CN103216849A - Fuel nozzle - Google Patents
Fuel nozzle Download PDFInfo
- Publication number
- CN103216849A CN103216849A CN2013100231995A CN201310023199A CN103216849A CN 103216849 A CN103216849 A CN 103216849A CN 2013100231995 A CN2013100231995 A CN 2013100231995A CN 201310023199 A CN201310023199 A CN 201310023199A CN 103216849 A CN103216849 A CN 103216849A
- Authority
- CN
- China
- Prior art keywords
- fuel
- air
- fuel nozzle
- stream
- nozzle
- 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.)
- Pending
Links
Images
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23D—BURNERS
- F23D11/00—Burners using a direct spraying action of liquid droplets or vaporised liquid into the combustion space
- F23D11/36—Details, e.g. burner cooling means, noise reduction means
- F23D11/38—Nozzles; Cleaning devices therefor
- F23D11/383—Nozzles; Cleaning devices therefor with swirl means
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23D—BURNERS
- F23D11/00—Burners using a direct spraying action of liquid droplets or vaporised liquid into the combustion space
- F23D11/36—Details, e.g. burner cooling means, noise reduction means
- F23D11/38—Nozzles; Cleaning devices therefor
- F23D11/386—Nozzle cleaning
-
- 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
-
- 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
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Pre-Mixing And Non-Premixing Gas Burner (AREA)
- Spray-Type Burners (AREA)
Abstract
The present invention relates to a fuel nozzle. The present invention provides a fuel nozzle for mixing a flow of fuel and a flow of air. The fuel nozzle may include a downstream face, a number of fuel passages positioned about the downstream face for the flow of fuel, and a nozzle collar positioned about the downstream face. The nozzle collar may include a number of air vanes for the flow of air and one or more purge holes therethrough.
Description
Technical field
The patent relate generally to gas-turbine unit of the application and generation, relate more specifically to have the fuel nozzle of the nozzle collar, fuel-air mixes to improve, flame keeps (flame holding) patience and overall performance to have a plurality of purge holes in this nozzle collar.
Background technology
In general, gas-turbine unit can adopt one or more fuel nozzles to mix to promote the fuel-air in burner.Each fuel nozzle can flow fuel, air stream and optionally other fluid streams guide in the burner in burner, to burn.In some cases, combustion flame can be tempered to and/or flame remains to the surface of fuel nozzle.Flame keeps causing to the apparent damage of fuel nozzle and/or the performance of reduction fuel nozzle and whole gas-turbine unit.
Particularly, if flammable fuel-air mixture is present in very in the low-speed region near Combustion Source, flame then can takes place keep.In the fuel nozzle of combustion system that is used for based on diffusion, near the general because aerodynamics wherein of low-speed region and can the inwall of fuel nozzle, finding.This flammable mixture may cause keeping at the flame of fuel nozzle inner.The flame maintenance of fuel nozzle inner can cause fuel nozzle to burn out, and promptly is subjected to flame from damaging in nozzle.
Therefore need improved fuel nozzle design.Preferably, this improved fuel nozzle design can limit or reduce in the flammable fuel/air mixture in the low-speed region of fuel nozzle to limit flame maintenance etc.Restriction flame keeps improving the overall performance and the durability of fuel nozzle and gas-turbine unit.
Summary of the invention
Therefore the patent of the application and generation provides a kind of example that is used for the fuel nozzle of fuel combination stream and air stream.Fuel nozzle can comprise downstream surface; Be positioned to around downstream surface to be used for a plurality of fuel channels of fuel stream; With the nozzle collar that is positioned to around downstream surface.This nozzle collar can comprise that a plurality of air stators flow to be used for air, and comprises the one or more purge holes that therefrom pass.
The patent of the application and generation also provides the example of a kind of restriction around the method for the flame maintenance of fuel nozzle.This method can comprise the steps: to provide the fuel stream of the downstream surface of passing fuel nozzle; The air stream of a plurality of air stators of the nozzle collar that passes fuel nozzle is provided; Fuel stream and air stream are mixed; The sweep air flow of passing a plurality of purge holes in the air stator is provided; Restriction produces one or more recirculation regions in the fuel nozzle downstream with utilizing sweep air flow.
