively constant while varying the fuel input into the turbine.
- Fuel staging allows for higher turbine inlet temperatures with a uniform heat release.
- Axially staged systems generally employ multiple planes of fuel injection along the combustor flow path. Even with advances in materials and heat transfer methods, however, current combustor designs are challenged to produce low nitrogen oxide emissions at full load conditions. Likewise, carbon monoxide emissions at part load conditions pose a challenge in reducing combustion firing temperatures. By firing only selected nozzles, the adjacent unfired nozzles may quench the reaction and produce carbon monoxide. The fired nozzle also may cause significant thermal stresses in the combustor liner so as to reduce component life time.
- the present invention resides in a combustor for a turbine engine including a number of fuel nozzles with one or more of the fuel nozzles including a swirler assembly.
- the swirler assembly includes a number of stages with a number of fueled structures and a number of unfueled structures.
- the present invention further resides in a method of operating a combustor for late lean injection including the steps of providing a flow of air to a fuel nozzle, providing a flow of fuel through one or more fueled structures of a swirler assembly, swirling the flow of air and the flow of fuel through multiple stages of the swirler assembly, establishing a primary recirculation zone about the fuel nozzle for low emissions, and establishing a secondary recirculation zone downstream of the fuel nozzle for high temperatures.
- Fig. 1 shows a schematic view of a turbo-machine such as a gas turbine engine 10 as may be described herein.
- the gas turbine engine 10 may include a compressor 15.
- the compressor 15 compresses an incoming flow of air 20.
- the compressor 15 delivers the compressed flow of air 20 to a combustor 25.
- the combustor 25 mixes the compressed flow of air 20 with a compressed flow of fuel 30 and ignites the mixture to create a flow of combustion gases 35.
- the gas turbine engine 10 may include any number of combustors 25.
- the flow of combustion gases 35 is delivered in turn to a turbine 40.
- the flow of combustion gases 35 drives the turbine 40 so as to produce mechanical work.
- the mechanical work produced in the turbine 40 drives the compressor 15 via a shaft 45 and an external load 50 such as an electrical generator and the like.
- the gas turbine engine 10 may use natural gas, various types of syngas, and/or other types of fuels.
- the gas turbine engine 10 may be any one of a number of different gas turbine engines such as those offered by General Electric Company of Schenectady, New York and the like.
- the gas turbine engine 10 may have different configurations and may use other types of components.
- Other types of gas turbine engines also may be used herein.
- Multiple gas turbine engines, other types of turbines, and other types of power generation equipment also may be used herein together.
- Figs. 2 and 3 show an example of a known combustor 25.
- the combustor includes an outer casing 55.
- the outer casing 55 may be bolted to the turbine 40 or otherwise attached.
- One end of the outer casing 55 may be enclosed by an end cover 60.
- the end cover 60 receives supply tubes, manifolds, and associated valves for feeding gaseous fuel, liquid fuel, air, and water.
- the end cover 60 supports a number of outer fuel nozzles 65 that surround a center nozzle 70.
- Other components and other configurations may be used herein.
- a combustion zone 75 may be positioned within the outer casing 55 downstream of the end cover 60 and the fuel nozzles 65, 70.
- the combustion zone 75 may be enclosed via a combustion liner 80.
- a flow sleeve 85 may surround the combustion liner 80 and define a flow path 90 therebetween.
- the flow of air 20 from the compressor 15 flows through the flow path 90, reverses direction about the end cover 60, and flows into the fuel nozzle 65, 70.
- a transition piece 95 may extend about the downstream end of the outer casing 55. The transition piece 95 may be in communication with the turbine 10 for directing the flow of combustion gases 35 thereto.
- Other components and other configurations may be used herein.
- the combustor 25 may be late lean injection compatible.
- a late lean injection compatible combustor may be any combustor with either an exit temperatures that exceeds about 2,500 degrees Fahrenheit (about 1,371 degrees Celsius) or handles fuels with components that are more reactive than, for example, methane with a hot side residence time greater than about 10 milliseconds.
- Examples of late lean injection compatible combustors include a DLN-1 ("Dry-Low NO x ”) combustor, a DLN-2 combustor, and a DLN-2.6 combustor offered by General Electric Company of Schenectady, New York. Other types of late lean injection compatible combustors may be used herein.
- Such late lean injection compatible combustors may have a number of fuel injectors (not shown) positioned about the transition piece 95 or otherwise for fuel staging and the like. These downstream fuel injectors, however, may increase the overall complexity of the combustor 25. Other components and other configurations may be used herein.
