EP1351022A3 - Air passage for turbine combustor with shingles - Google Patents

Air passage for turbine combustor with shingles Download PDF

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Publication number
EP1351022A3
EP1351022A3 EP03001782A EP03001782A EP1351022A3 EP 1351022 A3 EP1351022 A3 EP 1351022A3 EP 03001782 A EP03001782 A EP 03001782A EP 03001782 A EP03001782 A EP 03001782A EP 1351022 A3 EP1351022 A3 EP 1351022A3
Authority
EP
European Patent Office
Prior art keywords
shingles
air hole
turbine combustor
air passage
support structure
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.)
Granted
Application number
EP03001782A
Other languages
German (de)
French (fr)
Other versions
EP1351022B1 (en
EP1351022A2 (en
Inventor
Miklos Dr.-Ing. Gerendas
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.)
Rolls Royce Deutschland Ltd and Co KG
Original Assignee
Rolls Royce Deutschland Ltd and Co KG
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.)
Filing date
Publication date
Application filed by Rolls Royce Deutschland Ltd and Co KG filed Critical Rolls Royce Deutschland Ltd and Co KG
Publication of EP1351022A2 publication Critical patent/EP1351022A2/en
Publication of EP1351022A3 publication Critical patent/EP1351022A3/en
Application granted granted Critical
Publication of EP1351022B1 publication Critical patent/EP1351022B1/en
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

Links

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
    • F23R3/06—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
    • F23R3/002—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
    • F23R2900/00—Special features of, or arrangements for continuous combustion chambers; Combustion processes therefor
    • F23R2900/03041—Effusion cooled combustion chamber walls or domes

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)

Abstract

Die Erfindung bezieht sich auf eine Gasturbinenbrennkammer mit Brennkammerschindeln, wobei die Brennkammerschindeln 3 an einer Tragstruktur 6 der Gasturbinenbrennkammer befestigt sind und jeweils zumindest ein Mischluftloch 4 aufweisen, welches fluchtend zu einem Mischluftloch der Tragstruktur 6 angeordnet sind, dadurch gekennzeichnet, dass der Durchmesser des Mischluftlochs der Tragstruktur 6 erheblich größer ist, als der Durchmesser 14 des Mischluftlochs 4 der Brennkammerschindel 3.

Figure 00000001
The invention relates to a gas turbine combustion chamber with combustion shingles, wherein the combustion chamber shingles 3 are attached to a support structure 6 of the gas turbine combustor and each having at least one mixing air hole 4, which are arranged in alignment with a mixing air hole of the support structure 6, characterized in that the diameter of the mixed air hole Support structure 6 is considerably larger than the diameter 14 of the mixing air hole 4 of the combustion chamber shingle. 3
Figure 00000001
EP03001782A 2002-04-02 2003-01-28 Air passage for turbine combustor with shingles Expired - Lifetime EP1351022B1 (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE10214570 2002-04-02
DE10214570A DE10214570A1 (en) 2002-04-02 2002-04-02 Mixed air hole in gas turbine combustion chamber with combustion chamber shingles

Publications (3)

Publication Number Publication Date
EP1351022A2 EP1351022A2 (en) 2003-10-08
EP1351022A3 true EP1351022A3 (en) 2005-01-26
EP1351022B1 EP1351022B1 (en) 2010-08-04

Family

ID=27816106

Family Applications (1)

Application Number Title Priority Date Filing Date
EP03001782A Expired - Lifetime EP1351022B1 (en) 2002-04-02 2003-01-28 Air passage for turbine combustor with shingles

Country Status (3)

Country Link
US (1) US7059133B2 (en)
EP (1) EP1351022B1 (en)
DE (2) DE10214570A1 (en)

