EP2317227A3 - Burner for a turbine and gas turbine with same - Google Patents

Burner for a turbine and gas turbine with same Download PDF

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Publication number
EP2317227A3
EP2317227A3 EP10171616.5A EP10171616A EP2317227A3 EP 2317227 A3 EP2317227 A3 EP 2317227A3 EP 10171616 A EP10171616 A EP 10171616A EP 2317227 A3 EP2317227 A3 EP 2317227A3
Authority
EP
European Patent Office
Prior art keywords
subspace
burner
chamber
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
EP10171616.5A
Other languages
German (de)
French (fr)
Other versions
EP2317227A2 (en
EP2317227B1 (en
Inventor
Frank Reiss
Jaman El Masalme
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.)
MAN Energy Solutions SE
Original Assignee
MAN Diesel and Turbo SE
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 MAN Diesel and Turbo SE filed Critical MAN Diesel and Turbo SE
Publication of EP2317227A2 publication Critical patent/EP2317227A2/en
Publication of EP2317227A3 publication Critical patent/EP2317227A3/en
Application granted granted Critical
Publication of EP2317227B1 publication Critical patent/EP2317227B1/en
Active legal-status Critical Current
Anticipated expiration legal-status Critical

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
    • F23R3/10—Air inlet arrangements for primary air
    • F23R3/12—Air inlet arrangements for primary air inducing a vortex
    • F23R3/14—Air inlet arrangements for primary air inducing a vortex by using swirl vanes
    • 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
    • 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
    • F23R3/286—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply having fuel-air premixing devices
    • 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
    • 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
    • F23R2900/03044—Impingement cooled combustion chamber walls or subassemblies
    • 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
    • F23R2900/03045—Convection cooled combustion chamber walls provided with turbolators or means for creating turbulences to increase cooling
    • 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
    • F23R3/26—Controlling the air flow
    • 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

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Gas Burners (AREA)

Abstract

Brenner für eine Turbine und damit ausgerüstete Gasturbine wobei der Brenner aufweist ein Gehäuse (10), in dem ein Luftsammelraum (13), ein Verbrennungsvorraum (16) und ein Brennraum ausgebildet sind, eine Brenner-Kopfplatte (40), die in dem Gehäuse angeordnet ist, so dass die Brenner-Kopfplatte den Verbrennungsvorraum von dem Brennraum trennt eine Prallplatte (30), die in dem Verbrennungsvorraum angeordnet ist, so dass die Prallplatte den Verbrennungsvorraum in einen an eine mit dem Luftsammelraum fluidverbundene Luftzuführung angrenzenden ersten Teilraum (16a) und einen an die Brenner-Kopfplatte angrenzenden zweiten Teilraum (16b) unterteilt, wobei die Prallplatte eine Mehrzahl von Durchgangspassagen aufweist, die den ersten Teilraum (16a) mit dem zweiten Teilraum (16b) so dass Über die Luftzufhrung aus dem Luftsammelraum in den ersten Teilraum eingeströmte Luft über die Durchgangspassagen (31) in den zweiten Teilraum einströmen und auf eine dem zweiten Teilraum zugewandte Rückfläche (40a) der Brenner-Kopfplatte strömen kann.

Figure imgaf001
A burner for a turbine and gas turbine equipped therewith, wherein the burner has a housing (10) in which an air collecting space (13), a combustion pre-chamber (16) and a combustion chamber are formed, a burner head plate (40) disposed in the housing is, so that the burner head plate separates the combustion pre-chamber from the combustion chamber, a baffle plate (30) which is arranged in the combustion pre-space, so that the baffle plate in a combustion chamber adjacent to an air intake connected to the air intake chamber first subspace (16a) and a subdivided to the burner head plate second subspace (16b), wherein the baffle plate has a plurality of through passages, the first subspace (16a) with the second subspace (16b) so that via the air supply from the air collecting space in the first subspace air flowed via the through passages (31) flow into the second subspace and on an R facing the second subspace ückfläche (40 a) of the burner top plate can flow.
Figure imgaf001
EP10171616.5A 2009-10-28 2010-08-02 Burner for a turbine and gas turbine with same Active EP2317227B1 (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
DE102009046066A DE102009046066A1 (en) 2009-10-28 2009-10-28 Burner for a turbine and thus equipped gas turbine

