EP1865259A3 - Gas-turbine combustion chamber wall for a lean-burning gas-turbine combustion chamber - Google Patents

Gas-turbine combustion chamber wall for a lean-burning gas-turbine combustion chamber Download PDF

Info

Publication number
EP1865259A3
EP1865259A3 EP07109395.9A EP07109395A EP1865259A3 EP 1865259 A3 EP1865259 A3 EP 1865259A3 EP 07109395 A EP07109395 A EP 07109395A EP 1865259 A3 EP1865259 A3 EP 1865259A3
Authority
EP
European Patent Office
Prior art keywords
combustion chamber
turbine combustion
gas
lean
chamber wall
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.)
Withdrawn
Application number
EP07109395.9A
Other languages
German (de)
French (fr)
Other versions
EP1865259A2 (en
Inventor
Miklós Gerendás
Michael Ebel
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 EP1865259A2 publication Critical patent/EP1865259A2/en
Publication of EP1865259A3 publication Critical patent/EP1865259A3/en
Withdrawn legal-status Critical Current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
    • F23R2900/00014—Reducing thermo-acoustic vibrations by passive means, e.g. by Helmholtz resonators
    • 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

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 besieht auf eine Gasturbinenbrennkammerwand für eine mager-brennende Gasturbinenbrennkammer mit einem Brennkamstergehäuse 2, 3 und mehreren in dem Brennkammergehäuse 2, 3 angeordneten, eine Brennkammerwand 10 bildenden Brennkamner segmenten, welche jeweils über axiale und/oder radiale Kühlungslöcher 16, 17 mit Kühlluft mit einer Filmkühlung beaufschlagt werden, wobei die Kühlungslöcher 16, 17 zueinander in Axialrichtung beabstandet sind und wobei in diesem Bereich Dämpfungsöffnungen 19a zur Einleitung von Kühlluft vorgesehen sind.

Figure imgaf001
The invention relates to a gas turbine combustor wall for a lean-burning gas turbine combustor with a Brennkamstergehäuse 2, 3 and a plurality arranged in the combustion chamber housing 2, 3, a combustion chamber wall 10 forming Brennamamner segments, each with axial and / or radial cooling holes 16, 17 with cooling air a film cooling are applied, wherein the cooling holes 16, 17 are spaced from each other in the axial direction and wherein in this area damping openings 19a are provided for the introduction of cooling air.
Figure imgaf001
EP07109395.9A 2006-06-09 2007-06-01 Gas-turbine combustion chamber wall for a lean-burning gas-turbine combustion chamber Withdrawn EP1865259A3 (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
DE102006026969A DE102006026969A1 (en) 2006-06-09 2006-06-09 Gas turbine combustor wall for a lean-burn gas turbine combustor

Publications (2)

Publication Number Publication Date
EP1865259A2 EP1865259A2 (en) 2007-12-12
EP1865259A3 true EP1865259A3 (en) 2014-08-06

Family

ID=38457606

Family Applications (1)

Application Number Title Priority Date Filing Date
EP07109395.9A Withdrawn EP1865259A3 (en) 2006-06-09 2007-06-01 Gas-turbine combustion chamber wall for a lean-burning gas-turbine combustion chamber

Country Status (3)

Country Link
US (1) US7926278B2 (en)
EP (1) EP1865259A3 (en)
DE (1) DE102006026969A1 (en)