The patent of the application and generation also provides a kind of example of the burner that uses with gas-turbine unit.This burner can comprise the combustion chamber and be positioned to center on a plurality of fuel nozzles of combustion chamber.Comprise the nozzle collar in a plurality of fuel nozzles each.The nozzle collar can comprise one or more air stators with one or more purge holes so that sweep air flow is therefrom passed.
After checking following detailed description in conjunction with several accompanying drawings and appending claims, these and other features of the patent of the application and generation and to improve will be conspicuous to those skilled in the art.
Description of drawings
Fig. 1 is the schematic diagram of gas-turbine unit, and compressor, burner and turbine are shown.
Fig. 2 is the side view of the example of the compressor shown in Fig. 1 for example.
Fig. 3 is the perspective view as the example of the fuel nozzle of describing in this manual with nozzle collar.
Fig. 4 is the part side cross-sectional view of the fuel nozzle with nozzle collar of Fig. 3.
The specific embodiment
Referring now to accompanying drawing, similarly Reference numeral is represented similar elements in whole accompanying drawings, and Fig. 1 illustrates the schematic diagram as the gas-turbine unit 10 that uses in this specification.Gas-turbine unit 10 can comprise compressor 15.The air stream 20 that compressor 15 compressions enter.Compressor 15 is sent to burner 25 with the air stream 20 of compression.Burner 25 makes the air stream 20 of compression mix with the fuel stream 30 of pressurization, and the some burning mixt is to produce burning gases stream 35.Although single burner 25 only is shown, gas-turbine unit 10 can comprise the burner 25 of any amount.Burning gases stream 35 then be transferred into turbine 40.Burning gases stream 35 drives turbine 40 to produce mechanical power.The mechanical power that produces in the turbine 40 is via axle 45 drive compression machines 15 and drive external load 50 (for example generator etc.).Here can use other structures and miscellaneous part.
Gas-turbine unit 10 can use the fuel of natural gas, various types of synthesis gas and/or other types.Gas-turbine unit 10 can be by being positioned at Schenectady, in the multiple different gas-turbine units that the General Electric Company of NewYork is provided to any includes but not limited to for example 7 or 9 serial heavily loaded gas-turbine units etc.Gas-turbine unit 10 can have different structures and can use the parts of other types.Here can also use the gas-turbine unit of other types.Here can also use the turbine of a plurality of gas-turbine units, other types and the generating equipment of other types together.
Fig. 2 illustrates the example of the burner 25 that can use with gas-turbine unit 10 grades.Can comprise a plurality of fuel nozzles 55 in the burner 25.As mentioned above, each fuel nozzle 55 air can be flowed 20, fuel stream 30 and optionally other fluid streams guide in the burner 25 in burner, to burn.The fuel nozzle 55 of any amount can be used for any configuration.Fuel nozzle 55 can be connected to end cap 60 near the top 65 of burner 25.Air stream 20 and fuel stream 30 can be guided through end cap 60 and top 65 and arrive each fuel nozzle 55, to distribute fuel-air mixture in fuel nozzle.
Can also comprise combustion chamber 70 in the burner 25.Burner 70 can be limited by burning housing 75, burning lining 80, flowing sleeve 85 etc.Lining 80 and flowing sleeve 85 can compare and locate coaxially to each other, to be defined for air stream 20 air path of passing 90.Downstream transition piece 95 can be led in combustion chamber 70.Air stream 20 and fuel stream 30 can be in the mixed downstream of fuel nozzle 55, to burn in combustion chamber 70.Burning gases stream 35 can be directed through transition piece 95, to produce useful work in turbine 40 towards turbine 40 then.Here can also use miscellaneous part and other structures.