- Fig. 4 shows an example of a portion of a combustor 100 as may be described herein.
- the combustor 100 includes a number of fuel nozzles 110. Any number of the fuel nozzles 110 may be used.
- at least a center nozzle 120 may include a swirler assembly 130.
- the swirler assembly 130 may be a swirler with three stages 140.
- the three stages 140 thus include a first stage 150, a second stage 160, and a third stage 170. Any number of stages 140 may be used herein.
- the stages 140 may be positioned in an axial direction 180 as is shown in Fig. 4 , in a circumferential direction 190 as shown in Fig. 5 , or in combinations thereof.
- the outer swirler may have a swirl number S3 > 0.6 and the inner swirlers may have a swirl number S2 > S3 and a swirl number S 1 > S3.
- the swirl number characterizes combustor recirculation with a swirl number greater than 0.6 indicating good recirculation.
- Other components and other configurations may be used herein.
- the stages 140 of the swirler assembly 130 may take many different forms.
- the swirlers 130 may include a number of radial vanes 200 as is shown in Fig. 6 , a number of blocks 210 as shown in Fig. 7 , and/or combinations thereof. Other shapes also may be used herein.
- a number of fixed blocks 220 and a number of movable blocks 230 may be used so as to provide a variable swirler.
- a number of injection ports 240 may be used as are shown in Fig. 8 for a fueled structure 245.
- the injection ports 240 may be positioned in radial, axial, and/or circumferential directions. For example, three (3) different directions may be used in the vane 200 of Fig. 7 .
- the vanes 200 and blocks 210 also may be unfueled structures 250. Other configurations and other components may be used herein.
- vanes 200 and blocks 210 being fueled or unfueled may be used herein.
- the fuel nozzle 110 thus creates a primary recirculation zone 260 near the nozzle 120 and a secondary recirculation zone 270 downstream.
- the primary recirculation zone 260 operates near the flammability limits (about Phi - 2.5 or about Phi - 0.4) and the combustion products travel downstream without forming significant nitrogen oxides or other emissions.
- the secondary recirculation zone 270 the core and tertiary air mix at overall lean conditions and raise the overall temperature of the hot combustion gases so as to reduce fuel staging by aerodynamic means.
- the primary recirculation zone 260 may be fired at moderately lean temperatures (about Phi - 0.5 to 0.6). This may accomplish good fuel burnout and maintain low emissions. Further downstream, the inner products mix with the tertiary stream in the secondary recirculation zone 270 so as to bring the mixture to overall lean conditions.
- the fuel nozzle 110 thus is able to form turndown while maintaining low carbon monoxide in the presence of unfired nozzles.
- the nozzle 110 thus enables increased combustion firing temperatures without increasing nitrogen oxides by effectively implementing late lean injection performance without significant hardware changes.
- the nozzle 110 also enables high combustion turndown without producing significant levels of carbon monoxide.
- the nozzle 110 may be used in conjunction with existing nozzles that may remain unfired without impacting on the low carbon monoxide performance.
- the use of the swirler assembly 130 with a center nozzle 120 thus provides fuel staging so as to create a downstream aero-staged flame. Fuel staging herein thus may be maximized. Moreover, such fuel staging may dampen combustion dynamics.
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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)
Abstract
Description
- The present application relates generally to gas turbine engines and more particularly relates to an aerodynamic fuel nozzle with a triple stage swirler for late lean injection and turndown.
- Dry Low NOx technology may be applied for emissions control with gaseous fuel combustion in industrial gas turbines using annular can combustion systems and the like. These known Dry Low NOx combustion systems provide premixing of the fuel and the air for a generally uniform rate of combustion with relatively constant reaction zone temperatures. Through careful air management, these reaction zone temperatures may be optimized for very low production of nitrogen oxides ("NOx"), carbon monoxide ("CO"), unburned hydrocarbons ("UHC"), and other types of undesirable emissions. Specifically, the modulation of a center premix fuel nozzle may expand the range of operation by allowing the fuel-air ratio and the corresponding reaction rates of the outer nozzles to remain relatively constant while varying the fuel input into the turbine.
