JP5544141B2 - ガスタービンにおける統合型燃焼器−第1段ノズル並びに関連する方法 - Google Patents
ガスタービンにおける統合型燃焼器−第1段ノズル並びに関連する方法 Download PDFInfo
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- JP5544141B2 JP5544141B2 JP2009251575A JP2009251575A JP5544141B2 JP 5544141 B2 JP5544141 B2 JP 5544141B2 JP 2009251575 A JP2009251575 A JP 2009251575A JP 2009251575 A JP2009251575 A JP 2009251575A JP 5544141 B2 JP5544141 B2 JP 5544141B2
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- stage
- fuel
- stage nozzle
- nozzle
- transition piece
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- 238000000034 method Methods 0.000 title claims description 6
- 239000000446 fuel Substances 0.000 claims description 39
- 230000007704 transition Effects 0.000 claims description 32
- 238000002485 combustion reaction Methods 0.000 claims description 22
- 239000007789 gas Substances 0.000 claims description 16
- 239000000567 combustion gas Substances 0.000 claims description 12
- 230000020169 heat generation Effects 0.000 claims description 8
- 238000004904 shortening Methods 0.000 claims description 3
- 230000008901 benefit Effects 0.000 claims description 2
- 238000002347 injection Methods 0.000 claims 1
- 239000007924 injection Substances 0.000 claims 1
- 239000012141 concentrate Substances 0.000 description 4
- 230000009467 reduction Effects 0.000 description 2
- 230000002411 adverse Effects 0.000 description 1
- 238000009826 distribution Methods 0.000 description 1
- 238000004519 manufacturing process Methods 0.000 description 1
- 239000000203 mixture Substances 0.000 description 1
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Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D9/00—Stators
- F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
- F01D9/023—Transition ducts between combustor cans and first stage of the turbine in gas-turbine engines; their cooling or sealings
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D9/00—Stators
- F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
- F01D9/04—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector
- F01D9/041—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector using blades
-
- 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
- F23R3/002—Wall structures
-
- 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
- F23R3/46—Combustion chambers comprising an annular arrangement of several essentially tubular flame tubes within a common annular casing or within individual casings
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/60—Efficient propulsion technologies, e.g. for aircraft
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
- Gas Burners (AREA)
Description
12 ライナ
14 トランジションピース
20 統合型燃焼器/S1ノズル
22 燃焼チャンバ
24 燃料ノズル群
26 燃焼ライナ
28 トランジションピース
29 第1段ノズル
30 小型混合装置
32 第2段階燃料噴射器
34 チョーク端部
36 延長シュラウド
Claims (9)
- ガスタービンにおける統合型燃焼器−第1段ノズルであって、
個別軸方向位置において少なくとも1つの燃料ノズル群(24)から予混合燃料−空気を受ける燃焼チャンバ(22)、を含み、
前記燃焼チャンバが、高温燃焼ガスをタービンに送給するライナ(26)及びトランジションピース(28)を含み、
前記第1段ノズル(29)、ライナ(26)及びトランジションピース(28)が、単一部品に統合され、
前記1以上の燃料ノズル群の軸方向位置の少なくとも1つが、熱発生を集中させかつ火炎長さを短縮させる複数の小型混合装置(30)を含み、
前記混合装置(30)が、複数の軸方向位置におけるアレイの形態で配置される、
統合型燃焼器−第1段ノズル。 - 前記小型混合装置(30)が、単一平面又は複数の軸方向位置内に配置されかつ各軸方向位置についての燃料制御装置を含む、請求項1記載の統合型燃焼器−第1段ノズル。
- 統合型燃焼器−第1段ノズルが、前記少なくとも1つの燃料ノズル群と共に作動可能である少なくとも1つの第1段階燃料噴射器と、前記トランジションピース(28)内に配置された第2段階燃料噴射器(32)とをさらに含み、前記燃料制御装置が、前記少なくとも1つの第1段階燃料噴射器及び第2段階燃料噴射器間で燃料流量を制御可能に分割する燃料回路を含む、請求項2記載の統合型燃焼器−第1段ノズル。
- 前記混合装置(30)が、ライナ直径の1/10〜1/100の長さスケールを有する、請求項1乃至3のいずれかに記載の統合型燃焼器−第1段ノズル。
- 前記混合装置(30)が、単一平面内におけるアレイの形態で配置される、請求項1乃至4のいずれかに記載の統合型燃焼器−第1段ノズル。