Families Citing this family (64)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2009103671A1 (en) * 2008-02-20 2009-08-27 Alstom Technology Ltd Gas turbine having an improved cooling architecture
EP2299177A1 (en) * 2009-09-21 2011-03-23 Alstom Technology Ltd Combustor of a gas turbine
US9310079B2 (en) 2010-12-30 2016-04-12 Rolls-Royce North American Technologies, Inc. Combustion liner with open cell foam and acoustic damping layers
GB201105790D0 (en) * 2011-04-06 2011-05-18 Rolls Royce Plc A cooled double walled article
EP2559942A1 (en) * 2011-08-19 2013-02-20 Rolls-Royce Deutschland Ltd & Co KG Gas turbine combustion chamber head with cooling and damping
DE102011081962A1 (en) * 2011-09-01 2013-03-07 Siemens Aktiengesellschaft Combustion chamber for a gas turbine plant
US8745988B2 (en) 2011-09-06 2014-06-10 Pratt & Whitney Canada Corp. Pin fin arrangement for heat shield of gas turbine engine
GB201116608D0 (en) * 2011-09-27 2011-11-09 Rolls Royce Plc A method of operating a combustion chamber
DE102011114928A1 (en) * 2011-10-06 2013-04-11 Lufthansa Technik Ag Combustion chamber for a gas turbine
EP2613080A1 (en) 2012-01-05 2013-07-10 Siemens Aktiengesellschaft Combustion chamber of an annular combustor for a gas turbine
EP2762784B1 (en) * 2012-11-30 2016-02-03 Alstom Technology Ltd Damping device for a gas turbine combustor
WO2014137428A1 (en) 2013-03-05 2014-09-12 Rolls-Royce Corporation Dual-wall impingement, convection, effusion combustor tile
US9651258B2 (en) 2013-03-15 2017-05-16 Rolls-Royce Corporation Shell and tiled liner arrangement for a combustor
US9400108B2 (en) 2013-05-14 2016-07-26 Siemens Aktiengesellschaft Acoustic damping system for a combustor of a gas turbine engine
US9410484B2 (en) * 2013-07-19 2016-08-09 Siemens Aktiengesellschaft Cooling chamber for upstream weld of damping resonator on turbine component
EP3052786B1 (en) * 2013-10-04 2019-05-15 United Technologies Corporation Heat shield panels with overlap joints for a turbine engine combustor
EP2860451A1 (en) * 2013-10-11 2015-04-15 Alstom Technology Ltd Combustion chamber of a gas turbine with improved acoustic damping
US20160245519A1 (en) * 2013-10-18 2016-08-25 United Technologies Corporation Panel with cooling holes and methods for fabricating same
US10816206B2 (en) 2013-10-24 2020-10-27 Raytheon Technologies Corporation Gas turbine engine quench pattern for gas turbine engine combustor
JP6246562B2 (en) * 2013-11-05 2017-12-13 三菱日立パワーシステムズ株式会社 Gas turbine combustor
CN103807844B (en) * 2014-01-24 2016-01-20 华东理工大学 A kind of metallic walls cooling means contacted with high-temperature gas
WO2015117137A1 (en) * 2014-02-03 2015-08-06 United Technologies Corporation Film cooling a combustor wall of a turbine engine
US9410702B2 (en) 2014-02-10 2016-08-09 Honeywell International Inc. Gas turbine engine combustors with effusion and impingement cooling and methods for manufacturing the same using additive manufacturing techniques
EP2913589B1 (en) * 2014-02-28 2020-01-22 Ansaldo Energia Switzerland AG Acoustic damping device for chambers with grazing flow
EP3048370A1 (en) * 2015-01-23 2016-07-27 Siemens Aktiengesellschaft Combustion chamber for a gas turbine engine
CN104676649A (en) * 2015-02-05 2015-06-03 北京华清燃气轮机与煤气化联合循环工程技术有限公司 Damping thermo-acoustic vibration acoustic flame tube
CA2933884A1 (en) * 2015-06-30 2016-12-30 Rolls-Royce Corporation Combustor tile
US9995151B2 (en) * 2015-08-17 2018-06-12 General Electric Company Article and manifold for thermal adjustment of a turbine component
