US3854285A - Combustor dome assembly - Google Patents

Combustor dome assembly Download PDF

Info

Publication number
US3854285A
US3854285A US00335684A US33568473A US3854285A US 3854285 A US3854285 A US 3854285A US 00335684 A US00335684 A US 00335684A US 33568473 A US33568473 A US 33568473A US 3854285 A US3854285 A US 3854285A
Authority
US
United States
Prior art keywords
mounting ring
liner
dome
coolant
assembly
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.)
Expired - Lifetime
Application number
US00335684A
Other languages
English (en)
Inventor
R Stenger
A Gardella
T Campbell
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
General Electric Co
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 General Electric Co filed Critical General Electric Co
Priority to US00335684A priority Critical patent/US3854285A/en
Priority to CA191,797A priority patent/CA1005242A/en
Priority to GB669974A priority patent/GB1459591A/en
Priority to DE19742408818 priority patent/DE2408818A1/de
Priority to JP49022010A priority patent/JPS5024617A/ja
Priority to FR7406495A priority patent/FR2219311A1/fr
Priority to BE141381A priority patent/BE811568A/xx
Application granted granted Critical
Publication of US3854285A publication Critical patent/US3854285A/en
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

Links

Images

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
    • F23R3/42—Continuous combustion chambers using liquid or gaseous fuel characterised by the arrangement or form of the flame tubes or combustion chambers
    • F23R3/50—Combustion chambers comprising an annular flame tube within an annular casing
    • 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

Definitions

  • the actual combustion occurs within a combustion zone or space defined by a pair of combustion liners or walls.
  • the upstream end of the combustion zone is normally defined by a dome member which is connected to the combustion liners and which is adapted to provide openings for a plurality of fuel/air carbureting devices, which provide the combustion zone with a continuous flow of high energy fuel.
  • the dome memher is surrounded by a snout assembly which is located immediately downstream of the compressor section of the engine and defines an inlet through which a major portion of the combustion air flows.
  • the combustion liners are normally of perforated construction to permit large quantities of air to flow therethrough into the combustion space to support the combustion process and to dilute the combustion products to provide a desired turbine temperature. Cool compressor air is supplied to the space surrounding the liners and to the inlet formed by the snout assembly.
  • a combustor dome plate which includes a pair of embossed mounting rings which extend upstream from the dome plate and are adapted to be connected to a pair of combustor liners, which form the combustion zone, and to a pair of snout rings which form an inlet plenum upstream of the combustion zone.
  • Each of the mounting rings includes a corrugated wiggle strip at its downstream end which cooperates with the dome plate to form a first plurality of coolant flow passages therebetween.
  • FIG. 1 is a partial, cross-sectional view of the combustion apparatus of a gas turbine engine, with the combustion apparatus including the improved film assembly joint construction of this invention;
  • FIG. 5 is an enlarged, cross-sectional view, with portions deleted, taken generally along line 5-5 of FIG.
  • FIG. 6 is an enlarged, sectional view, with portions deleted, taken along line 6-6 of FIG. 3;
  • FIG. 7 is an exploded view, similar to FIG. 2, showing an alternative embodiment
  • FIG. 10 is an enlarged, sectional view, with portions deleted, taken along line 1010 of FIG. 8.
  • Each of the cooling passages 76 lies in fluid flow communication with the inlet plenum 50, and the bolts 68 and nuts are positioned a sufficient distance upstream from the inlet of the coolant passages 76, as shown in FIG. 3, so as to have little effect on the coolant flow therethrough.
  • the inner mounting ring 40 and the snout ring 46 could be made identical to the outer mounting ring 42 and outer snout ring 44, a suitable alternative design is shown in FIGS. 7 10 which will provide the same continuous film cooling for the upstream panel of the combustion liner.
  • the inner mounting ring 40 includes a forward end cylindrical ring 84, a conical intermediate portion 86 and a downstream embossed wiggle strip 88.
  • the wiggle strip 88 is similar to the wiggle strip 58 in that it includes outer flat sections 90 and inner flat sections 92 which are interconnected to one another by a small angled rib member 94.
  • the upstream cylindrical portion 84 of the inner mounting ring 40 is provided with a plurality of equally spaced holes 100 which are adapted to cooperate with a like number of holes 102 located in the inner liner 18.
  • the holes 100 and 102 are further adapted to align with holes 104 located in the snout ring 46 such that the snout ring 46, the liner l8, and the inner mounting ring 40 may be suitably interconnected by some suitable fastening means, such as the bolts 106 and nuts 108.
  • the liner 18 cooperates with the intermediate portion 86 of the mounting ring 40 to form a coolant chamber 110.
  • the chamber 110 is fluidically connected to the inlet plenum 50 by means of a plurality of holes 112 (FIG. 8) located within the intermediate portion 86 of the mounting ring 40.
  • the liner l8 and the outer fiat portions 90 of the wiggle strip 88 cooperate as shown in FIG. 9 to form a plurality of coolant passages 114, one of which is positioned between each pair of the coolant passages 98 as shown in FIG. 10.
  • the coolant passage 78 communicates directly with inlet plenum 50, and the coolant passage 114 lies in fluid flow communication with the chamber 110 which is supplied with coolant through the holes 112 from inlet plenum 50.
  • the coolant passages 98 and 1 14 act to provide a continuous film of coolant on the inner side 116 of upstream panel of the inner combustor liner 18.
  • both the inner mounting ring 40 and the outer mounting ring 42 provide an assembly which yields a continuous film coolant on the inner side of an upstream panel of a combustor liner.
  • the inner mounting ring 40 and the outer mounting ring 42 are distinguished by the fact that the outer mounting ring 42 includes the plurality of dimples 52, whereas the inner mounting ring 40 provides a continuous annular chamber 110.
  • the outer mounting ring 42 may be more susceptible to use where it is desirable to have the fastening means, such as the bolts 68, located close to the joint between the dome plate and the combustion liner, whereas the inner mounting ring 40 may be more appropriate for use in situations where the fastening means can be located a greater distance away from the joint.
  • either case provides a continuous film of coolant on the upstream panel of the combustion liner and further provides a system wherein the fastening means are located entirely outside of the high temperature combustion zone.
  • either of the abovedescribed devices provides an assembly in which the fastening means are positioned a sufficient distance upstream of the cooling passages such that the fastening means will not cause wakes to appear in the coolant flow. In this manner, the need for wake reduction holes in the combustion liner is eliminated.
  • a combustor assembly including a pair of combustor liners radially spaced from one another and adapted to form a combustion zone therebetween, a dome assembly adapted to be positioned between said liners and to cooperate therewith to form the upstream end of said combustion zone, and a pair of snout rings adapted to surround said dome assembly and to define an inlet plenum upstream of said combustion zone, the improvement comprising:
  • first connecting and said second connecting means comprises a plurality of bolts and nuts and said nuts are mounted to the inner side of said first and second mounting rings.

