EP0924470A3 - Premix combustor for a gas turbine - Google Patents

Premix combustor for a gas turbine Download PDF

Info

Publication number
EP0924470A3
EP0924470A3 EP98123199A EP98123199A EP0924470A3 EP 0924470 A3 EP0924470 A3 EP 0924470A3 EP 98123199 A EP98123199 A EP 98123199A EP 98123199 A EP98123199 A EP 98123199A EP 0924470 A3 EP0924470 A3 EP 0924470A3
Authority
EP
European Patent Office
Prior art keywords
combustion
chamber
gas turbine
combustion zone
combustion chamber
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
EP98123199A
Other languages
German (de)
French (fr)
Other versions
EP0924470A2 (en
EP0924470B1 (en
Inventor
Nikolaos Dr. Zarzalis
Thomas Ripplinger
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.)
MTU Aero Engines AG
Original Assignee
MTU Motoren und Turbinen Union Muenchen GmbH
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
Priority claimed from DE1997156663 external-priority patent/DE19756663B4/en
Priority claimed from DE1998110648 external-priority patent/DE19810648A1/en
Application filed by MTU Motoren und Turbinen Union Muenchen GmbH filed Critical MTU Motoren und Turbinen Union Muenchen GmbH
Publication of EP0924470A2 publication Critical patent/EP0924470A2/en
Publication of EP0924470A3 publication Critical patent/EP0924470A3/en
Application granted granted Critical
Publication of EP0924470B1 publication Critical patent/EP0924470B1/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
    • F23R3/28—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
    • F23R3/34—Feeding into different combustion zones
    • F23R3/343—Pilot flames, i.e. fuel nozzles or injectors using only a very small proportion of the total fuel to insure continuous combustion
    • 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

Abstract

Vormischbrennkammer für eine Gasturbine, umfassend eine Hauptstufe mit mindestens einer Vormischkammer und einer wenigstens zum Teil rotationssymmetrisch zu ihrer Längsachse ausgebildeten Brennkammer mit einer Hauptverbrennungszone und einer stromabwärtigen Nachverbrennungszone, wobei die mindestens eine Vormischkammer tangential drallerzeugend in die Brennkammer mündet; und eine Pilotstufe mit einer Piloteinspritzvorrichtung, wobei die Hauptverbrennungszone in der Brennkammer im wesentlichen koaxial zur Nachverbrennungszone verläuft und die Pilotstufe an dem der Nachverbrennungszone entfernten Ende der Brennkammer angeordnet ist.

Figure 00000001
Premixing combustion chamber for a gas turbine, comprising a main stage with at least one premixing chamber and a combustion chamber which is at least partially rotationally symmetrical to its longitudinal axis and has a main combustion zone and a downstream post-combustion zone, the at least one premixing chamber opening into the combustion chamber tangentially generating swirl; and a pilot stage with a pilot injector, the main combustion zone in the combustion chamber being substantially coaxial with the post-combustion zone and the pilot stage being located at the end of the combustion chamber remote from the post-combustion zone.
Figure 00000001
EP98123199A 1997-12-19 1998-12-05 Premix combustor for a gas turbine Expired - Lifetime EP0924470B1 (en)

Applications Claiming Priority (4)

Application Number Priority Date Filing Date Title
DE1997156663 DE19756663B4 (en) 1997-12-19 1997-12-19 Premix combustion chamber for a gas turbine
DE19756663 1997-12-19
DE1998110648 DE19810648A1 (en) 1998-03-12 1998-03-12 Premix combustion chamber for gas turbine
DE19810648 1998-03-12

Publications (3)

Publication Number Publication Date
EP0924470A2 EP0924470A2 (en) 1999-06-23
EP0924470A3 true EP0924470A3 (en) 2001-03-14
EP0924470B1 EP0924470B1 (en) 2003-06-18

Family

ID=26042638

Family Applications (1)

Application Number Title Priority Date Filing Date
EP98123199A Expired - Lifetime EP0924470B1 (en) 1997-12-19 1998-12-05 Premix combustor for a gas turbine

Country Status (4)

Country Link
US (1) US6202420B1 (en)
EP (1) EP0924470B1 (en)
JP (1) JPH11248159A (en)
DE (1) DE59808754D1 (en)