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EP1423645B1 (en) * 2001-09-07 2008-10-08 Alstom Technology Ltd Damping arrangement for reducing combustion chamber pulsations in a gas turbine system
EP1507116A1 (en) * 2003-08-13 2005-02-16 Siemens Aktiengesellschaft Heat shield arrangement for a high temperature gas conveying component, in particular for a gas turbine combustion chamber
US7140185B2 (en) * 2004-07-12 2006-11-28 United Technologies Corporation Heatshielded article
US9587832B2 (en) * 2008-10-01 2017-03-07 United Technologies Corporation Structures with adaptive cooling
US8161752B2 (en) * 2008-11-20 2012-04-24 Honeywell International Inc. Combustors with inserts between dual wall liners
US9010121B2 (en) 2010-12-10 2015-04-21 Rolls-Royce Plc Combustion chamber
US9062884B2 (en) 2011-05-26 2015-06-23 Honeywell International Inc. Combustors with quench inserts
GB201116608D0 (en) * 2011-09-27 2011-11-09 Rolls Royce Plc A method of operating a combustion chamber
US9038395B2 (en) 2012-03-29 2015-05-26 Honeywell International Inc. Combustors with quench inserts
US9174309B2 (en) 2012-07-24 2015-11-03 General Electric Company Turbine component and a process of fabricating a turbine component
DE102012015452A1 (en) * 2012-08-03 2014-04-24 Rolls-Royce Deutschland Ltd & Co Kg Gas turbine combustion chamber wall for gas turbine engine, has mixed air openings formed by tubular air guide elements, which are fastened at wall and penetrate shingles arranged at inner side of wall
DE102012022259A1 (en) 2012-11-13 2014-05-28 Rolls-Royce Deutschland Ltd & Co Kg Combustor shingle of a gas turbine and process for its production
DE102012022199A1 (en) 2012-11-13 2014-05-28 Rolls-Royce Deutschland Ltd & Co Kg Combustor shingle of a gas turbine
DE102012023297A1 (en) * 2012-11-28 2014-06-12 Rolls-Royce Deutschland Ltd & Co Kg Shingle fastening arrangement of a gas turbine combustion chamber
WO2014112992A1 (en) * 2013-01-16 2014-07-24 United Technologies Corporation Combustor cooled quench zone array
US9228747B2 (en) * 2013-03-12 2016-01-05 Pratt & Whitney Canada Corp. Combustor for gas turbine engine
WO2014197045A2 (en) * 2013-03-12 2014-12-11 United Technologies Corporation Active cooling of grommet bosses for a combustor panel of a gas turbine engine
US9651258B2 (en) 2013-03-15 2017-05-16 Rolls-Royce Corporation Shell and tiled liner arrangement for a combustor
US11112115B2 (en) * 2013-08-30 2021-09-07 Raytheon Technologies Corporation Contoured dilution passages for gas turbine engine combustor
US10648666B2 (en) * 2013-09-16 2020-05-12 United Technologies Corporation Angled combustor liner cooling holes through transverse structure within a gas turbine engine combustor
US10731858B2 (en) 2013-09-16 2020-08-04 Raytheon Technologies Corporation Controlled variation of pressure drop through effusion cooling in a double walled combustor of a gas turbine engine
DE102013223258A1 (en) 2013-11-14 2015-06-03 Rolls-Royce Deutschland Ltd & Co Kg Combustion heat shield element of a gas turbine
WO2015085065A1 (en) 2013-12-05 2015-06-11 United Technologies Corporation Cooling a quench aperture body of a combustor wall
WO2015085069A1 (en) * 2013-12-06 2015-06-11 United Technologies Corporation Combustor quench aperture cooling
WO2015084963A1 (en) * 2013-12-06 2015-06-11 United Technologies Corporation Cooling a quench aperture body of a combustor wall
US10317079B2 (en) 2013-12-20 2019-06-11 United Technologies Corporation Cooling an aperture body of a combustor wall
DE102014204472A1 (en) 2014-03-11 2015-09-17 Rolls-Royce Deutschland Ltd & Co Kg Combustor shingle of a gas turbine
DE102014204466A1 (en) 2014-03-11 2015-10-01 Rolls-Royce Deutschland Ltd & Co Kg Combustion chamber of a gas turbine
DE102014222320A1 (en) 2014-10-31 2016-05-04 Rolls-Royce Deutschland Ltd & Co Kg Combustion chamber wall of a gas turbine with cooling for a mixed air hole edge
US10788212B2 (en) * 2015-01-12 2020-09-29 General Electric Company System and method for an oxidant passageway in a gas turbine system with exhaust gas recirculation
US10094564B2 (en) 2015-04-17 2018-10-09 Pratt & Whitney Canada Corp. Combustor dilution hole cooling system
EP3139090B1 (en) 2015-09-04 2018-06-13 Rolls-Royce Deutschland Ltd & Co KG Assembly with a combustion chamber shingle for a gas turbine
DE102015217161A1 (en) 2015-09-04 2017-03-09 Rolls-Royce Deutschland Ltd & Co Kg Assembly with a combustion chamber shingle for a gas turbine
DE102016219424A1 (en) 2016-10-06 2018-04-12 Rolls-Royce Deutschland Ltd & Co Kg Combustion chamber arrangement of a gas turbine and aircraft gas turbine
DE102016222099A1 (en) 2016-11-10 2018-05-17 Rolls-Royce Deutschland Ltd & Co Kg Combustion chamber of a gas turbine
US10408453B2 (en) * 2017-07-19 2019-09-10 United Technologies Corporation Dilution holes for gas turbine engines
US11268438B2 (en) 2017-09-15 2022-03-08 General Electric Company Combustor liner dilution opening
US11137140B2 (en) 2017-10-04 2021-10-05 Raytheon Technologies Corporation Dilution holes with ridge feature for gas turbine engines
US11255543B2 (en) 2018-08-07 2022-02-22 General Electric Company Dilution structure for gas turbine engine combustor
US11339966B2 (en) 2018-08-21 2022-05-24 General Electric Company Flow control wall for heat engine
US11029027B2 (en) 2018-10-03 2021-06-08 Raytheon Technologies Corporation Dilution/effusion hole pattern for thick combustor panels
US11391460B2 (en) * 2019-07-16 2022-07-19 Raytheon Technologies Corporation Effusion cooling for dilution/quench hole edges in combustor liner panels
US11371701B1 (en) 2021-02-03 2022-06-28 General Electric Company Combustor for a gas turbine engine
US11560837B2 (en) 2021-04-19 2023-01-24 General Electric Company Combustor dilution hole
US11572835B2 (en) 2021-05-11 2023-02-07 General Electric Company Combustor dilution hole
US11959643B2 (en) 2021-06-07 2024-04-16 General Electric Company Combustor for a gas turbine engine
US12085283B2 (en) 2021-06-07 2024-09-10 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

