EP1150072A3 - Gas turbine combustion chamber with supply openings - Google Patents

Gas turbine combustion chamber with supply openings Download PDF

Info

Publication number
EP1150072A3
EP1150072A3 EP01109768A EP01109768A EP1150072A3 EP 1150072 A3 EP1150072 A3 EP 1150072A3 EP 01109768 A EP01109768 A EP 01109768A EP 01109768 A EP01109768 A EP 01109768A EP 1150072 A3 EP1150072 A3 EP 1150072A3
Authority
EP
European Patent Office
Prior art keywords
combustion chamber
gas turbine
tube wall
flame tube
turbine combustion
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
EP01109768A
Other languages
German (de)
French (fr)
Other versions
EP1150072A2 (en
EP1150072B1 (en
Inventor
Thomas Dr.-Ing. Schilling
Thomas Dr.-Ing. Dörr
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 EP1150072A2 publication Critical patent/EP1150072A2/en
Publication of EP1150072A3 publication Critical patent/EP1150072A3/en
Application granted granted Critical
Publication of EP1150072B1 publication Critical patent/EP1150072B1/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
    • F23R3/28—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

Abstract

Die Erfindung betrifft eine Gasturbinenbrennkammer mit zumindest einem Pilotbrenner (2) und zumindest einem Hauptbrenner (3), welche zueinander axial und radial versetzt angeordnet sind, wobei die Brennkammer (1) eine äußere (4) und eine innere (5) Flammrohrwand umfasst, in welchen jeweils Öffnungen zur Zuleitung von Luft ausgebildet sind, wobei der Hauptbrenner (3) an die äußere Flammrohrwand (4) und der Pilotbrenner (2) angrenzend an die innere Flammrohrwand (5) angeordnet sind, dadurch gekennzeichnet, dass die äußere Flammrohrwand (4) mit einer ersten Anordnung (6) von Öffnungen versehen ist und dass in der inneren Flammrohrwand (5) eine zweite Anordnung (7) von Öffnungen ausgebildet ist.

Figure 00000001
The invention relates to a gas turbine combustion chamber with at least one pilot burner (2) and at least one main burner (3), which are axially and radially offset from one another, the combustion chamber (1) comprising an outer (4) and an inner (5) flame tube wall in which each have openings for supplying air, the main burner (3) being arranged on the outer flame tube wall (4) and the pilot burner (2) adjacent to the inner flame tube wall (5), characterized in that the outer flame tube wall (4) is provided with a first arrangement (6) of openings and that a second arrangement (7) of openings is formed in the inner flame tube wall (5).
Figure 00000001
EP01109768A 2000-04-27 2001-04-20 Gas turbine combustion chamber with supply openings Expired - Lifetime EP1150072B1 (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE10020598A DE10020598A1 (en) 2000-04-27 2000-04-27 Gas turbine combustion chamber with inlet openings
DE10020598 2000-04-27

Publications (3)

Publication Number Publication Date
EP1150072A2 EP1150072A2 (en) 2001-10-31
EP1150072A3 true EP1150072A3 (en) 2001-12-19
EP1150072B1 EP1150072B1 (en) 2006-07-05

Family

ID=7640079

Family Applications (1)

Application Number Title Priority Date Filing Date
EP01109768A Expired - Lifetime EP1150072B1 (en) 2000-04-27 2001-04-20 Gas turbine combustion chamber with supply openings

Country Status (3)

Country Link
US (1) US7654089B2 (en)
EP (1) EP1150072B1 (en)
DE (2) DE10020598A1 (en)

Families Citing this family (15)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2897143B1 (en) * 2006-02-08 2012-10-05 Snecma COMBUSTION CHAMBER OF A TURBOMACHINE
US8616004B2 (en) * 2007-11-29 2013-12-31 Honeywell International Inc. Quench jet arrangement for annular rich-quench-lean gas turbine combustors
US8171740B2 (en) * 2009-02-27 2012-05-08 Honeywell International Inc. Annular rich-quench-lean gas turbine combustors with plunged holes
US9416970B2 (en) * 2009-11-30 2016-08-16 United Technologies Corporation Combustor heat panel arrangement having holes offset from seams of a radially opposing heat panel
US8850819B2 (en) * 2010-06-25 2014-10-07 United Technologies Corporation Swirler, fuel and air assembly and combustor
US9416972B2 (en) * 2011-12-07 2016-08-16 Pratt & Whitney Canada Corp. Two-stage combustor for gas turbine engine
CN104755844B (en) 2012-10-24 2017-11-07 通用电器技术有限公司 Sequential combustion with diluent gas blender
JP2016516975A (en) * 2013-04-25 2016-06-09 ゼネラル エレクトリック テクノロジー ゲゼルシャフト ミット ベシュレンクテル ハフツングＧｅｎｅｒａｌ Ｅｌｅｃｔｒｉｃ Ｔｅｃｈｎｏｌｏｇｙ ＧｍｂＨ Multistage combustion with dilution gas
US11143407B2 (en) 2013-06-11 2021-10-12 Raytheon Technologies Corporation Combustor with axial staging for a gas turbine engine
EP2957833B1 (en) 2014-06-17 2018-10-24 Rolls-Royce Corporation Combustor assembly with chutes
US9453646B2 (en) * 2015-01-29 2016-09-27 General Electric Company Method for air entry in liner to reduce water requirement to control NOx
US11754284B2 (en) 2021-11-11 2023-09-12 General Electric Company Combustion liner
US11808454B2 (en) 2021-11-11 2023-11-07 General Electric Company Combustion liner
US11686473B2 (en) 2021-11-11 2023-06-27 General Electric Company Combustion liner
DE102021214499A1 (en) * 2021-12-16 2023-06-22 Rolls-Royce Deutschland Ltd & Co Kg Combustion chamber assembly with specifically positioned mixed air holes on inner and outer combustion chamber wall

Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4246758A (en) * 1977-09-02 1981-01-27 Societe Nationale D'etude Et De Construction De Moteurs D'aviation Antipollution combustion chamber
US5284019A (en) * 1990-06-12 1994-02-08 The United States Of America As Represented By The Secretary Of The Air Force Double dome, single anular combustor with daisy mixer
US5490380A (en) * 1992-06-12 1996-02-13 United Technologies Corporation Method for performing combustion
US5524430A (en) * 1992-01-28 1996-06-11 Societe National D'etude Et De Construction De Moteurs D'aviation S.N.E.C.M.A. Gas-turbine engine with detachable combustion chamber
US5642621A (en) * 1994-11-23 1997-07-01 Socoiete Nationale D'etude Et De Construction De Moteurs D'aviation S.N.E.C.M.A. Dual head combustion chamber
DE19720402A1 (en) * 1997-05-15 1998-11-19 Bmw Rolls Royce Gmbh Axially stepped annular combustion chamber for gas turbine
EP0913645A1 (en) * 1997-10-29 1999-05-06 SOCIETE NATIONALE D'ETUDE ET DE CONSTRUCTION DE MOTEURS D'AVIATION -Snecma Combustion chamber for a turbo-machine

Family Cites Families (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JPH05149543A (en) 1991-11-27 1993-06-15 Mitsubishi Heavy Ind Ltd Burner of gas turbine
DE59605505D1 (en) * 1995-03-08 2000-08-03 Rolls Royce Deutschland AXIAL STAGE DOUBLE RING COMBUSTION CHAMBER OF A GAS TURBINE
FR2748088B1 (en) * 1996-04-24 1998-05-29 Snecma OPTIMIZATION OF THE MIXTURE OF BURNED GASES IN AN ANNULAR COMBUSTION CHAMBER
US6240731B1 (en) 1997-12-31 2001-06-05 United Technologies Corporation Low NOx combustor for gas turbine engine
US6192689B1 (en) 1998-03-18 2001-02-27 General Electric Company Reduced emissions gas turbine combustor
US6474070B1 (en) * 1998-06-10 2002-11-05 General Electric Company Rich double dome combustor

Patent Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4246758A (en) * 1977-09-02 1981-01-27 Societe Nationale D'etude Et De Construction De Moteurs D'aviation Antipollution combustion chamber
US5284019A (en) * 1990-06-12 1994-02-08 The United States Of America As Represented By The Secretary Of The Air Force Double dome, single anular combustor with daisy mixer
US5524430A (en) * 1992-01-28 1996-06-11 Societe National D'etude Et De Construction De Moteurs D'aviation S.N.E.C.M.A. Gas-turbine engine with detachable combustion chamber
US5490380A (en) * 1992-06-12 1996-02-13 United Technologies Corporation Method for performing combustion
US5642621A (en) * 1994-11-23 1997-07-01 Socoiete Nationale D'etude Et De Construction De Moteurs D'aviation S.N.E.C.M.A. Dual head combustion chamber
DE19720402A1 (en) * 1997-05-15 1998-11-19 Bmw Rolls Royce Gmbh Axially stepped annular combustion chamber for gas turbine
EP0913645A1 (en) * 1997-10-29 1999-05-06 SOCIETE NATIONALE D'ETUDE ET DE CONSTRUCTION DE MOTEURS D'AVIATION -Snecma Combustion chamber for a turbo-machine

Also Published As

Publication number Publication date
DE10020598A1 (en) 2002-03-07
US20020017101A1 (en) 2002-02-14
EP1150072A2 (en) 2001-10-31
US7654089B2 (en) 2010-02-02
EP1150072B1 (en) 2006-07-05
DE50110374D1 (en) 2006-08-17

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