- Fuel staging allows for higher turbine inlet temperatures with a uniform heat release. Axially staged systems generally employ multiple planes of fuel injection along the combustor flow path. Even with advances in materials and heat transfer methods, however, current combustor designs are challenged to produce low nitrogen oxide emissions at full load conditions. Likewise, carbon monoxide emissions at part load conditions pose a challenge in reducing combustion firing temperatures. By firing only selected nozzles, the adjacent unfired nozzles may quench the reaction and produce carbon monoxide. The fired nozzle also may cause significant thermal stresses in the combustor liner so as to reduce component life time.
- There is thus a desire for improved fuel nozzle and combustor designs and/or methods of staging fuel therein so as to lower peak fuel temperatures. Such improved designs should maintain adequate system output and efficiency with correspondingly low production of nitrogen oxides, carbon monoxide, and other types of emissions.
- The present invention resides in a combustor for a turbine engine including a number of fuel nozzles with one or more of the fuel nozzles including a swirler assembly. The swirler assembly includes a number of stages with a number of fueled structures and a number of unfueled structures.
- The present invention further resides in a method of operating a combustor for late lean injection including the steps of providing a flow of air to a fuel nozzle, providing a flow of fuel through one or more fueled structures of a swirler assembly, swirling the flow of air and the flow of fuel through multiple stages of the swirler assembly, establishing a primary recirculation zone about the fuel nozzle for low emissions, and establishing a secondary recirculation zone downstream of the fuel nozzle for high temperatures.
- These and other features and improvements of the present application and the resultant patent will become apparent to one of ordinary skill in the art upon review of the following detailed description when taken in conjunction with the several drawings and the appended claims.
- Embodiments of the present invention will now be described, by way of example only, with reference to the accompanying drawings in which:
-
Fig. 1 is a schematic view of a known gas turbine engine. -
Fig. 2 is a schematic cross-sectional view of a known combustor. -
Fig. 3 is a schematic front view of an end cover and fuel nozzle assembly of the combustor ofFig. 2 . -
Fig. 4 is a partial side cross-sectional view of a fuel nozzle with a swirler as may be described herein. -
Fig. 5 is a partial side cross-sectional view of a fuel nozzle with an alternative embodiment of a swirler as may be described herein. -
Fig. 6 is a front plan view of a radial embodiment of the swirler of the fuel nozzle ofFig. 4 . -
Fig. 7 is a schematic view of a block embodiment of the swirler of the fuel nozzle ofFig. 4 . -
Fig. 8 is a partial side view of the block embodiment of the swirler ofFig. 7 . - Referring now to the drawings, in which like numerals refer to like elements throughout the several views,
Fig. 1 shows a schematic view of a turbo-machine such as agas turbine engine 10 as may be described herein. Thegas turbine engine 10 may include acompressor 15. Thecompressor 15 compresses an incoming flow ofair 20. Thecompressor 15 delivers the compressed flow ofair 20 to acombustor 25. Thecombustor 25 mixes the compressed flow ofair 20 with a compressed flow offuel 30 and ignites the mixture to create a flow ofcombustion gases 35. Although only asingle combustor 25 is shown, thegas turbine engine 10 may include any number ofcombustors 25. The flow ofcombustion gases 35 is delivered in turn to aturbine 40. The flow ofcombustion gases 35 drives theturbine 40 so as to produce mechanical work. The mechanical work produced in theturbine 40 drives thecompressor 15 via ashaft 45 and anexternal load 50 such as an electrical generator and the like. - The
gas turbine engine 10 may use natural gas, various types of syngas, and/or other types of fuels. Thegas turbine engine 10 may be any one of a number of different gas turbine engines such as those offered by General Electric Company of Schenectady, New York and the like. Thegas turbine engine 10 may have different configurations and may use other types of components. Other types of gas turbine engines also may be used herein. Multiple gas turbine engines, other types of turbines, and other types of power generation equipment also may be used herein together. -
Figs. 2 and3 show an example of a knowncombustor 25. Generally described, the combustor includes anouter casing 55. Theouter casing 55 may be bolted to theturbine 40 or otherwise attached. One end of theouter casing 55 may be enclosed by anend cover 60. Theend cover 60 receives supply tubes, manifolds, and associated valves for feeding gaseous fuel, liquid fuel, air, and water. Theend cover 60 supports a number ofouter fuel nozzles 65 that surround acenter nozzle 70. Other components and other configurations may be used herein. - A
combustion zone 75 may be positioned within theouter casing 55 downstream of theend cover 60 and thefuel nozzles combustion zone 75 may be enclosed via acombustion liner 80. Aflow sleeve 85 may surround thecombustion liner 80 and define aflow path 90 therebetween. The flow ofair 20 from thecompressor 15 flows through theflow path 90, reverses direction about theend cover 60, and flows into thefuel nozzle transition piece 95 may extend about the downstream end of theouter casing 55. Thetransition piece 95 may be in communication with theturbine 10 for directing the flow ofcombustion gases 35 thereto. Other components and other configurations may be used herein. - The