US10280760B2 (en) * 2015-09-30 2019-05-07 General Electric Company Turbine engine assembly and method of assembling the same
GB201518345D0 (en) * 2015-10-16 2015-12-02 Rolls Royce Combustor for a gas turbine engine
US10520193B2 (en) * 2015-10-28 2019-12-31 General Electric Company Cooling patch for hot gas path components
DE102016104957A1 (en) * 2016-03-17 2017-09-21 Rolls-Royce Deutschland Ltd & Co Kg Cooling device for cooling platforms of a vane ring of a gas turbine
US10309228B2 (en) * 2016-06-09 2019-06-04 General Electric Company Impingement insert for a gas turbine engine
WO2018021996A1 (en) * 2016-07-25 2018-02-01 Siemens Aktiengesellschaft Gas turbine engine with resonator rings
JP2018054210A (en) * 2016-09-28 2018-04-05 株式会社Ihi Liner for combustor
US10724739B2 (en) 2017-03-24 2020-07-28 General Electric Company Combustor acoustic damping structure
JP7008722B2 (en) * 2017-03-30 2022-01-25 シーメンス アクティエンゲゼルシャフト A system with a conduit arrangement for dual use of cooling fluid in the combustor section of a gas turbine engine
US10415480B2 (en) 2017-04-13 2019-09-17 General Electric Company Gas turbine engine fuel manifold damper and method of dynamics attenuation
US10663168B2 (en) * 2017-08-02 2020-05-26 Raytheon Technologies Corporation End rail mate-face low pressure vortex minimization
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
US11156162B2 (en) 2018-05-23 2021-10-26 General Electric Company Fluid manifold damper for gas turbine engine
US11506125B2 (en) 2018-08-01 2022-11-22 General Electric Company Fluid manifold assembly for gas turbine engine
US11268696B2 (en) 2018-10-19 2022-03-08 Raytheon Technologies Corporation Slot cooled combustor
DE102019204746A1 (en) * 2019-04-03 2020-10-08 Siemens Aktiengesellschaft Heat shield tile with damping function
DE102019205540A1 (en) * 2019-04-17 2020-10-22 Siemens Aktiengesellschaft Resonator, method for producing such and burner arrangement provided with such
US11959641B2 (en) 2020-01-31 2024-04-16 Rtx Corporation Combustor shell with shaped impingement holes
JP7393262B2 (en) * 2020-03-23 2023-12-06 三菱重工業株式会社 Combustor and gas turbine equipped with the same
CN111648866A (en) * 2020-04-14 2020-09-11 南京航空航天大学 Impact air film-divergent hole composite cooling structure
US20210372616A1 (en) * 2020-05-27 2021-12-02 Raytheon Technologies Corporation Multi-walled structure for a gas turbine engine
US11460191B2 (en) 2020-08-31 2022-10-04 General Electric Company Cooling insert for a turbomachine
US11614233B2 (en) 2020-08-31 2023-03-28 General Electric Company Impingement panel support structure and method of manufacture
US11994292B2 (en) 2020-08-31 2024-05-28 General Electric Company Impingement cooling apparatus for turbomachine
US11994293B2 (en) 2020-08-31 2024-05-28 General Electric Company Impingement cooling apparatus support structure and method of manufacture
US11371702B2 (en) 2020-08-31 2022-06-28 General Electric Company Impingement panel for a turbomachine
US11255545B1 (en) 2020-10-26 2022-02-22 General Electric Company Integrated combustion nozzle having a unified head end
US20220282688A1 (en) * 2021-03-08 2022-09-08 Raytheon Company Attenuators for combustion noise in dual mode ramjets and scramjets
US11867402B2 (en) * 2021-03-19 2024-01-09 Rtx Corporation CMC stepped combustor liner
CN113701193B (en) * 2021-08-13 2023-02-28 中国航发沈阳发动机研究所 Flame tube of gas turbine
CN114811649B (en) * 2022-04-07 2024-05-10 中国联合重型燃气轮机技术有限公司 Combustion chamber and gas turbine with same
US11767766B1 (en) 2022-07-29 2023-09-26 General Electric Company Turbomachine airfoil having impingement cooling passages

Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0937946A2 (en) * 1998-02-18 1999-08-25 ROLLS-ROYCE plc Wall structure for a gas turbine combustor
EP1098141A1 (en) * 1999-11-06 2001-05-09 Rolls-Royce Plc Wall elements for gas turbine engine combustors
EP1213538A2 (en) * 2000-12-08 2002-06-12 ABB Turbo Systems AG Exhaust gas system with Helmholtz resonator
US20030233831A1 (en) * 2000-12-06 2003-12-25 Mitsubishi Heavy Industries, Ltd. Gas turbine combustor, gas turbine, and jet engine

Family Cites Families (24)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4242871A (en) * 1979-09-18 1981-01-06 United Technologies Corporation Louver burner liner
US4916906A (en) * 1988-03-25 1990-04-17 General Electric Company Breach-cooled structure
GB9127505D0 (en) * 1991-03-11 2013-12-25 Gen Electric Multi-hole film cooled afterburner combustor liner
US5435139A (en) * 1991-03-22 1995-07-25 Rolls-Royce Plc Removable combustor liner for gas turbine engine combustor
EP0576717A1 (en) * 1992-07-03 1994-01-05 Abb Research Ltd. Gas turbine combustor
EP0971172B1 (en) * 1998-07-10 2003-12-03 ALSTOM (Switzerland) Ltd Gas turbine combustion chamber with silencing wall structure
US6266961B1 (en) * 1999-10-14 2001-07-31 General Electric Company Film cooled combustor liner and method of making the same
US6260359B1 (en) * 1999-11-01 2001-07-17 General Electric Company Offset dilution combustor liner
US6351947B1 (en) * 2000-04-04 2002-03-05 Abb Alstom Power (Schweiz) Combustion chamber for a gas turbine
US6397603B1 (en) * 2000-05-05 2002-06-04 The United States Of America As Represented By The Secretary Of The Air Force Conbustor having a ceramic matrix composite liner
US6530221B1 (en) * 2000-09-21 2003-03-11 Siemens Westinghouse Power Corporation Modular resonators for suppressing combustion instabilities in gas turbine power plants
JP3676228B2 (en) * 2000-12-06 2005-07-27 三菱重工業株式会社 Gas turbine combustor, gas turbine and jet engine
US6543233B2 (en) * 2001-02-09 2003-04-08 General Electric Company Slot cooled combustor liner
JP3962554B2 (en) * 2001-04-19 2007-08-22 三菱重工業株式会社 Gas turbine combustor and gas turbine
US6675582B2 (en) * 2001-05-23 2004-01-13 General Electric Company Slot cooled combustor line
US6655146B2 (en) * 2001-07-31 2003-12-02 General Electric Company Hybrid film cooled combustor liner
US7086232B2 (en) * 2002-04-29 2006-08-08 General Electric Company Multihole patch for combustor liner of a gas turbine engine
GB2390150A (en) * 2002-06-26 2003-12-31 Alstom Reheat combustion system for a gas turbine including an accoustic screen
US6964170B2 (en) * 2003-04-28 2005-11-15 Pratt & Whitney Canada Corp. Noise reducing combustor
EP1475567A1 (en) * 2003-05-08 2004-11-10 Siemens Aktiengesellschaft Layered structure and method to produce such a layered structure
US7007481B2 (en) * 2003-09-10 2006-03-07 General Electric Company Thick coated combustor liner
US6868675B1 (en) * 2004-01-09 2005-03-22 Honeywell International Inc. Apparatus and method for controlling combustor liner carbon formation
US7334408B2 (en) * 2004-09-21 2008-02-26 Siemens Aktiengesellschaft Combustion chamber for a gas turbine with at least two resonator devices
GB0425794D0 (en) * 2004-11-24 2004-12-22 Rolls Royce Plc Acoustic damper