Fig. 3 and Fig. 4 illustrate the example as the fuel nozzle of describing in this specification 100.Fuel nozzle 100 can comprise outer tube 110.Outer tube 110 can lead to the downstream surface 120 with fuel nozzle tip 130.Can comprise a plurality of fuel and air duct in the outer tube 110.Particularly, a plurality of fuel channels 140 can extend through and can locate vertically around downstream surface 120.Fuel channel 140 can flow 30 with fuel and be communicated with.A plurality of most advanced and sophisticated outlets 150 also can extend through, and can be around most advanced and sophisticated 130 location of fuel nozzle.Most advanced and sophisticated outlet 150 can flow 30 with fuel, the stream of air stream 20 or other types is communicated with.The fuel stream 30 that extends through fuel channel 140 and pass most advanced and sophisticated outlet 150 can be identical and/or dissimilar fuel stream according to combustion characteristics and other types parameter.Here can also use miscellaneous part and other structures.
As mentioned above, because the interaction between air stream 20 and the fuel stream 30 can form a plurality of recirculation regions 190.These recirculation regions 190 can cause via the flame maintenance (flame holding) of low-speed region around fuel nozzle 100.As a result, a plurality of purge holes (purgeholes) 200 can be positioned to pass air stator 170.Purge hole 200 can have arbitrary dimension, shape or structure.Here can use the purge hole 200 of any amount.Purge hole 200 can angled (inclination) and/or can be used a plurality of angles (inclination) here.Additional purge hole 200 can also extend through downstream ring 180 and/or other places.Here can also use miscellaneous part and other structures.
Purge hole 200 therefore provide therefrom pass, the sweep air flow 210 of the part of air stream 20 as a whole.The sweep air flow 210 of passing purge hole 200 can upset (disrupt) recirculation regions 190 that caused by low-speed region or other reasons, that be positioned at fuel nozzle 100 downstreams.Purge hole 200 can be in the tilted angle, and produces recirculation regions 190 so that purging air 210 is upset along circumferential direction roughly.Eliminate or reduce these recirculation regions 190 and will reduce flame maintenance on it along circumferential direction.Thus, reducing flame keeps the fuel nozzle 100 with improved durability and service life will be provided.In addition, whole gas-turbine unit 100 can have the performance of improved discharging and overall improvement.The purge hole 200 that use has a sweep air flow 210 of therefrom passing can be used as original device or increases to the part of remodeling.
Clearly aforementioned some embodiment that only relates to the patent of the application and generation.Under the situation that does not break away from the general spirit and scope of the present invention that limited by the following claims and the equivalent form of value thereof, those of ordinary skills can carry out various changes and modification.
Claims (20)
1. one kind is used to make fuel stream and air to flow the fuel nozzle that mixes, and described fuel nozzle comprises:
Downstream surface;
Be positioned to a plurality of fuel channels, so that described fuel stream therefrom passes around described downstream surface;
Be positioned to the nozzle collar around described downstream surface;
The described nozzle collar comprises a plurality of air stators, so that described air stream therefrom passes; With
In described a plurality of air stator one or more comprises the one or more purge holes that therefrom pass.
2. fuel nozzle according to claim 1 is characterized in that described fuel nozzle also comprises outer tube, and described a plurality of fuel channels extend through described outer tube and arrive described downstream surface.
3. fuel nozzle according to claim 1 is characterized in that, described downstream surface comprises fuel nozzle tip thereon, location.
4. fuel nozzle according to claim 3 is characterized in that, described fuel nozzle tip comprises location one or more most advanced and sophisticated outlet thereon, so that described fuel stream and/or described air stream therefrom pass.
5. fuel nozzle according to claim 4 is characterized in that, the described fuel stream that passes described a plurality of fuel channels comprises first fuel stream, and the described fuel stream that passes described one or more most advanced and sophisticated outlets comprises second fuel stream.
6. fuel nozzle according to claim 1 is characterized in that, the described fuel collar comprises the downstream ring adjacent with described a plurality of air stators.
7. fuel nozzle according to claim 1 is characterized in that, described fuel nozzle also comprises a plurality of fuel nozzles that are positioned to around the combustion chamber.
8. fuel nozzle according to claim 1 is characterized in that described fuel nozzle also comprises the sweep air flow of passing described one or more purge holes.
9. fuel nozzle according to claim 8 is characterized in that, the described sweep air flow restriction of passing described one or more purge holes is positioned at the recirculation regions of the described fuel stream and the described air stream in described fuel nozzle downstream.
