CN103375262B - 涡轮机系统中具有延迟喷射的过渡管道 - Google Patents
涡轮机系统中具有延迟喷射的过渡管道 Download PDFInfo
- Publication number
- CN103375262B CN103375262B CN201310064353.3A CN201310064353A CN103375262B CN 103375262 B CN103375262 B CN 103375262B CN 201310064353 A CN201310064353 A CN 201310064353A CN 103375262 B CN103375262 B CN 103375262B
- Authority
- CN
- China
- Prior art keywords
- transition conduit
- pipeline
- transition
- outlet
- fuel
- 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.)
- Active
Links
- 230000007704 transition Effects 0.000 title claims abstract description 136
- 238000002347 injection Methods 0.000 title abstract description 19
- 239000007924 injection Substances 0.000 title abstract description 19
- 230000003111 delayed effect Effects 0.000 title abstract description 5
- 239000012530 fluid Substances 0.000 claims abstract description 64
- 238000002485 combustion reaction Methods 0.000 claims abstract description 27
- 239000000446 fuel Substances 0.000 claims description 53
- 238000004891 communication Methods 0.000 claims description 16
- 238000011144 upstream manufacturing Methods 0.000 claims description 4
- 230000037361 pathway Effects 0.000 abstract 1
- 239000007789 gas Substances 0.000 description 31
- 239000000567 combustion gas Substances 0.000 description 12
- 238000013461 design Methods 0.000 description 5
- 238000010586 diagram Methods 0.000 description 3
- 238000004519 manufacturing process Methods 0.000 description 3
- 239000000203 mixture Substances 0.000 description 3
- MWUXSHHQAYIFBG-UHFFFAOYSA-N nitrogen oxide Inorganic materials O=[N] MWUXSHHQAYIFBG-UHFFFAOYSA-N 0.000 description 3
- 238000003491 array Methods 0.000 description 2
- 230000008030 elimination Effects 0.000 description 2
- 238000003379 elimination reaction Methods 0.000 description 2
- VNWKTOKETHGBQD-UHFFFAOYSA-N methane Chemical compound C VNWKTOKETHGBQD-UHFFFAOYSA-N 0.000 description 2
- 238000000034 method Methods 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
- 230000004048 modification Effects 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
- 229910002091 carbon monoxide Inorganic materials 0.000 description 1
- 238000006243 chemical reaction Methods 0.000 description 1
- 238000001816 cooling Methods 0.000 description 1
- 238000010494 dissociation reaction Methods 0.000 description 1
- 230000005593 dissociations Effects 0.000 description 1
- 230000005611 electricity Effects 0.000 description 1
- 238000004146 energy storage Methods 0.000 description 1
- 229930195733 hydrocarbon Natural products 0.000 description 1
- 150000002430 hydrocarbons Chemical class 0.000 description 1
- 239000007788 liquid Substances 0.000 description 1
- 239000003345 natural gas Substances 0.000 description 1
- 239000007800 oxidant agent Substances 0.000 description 1
- 238000010248 power generation Methods 0.000 description 1
- 238000011084 recovery Methods 0.000 description 1
- 238000011160 research Methods 0.000 description 1
- 239000007921 spray Substances 0.000 description 1
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
- 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
- F23R3/06—Arrangement of apertures along the flame tube
-
- 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
- F23R3/28—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
- F23R3/34—Feeding into different combustion zones
- F23R3/346—Feeding into different combustion zones for staged combustion
-
- 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
-
- 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
- F23R2900/00—Special features of, or arrangements for continuous combustion chambers; Combustion processes therefor
- F23R2900/03044—Impingement cooled combustion chamber walls or subassemblies