- 前記ガスタービンが、前記単一部品に隣接して配置された第1段タービンバケットを含み、前記トランジションピースが、前記第1段タービンバケットに向けて好適な角度で前記高温燃焼ガスの流れを導くチョーク端部(34)を含む、請求項1乃至5のいずれかに記載の統合型燃焼器−第1段ノズル。
- 前記トランジションピースのチョーク端部(34)が、前記第1段ノズルとしての働きをする、請求項6記載の統合型燃焼器−第1段ノズル。
- 前記ガスタービンが、前記単一部品に隣接して配置された第1段タービンバケットを含み、前記トランジションピースが、前記第1段ノズルを囲んで配置された延長シュラウド(36)を含み、前記延長シュラウド及び第1段ノズルが、前記第1段タービンバケットに向けて好適な角度で前記高温燃焼ガスの流れを導く、請求項1乃至7のいずれかに記載の統合型燃焼器−第1段ノズル。
- ガスタービンにおいて燃焼器及び第1段ノズルを統合する方法であって、
高温燃焼ガスをタービンに送給するライナ(26)及びトランジションピース(28)を含む燃焼チャンバ(22)を、個別軸方向位置において少なくとも1つの燃料ノズル群(24)から予混合燃料−空気を受けるように配置するステップと、
前記1以上の燃料ノズル群の軸方向位置の少なくとも1つに、熱発生を集中させかつ火炎長さを短縮させる複数の小型混合装置(30)を設けるステップと、
前記火炎長さの短縮の利点を生かして、前記第1段ノズル、ライナ及びトランジションピースを単一部品に統合するステップと
を含み、
前記混合装置(30)が、複数の軸方向位置におけるアレイの形態で配置される、
方法。
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US12/269,411 | 2008-11-12 | ||
US12/269,411 US9822649B2 (en) | 2008-11-12 | 2008-11-12 | Integrated combustor and stage 1 nozzle in a gas turbine and method |
Publications (2)
Publication Number | Publication Date |
---|---|
JP2010117124A JP2010117124A (ja) | 2010-05-27 |
JP5544141B2 true JP5544141B2 (ja) | 2014-07-09 |
Family
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Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
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JP2009251575A Active JP5544141B2 (ja) | 2008-11-12 | 2009-11-02 | ガスタービンにおける統合型燃焼器−第1段ノズル並びに関連する方法 |
Country Status (4)
Country | Link |
---|---|
US (1) | US9822649B2 (ja) |
JP (1) | JP5544141B2 (ja) |
CN (1) | CN101737801B (ja) |
DE (1) | DE102009044513B4 (ja) |
Families Citing this family (59)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
JP5180807B2 (ja) | 2008-12-24 | 2013-04-10 | 三菱重工業株式会社 | 1段静翼の冷却構造、及びガスタービン |
US8701383B2 (en) * | 2009-01-07 | 2014-04-22 | General Electric Company | Late lean injection system configuration |
US8112216B2 (en) | 2009-01-07 | 2012-02-07 | General Electric Company | Late lean injection with adjustable air splits |
US8683808B2 (en) * | 2009-01-07 | 2014-04-01 | General Electric Company | Late lean injection control strategy |
US8707707B2 (en) * | 2009-01-07 | 2014-04-29 | General Electric Company | Late lean injection fuel staging configurations |
US8701382B2 (en) * | 2009-01-07 | 2014-04-22 | General Electric Company | Late lean injection with expanded fuel flexibility |
US8701418B2 (en) * | 2009-01-07 | 2014-04-22 | General Electric Company | Late lean injection for fuel flexibility |
JP5479058B2 (ja) * | 2009-12-07 | 2014-04-23 | 三菱重工業株式会社 | 燃焼器とタービン部との連通構造、および、ガスタービン |
US8978388B2 (en) | 2011-06-03 | 2015-03-17 | General Electric Company | Load member for transition duct in turbine system |
US8966910B2 (en) * | 2011-06-21 | 2015-03-03 | General Electric Company | Methods and systems for cooling a transition nozzle |
US8915087B2 (en) * | 2011-06-21 | 2014-12-23 | General Electric Company | Methods and systems for transferring heat from a transition nozzle |
US20120324898A1 (en) * | 2011-06-21 | 2012-12-27 | Mcmahan Kevin Weston | Combustor assembly for use in a turbine engine and methods of assembling same |
US8650852B2 (en) * | 2011-07-05 | 2014-02-18 | General Electric Company | Support assembly for transition duct in turbine system |
US8448450B2 (en) * | 2011-07-05 | 2013-05-28 | General Electric Company | Support assembly for transition duct in turbine system |
JP5848074B2 (ja) * | 2011-09-16 | 2016-01-27 | 三菱日立パワーシステムズ株式会社 | ガスタービン、尾筒及び燃焼器 |
US9388738B2 (en) * | 2011-10-04 | 2016-07-12 | Siemens Energy, Inc. | Casing for a gas turbine engine |
US9328623B2 (en) * | 2011-10-05 | 2016-05-03 | General Electric Company | Turbine system |
US8915706B2 (en) * | 2011-10-18 | 2014-12-23 | General Electric Company | Transition nozzle |