10. fuel nozzle according to claim 9 is characterized in that, restriction is positioned at the flame maintenance of the recirculation regions limit value that described fuel flows and described air flows in described fuel nozzle downstream around described fuel nozzle.
11. a restriction centers on the method for the flame maintenance of fuel nozzle, described method comprises:
The fuel stream of the downstream surface of passing described fuel nozzle is provided;
The air stream of a plurality of air stators of the nozzle collar that passes described fuel nozzle is provided;
Described fuel stream and described air stream are mixed;
The sweep air flow of passing a plurality of purge holes in described a plurality of air stator is provided; With
Restriction produces one or more recirculation regions in described fuel nozzle downstream to utilize described sweep air flow.
12. method according to claim 11 is characterized in that, the step that provides fuel to flow comprises provides the fuel that passes a plurality of fuel channels stream.
13. method according to claim 11 is characterized in that, the step that provides fuel to flow comprises provides the fuel of a plurality of most advanced and sophisticated outlets of passing in fuel nozzle tip stream.
14. method according to claim 11 is characterized in that, provides the step of the air stream that passes a plurality of air stators to comprise the air that passes a plurality of angled air stators stream is provided.
15. method according to claim 11 is characterized in that, the step that limits one or more recirculation regions comprises the generation of restriction along one or more recirculation regions of circumferential direction extension.
16. a burner that uses with gas-turbine unit, described burner comprises:
The combustion chamber; With
Be positioned to a plurality of fuel nozzles around described combustion chamber;
Comprise the nozzle collar in described a plurality of fuel nozzle each;
The described nozzle collar comprises one or more air stators, and one or more purge holes pass described one or more air stator.
17. burner according to claim 16 is characterized in that, each in described a plurality of fuel nozzles comprises: a plurality of fuel channels so that fuel stream therefrom pass; Described one or more air stator so that air stream therefrom pass; Reach described one or more purge holes so that sweep air flow is therefrom passed.
18. burner according to claim 16 is characterized in that, described a plurality of fuel nozzles are positioned to around end cap.
19. burner according to claim 16 is characterized in that, each in described a plurality of fuel nozzles comprises downstream surface, and a plurality of fuel channels extend through described downstream surface.
20. burner according to claim 19 is characterized in that, described downstream surface comprises fuel nozzle tip thereon, location, and one or more most advanced and sophisticated outlets extend through described fuel nozzle tip.
Applications Claiming Priority (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| US13/355,580 | 2012-01-23 | ||
| US13/355,580 US20130189632A1 (en) | 2012-01-23 | 2012-01-23 | Fuel nozzel |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN103216849A true CN103216849A (en) | 2013-07-24 |
Family
ID=47563290
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN2013100231995A Pending CN103216849A (en) | 2012-01-23 | 2013-01-22 | Fuel nozzle |
Country Status (5)
| Country | Link |
|---|---|
| US (1) | US20130189632A1 (en) |
| EP (1) | EP2618052A1 (en) |
| JP (1) | JP2013148341A (en) |
| CN (1) | CN103216849A (en) |
| RU (1) | RU2013102632A (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107166435A (en) * | 2017-07-07 | 2017-09-15 | 西安富兰克石油技术有限公司 | A kind of multi fuel nozzle, fuel spray system and its turbogenerator |
| CN108626746A (en) * | 2017-03-15 | 2018-10-09 | 通用电气公司 | Fuel nozzle for gas-turbine unit |
