CA2685342A1 - Trous de refroidissement pour chemise de chambre de combustion de turbine a gaz ayant un diametre non uniforme au travers - Google Patents

Trous de refroidissement pour chemise de chambre de combustion de turbine a gaz ayant un diametre non uniforme au travers Download PDF

Info

Publication number: CA2685342A1
Authority: CA; Canada
Prior art keywords: shell; liner; cooling; diameter; combustor
Prior art date: 2007-05-01
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.): Abandoned

Application number

CA002685342A

Other languages

English (en)

Inventor

Marie Ann Mcmasters

David Louis Burrus

George Chia-Chun Hsiao

Hongtao Zhang

Hukam Chand Mongia

Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)

General Electric Co

Original Assignee

Individual

Priority date (The priority date 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 date listed.)

2007-05-01

Filing date

2008-03-04

Publication date

2008-11-13

2008-03-04 Application filed by Individual filed Critical Individual

2008-11-13 Publication of CA2685342A1 publication Critical patent/CA2685342A1/fr

Status Abandoned legal-status Critical Current

Links

238000001816 cooling Methods 0.000 title claims abstract description 120
238000011144 upstream manufacturing Methods 0.000 claims abstract description 10
238000009792 diffusion process Methods 0.000 claims description 8
238000000034 method Methods 0.000 claims description 7
239000000446 fuel Substances 0.000 claims description 6
230000007423 decrease Effects 0.000 claims description 3
239000007789 gas Substances 0.000 description 10
238000002485 combustion reaction Methods 0.000 description 8
238000010790 dilution Methods 0.000 description 6
239000012895 dilution Substances 0.000 description 6
239000002184 metal Substances 0.000 description 3
230000000712 assembly Effects 0.000 description 2
238000000429 assembly Methods 0.000 description 2
239000000567 combustion gas Substances 0.000 description 2
230000006978 adaptation Effects 0.000 description 1
230000004323 axial length Effects 0.000 description 1
230000008859 change Effects 0.000 description 1
RLQJEEJISHYWON-UHFFFAOYSA-N flonicamid Chemical compound FC(F)(F)C1=CC=NC=C1C(=O)NCC#N RLQJEEJISHYWON-UHFFFAOYSA-N 0.000 description 1
238000004519 manufacturing process Methods 0.000 description 1
239000000203 mixture Substances 0.000 description 1
238000012986 modification Methods 0.000 description 1
230000004048 modification Effects 0.000 description 1
230000008569 process Effects 0.000 description 1
230000009467 reduction Effects 0.000 description 1
230000008439 repair process Effects 0.000 description 1

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
- F23R3/002—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
- F23R3/02—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
- F23R2900/00—Special features of, or arrangements for continuous combustion chambers; Combustion processes therefor
- F23R2900/03042—Film cooled combustion chamber walls or domes
- 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)
Chemical & Material Sciences (AREA)
Combustion & Propulsion (AREA)
Mechanical Engineering (AREA)
General Engineering & Computer Science (AREA)
Turbine Rotor Nozzle Sealing (AREA)

CA002685342A 2007-05-01 2008-03-04 Trous de refroidissement pour chemise de chambre de combustion de turbine a gaz ayant un diametre non uniforme au travers Abandoned CA2685342A1 (fr)

Applications Claiming Priority (3)

Application Number	Priority Date	Filing Date	Title
US11/743,126 US20080271457A1 (en)	2007-05-01	2007-05-01	Cooling Holes For Gas Turbine Combustor Having A Non-Uniform Diameter Therethrough
US11/743,126		2007-05-01
PCT/US2008/055758 WO2008137201A1 (fr)	2007-05-01	2008-03-04	Trous de refroidissement pour chemise de chambre de combustion de turbine à gaz ayant un diamètre non uniforme au travers

Publications (1)

Publication Number	Publication Date
CA2685342A1 true CA2685342A1 (fr)	2008-11-13

Family

ID=39645559

Family Applications (1)

Application Number	Title	Priority Date	Filing Date
CA002685342A Abandoned CA2685342A1 (fr)	2007-05-01	2008-03-04	Trous de refroidissement pour chemise de chambre de combustion de turbine a gaz ayant un diametre non uniforme au travers

Country Status (5)

Country	Link
US (1)	US20080271457A1 (fr)
EP (1)	EP2153133A1 (fr)
JP (1)	JP2010526274A (fr)
CA (1)	CA2685342A1 (fr)
WO (1)	WO2008137201A1 (fr)

Families Citing this family (32)