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)
  • Combustion Of Fluid Fuel (AREA)
US00335684A 1973-02-26 1973-02-26 Combustor dome assembly Expired - Lifetime US3854285A (en)

Priority Applications (7)

Application Number Priority Date Filing Date Title
US00335684A US3854285A (en) 1973-02-26 1973-02-26 Combustor dome assembly
CA191,797A CA1005242A (en) 1973-02-26 1974-02-05 Combustor dome assembly for a gas turbine engine
GB669974A GB1459591A (en) 1973-02-26 1974-02-14 Combustion equipment
DE19742408818 DE2408818A1 (de) 1973-02-26 1974-02-23 Brenner-dom-anordnung
JP49022010A JPS5024617A (GUID-C5D7CC26-194C-43D0-91A1-9AE8C70A9BFF.html) 1973-02-26 1974-02-26
FR7406495A FR2219311A1 (GUID-C5D7CC26-194C-43D0-91A1-9AE8C70A9BFF.html) 1973-02-26 1974-02-26
BE141381A BE811568A (fr) 1973-02-26 1974-02-26 Chambre de combustion

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US00335684A US3854285A (en) 1973-02-26 1973-02-26 Combustor dome assembly

Publications (1)

Publication Number Publication Date
US3854285A true US3854285A (en) 1974-12-17

Family

ID=23312822

Family Applications (1)

Application Number Title Priority Date Filing Date
US00335684A Expired - Lifetime US3854285A (en) 1973-02-26 1973-02-26 Combustor dome assembly

Country Status (7)