Families Citing this family (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP2940389A1 (en) * | 2014-05-02 | 2015-11-04 | Siemens Aktiengesellschaft | Combustor burner arrangement |
| US9803552B2 (en) | 2015-10-30 | 2017-10-31 | General Electric Company | Turbine engine fuel injection system and methods of assembling the same |
| US11680709B2 (en) * | 2020-10-26 | 2023-06-20 | Solar Turbines Incorporated | Flashback resistant premixed fuel injector for a gas turbine engine |
Family Cites Families (35)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4155220A (en) * | 1977-01-21 | 1979-05-22 | Westinghouse Electric Corp. | Combustion apparatus for a gas turbine engine |
| JPS57187531A (en) * | 1981-05-12 | 1982-11-18 | Hitachi Ltd | Low nox gas turbine burner |
| US5193346A (en) * | 1986-11-25 | 1993-03-16 | General Electric Company | Premixed secondary fuel nozzle with integral swirler |
| US5345768A (en) * | 1993-04-07 | 1994-09-13 | General Electric Company | Dual-fuel pre-mixing burner assembly |
| GB2332509B (en) * | 1997-12-19 | 2002-06-19 | Europ Gas Turbines Ltd | Fuel/air mixing arrangement for combustion apparatus |
| EP0935097B1 (en) * | 1998-02-09 | 2004-09-01 | Mitsubishi Heavy Industries, Ltd. | Combustor |
| US6082113A (en) * | 1998-05-22 | 2000-07-04 | Pratt & Whitney Canada Corp. | Gas turbine fuel injector |
| US6547163B1 (en) * | 1999-10-01 | 2003-04-15 | Parker-Hannifin Corporation | Hybrid atomizing fuel nozzle |
| GB2373043B (en) * | 2001-03-09 | 2004-09-22 | Alstom Power Nv | Fuel injector |
| US6655145B2 (en) * | 2001-12-20 | 2003-12-02 | Solar Turbings Inc | Fuel nozzle for a gas turbine engine |
| US7000403B2 (en) * | 2004-03-12 | 2006-02-21 | Power Systems Mfg., Llc | Primary fuel nozzle having dual fuel capability |
| US7251940B2 (en) * | 2004-04-30 | 2007-08-07 | United Technologies Corporation | Air assist fuel injector for a combustor |
| JP4070758B2 (en) * | 2004-09-10 | 2008-04-02 | 三菱重工業株式会社 | Gas turbine combustor |
| US7237730B2 (en) * | 2005-03-17 | 2007-07-03 | Pratt & Whitney Canada Corp. | Modular fuel nozzle and method of making |
| 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 |
| FR2903169B1 (en) * | 2006-06-29 | 2011-11-11 | Snecma | DEVICE FOR INJECTING A MIXTURE OF AIR AND FUEL, COMBUSTION CHAMBER AND TURBOMACHINE HAVING SUCH A DEVICE |
| US8276836B2 (en) * | 2007-07-27 | 2012-10-02 | General Electric Company | Fuel nozzle assemblies and methods |
| US20090111063A1 (en) * | 2007-10-29 | 2009-04-30 | General Electric Company | Lean premixed, radial inflow, multi-annular staged nozzle, can-annular, dual-fuel combustor |
| US8113000B2 (en) * | 2008-09-15 | 2012-02-14 | Siemens Energy, Inc. | Flashback resistant pre-mixer assembly |
| US8186165B2 (en) * | 2009-03-16 | 2012-05-29 | General Electric Company | Turbine fuel nozzle having heat control |
| US8256226B2 (en) * | 2009-04-23 | 2012-09-04 | General Electric Company | Radial lean direct injection burner |
| US20100281869A1 (en) * | 2009-05-06 | 2010-11-11 | Mark Allan Hadley | Airblown Syngas Fuel Nozzle With Diluent Openings |
| US8607570B2 (en) * | 2009-05-06 | 2013-12-17 | General Electric Company | Airblown syngas fuel nozzle with diluent openings |
| US8359870B2 (en) * | 2009-05-12 | 2013-01-29 | General Electric Company | Automatic fuel nozzle flame-holding quench |
| US20110005189A1 (en) * | 2009-07-08 | 2011-01-13 | General Electric Company | Active Control of Flame Holding and Flashback in Turbine Combustor Fuel Nozzle |
| US20110107769A1 (en) * | 2009-11-09 | 2011-05-12 | General Electric Company | Impingement insert for a turbomachine injector |
| US20110225973A1 (en) * | 2010-03-18 | 2011-09-22 | General Electric Company | Combustor with Pre-Mixing Primary Fuel-Nozzle Assembly |
| US8959921B2 (en) * | 2010-07-13 | 2015-02-24 | General Electric Company | Flame tolerant secondary fuel nozzle |
| US8418469B2 (en) * | 2010-09-27 | 2013-04-16 | General Electric Company | Fuel nozzle assembly for gas turbine system |