Patent Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0937946A2 (en) * 1998-02-18 1999-08-25 ROLLS-ROYCE plc Wall structure for a gas turbine combustor
EP1098141A1 (en) * 1999-11-06 2001-05-09 Rolls-Royce Plc Wall elements for gas turbine engine combustors
US20030233831A1 (en) * 2000-12-06 2003-12-25 Mitsubishi Heavy Industries, Ltd. Gas turbine combustor, gas turbine, and jet engine
EP1213538A2 (en) * 2000-12-08 2002-06-12 ABB Turbo Systems AG Exhaust gas system with Helmholtz resonator

Also Published As

Publication number Publication date
US7926278B2 (en) 2011-04-19
EP1865259A2 (en) 2007-12-12
DE102006026969A1 (en) 2007-12-13
US20070283700A1 (en) 2007-12-13

Similar Documents

Publication Publication Date Title
EP1865259A3 (en) Gas-turbine combustion chamber wall for a lean-burning gas-turbine combustion chamber
EP2236930A3 (en) Combustor for gas turbine engine
EP2096293A3 (en) Aircraft engine with multiple fans
EP1732062A3 (en) Silencer
EP2028343A3 (en) Turbine shroud for gas turbine assemblies and processes for forming the shroud
EP2108786A3 (en) Aeroengine fan assembly
EP1811231A3 (en) Segmented effusion cooled gas turbine engine combustor
EP2796668A3 (en) Casing section of a turbo engine compressor or turbo engine turbine stage
EP2224168A3 (en) Annular rich-quench-lean gas turbine combustors with plunged holes
EP1998004A3 (en) Turbine component with axially spaced radially flowing microcircuit cooling channels
EP2011971A3 (en) Mounting of a casing shroud segment
EP2302174A3 (en) Gas turbine shroud labyrinth seal
DE602006002673D1 (en) Vibration damping elements for an axial retaining ring of fan blades of a turbomachine
EP1780379A3 (en) Steam turbine and hydrophilic coating material used therefor
EP1586741A3 (en) Apparatus for damping vibrations of the stator vanes of a gas turbine engine
EP1995544A3 (en) Heat exchanger, in particular charger air cooler or exhaust gas cooler for a combustion engine of a motor vehicle and manufacturing method therefor
EP2224170A3 (en) Plunged hole arrangement for annular rich-quench-lean gas turbine combustors
WO2007015916A3 (en) Reinforcement rings for a diffuser section of a tip turbine engine fan rotor assembly
DE112015003440T5 (en) Cylinder for combustion chamber, combustion chamber and gas turbine
EP1635118A3 (en) Hot gas chamber and shingle for a hot gas chamber
EP1921382A3 (en) Combustor dome mixer retaining means
EP1748253A3 (en) Combustion chamber and method for producing a combustion chamber
EP2927594A3 (en) Combustion chamber of a gas turbine
EP2093487A3 (en) Gas turbine combustion chamber with ceramic flame tube
EP2028346A3 (en) Steam turbine

Legal Events

Date Code Title Description
PUAI Public reference made under article 153(3) epc to a published international application that has entered the european phase

Free format text: ORIGINAL CODE: 0009012

AK Designated contracting states

Kind code of ref document: A2

Designated state(s): AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HU IE IS IT LI LT LU LV MC MT NL PL PT RO SE SI SK TR

AX Request for extension of the european patent

Extension state: AL BA HR MK YU

PUAL Search report despatched

Free format text: ORIGINAL CODE: 0009013

AK Designated contracting states

Kind code of ref document: A3

Designated state(s): AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HU IE IS IT LI LT LU LV MC MT NL PL PT RO SE SI SK TR

AX Request for extension of the european patent

Extension state: AL BA HR MK RS

RIC1 Information provided on ipc code assigned before grant

Ipc: F23R 3/00 20060101AFI20140630BHEP

Ipc: F23R 3/06 20060101ALI20140630BHEP

STAA Information on the status of an ep patent application or granted ep patent

Free format text: STATUS: THE APPLICATION HAS BEEN WITHDRAWN

18W Application withdrawn

Effective date: 20140812