Families Citing this family (24)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN100443806C (en) * 2006-05-16 2008-12-17 北京航空航天大学 Tangential standing vortex burning chamber
EP2299178B1 (en) * 2009-09-17 2015-11-04 Alstom Technology Ltd A method and gas turbine combustion system for safely mixing H2-rich fuels with air
CN102032597B (en) * 2010-11-29 2012-07-04 北京航空航天大学 Premixing pre-vaporization combustion chamber for main combustible stage of discrete pipe
US8978388B2 (en) 2011-06-03 2015-03-17 General Electric Company Load member for transition duct in turbine system
US8448450B2 (en) 2011-07-05 2013-05-28 General Electric Company Support assembly for transition duct in turbine system
US8650852B2 (en) 2011-07-05 2014-02-18 General Electric Company Support assembly for transition duct in turbine system
US9328623B2 (en) * 2011-10-05 2016-05-03 General Electric Company Turbine system
US8459041B2 (en) 2011-11-09 2013-06-11 General Electric Company Leaf seal for transition duct in turbine system
US8974179B2 (en) 2011-11-09 2015-03-10 General Electric Company Convolution seal for transition duct in turbine system
US8701415B2 (en) 2011-11-09 2014-04-22 General Electric Company Flexible metallic seal for transition duct in turbine system
CN102393028B (en) * 2011-12-09 2013-08-28 中国船舶重工集团公司第七�三研究所 Dry-type low-emission combustion chamber of natural gas fuel turbine
US9133722B2 (en) 2012-04-30 2015-09-15 General Electric Company Transition duct with late injection in turbine system
US9038394B2 (en) 2012-04-30 2015-05-26 General Electric Company Convolution seal for transition duct in turbine system
US8707673B1 (en) 2013-01-04 2014-04-29 General Electric Company Articulated transition duct in turbomachine
US9080447B2 (en) 2013-03-21 2015-07-14 General Electric Company Transition duct with divided upstream and downstream portions
CN103266922B (en) * 2013-06-15 2014-11-12 厦门大学 Turbine stator blade with interstage combustor
US9458732B2 (en) 2013-10-25 2016-10-04 General Electric Company Transition duct assembly with modified trailing edge in turbine system
US10260360B2 (en) 2016-03-24 2019-04-16 General Electric Company Transition duct assembly
US10227883B2 (en) 2016-03-24 2019-03-12 General Electric Company Transition duct assembly
US10145251B2 (en) 2016-03-24 2018-12-04 General Electric Company Transition duct assembly
US10260752B2 (en) 2016-03-24 2019-04-16 General Electric Company Transition duct assembly with late injection features
US10260424B2 (en) 2016-03-24 2019-04-16 General Electric Company Transition duct assembly with late injection features
EP3755946A1 (en) * 2018-02-23 2020-12-30 Fulton Group N.A., Inc. Inward-firing premix fuel combustion burner
CN109113895B (en) * 2018-09-11 2019-08-27 中国人民解放军国防科技大学 Flame stabilizing device of ramjet engine

Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2552492A (en) * 1948-06-07 1951-05-08 Power Jets Res & Dev Ltd Air ducting arrangement for combustion chambers
DE2944863A1 (en) * 1979-11-07 1981-05-27 Daimler-Benz Ag, 7000 Stuttgart Gas-turbine combustion chamber - has tangential inlet for fine granular fuel and air near end wall
US5473882A (en) * 1993-06-03 1995-12-12 Mtu Motoren-Und Turbinen-Union Munchen Gmbh Combustion apparatus for a gas turbine having separate combustion and vaporization zones
EP0870990A1 (en) * 1997-03-20 1998-10-14 Asea Brown Boveri AG Gas turbine with toroidal combustor

Family Cites Families (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3872664A (en) * 1973-10-15 1975-03-25 United Aircraft Corp Swirl combustor with vortex burning and mixing
US3958416A (en) 1974-12-12 1976-05-25 General Motors Corporation Combustion apparatus
US4204402A (en) * 1976-05-07 1980-05-27 The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration Reduction of nitric oxide emissions from a combustor
US4498288A (en) * 1978-10-13 1985-02-12 General Electric Company Fuel injection staged sectoral combustor for burning low-BTU fuel gas
CH672366A5 (en) * 1986-12-09 1989-11-15 Bbc Brown Boveri & Cie
JPH01114623A (en) * 1987-10-27 1989-05-08 Toshiba Corp Gas turbine combustor
GB9023004D0 (en) 1990-10-23 1990-12-05 Rolls Royce Plc A gas turbine engine combustion chamber and a method of operating a gas turbine engine combustion chamber
CA2124069A1 (en) 1993-05-24 1994-11-25 Boris M. Kramnik Low emission, fixed geometry gas turbine combustor
JP2950720B2 (en) * 1994-02-24 1999-09-20 株式会社東芝 Gas turbine combustion device and combustion control method therefor
US5687571A (en) * 1995-02-20 1997-11-18 Asea Brown Boveri Ag Combustion chamber with two-stage combustion

Patent Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2552492A (en) * 1948-06-07 1951-05-08 Power Jets Res & Dev Ltd Air ducting arrangement for combustion chambers
DE2944863A1 (en) * 1979-11-07 1981-05-27 Daimler-Benz Ag, 7000 Stuttgart Gas-turbine combustion chamber - has tangential inlet for fine granular fuel and air near end wall
US5473882A (en) * 1993-06-03 1995-12-12 Mtu Motoren-Und Turbinen-Union Munchen Gmbh Combustion apparatus for a gas turbine having separate combustion and vaporization zones
EP0870990A1 (en) * 1997-03-20 1998-10-14 Asea Brown Boveri AG Gas turbine with toroidal combustor

Also Published As

Publication number Publication date
US6202420B1 (en) 2001-03-20
EP0924470A2 (en) 1999-06-23
EP0924470B1 (en) 2003-06-18
DE59808754D1 (en) 2003-07-24
JPH11248159A (en) 1999-09-14

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