| US8579211B2 (en) * | 2011-01-06 | 2013-11-12 | General Electric Company | System and method for enhancing flow in a nozzle |
| US20120208136A1 (en) * | 2011-02-11 | 2012-08-16 | General Electric Company | System and method for operating a combustor |
| US20120208135A1 (en) * | 2011-02-11 | 2012-08-16 | General Electric Company | System and method for operating a combustor |
| US20120208137A1 (en) * | 2011-02-11 | 2012-08-16 | General Electric Company | System and method for operating a combustor |
| US9371989B2 (en) * | 2011-05-18 | 2016-06-21 | General Electric Company | Combustor nozzle and method for supplying fuel to a combustor |
| US8978384B2 (en) * | 2011-11-23 | 2015-03-17 | General Electric Company | Swirler assembly with compressor discharge injection to vane surface |
-
2012
- 2012-01-23 US US13/355,580 patent/US20130189632A1/en not_active Abandoned
-
2013
- 2013-01-17 JP JP2013005861A patent/JP2013148341A/en active Pending
- 2013-01-21 EP EP20130152025 patent/EP2618052A1/en not_active Withdrawn
- 2013-01-22 CN CN2013100231995A patent/CN103216849A/en active Pending
- 2013-01-22 RU RU2013102632/06A patent/RU2013102632A/en not_active Application Discontinuation
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108626746A (en) * | 2017-03-15 | 2018-10-09 | 通用电气公司 | Fuel nozzle for gas-turbine unit |
| CN107166435A (en) * | 2017-07-07 | 2017-09-15 | 西安富兰克石油技术有限公司 | A kind of multi fuel nozzle, fuel spray system and its turbogenerator |
Also Published As
| Publication number | Publication date |
|---|---|
| JP2013148341A (en) | 2013-08-01 |
| RU2013102632A (en) | 2014-07-27 |
| EP2618052A1 (en) | 2013-07-24 |
| US20130189632A1 (en) | 2013-07-25 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN103375816B (en) | For supplying fuel to the system of burner | |
| JP6188127B2 (en) | Transition duct with late injection in turbine system | |
| CN103388837B (en) | For the system by working fluid supply to burner | |
| US10309653B2 (en) | Bundled tube fuel nozzle with internal cooling | |
| CN103363549B (en) | A kind of burner and the method being used for supplying fuel to burner | |
| US8677760B2 (en) | Fuel nozzle with integrated passages and method of operation | |
| CN103216849A (en) | Fuel nozzle | |
| CN103256629A (en) | Combustor and method for supplying fuel to a combustor | |
| CN204026742U (en) | For supplying fuel to the system of burner | |
| JP2014088874A (en) | Combustor cap assembly | |
| CA2668219A1 (en) | Turbomachine injection nozzle including a coolant delivery system | |
| JP2016098830A (en) | Premix fuel nozzle assembly | |
| CN102777932A (en) | A combustor nozzle and method for supplying fuel to a combustor | |
| US20180051883A1 (en) | Pre-mixing based fuel nozzle for use in a combustion turbine engine | |
| JP2014119250A (en) | Systems and methods for late lean injection premixing | |
| CN102721084B (en) | Burner flame tube interconnector | |
| JP2013145109A (en) | System and method for supplying working fluid to combustor | |
| JP6220223B2 (en) | Micro mixer nozzle | |
| CN102692036A (en) | Combustor with fuel nozzle liner having chevron ribs | |
| CN103075747A (en) | Fuel injection assembly for use in turbine engines and method of assembling same | |
| EP2647910A2 (en) | Diffusion combustor fuel nozzle | |
| US20140260302A1 (en) | DIFFUSION COMBUSTOR FUEL NOZZLE FOR LIMITING NOx EMISSIONS | |
| JP2010085088A (en) | Off center combustor liner | |
| US8448442B2 (en) | Flexible combustor fuel nozzle | |
| JP2018091604A (en) | Fuel supply system for turbine engines and methods of assembling the same |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C06 | Publication | ||
| PB01 | Publication | ||
| C10 | Entry into substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| C02 | Deemed withdrawal of patent application after publication (patent law 2001) | ||
| WD01 | Invention patent application deemed withdrawn after publication |
Application publication date: 20130724 |