US8701415B2 (en) | 2011-11-09 | 2014-04-22 | General Electric Company | Flexible metallic seal for transition duct in turbine system |
US8974179B2 (en) | 2011-11-09 | 2015-03-10 | General Electric Company | Convolution seal for transition duct in turbine system |
US8459041B2 (en) | 2011-11-09 | 2013-06-11 | General Electric Company | Leaf seal for transition duct in turbine system |
US9145778B2 (en) * | 2012-04-03 | 2015-09-29 | General Electric Company | Combustor with non-circular head end |
US9506359B2 (en) * | 2012-04-03 | 2016-11-29 | General Electric Company | Transition nozzle combustion system |
FR2989426B1 (fr) * | 2012-04-11 | 2014-03-28 | Snecma | Turbomachine, telle qu'un turboreacteur ou un turbopropulseur d'avion |
US20130283802A1 (en) * | 2012-04-27 | 2013-10-31 | General Electric Company | Combustor |
US9038394B2 (en) | 2012-04-30 | 2015-05-26 | General Electric Company | Convolution seal for transition duct in turbine system |
US9133722B2 (en) * | 2012-04-30 | 2015-09-15 | General Electric Company | Transition duct with late injection in turbine system |
US20130318986A1 (en) * | 2012-06-05 | 2013-12-05 | General Electric Company | Impingement cooled combustor |
US9127554B2 (en) * | 2012-09-04 | 2015-09-08 | Siemens Energy, Inc. | Gas turbine engine with radial diffuser and shortened mid section |
EP2725197A1 (en) * | 2012-10-24 | 2014-04-30 | Alstom Technology Ltd | Combustor transition |
EP2725196A1 (en) * | 2012-10-24 | 2014-04-30 | Alstom Technology Ltd | Combustor transition |
US20140127008A1 (en) * | 2012-11-08 | 2014-05-08 | General Electric Company | Transition duct having airfoil and hot gas path assembly for turbomachine |
US9551492B2 (en) * | 2012-11-30 | 2017-01-24 | General Electric Company | Gas turbine engine system and an associated method thereof |
US8707673B1 (en) * | 2013-01-04 | 2014-04-29 | General Electric Company | Articulated transition duct in turbomachine |
US9435541B2 (en) | 2013-03-15 | 2016-09-06 | General Electric Company | Systems and apparatus relating to downstream fuel and air injection in gas turbines |
US9528439B2 (en) | 2013-03-15 | 2016-12-27 | General Electric Company | Systems and apparatus relating to downstream fuel and air injection in gas turbines |
US9482434B2 (en) | 2013-03-15 | 2016-11-01 | General Electric Company | Methods relating to downstream fuel and air injection in gas turbines |
US9714768B2 (en) | 2013-03-15 | 2017-07-25 | General Electric Company | Systems and apparatus relating to downstream fuel and air injection in gas turbines |
US9080447B2 (en) | 2013-03-21 | 2015-07-14 | General Electric Company | Transition duct with divided upstream and downstream portions |
US9458732B2 (en) | 2013-10-25 | 2016-10-04 | General Electric Company | Transition duct assembly with modified trailing edge in turbine system |
US9528706B2 (en) * | 2013-12-13 | 2016-12-27 | Siemens Energy, Inc. | Swirling midframe flow for gas turbine engine having advanced transitions |
US9593853B2 (en) | 2014-02-20 | 2017-03-14 | Siemens Energy, Inc. | Gas flow path for a gas turbine engine |
US20150323185A1 (en) | 2014-05-07 | 2015-11-12 | General Electric Compamy | Turbine engine and method of assembling thereof |
US10024180B2 (en) * | 2014-11-20 | 2018-07-17 | Siemens Energy, Inc. | Transition duct arrangement in a gas turbine engine |
US10072846B2 (en) * | 2015-07-06 | 2018-09-11 | General Electric Company | Trapped vortex cavity staging in a combustor |
EP3124749B1 (en) * | 2015-07-28 | 2018-12-19 | Ansaldo Energia Switzerland AG | First stage turbine vane arrangement |