Country Link
US (1) US3854285A (GUID-C5D7CC26-194C-43D0-91A1-9AE8C70A9BFF.html)
JP (1) JPS5024617A (GUID-C5D7CC26-194C-43D0-91A1-9AE8C70A9BFF.html)
BE (1) BE811568A (GUID-C5D7CC26-194C-43D0-91A1-9AE8C70A9BFF.html)
CA (1) CA1005242A (GUID-C5D7CC26-194C-43D0-91A1-9AE8C70A9BFF.html)
DE (1) DE2408818A1 (GUID-C5D7CC26-194C-43D0-91A1-9AE8C70A9BFF.html)
FR (1) FR2219311A1 (GUID-C5D7CC26-194C-43D0-91A1-9AE8C70A9BFF.html)
GB (1) GB1459591A (GUID-C5D7CC26-194C-43D0-91A1-9AE8C70A9BFF.html)

Cited By (36)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3898797A (en) * 1973-08-16 1975-08-12 Rolls Royce Cooling arrangements for duct walls
US3903754A (en) * 1974-06-07 1975-09-09 Pino International Ltd Bicycle crank hub assembly
US3990232A (en) * 1975-12-11 1976-11-09 General Electric Company Combustor dome assembly having improved cooling means
US4222230A (en) * 1978-08-14 1980-09-16 General Electric Company Combustor dome assembly
US4532762A (en) * 1982-07-22 1985-08-06 The Garrett Corporation Gas turbine engine variable geometry combustor apparatus
US5012645A (en) * 1987-08-03 1991-05-07 United Technologies Corporation Combustor liner construction for gas turbine engine
US5142871A (en) * 1991-01-22 1992-09-01 General Electric Company Combustor dome plate support having uniform thickness arcuate apex with circumferentially spaced coolant apertures
US5181377A (en) * 1991-04-16 1993-01-26 General Electric Company Damped combustor cowl structure
US5265409A (en) * 1992-12-18 1993-11-30 United Technologies Corporation Uniform cooling film replenishment thermal liner assembly
US5329761A (en) * 1991-07-01 1994-07-19 General Electric Company Combustor dome assembly
US5329772A (en) * 1992-12-09 1994-07-19 General Electric Company Cast slot-cooled single nozzle combustion liner cap
US5353587A (en) * 1992-06-12 1994-10-11 General Electric Company Film cooling starter geometry for combustor lines
US5924288A (en) * 1994-12-22 1999-07-20 General Electric Company One-piece combustor cowl
US20030115879A1 (en) * 2001-12-21 2003-06-26 Mitsubishi Heavy Industries Ltd. Gas turbine combustor
US6672067B2 (en) * 2002-02-27 2004-01-06 General Electric Company Corrugated cowl for combustor of a gas turbine engine and method for configuring same
US6711900B1 (en) * 2003-02-04 2004-03-30 Pratt & Whitney Canada Corp. Combustor liner V-band design
US20040074236A1 (en) * 2001-06-27 2004-04-22 Shigemi Mandai Gas turbine combustor
US6725667B2 (en) 2002-08-22 2004-04-27 General Electric Company Combustor dome for gas turbine engine
US20060053798A1 (en) * 2004-09-10 2006-03-16 Honeywell International Inc. Waffled impingement effusion method
US20060242939A1 (en) * 2005-04-28 2006-11-02 Snecma Easily demountable combustion chamber with improved aerodynamic performance
US20080010997A1 (en) * 2006-02-08 2008-01-17 Snecma Turbine engine combustion chamber with tangential slots
US20080072603A1 (en) * 2006-09-22 2008-03-27 Snecma Annular turbomachine combustion chamber
US20080110022A1 (en) * 2006-11-10 2008-05-15 Daniel Dale Brown Combustor dome mixer retaining means
US20080110174A1 (en) * 2006-11-10 2008-05-15 Daniel Dale Brown Combustor dome and methods of assembling such
US20080155988A1 (en) * 2006-08-28 2008-07-03 Snecma Annular combustion chamber for a turbomachine
US20080236164A1 (en) * 2007-03-27 2008-10-02 Snecma Fairing for a combustion chamber end wall
US20100050640A1 (en) * 2008-08-29 2010-03-04 General Electric Company Thermally compliant combustion cap device and system
US7757495B2 (en) * 2006-02-08 2010-07-20 Snecma Turbine engine annular combustion chamber with alternate fixings
US20100205969A1 (en) * 2007-10-24 2010-08-19 Man Turbo Ag Burner for a Turbo Machine, Baffle plate for Such a Burner and a Turbo Machine Having Such a Burner
US20110000216A1 (en) * 2009-07-06 2011-01-06 Kawasaki Jukogyo Kabushiki Kaisha Gas turbine combustor
US20120192567A1 (en) * 2010-12-30 2012-08-02 Rolls-Royce Corporation Gas turbine engine flange assembly including flow circuit
US20160018109A1 (en) * 2013-03-13 2016-01-21 Siemens Aktiengesellschaft Jet burner with cooling duct in the base plate
DE102015213629A1 (de) * 2015-07-20 2017-01-26 Rolls-Royce Deutschland Ltd & Co Kg Abdeckteil und Brennkammerbaugruppe für eine Gasturbine
US10619856B2 (en) * 2017-03-13 2020-04-14 Rolls-Royce Corporation Notched gas turbine combustor cowl
US10982852B2 (en) 2018-11-05 2021-04-20 Rolls-Royce Corporation Cowl integration to combustor wall
US11859819B2 (en) 2021-10-15 2024-01-02 General Electric Company Ceramic composite combustor dome and liners