* Cited by examiner, † Cited by third party
Publication number	Priority date	Publication date	Assignee	Title
DE102009007164A1 (de)	2009-02-03	2010-08-12	Rolls-Royce Deutschland Ltd & Co Kg	Verfahren zum Ausbilden einer Kühlluftöffnung in einer Wand einer Gasturbinenbrennkammer sowie nach dem Verfahren hergestellte Brennkammerwand
US8307657B2 (en) *	2009-03-10	2012-11-13	General Electric Company	Combustor liner cooling system
US20100263384A1 (en) *	2009-04-17	2010-10-21	Ronald James Chila	Combustor cap with shaped effusion cooling holes
US8371814B2 (en) *	2009-06-24	2013-02-12	Honeywell International Inc.	Turbine engine components
US8529193B2 (en) *	2009-11-25	2013-09-10	Honeywell International Inc.	Gas turbine engine components with improved film cooling
US8628293B2 (en)	2010-06-17	2014-01-14	Honeywell International Inc.	Gas turbine engine components with cooling hole trenches
US9052113B1 (en) *	2011-06-06	2015-06-09	General Electric Company	Combustor nozzle and method for modifying the combustor nozzle
US9650900B2 (en)	2012-05-07	2017-05-16	Honeywell International Inc.	Gas turbine engine components with film cooling holes having cylindrical to multi-lobe configurations
US10113433B2 (en)	2012-10-04	2018-10-30	Honeywell International Inc.	Gas turbine engine components with lateral and forward sweep film cooling holes
US9194585B2 (en)	2012-10-04	2015-11-24	United Technologies Corporation	Cooling for combustor liners with accelerating channels
US9309809B2 (en) *	2013-01-23	2016-04-12	General Electric Company	Effusion plate using additive manufacturing methods
US9939154B2 (en) *	2013-02-14	2018-04-10	United Technologies Corporation	Combustor liners with U-shaped cooling channels
CA2907048A1 (fr)	2013-03-15	2014-09-25	President And Fellows Of Harvard College	Feuille auxetique a faible porosite
WO2015030927A1 (fr) *	2013-08-30	2015-03-05	United Technologies Corporation	Passages de dilution profilés pour chambre à combustion de turbine à gaz
EP3066388B1 (fr) *	2013-11-04	2024-04-10	RTX Corporation	Bouclier thermique de chambre de combustion de moteur à turbine à ouvertures de refroidissement à inclinaisons multiples
US10190773B2 (en) *	2013-11-05	2019-01-29	United Technologies Corporation	Attachment stud on a combustor floatwall panel with internal cooling holes
JP6456481B2 (ja) *	2014-08-26	2019-01-23	シーメンスエナジーインコーポレイテッド	ガスタービンエンジン内の音響共鳴器用のフィルム冷却孔配列
GB201419327D0 (en)	2014-10-30	2014-12-17	Rolls Royce Plc	A cooled component
US20160258623A1 (en) *	2015-03-05	2016-09-08	United Technologies Corporation	Combustor and heat shield configurations for a gas turbine engine
US11021965B2 (en)	2016-05-19	2021-06-01	Honeywell International Inc.	Engine components with cooling holes having tailored metering and diffuser portions
US20180266687A1 (en) *	2017-03-16	2018-09-20	General Electric Company	Reducing film scrubbing in a combustor
US11149948B2 (en) *	2017-08-21	2021-10-19	General Electric Company	Fuel nozzle with angled main injection ports and radial main injection ports
US11009230B2 (en)	2018-02-06	2021-05-18	Raytheon Technologies Corporation	Undercut combustor panel rail
US10830435B2 (en)	2018-02-06	2020-11-10	Raytheon Technologies Corporation	Diffusing hole for rail effusion
US11248791B2 (en)	2018-02-06	2022-02-15	Raytheon Technologies Corporation	Pull-plane effusion combustor panel
US11022307B2 (en)	2018-02-22	2021-06-01	Raytheon Technology Corporation	Gas turbine combustor heat shield panel having multi-direction hole for rail effusion cooling
US11306659B2 (en)	2019-05-28	2022-04-19	Honeywell International Inc.	Plug resistant effusion holes for gas turbine engine
US11371701B1 (en)	2021-02-03	2022-06-28	General Electric Company	Combustor for a gas turbine engine
US11959643B2 (en)	2021-06-07	2024-04-16	General Electric Company	Combustor for a gas turbine engine
US11885495B2 (en)	2021-06-07	2024-01-30	General Electric Company	Combustor for a gas turbine engine including a liner having a looped feature
US11774098B2 (en)	2021-06-07	2023-10-03	General Electric Company	Combustor for a gas turbine engine
CN115493163B (zh) *	2022-09-06	2024-02-20	清华大学	燃烧室火焰筒及燃烧室火焰筒高效冷却方法

Family Cites Families (12)