US10145251B2 (en) | 2016-03-24 | 2018-12-04 | General Electric Company | Transition duct assembly |
US10260752B2 (en) | 2016-03-24 | 2019-04-16 | General Electric Company | Transition duct assembly with late injection features |
US10260360B2 (en) | 2016-03-24 | 2019-04-16 | General Electric Company | Transition duct assembly |
US10260424B2 (en) | 2016-03-24 | 2019-04-16 | General Electric Company | Transition duct assembly with late injection features |
US10227883B2 (en) | 2016-03-24 | 2019-03-12 | General Electric Company | Transition duct assembly |
US10393381B2 (en) * | 2017-01-27 | 2019-08-27 | General Electric Company | Unitary flow path structure |
US10823418B2 (en) | 2017-03-02 | 2020-11-03 | General Electric Company | Gas turbine engine combustor comprising air inlet tubes arranged around the combustor |
US10837299B2 (en) | 2017-03-07 | 2020-11-17 | General Electric Company | System and method for transition piece seal |
JP6871377B2 (ja) * | 2017-06-29 | 2021-05-12 | 三菱パワー株式会社 | ガスタービンの1段静翼、ガスタービン、ガスタービンの静翼ユニット及び燃焼器アセンブリ |
US11181005B2 (en) | 2018-05-18 | 2021-11-23 | Raytheon Technologies Corporation | Gas turbine engine assembly with mid-vane outer platform gap |
US11480337B2 (en) | 2019-11-26 | 2022-10-25 | Collins Engine Nozzles, Inc. | Fuel injection for integral combustor and turbine vane |
CN114838386B (zh) * | 2022-04-20 | 2023-06-23 | 中国航发沈阳发动机研究所 | 一种用于低污染燃烧室的气体燃料喷嘴 |
CN116202104B (zh) * | 2023-02-06 | 2024-05-07 | 中国科学院工程热物理研究所 | 一种燃气轮机多喷嘴阵列增稳燃烧室 |
Family Cites Families (42)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US3018624A (en) | 1954-03-02 | 1962-01-30 | Bristol Siddeley Engines Ltd | Flame tubes for use in combustion systems of gas turbine engines |
US4023919A (en) * | 1974-12-19 | 1977-05-17 | General Electric Company | Thermal actuated valve for clearance control |
US4409787A (en) | 1979-04-30 | 1983-10-18 | General Electric Company | Acoustically tuned combustor |
US4445339A (en) | 1980-11-24 | 1984-05-01 | General Electric Co. | Wingtip vortex flame stabilizer for gas turbine combustor flame holder |
US4432207A (en) | 1981-08-06 | 1984-02-21 | General Electric Company | Modular catalytic combustion bed support system |
US4719748A (en) | 1985-05-14 | 1988-01-19 | General Electric Company | Impingement cooled transition duct |
US4928481A (en) * | 1988-07-13 | 1990-05-29 | Prutech Ii | Staged low NOx premix gas turbine combustor |
US5000004A (en) * | 1988-08-16 | 1991-03-19 | Kabushiki Kaisha Toshiba | Gas turbine combustor |
US5749219A (en) * | 1989-11-30 | 1998-05-12 | United Technologies Corporation | Combustor with first and second zones |
US5203796A (en) | 1990-08-28 | 1993-04-20 | General Electric Company | Two stage v-gutter fuel injection mixer |
US5289677A (en) * | 1992-12-16 | 1994-03-01 | United Technologies Corporation | Combined support and seal ring for a combustor |
US5491970A (en) | 1994-06-10 | 1996-02-20 | General Electric Co. | Method for staging fuel in a turbine between diffusion and premixed operations |
US5749701A (en) | 1996-10-28 | 1998-05-12 | General Electric Company | Interstage seal assembly for a turbine |
DE19651881A1 (de) | 1996-12-13 | 1998-06-18 | Asea Brown Boveri | Brennkammer mit integrierten Leitschaufeln |
US6089025A (en) | 1998-08-24 | 2000-07-18 | General Electric Company | Combustor baffle |
US6250063B1 (en) | 1999-08-19 | 2001-06-26 | General Electric Co. | Fuel staging apparatus and methods for gas turbine nozzles |
FI112681B (fi) * | 1999-08-24 | 2003-12-31 | Metso Paper Inc | Menetelmä ja sovitelma paperi- ja/tai kartonkirainan pintakäsittelyä varten |