Families Citing this family (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JPS5363208U (GUID-C5D7CC26-194C-43D0-91A1-9AE8C70A9BFF.html) * 1976-10-30 1978-05-29
JPS5556521A (en) * 1978-10-23 1980-04-25 Hitachi Ltd Combustion device
JPS58106541U (ja) * 1982-01-13 1983-07-20 アイシン精機株式会社 スタ−リング機関用燃焼器
JP3415663B2 (ja) * 1992-12-28 2003-06-09 アルストム 冷却面を衝撃式に冷却するための装置
DE4244302C2 (de) * 1992-12-28 2002-08-29 Alstom Vorrichtung zur Prallkühlung
DE4244303A1 (de) * 1992-12-28 1994-06-30 Abb Research Ltd Vorrichtung zur Prallkühlung
US7051532B2 (en) * 2003-10-17 2006-05-30 General Electric Company Methods and apparatus for film cooling gas turbine engine combustors

Citations (11)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2537033A (en) * 1947-07-18 1951-01-09 Westinghouse Electric Corp Gas turbine combustion chamber construction
US2549858A (en) * 1946-07-30 1951-04-24 Westinghouse Electric Corp Annular combustion chamber having telescoping walls with corrugated ends for spacing
GB697027A (en) * 1950-11-27 1953-09-16 Lucas Ltd Joseph Combustion chambers for prime movers
GB710353A (en) * 1951-06-18 1954-06-09 Rolls Royce Improvements in or relating to combustion equipment for gas-turbine engines
GB736028A (en) * 1952-11-29 1955-08-31 Lucas Industries Ltd Combustion chambers for prime movers
US3038309A (en) * 1959-07-21 1962-06-12 Gen Electric Cooling liner for jet engine afterburner
US3064425A (en) * 1959-10-05 1962-11-20 Gen Motors Corp Combustion liner
US3307354A (en) * 1965-10-01 1967-03-07 Gen Electric Cooling structure for overlapped panels
US3385055A (en) * 1966-11-23 1968-05-28 United Aircraft Corp Combustion chamber with floating swirler rings
US3408812A (en) * 1967-02-24 1968-11-05 Gen Electric Cooled joint construction for combustion wall means
US3458997A (en) * 1966-08-18 1969-08-05 Lucas Industries Ltd Supports for fuel burners

Patent Citations (11)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2549858A (en) * 1946-07-30 1951-04-24 Westinghouse Electric Corp Annular combustion chamber having telescoping walls with corrugated ends for spacing
US2537033A (en) * 1947-07-18 1951-01-09 Westinghouse Electric Corp Gas turbine combustion chamber construction
GB697027A (en) * 1950-11-27 1953-09-16 Lucas Ltd Joseph Combustion chambers for prime movers
GB710353A (en) * 1951-06-18 1954-06-09 Rolls Royce Improvements in or relating to combustion equipment for gas-turbine engines
GB736028A (en) * 1952-11-29 1955-08-31 Lucas Industries Ltd Combustion chambers for prime movers
US3038309A (en) * 1959-07-21 1962-06-12 Gen Electric Cooling liner for jet engine afterburner
US3064425A (en) * 1959-10-05 1962-11-20 Gen Motors Corp Combustion liner
US3307354A (en) * 1965-10-01 1967-03-07 Gen Electric Cooling structure for overlapped panels
US3458997A (en) * 1966-08-18 1969-08-05 Lucas Industries Ltd Supports for fuel burners
US3385055A (en) * 1966-11-23 1968-05-28 United Aircraft Corp Combustion chamber with floating swirler rings
US3408812A (en) * 1967-02-24 1968-11-05 Gen Electric Cooled joint construction for combustion wall means