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)
Applications Claiming Priority (3)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| US13/459,516 US9133722B2 (en) | 2012-04-30 | 2012-04-30 | Transition duct with late injection in turbine system |
| US13/459516 | 2012-04-30 | ||
| US13/459,516 | 2012-04-30 |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN103375262A CN103375262A (zh) | 2013-10-30 |
| CN103375262B true CN103375262B (zh) | 2016-12-07 |
Family
ID=47843080
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201310064353.3A Active CN103375262B (zh) | 2012-04-30 | 2013-02-28 | 涡轮机系统中具有延迟喷射的过渡管道 |
Country Status (5)
| Country | Link |
|---|---|
| US (1) | US9133722B2 (enExample) |
| EP (1) | EP2660519B1 (enExample) |
| JP (1) | JP6188127B2 (enExample) |
| CN (1) | CN103375262B (enExample) |
| RU (1) | RU2013108686A (enExample) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110476017A (zh) * | 2017-02-24 | 2019-11-19 | 通用电气公司 | 具有轴向分级燃料喷射的燃烧系统 |
Families Citing this family (21)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US9551492B2 (en) * | 2012-11-30 | 2017-01-24 | General Electric Company | Gas turbine engine system and an associated method thereof |
| US9593853B2 (en) * | 2014-02-20 | 2017-03-14 | Siemens Energy, Inc. | Gas flow path for a gas turbine engine |
| CN106460532A (zh) * | 2014-06-17 | 2017-02-22 | 西门子能源公司 | 燃气涡轮发动机中的具有在相邻收敛过渡管道之间的交接部处的接合部的过渡管道系统 |
| WO2015199693A1 (en) * | 2014-06-26 | 2015-12-30 | Siemens Energy, Inc. | Converging flow joint insert system at an intersection between adjacent transition duct bodljs |
| US9771813B2 (en) | 2014-06-26 | 2017-09-26 | Siemens Energy, Inc. | Converging flow joint insert system at an intersection between adjacent transitions extending between a combustor and a turbine assembly in a gas turbine engine |
| EP3015770B1 (en) * | 2014-11-03 | 2020-07-01 | Ansaldo Energia Switzerland AG | Can combustion chamber |
| US20160265782A1 (en) * | 2015-03-10 | 2016-09-15 | General Electric Company | Air shield for a fuel injector of a combustor |
| EP3325887A1 (en) * | 2015-07-24 | 2018-05-30 | Siemens Aktiengesellschaft | Gas turbine transition duct with late lean injection having reduced combustion residence time |
| EP3289185A1 (en) * | 2015-08-06 | 2018-03-07 | Siemens Aktiengesellschaft | Transition ducts of a gas turbine combustor |
| JP6625427B2 (ja) * | 2015-12-25 | 2019-12-25 | 川崎重工業株式会社 | ガスタービンエンジン |
| US9810434B2 (en) * | 2016-01-21 | 2017-11-07 | Siemens Energy, Inc. | Transition duct system with arcuate ceramic liner for delivering hot-temperature gases in a combustion turbine engine |
| US10227883B2 (en) | 2016-03-24 | 2019-03-12 | General Electric Company | Transition duct assembly |
| US10145251B2 (en) | 2016-03-24 | 2018-12-04 | General Electric Company | Transition duct assembly |
| US10260360B2 (en) * | 2016-03-24 | 2019-04-16 | General Electric Company | Transition duct assembly |
| US10260752B2 (en) * | 2016-03-24 | 2019-04-16 | General Electric Company | Transition duct assembly with late injection features |
| US10260424B2 (en) * | 2016-03-24 | 2019-04-16 | General Electric Company | Transition duct assembly with late injection features |
| US10415831B2 (en) | 2016-10-27 | 2019-09-17 | General Electric Company | Combustor assembly with mounted auxiliary component |
| US10823418B2 (en) * | 2017-03-02 | 2020-11-03 | General Electric Company | Gas turbine engine combustor comprising air inlet tubes arranged around the combustor |
| US11137144B2 (en) | 2017-12-11 | 2021-10-05 | General Electric Company | Axial fuel staging system for gas turbine combustors |
| US10816203B2 (en) * | 2017-12-11 | 2020-10-27 | General Electric Company | Thimble assemblies for introducing a cross-flow into a secondary combustion zone |