combustor 25 may be late lean injection compatible. A late lean injection compatible combustor may be any combustor with either an exit temperatures that exceeds about 2,500 degrees Fahrenheit (about 1,371 degrees Celsius) or handles fuels with components that are more reactive than, for example, methane with a hot side residence time greater than about 10 milliseconds. Examples of late lean injection compatible combustors include a DLN-1 ("Dry-Low NOx") combustor, a DLN-2 combustor, and a DLN-2.6 combustor offered by General Electric Company of Schenectady, New York. Other types of late lean injection compatible combustors may be used herein. Such late lean injection compatible combustors may have a number of fuel injectors (not shown) positioned about thetransition piece 95 or otherwise for fuel staging and the like. These downstream fuel injectors, however, may increase the overall complexity of thecombustor 25. Other components and other configurations may be used herein. -
Fig. 4 shows an example of a portion of acombustor 100 as may be described herein. Thecombustor 100 includes a number offuel nozzles 110. Any number of thefuel nozzles 110 may be used. In this example, at least acenter nozzle 120 may include aswirler assembly 130. Theswirler assembly 130 may be a swirler with threestages 140. The threestages 140 thus include afirst stage 150, asecond stage 160, and athird stage 170. Any number ofstages 140 may be used herein. Thestages 140 may be positioned in anaxial direction 180 as is shown inFig. 4 , in acircumferential direction 190 as shown inFig. 5 , or in combinations thereof. The outer swirler may have a swirl number S3 > 0.6 and the inner swirlers may have a swirl number S2 > S3 and a swirl number S 1 > S3. The swirl number characterizes combustor recirculation with a swirl number greater than 0.6 indicating good recirculation. Other components and other configurations may be used herein. - The
stages 140 of theswirler assembly 130 may take many different forms. For example, theswirlers 130 may include a number ofradial vanes 200 as is shown inFig. 6 , a number ofblocks 210 as shown inFig. 7 , and/or combinations thereof. Other shapes also may be used herein. In the block embodiment ofFig. 7 , a number of fixedblocks 220 and a number ofmovable blocks 230 may be used so as to provide a variable swirler. In either embodiment, a number ofinjection ports 240 may be used as are shown inFig. 8 for a fueledstructure 245. Theinjection ports 240 may be positioned in radial, axial, and/or circumferential directions. For example, three (3) different directions may be used in thevane 200 ofFig. 7 . Thevanes 200 and blocks 210 also may beunfueled structures 250. Other configurations and other components may be used herein. - Combinations of the
vanes 200 and theblocks 210 may be used together. Specifically, different types of swirlers with different types ofvanes 200, blocks 210, or other shapes may be used herein. The following chart shows several examples of differing embodiments of the swirler assemblies 130:Embodiment Swirler 1 Swirler 2 Swirler 3 1 Radial Vane, Fueled Radial Vane, Fueled Block Vane, Unfueled 2 Radial Vane, Fueled Block Vane, Fueled Block Vane, Unfueled 3 Radial Vane, Fueled Radial Vane, Fueled Radial Vane, Unfueled 4 Radial Vane, Fueled Radial Vane, Unfueled Radial Vane, Fueled 5 Block Vane, Fueled Block Vane, Fueled Block Vane, Fueled - The examples shown herein are not exclusive. As one can appreciate, any number of different combinations of
vanes 200 and blocks 210 being fueled or unfueled may be used herein. - The
fuel nozzle 110 thus creates aprimary recirculation zone 260 near thenozzle 120 and asecondary recirculation zone 270 downstream. With late lean injection operations, theprimary recirculation zone 260 operates near the flammability limits (about Phi - 2.5 or about Phi - 0.4) and the combustion products travel downstream without forming significant nitrogen oxides or other emissions. In thesecondary recirculation zone 270, the core and tertiary air mix at overall lean conditions and raise the overall temperature of the hot combustion gases so as to reduce fuel staging by aerodynamic means. - For high turndown, the
primary recirculation zone 260 may be fired at moderately lean temperatures (about Phi - 0.5 to 0.6). This may accomplish good fuel burnout and maintain low emissions. Further downstream, the inner products mix with the tertiary stream in thesecondary recirculation zone 270 so as to bring the mixture to overall lean conditions. Thefuel nozzle 110 thus is able to form turndown while maintaining low carbon monoxide in the presence of unfired nozzles. - The
nozzle 110 thus enables increased combustion firing temperatures without increasing nitrogen oxides by effectively implementing late lean injection performance without significant hardware changes. Thenozzle 110 also enables high combustion turndown without producing significant levels of carbon monoxide. Thenozzle 110 may be used in conjunction with existing nozzles that may remain unfired without impacting on the low carbon monoxide performance. - The use of the
swirler assembly 130 with acenter nozzle 120 thus provides fuel staging so as to create a downstream aero-staged flame. Fuel staging herein thus may be maximized. Moreover, such fuel staging may dampen combustion dynamics. - It should be apparent that the foregoing relates only to certain embodiments of the present application and the resultant patent. Numerous changes and modifications may be made herein by one of ordinary skill in the art without departing from the general spirit and scope of the invention as defined by the following claims and the equivalents thereof.