* Cited by examiner, † Cited by third party
Publication number	Priority date	Publication date	Assignee	Title
GB2221979B (en) *	1988-08-17	1992-03-25	Rolls Royce Plc	A combustion chamber for a gas turbine engine
US5660525A (en) *	1992-10-29	1997-08-26	General Electric Company	Film cooled slotted wall
US5528904A (en) *	1994-02-28	1996-06-25	Jones; Charles R.	Coated hot gas duct liner
JPH09119322A (ja) *	1995-10-27	1997-05-06	Ishikawajima Harima Heavy Ind Co Ltd	航空機エンジンの冷却ライナ
US6383602B1 (en) *	1996-12-23	2002-05-07	General Electric Company	Method for improving the cooling effectiveness of a gaseous coolant stream which flows through a substrate, and related articles of manufacture
DE59808269D1 (de) *	1998-03-23	2003-06-12	Alstom Switzerland Ltd	Filmkühlungsbohrung
CA2288557C (fr) *	1998-11-12	2007-02-06	Mitsubishi Heavy Industries, Ltd.	Montage de refroidissement de chambre de combustion a turbine a gaz
US6408629B1 (en) *	2000-10-03	2002-06-25	General Electric Company	Combustor liner having preferentially angled cooling holes
US7093439B2 (en) *	2002-05-16	2006-08-22	United Technologies Corporation	Heat shield panels for use in a combustor for a gas turbine engine
US7328580B2 (en) *	2004-06-23	2008-02-12	General Electric Company	Chevron film cooled wall
JP4898253B2 (ja) *	2005-03-30	2012-03-14	三菱重工業株式会社	ガスタービン用高温部材
EP1712739A1 (fr) *	2005-04-12	2006-10-18	Siemens Aktiengesellschaft	Elément avec trou de refroidissement par film

2007
- 2007-05-01 US US11/743,126 patent/US20080271457A1/en not_active Abandoned
2008
- 2008-03-04 EP EP08731322A patent/EP2153133A1/fr not_active Withdrawn
- 2008-03-04 JP JP2010506353A patent/JP2010526274A/ja active Pending
- 2008-03-04 WO PCT/US2008/055758 patent/WO2008137201A1/fr active Application Filing
- 2008-03-04 CA CA002685342A patent/CA2685342A1/fr not_active Abandoned

Also Published As

Publication number	Publication date
JP2010526274A (ja)	2010-07-29
EP2153133A1 (fr)	2010-02-17
WO2008137201A1 (fr)	2008-11-13
US20080271457A1 (en)	2008-11-06

Legal Events

Date	Code	Title	Description
2013-01-28	EEER	Examination request	Effective date: 20130117
2015-06-22	FZDE	Discontinued	Effective date: 20150427

Publication	Publication Date	Title
US20080271457A1 (en)	2008-11-06	Cooling Holes For Gas Turbine Combustor Having A Non-Uniform Diameter Therethrough
JP5374031B2 (ja)	2013-12-25	タービンエンジンにおけるＮＯｘエミッションを低減するのを可能にするための装置及びガスタービンエンジン
US7086232B2 (en)	2006-08-08	Multihole patch for combustor liner of a gas turbine engine
US7546739B2 (en)	2009-06-16	Igniter tube and method of assembling same
US5261223A (en)	1993-11-16	Multi-hole film cooled combustor liner with rectangular film restarting holes
US7506512B2 (en)	2009-03-24	Advanced effusion cooling schemes for combustor domes
EP2475933B1 (fr)	2018-06-13	Injecteur de carburant destiné à être utilisé dans un moteur à turbine à gaz
US6553767B2 (en)	2003-04-29	Gas turbine combustor liner with asymmetric dilution holes machined from a single piece form
US7325403B2 (en)	2008-02-05	Methods and apparatus for fabricating gas turbine engine combustors
US5307637A (en)	1994-05-03	Angled multi-hole film cooled single wall combustor dome plate
US20100186415A1 (en)	2010-07-29	Turbulated aft-end liner assembly and related cooling method
US7669422B2 (en)	2010-03-02	Combustor liner and method of fabricating same
EP2518406B1 (fr)	2015-08-26	Système Venturi complètement refroidi par projection avec résonateur incorporé pour capacités dynamiques réduites et de meilleures capacités de transfert de chaleur
EP1096205A1 (fr)	2001-05-02	Chemise de chambre de combustion à dilution décalée
US7765809B2 (en)	2010-08-03	Combustor dome and methods of assembling such
US20040079083A1 (en)	2004-04-29	Liner for a gas turbine engine combustor having trapped vortex cavity
US6986253B2 (en)	2006-01-17	Methods and apparatus for cooling gas turbine engine combustors
US20100242484A1 (en)	2010-09-30	Apparatus and method for cooling gas turbine engine combustors
US20060130486A1 (en)	2006-06-22	Method and apparatus for assembling gas turbine engine combustors
US7578134B2 (en)	2009-08-25	Methods and apparatus for assembling gas turbine engines