| FR3101670B1 (fr) * | 2019-10-08 | 2021-10-08 | Safran Aircraft Engines | Injecteur pour une turbine haute pression |
Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3652181A (en) * | 1970-11-23 | 1972-03-28 | Carl F Wilhelm Jr | Cooling sleeve for gas turbine combustor transition member |
| CN101017000A (zh) * | 2006-02-08 | 2007-08-15 | 斯奈克玛 | 带有切向槽的涡轮发动机燃烧室 |
| CN102252345A (zh) * | 2010-04-27 | 2011-11-23 | 通用电气公司 | 切向燃烧器 |
Family Cites Families (43)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4422288A (en) | 1981-03-02 | 1983-12-27 | General Electric Company | Aft mounting system for combustion transition duct members |
| US5118120A (en) | 1989-07-10 | 1992-06-02 | General Electric Company | Leaf seals |
| US5077967A (en) | 1990-11-09 | 1992-01-07 | General Electric Company | Profile matched diffuser |
| US5149250A (en) | 1991-02-28 | 1992-09-22 | General Electric Company | Gas turbine vane assembly seal and support system |
| US5249920A (en) | 1992-07-09 | 1993-10-05 | General Electric Company | Turbine nozzle seal arrangement |
| FR2711771B1 (fr) | 1993-10-27 | 1995-12-01 | Snecma | Diffuseur de chambre à alimentation circonférentielle variable. |
| US5414999A (en) | 1993-11-05 | 1995-05-16 | General Electric Company | Integral aft frame mount for a gas turbine combustor transition piece |
| US5457954A (en) | 1993-12-21 | 1995-10-17 | Solar Turbines Inc | Rolling contact mounting arrangement for a ceramic combustor |
| EP0718468B1 (en) | 1994-12-20 | 2001-10-31 | General Electric Company | Transition piece frame support |
| US5826429A (en) * | 1995-12-22 | 1998-10-27 | General Electric Co. | Catalytic combustor with lean direct injection of gas fuel for low emissions combustion and methods of operation |
| DE19549143A1 (de) | 1995-12-29 | 1997-07-03 | Abb Research Ltd | Gasturbinenringbrennkammer |
| US6076835A (en) | 1997-05-21 | 2000-06-20 | Allison Advanced Development Company | Interstage van seal apparatus |
| US5934687A (en) | 1997-07-07 | 1999-08-10 | General Electric Company | Gas-path leakage seal for a turbine |
| EP0924470B1 (de) | 1997-12-19 | 2003-06-18 | MTU Aero Engines GmbH | Vormischbrennkammer für eine Gasturbine |
| GB2335470B (en) | 1998-03-18 | 2002-02-13 | Rolls Royce Plc | A seal |
| US6471475B1 (en) | 2000-07-14 | 2002-10-29 | Pratt & Whitney Canada Corp. | Integrated duct diffuser |
| US6431825B1 (en) | 2000-07-28 | 2002-08-13 | Alstom (Switzerland) Ltd | Seal between static turbine parts |
| US6442946B1 (en) | 2000-11-14 | 2002-09-03 | Power Systems Mfg., Llc | Three degrees of freedom aft mounting system for gas turbine transition duct |
| JP2002243154A (ja) | 2001-02-16 | 2002-08-28 | Mitsubishi Heavy Ind Ltd | ガスタービン燃焼器尾筒出口構造及びガスタービン燃焼器 |
| US6431555B1 (en) | 2001-03-14 | 2002-08-13 | General Electric Company | Leaf seal for inner and outer casings of a turbine |
| US6564555B2 (en) | 2001-05-24 | 2003-05-20 | Allison Advanced Development Company | Apparatus for forming a combustion mixture in a gas turbine engine |
| US6537023B1 (en) | 2001-12-28 | 2003-03-25 | General Electric Company | Supplemental seal for the chordal hinge seal in a gas turbine |
| US6652229B2 (en) | 2002-02-27 | 2003-11-25 | General Electric Company | Leaf seal support for inner band of a turbine nozzle in a gas turbine engine |
| GB2390890B (en) | 2002-07-17 | 2005-07-06 | Rolls Royce Plc | Diffuser for gas turbine engine |
| US6662567B1 (en) | 2002-08-14 | 2003-12-16 | Power Systems Mfg, Llc | Transition duct mounting system |
| US7007480B2 (en) | 2003-04-09 | 2006-03-07 | Honeywell International, Inc. | Multi-axial pivoting combustor liner in gas turbine engine |
| US7024863B2 (en) | 2003-07-08 | 2006-04-11 | Pratt & Whitney Canada Corp. | Combustor attachment with rotational joint |