Cited By (52)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3898797A (en) * 1973-08-16 1975-08-12 Rolls Royce Cooling arrangements for duct walls
US3903754A (en) * 1974-06-07 1975-09-09 Pino International Ltd Bicycle crank hub assembly
US3990232A (en) * 1975-12-11 1976-11-09 General Electric Company Combustor dome assembly having improved cooling means
US4222230A (en) * 1978-08-14 1980-09-16 General Electric Company Combustor dome assembly
US4532762A (en) * 1982-07-22 1985-08-06 The Garrett Corporation Gas turbine engine variable geometry combustor apparatus
US5012645A (en) * 1987-08-03 1991-05-07 United Technologies Corporation Combustor liner construction for gas turbine engine
US5142871A (en) * 1991-01-22 1992-09-01 General Electric Company Combustor dome plate support having uniform thickness arcuate apex with circumferentially spaced coolant apertures
US5181377A (en) * 1991-04-16 1993-01-26 General Electric Company Damped combustor cowl structure
US5329761A (en) * 1991-07-01 1994-07-19 General Electric Company Combustor dome assembly
US5353587A (en) * 1992-06-12 1994-10-11 General Electric Company Film cooling starter geometry for combustor lines
US5479772A (en) * 1992-06-12 1996-01-02 General Electric Company Film cooling starter geometry for combustor liners
US5423368A (en) * 1992-12-09 1995-06-13 General Electric Company Method of forming slot-cooled single nozzle combustion liner cap
US5329772A (en) * 1992-12-09 1994-07-19 General Electric Company Cast slot-cooled single nozzle combustion liner cap
US5265409A (en) * 1992-12-18 1993-11-30 United Technologies Corporation Uniform cooling film replenishment thermal liner assembly
US5924288A (en) * 1994-12-22 1999-07-20 General Electric Company One-piece combustor cowl
US20040074236A1 (en) * 2001-06-27 2004-04-22 Shigemi Mandai Gas turbine combustor
US7032386B2 (en) * 2001-06-27 2006-04-25 Mitsubishi Heavy Industries, Ltd. Gas turbine combustor
US20030115879A1 (en) * 2001-12-21 2003-06-26 Mitsubishi Heavy Industries Ltd. Gas turbine combustor
US7013647B2 (en) * 2001-12-21 2006-03-21 Mitsubishi Heavy Industries, Ltd. Outer casing covering gas turbine combustor
EP1340941A3 (en) * 2002-02-27 2004-06-09 General Electric Company Corrugated cowl for combustor of a gas turbine engine and method for configuring the same
US6672067B2 (en) * 2002-02-27 2004-01-06 General Electric Company Corrugated cowl for combustor of a gas turbine engine and method for configuring same
US6725667B2 (en) 2002-08-22 2004-04-27 General Electric Company Combustor dome for gas turbine engine
US6711900B1 (en) * 2003-02-04 2004-03-30 Pratt & Whitney Canada Corp. Combustor liner V-band design
US20060053798A1 (en) * 2004-09-10 2006-03-16 Honeywell International Inc. Waffled impingement effusion method
US7219498B2 (en) * 2004-09-10 2007-05-22 Honeywell International, Inc. Waffled impingement effusion method
US20060242939A1 (en) * 2005-04-28 2006-11-02 Snecma Easily demountable combustion chamber with improved aerodynamic performance
US7637111B2 (en) * 2005-04-28 2009-12-29 Snecma Easily demountable combustion chamber with improved aerodynamic performance
US20080010997A1 (en) * 2006-02-08 2008-01-17 Snecma Turbine engine combustion chamber with tangential slots
US7673457B2 (en) * 2006-02-08 2010-03-09 Snecma Turbine engine combustion chamber with tangential slots
US7757495B2 (en) * 2006-02-08 2010-07-20 Snecma Turbine engine annular combustion chamber with alternate fixings
US20080155988A1 (en) * 2006-08-28 2008-07-03 Snecma Annular combustion chamber for a turbomachine
US8387395B2 (en) * 2006-08-28 2013-03-05 Snecma Annular combustion chamber for a turbomachine
US20080072603A1 (en) * 2006-09-22 2008-03-27 Snecma Annular turbomachine combustion chamber
US7971439B2 (en) * 2006-09-22 2011-07-05 Snecma Annular turbomachine combustion chamber
US7856826B2 (en) 2006-11-10 2010-12-28 General Electric Company Combustor dome mixer retaining means
US20080110174A1 (en) * 2006-11-10 2008-05-15 Daniel Dale Brown Combustor dome and methods of assembling such
US7765809B2 (en) 2006-11-10 2010-08-03 General Electric Company Combustor dome and methods of assembling such
US20080110022A1 (en) * 2006-11-10 2008-05-15 Daniel Dale Brown Combustor dome mixer retaining means
US20080236164A1 (en) * 2007-03-27 2008-10-02 Snecma Fairing for a combustion chamber end wall
US7861531B2 (en) * 2007-03-27 2011-01-04 Snecma Fairing for a combustion chamber end wall
US20100205969A1 (en) * 2007-10-24 2010-08-19 Man Turbo Ag Burner for a Turbo Machine, Baffle plate for Such a Burner and a Turbo Machine Having Such a Burner
US20100050640A1 (en) * 2008-08-29 2010-03-04 General Electric Company Thermally compliant combustion cap device and system
US20110000216A1 (en) * 2009-07-06 2011-01-06 Kawasaki Jukogyo Kabushiki Kaisha Gas turbine combustor
US8511088B2 (en) * 2009-07-06 2013-08-20 Kawasaki Jukogyo Kabushiki Kaisha Gas turbine fuel injector mounting system
US20120192567A1 (en) * 2010-12-30 2012-08-02 Rolls-Royce Corporation Gas turbine engine flange assembly including flow circuit
US8899051B2 (en) * 2010-12-30 2014-12-02 Rolls-Royce Corporation Gas turbine engine flange assembly including flow circuit
US20160018109A1 (en) * 2013-03-13 2016-01-21 Siemens Aktiengesellschaft Jet burner with cooling duct in the base plate
US10088163B2 (en) * 2013-03-13 2018-10-02 Siemens Aktiengesellschaft Jet burner with cooling duct in the base plate
DE102015213629A1 (de) * 2015-07-20 2017-01-26 Rolls-Royce Deutschland Ltd & Co Kg Abdeckteil und Brennkammerbaugruppe für eine Gasturbine
US10619856B2 (en) * 2017-03-13 2020-04-14 Rolls-Royce Corporation Notched gas turbine combustor cowl
US10982852B2 (en) 2018-11-05 2021-04-20 Rolls-Royce Corporation Cowl integration to combustor wall
US11859819B2 (en) 2021-10-15 2024-01-02 General Electric Company Ceramic composite combustor dome and liners