Claims (15)
- A combustor (100) for a turbine engine (10), comprising:a plurality of fuel nozzles (110); andone or more of the plurality of fuel nozzles (110) comprising a swirler assembly (130);wherein the swirler assembly (130) comprises a plurality of stages (140); andwherein the plurality of stages (140) comprises a plurality of fueled structures (245) and a plurality of unfueled structures (250).
- The combustor (100) of claim 1, wherein the plurality of fuel nozzles (110) comprises a central fuel nozzle (120).
- The combustor (100) of claim 1 or 2, wherein the plurality of stages (140) comprises a first stage (150), a second stage (160), and a third stage (170).
- The combustor (100) of any of claims 1, 2 or 3, wherein the plurality of stages (140) extend in an axial direction (180).
- The combustor (100) of any of claims 1 to 4, wherein the plurality of stages (140) extend in a circumferential direction (190).
- The combustor (100) of any preceding claim, wherein the plurality of stages (140) comprises one of a plurality of radial vanes (200) or a plurality of blocks (210).
- The combustor (100) of claim 6, wherein the plurality of stages (140) comprises a plurality of blocks (210) and wherein the plurality of blocks (210) comprises a plurality of fixed blocks (220) and a plurality of movable blocks (230).
- The combustor (100) of any preceding claim, wherein the plurality of fueled structures (245) comprises one of a plurality of radial vanes (200), a plurality of moveable blocks (210) or a plurality of radial vanes (200) and a plurality of blocks (210).
- The combustor (100) of any of claims 1 to 7, wherein the plurality of fueled structures (245) comprises a plurality of injection ports (240).
- The combustor (100) of claim 9, wherein the plurality of injection ports (240) comprises an axial direction (180) and/or a circumferential direction (190).
- The combustor (100) of any preceding claim, further comprising a primary recirculation zone (260) about the plurality of fuel nozzles (110) and a secondary recirculation zone (270) downstream of the plurality of fuel nozzles (110).
- A method of operating a combustor (100) for late lean injection, comprising:providing a flow of air (20) to a fuel nozzle (110);providing a flow of fuel (30) through one or more fueled structures (245) of a swirler assembly (130);swirling the flow of air (20) and the flow of fuel (30) through multiple stages (140) of the swirler assembly (130);establishing a primary recirculation zone (260) about the fuel nozzle (110) for low emissions; andestablishing a secondary recirculation zone (270) downstream of the fuel nozzle (110) for high temperatures.
- The method of claim 12, wherein the step of establishing a primary recirculation zone (260) comprises combusting the flow of fuel (30) and the flow of air (20) near a flammability limit.
- The method of claim 12 or 13, wherein the step of establishing a primary recirculation zone (260) comprises combusting the flow of fuel (30) and the flow of air (20) without forming nitrogen oxides.
- The method of any of claims 12 to 14, wherein the step of establishing a secondary recirculation zone (270) comprises lean mixing of the flow of fuel (30) and the flow of air (20).