US6220815B1 (en) | 1999-12-17 | 2001-04-24 | General Electric Company | Inter-stage seal retainer and assembly |
US6415608B1 (en) * | 2000-09-26 | 2002-07-09 | Siemens Westinghouse Power Corporation | Piloted rich-catalytic lean-burn hybrid combustor |
US6633623B2 (en) | 2000-11-29 | 2003-10-14 | General Electric Company | Apparatus and methods for protecting a jet pump nozzle assembly and inlet-mixer |
US6928823B2 (en) * | 2001-08-29 | 2005-08-16 | Hitachi, Ltd. | Gas turbine combustor and operating method thereof |
US6813889B2 (en) | 2001-08-29 | 2004-11-09 | Hitachi, Ltd. | Gas turbine combustor and operating method thereof |
EP1288441A1 (de) | 2001-09-03 | 2003-03-05 | Siemens Aktiengesellschaft | Übergangsabschnitt einer Gasturbinenbrennkammer |
US6680549B2 (en) | 2001-11-01 | 2004-01-20 | General Electric Company | Tapered rotor-stator air gap for superconducting synchronous machine |
US6840048B2 (en) * | 2002-09-26 | 2005-01-11 | General Electric Company | Dynamically uncoupled can combustor |
US6882068B2 (en) | 2002-10-08 | 2005-04-19 | General Electric Company | Forced air stator ventilation system and stator ventilation method for superconducting synchronous machine |
US6796130B2 (en) | 2002-11-07 | 2004-09-28 | Siemens Westinghouse Power Corporation | Integrated combustor and nozzle for a gas turbine combustion system |
US7185494B2 (en) | 2004-04-12 | 2007-03-06 | General Electric Company | Reduced center burner in multi-burner combustor and method for operating the combustor |
US7337057B2 (en) | 2004-05-28 | 2008-02-26 | General Electric Company | Methods and apparatus for predicting and/or for avoiding lean blow-outs |
US6979118B1 (en) | 2004-06-01 | 2005-12-27 | General Electric Company | Estimating combustor flame temperature based on frequency of combustor dynamics transverse mode |
US6993916B2 (en) | 2004-06-08 | 2006-02-07 | General Electric Company | Burner tube and method for mixing air and gas in a gas turbine engine |
US7278266B2 (en) | 2004-08-31 | 2007-10-09 | General Electric Company | Methods and apparatus for gas turbine engine lean blowout avoidance |
US7210297B2 (en) | 2004-11-04 | 2007-05-01 | General Electric Company | Method and apparatus for identification of hot and cold chambers in a gas turbine combustor |
US7082766B1 (en) | 2005-03-02 | 2006-08-01 | General Electric Company | One-piece can combustor |
US7441398B2 (en) | 2005-05-20 | 2008-10-28 | General Electric Company | NOx adjustment system for gas turbine combustors |
US7490471B2 (en) | 2005-12-08 | 2009-02-17 | General Electric Company | Swirler assembly |
EP1903184B1 (en) | 2006-09-21 | 2019-05-01 | Siemens Energy, Inc. | Combustion turbine subsystem with twisted transition duct |
GB2445565A (en) | 2006-09-26 | 2008-07-16 | Siemens Ag | Gas turbine engine having a plurality of modules comprising a combustor and transition duct |
JP5023687B2 (ja) | 2006-12-20 | 2012-09-12 | 株式会社Ihi | 燃焼器及びガスタービン |
US7886545B2 (en) | 2007-04-27 | 2011-02-15 | General Electric Company | Methods and systems to facilitate reducing NOx emissions in combustion systems |
US7665309B2 (en) * | 2007-09-14 | 2010-02-23 | Siemens Energy, Inc. | Secondary fuel delivery system |
CN101285591B (zh) | 2008-04-22 | 2010-06-09 | 北京航空航天大学 | 一种一体化燃油喷射径向旋流器预混预蒸发低污染燃烧室 |
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US20100115953A1 (en) | 2010-05-13 |
CN101737801B (zh) | 2014-12-10 |
US9822649B2 (en) | 2017-11-21 |
DE102009044513A1 (de) | 2010-05-20 |
JP2010117124A (ja) | 2010-05-27 |
CN101737801A (zh) | 2010-06-16 |
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