Also Published As

Publication number Publication date
JPS5024617A (GUID-C5D7CC26-194C-43D0-91A1-9AE8C70A9BFF.html) 1975-03-15
DE2408818A1 (de) 1974-09-05
CA1005242A (en) 1977-02-15
GB1459591A (en) 1976-12-22
FR2219311A1 (GUID-C5D7CC26-194C-43D0-91A1-9AE8C70A9BFF.html) 1974-09-20
BE811568A (fr) 1974-06-17

Similar Documents

Publication Publication Date Title
US3854285A (en) Combustor dome assembly
EP0284819B1 (en) Gas turbine combustor transition duct forced convection cooling
US8015817B2 (en) Cooling structure for gas turbine transition duct
US4805397A (en) Combustion chamber structure for a turbojet engine
US4195476A (en) Combustor construction
US7010921B2 (en) Method and apparatus for cooling combustor liner and transition piece of a gas turbine
US6494044B1 (en) Aerodynamic devices for enhancing sidepanel cooling on an impingement cooled transition duct and related method
US4232527A (en) Combustor liner joints
US4622821A (en) Combustion liner for a gas turbine engine
JP4433529B2 (ja) 多穴膜冷却燃焼器ライナ
US3793827A (en) Stiffener for combustor liner
EP0471437B1 (en) Gas turbine engine combustor
CA1156843A (en) Combustor liner construction
US3899882A (en) Gas turbine combustor basket cooling
US4700544A (en) Combustors
US4380906A (en) Combustion liner cooling scheme
US8544277B2 (en) Turbulated aft-end liner assembly and cooling method
US4191011A (en) Mount assembly for porous transition panel at annular combustor outlet
US3307354A (en) Cooling structure for overlapped panels
US6711900B1 (en) Combustor liner V-band design
JPS62272018A (ja) 環状燃焼室の摺動ジョイント部の構造
US5421158A (en) Segmented centerbody for a double annular combustor
CA2920188C (en) Combustor dome heat shield
WO1996018850A1 (en) Bulkhead cooling fairing
WO2018084943A1 (en) Cooled combustor case with over-pressurized cooling air