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US13/092,345 US20120266602A1 (en) | 2011-04-22 | 2011-04-22 | Aerodynamic Fuel Nozzle |
Publications (2)
Publication Number | Publication Date |
---|---|
EP2515042A2 true EP2515042A2 (en) | 2012-10-24 |
EP2515042A3 EP2515042A3 (en) | 2014-01-08 |
Family
ID=46084805
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP12164848.9A Withdrawn EP2515042A3 (en) | 2011-04-22 | 2012-04-19 | Aerodynamic fuel nozzle |
Country Status (3)
Country | Link |
---|---|
US (1) | US20120266602A1 (en) |
EP (1) | EP2515042A3 (en) |
CN (1) | CN102809176A (en) |
Cited By (2)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
CN104406197A (en) * | 2014-11-24 | 2015-03-11 | 中国科学院工程热物理研究所 | Low-emission reverse flow combustor adopting radial swirl injection and fuel oil grading schemes |
WO2023180315A3 (en) * | 2022-03-24 | 2023-11-16 | Rolls-Royce Deutschland Ltd & Co Kg | Nozzle assembly with a central fuel supply and at least one air channel |
Families Citing this family (7)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US9347378B2 (en) | 2013-05-13 | 2016-05-24 | Solar Turbines Incorporated | Outer premix barrel vent air sweep |
US11181274B2 (en) | 2017-08-21 | 2021-11-23 | General Electric Company | Combustion system and method for attenuation of combustion dynamics in a gas turbine engine |
CN109812341A (en) * | 2018-12-31 | 2019-05-28 | 华电电力科学研究院有限公司 | A kind of DLN-2.6+ combustion system firing optimization method using the LVE method of operation |
CN110345513B (en) * | 2019-07-12 | 2021-04-16 | 中国航发沈阳发动机研究所 | Cyclone atomization device for staged combustion |
US20230194092A1 (en) * | 2021-12-21 | 2023-06-22 | General Electric Company | Gas turbine fuel nozzle having a lip extending from the vanes of a swirler |
US20230212984A1 (en) * | 2021-12-30 | 2023-07-06 | General Electric Company | Engine fuel nozzle and swirler |
CN114526497B (en) * | 2022-01-07 | 2023-02-07 | 清华大学 | Double-necking combined spiral-flow type center-grading high-temperature-rise combustion chamber |
Family Cites Families (9)
Publication number | Priority date | Publication date | Assignee | Title |
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US5365865A (en) * | 1991-10-31 | 1994-11-22 | Monro Richard J | Flame stabilizer for solid fuel burner |
US6374615B1 (en) * | 2000-01-28 | 2002-04-23 | Alliedsignal, Inc | Low cost, low emissions natural gas combustor |
US6389815B1 (en) * | 2000-09-08 | 2002-05-21 | General Electric Company | Fuel nozzle assembly for reduced exhaust emissions |
US7134287B2 (en) * | 2003-07-10 | 2006-11-14 | General Electric Company | Turbine combustor endcover assembly |
EP1821035A1 (en) * | 2006-02-15 | 2007-08-22 | Siemens Aktiengesellschaft | Gas turbine burner and method of mixing fuel and air in a swirling area of a gas turbine burner |
US7631500B2 (en) * | 2006-09-29 | 2009-12-15 | General Electric Company | Methods and apparatus to facilitate decreasing combustor acoustics |
US20080083224A1 (en) * | 2006-10-05 | 2008-04-10 | Balachandar Varatharajan | Method and apparatus for reducing gas turbine engine emissions |
EP2192347B1 (en) * | 2008-11-26 | 2014-01-01 | Siemens Aktiengesellschaft | Tubular swirling chamber |
EP2233836B1 (en) * | 2009-03-23 | 2015-07-29 | Siemens Aktiengesellschaft | Swirler, method for reducing flashback in a burner with at least one swirler and burner |
-
2011
- 2011-04-22 US US13/092,345 patent/US20120266602A1/en not_active Abandoned
-
2012
- 2012-04-19 EP EP12164848.9A patent/EP2515042A3/en not_active Withdrawn
- 2012-04-20 CN CN2012101792348A patent/CN102809176A/en active Pending
Non-Patent Citations (1)
Title |
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None |
Cited By (2)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
CN104406197A (en) * | 2014-11-24 | 2015-03-11 | 中国科学院工程热物理研究所 | Low-emission reverse flow combustor adopting radial swirl injection and fuel oil grading schemes |
WO2023180315A3 (en) * | 2022-03-24 | 2023-11-16 | Rolls-Royce Deutschland Ltd & Co Kg | Nozzle assembly with a central fuel supply and at least one air channel |
Also Published As
Publication number | Publication date |
---|---|
CN102809176A (en) | 2012-12-05 |
EP2515042A3 (en) | 2014-01-08 |
US20120266602A1 (en) | 2012-10-25 |
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