| US7010921B2 (en) * | 2004-06-01 | 2006-03-14 | General Electric Company | Method and apparatus for cooling combustor liner and transition piece of a gas turbine |
| US7721547B2 (en) * | 2005-06-27 | 2010-05-25 | Siemens Energy, Inc. | Combustion transition duct providing stage 1 tangential turning for turbine engines |
| US7637110B2 (en) | 2005-11-30 | 2009-12-29 | General Electric Company | Methods and apparatuses for assembling a gas turbine engine |
| EP1903184B1 (en) * | 2006-09-21 | 2019-05-01 | Siemens Energy, Inc. | Combustion turbine subsystem with twisted transition duct |
| US7665309B2 (en) * | 2007-09-14 | 2010-02-23 | Siemens Energy, Inc. | Secondary fuel delivery system |
| KR101206891B1 (ko) * | 2007-09-14 | 2012-11-30 | 지멘스 에너지, 인코포레이티드 | 2차 연료 전달 시스템 |
| US20090249791A1 (en) * | 2008-04-08 | 2009-10-08 | General Electric Company | Transition piece impingement sleeve and method of assembly |
| US8186167B2 (en) * | 2008-07-07 | 2012-05-29 | General Electric Company | Combustor transition piece aft end cooling and related method |
| US8113003B2 (en) | 2008-08-12 | 2012-02-14 | Siemens Energy, Inc. | Transition with a linear flow path for use in a gas turbine engine |
| US8065881B2 (en) | 2008-08-12 | 2011-11-29 | Siemens Energy, Inc. | Transition with a linear flow path with exhaust mouths for use in a gas turbine engine |
| US8091365B2 (en) | 2008-08-12 | 2012-01-10 | Siemens Energy, Inc. | Canted outlet for transition in a gas turbine engine |
| US9822649B2 (en) | 2008-11-12 | 2017-11-21 | General Electric Company | Integrated combustor and stage 1 nozzle in a gas turbine and method |
| US8701382B2 (en) * | 2009-01-07 | 2014-04-22 | General Electric Company | Late lean injection with expanded fuel flexibility |
| US8616007B2 (en) | 2009-01-22 | 2013-12-31 | Siemens Energy, Inc. | Structural attachment system for transition duct outlet |
| 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 |
| US8082739B2 (en) | 2010-04-12 | 2011-12-27 | General Electric Company | Combustor exit temperature profile control via fuel staging and related method |
-
2012
- 2012-04-30 US US13/459,516 patent/US9133722B2/en active Active
-
2013
- 2013-02-25 JP JP2013034087A patent/JP6188127B2/ja active Active
- 2013-02-27 RU RU2013108686/06A patent/RU2013108686A/ru not_active Application Discontinuation
- 2013-02-27 EP EP13157044.2A patent/EP2660519B1/en active Active
- 2013-02-28 CN CN201310064353.3A patent/CN103375262B/zh active Active
Patent Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3652181A (en) * | 1970-11-23 | 1972-03-28 | Carl F Wilhelm Jr | Cooling sleeve for gas turbine combustor transition member |
| CN101017000A (zh) * | 2006-02-08 | 2007-08-15 | 斯奈克玛 | 带有切向槽的涡轮发动机燃烧室 |
| CN102252345A (zh) * | 2010-04-27 | 2011-11-23 | 通用电气公司 | 切向燃烧器 |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110476017A (zh) * | 2017-02-24 | 2019-11-19 | 通用电气公司 | 具有轴向分级燃料喷射的燃烧系统 |
Also Published As
| Publication number | Publication date |
|---|---|
| EP2660519B1 (en) | 2015-12-16 |
| RU2013108686A (ru) | 2014-09-10 |
| US20130283804A1 (en) | 2013-10-31 |
| CN103375262A (zh) | 2013-10-30 |
| US9133722B2 (en) | 2015-09-15 |
| JP2013231576A (ja) | 2013-11-14 |
| EP2660519A1 (en) | 2013-11-06 |
| JP6188127B2 (ja) | 2017-08-30 |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C06 | Publication | ||
| PB01 | Publication | ||
| C10 | Entry into substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| TR01 | Transfer of patent right |
Effective date of registration: 20240109 Address after: Swiss Baden Patentee after: GENERAL ELECTRIC CO. LTD. Address before: New York State, USA Patentee before: General Electric Co. |
|
| TR01 | Transfer of patent right |