Citations (8)

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US3303645A (en) * 1963-04-30 1967-02-14 Hitachi Ltd Ultra-high temperature burners
US4132066A (en) * 1977-09-23 1979-01-02 United Technologies Corporation Combustor liner for gas turbine engine
US4653279A (en) * 1985-01-07 1987-03-31 United Technologies Corporation Integral refilmer lip for floatwall panels
WO1988006257A1 (en) * 1987-02-11 1988-08-25 The Secretary Of State For Defence In Her Britanni Gas turbine engine combustion chambers
EP0937946A2 (en) * 1998-02-18 1999-08-25 ROLLS-ROYCE plc Wall structure for a gas turbine combustor
EP1022437A1 (en) * 1999-01-19 2000-07-26 Siemens Aktiengesellschaft Construction element for use in a thermal machine
GB2353589A (en) * 1999-08-24 2001-02-28 Rolls Royce Plc Combustor wall arrangement with air intake port
EP1098141A1 (en) * 1999-11-06 2001-05-09 Rolls-Royce Plc Wall elements for gas turbine engine combustors

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JPS5857658B2 (en) * 1980-04-02 1983-12-21 工業技術院長 Heat shielding structure for walls exposed to high heat using ceramics
GB2087065B (en) * 1980-11-08 1984-11-07 Rolls Royce Wall structure for a combustion chamber
US5687572A (en) * 1992-11-02 1997-11-18 Alliedsignal Inc. Thin wall combustor with backside impingement cooling
US6145319A (en) 1998-07-16 2000-11-14 General Electric Company Transitional multihole combustion liner
GB2368902A (en) * 2000-11-11 2002-05-15 Rolls Royce Plc A double wall combustor arrangement
US6606861B2 (en) * 2001-02-26 2003-08-19 United Technologies Corporation Low emissions combustor for a gas turbine engine
GB2373319B (en) * 2001-03-12 2005-03-30 Rolls Royce Plc Combustion apparatus
GB2384046B (en) * 2002-01-15 2005-07-06 Rolls Royce Plc A double wall combuster tile arrangement

Patent Citations (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3303645A (en) * 1963-04-30 1967-02-14 Hitachi Ltd Ultra-high temperature burners
US4132066A (en) * 1977-09-23 1979-01-02 United Technologies Corporation Combustor liner for gas turbine engine
US4653279A (en) * 1985-01-07 1987-03-31 United Technologies Corporation Integral refilmer lip for floatwall panels
WO1988006257A1 (en) * 1987-02-11 1988-08-25 The Secretary Of State For Defence In Her Britanni Gas turbine engine combustion chambers
EP0937946A2 (en) * 1998-02-18 1999-08-25 ROLLS-ROYCE plc Wall structure for a gas turbine combustor
EP1022437A1 (en) * 1999-01-19 2000-07-26 Siemens Aktiengesellschaft Construction element for use in a thermal machine
GB2353589A (en) * 1999-08-24 2001-02-28 Rolls Royce Plc Combustor wall arrangement with air intake port
EP1098141A1 (en) * 1999-11-06 2001-05-09 Rolls-Royce Plc Wall elements for gas turbine engine combustors

Also Published As

Publication number Publication date
US7059133B2 (en) 2006-06-13
US20030182942A1 (en) 2003-10-02
DE10214570A1 (en) 2004-01-15
DE50312938D1 (en) 2010-09-16
EP1351022B1 (en) 2010-08-04
EP1351022A2 (en) 2003-10-08

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