Publications (3)

Publication Number Publication Date
EP2317227A2 EP2317227A2 (en) 2011-05-04
EP2317227A3 true EP2317227A3 (en) 2017-09-13
EP2317227B1 EP2317227B1 (en) 2019-10-02

Family

ID=43532770

Family Applications (1)

Application Number Title Priority Date Filing Date
EP10171616.5A Active EP2317227B1 (en) 2009-10-28 2010-08-02 Burner for a turbine and gas turbine with same

Country Status (5)

Country Link
US (1) US9140452B2 (en)
EP (1) EP2317227B1 (en)
JP (1) JP5160616B2 (en)
CA (1) CA2714259C (en)
DE (1) DE102009046066A1 (en)

Families Citing this family (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102011082884A1 (en) 2011-09-16 2013-03-21 Man Diesel & Turbo Se Burner and gas turbine with such a burner
US10612781B2 (en) * 2014-11-07 2020-04-07 United Technologies Corporation Combustor wall aperture body with cooling circuit
EP3478941B1 (en) * 2016-08-30 2021-02-24 Siemens Energy Global GmbH & Co. KG Impingement cooling features for gas turbines
CN110925795A (en) * 2019-11-06 2020-03-27 西北工业大学 Afterburning chamber of doublestage burning
DE102020116245B4 (en) 2020-06-19 2024-03-07 Man Energy Solutions Se Gas turbine assembly with combustion chamber air bypass

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* Cited by examiner, † Cited by third party
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US5509270A (en) * 1994-03-01 1996-04-23 Rolls-Royce Plc Gas turbine engine combustor heatshield
EP1434007A2 (en) * 2002-12-23 2004-06-30 Siemens Westinghouse Power Corporation Gas turbine can annular combustor
EP1605209A1 (en) * 2004-06-07 2005-12-14 Siemens Aktiengesellschaft Combustor with thermo-acoustic vibrations dampening device
US20060059913A1 (en) * 2004-09-21 2006-03-23 Siemens Aktiengesellschaft Combustion chamber for a gas turbine with at least two resonator devices
FR2889732A1 (en) * 2005-08-12 2007-02-16 Snecma Combustion chamber for turbomachine, has annular inner and outer walls including perforations emerging relative to tabs and constituted of holes whose axis forms, with longitudinal axis, angle comprised between preset values
US20070137207A1 (en) * 2005-12-20 2007-06-21 Mancini Alfred A Pilot fuel injector for mixer assembly of a high pressure gas turbine engine

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DE2018641C2 (en) * 1970-04-18 1972-05-10 Motoren Turbinen Union REVERSE COMBUSTION CHAMBER FOR GAS TURBINE ENGINES
US4008568A (en) * 1976-03-01 1977-02-22 General Motors Corporation Combustor support
GB2098719B (en) * 1981-05-20 1984-11-21 Rolls Royce Gas turbine engine combustion apparatus
FR2572463B1 (en) 1984-10-30 1989-01-20 Snecma INJECTION SYSTEM WITH VARIABLE GEOMETRY.
GB2204672B (en) * 1987-05-06 1991-03-06 Rolls Royce Plc Combustor
US5012645A (en) * 1987-08-03 1991-05-07 United Technologies Corporation Combustor liner construction for gas turbine engine
GB2219653B (en) * 1987-12-18 1991-12-11 Rolls Royce Plc Improvements in or relating to combustors for gas turbine engines
US4843825A (en) * 1988-05-16 1989-07-04 United Technologies Corporation Combustor dome heat shield
GB9112324D0 (en) * 1991-06-07 1991-07-24 Rolls Royce Plc Gas turbine engine combustor
CA2070518C (en) * 1991-07-01 2001-10-02 Adrian Mark Ablett Combustor dome assembly
DE4328294A1 (en) * 1993-08-23 1995-03-02 Abb Management Ag Method for cooling a component and device for carrying out the method
DE4427222A1 (en) 1994-08-01 1996-02-08 Bmw Rolls Royce Gmbh Heat shield for a gas turbine combustor
US5623827A (en) * 1995-01-26 1997-04-29 General Electric Company Regenerative cooled dome assembly for a gas turbine engine combustor
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DE10048864A1 (en) * 2000-10-02 2002-04-11 Rolls Royce Deutschland Combustion chamber head for a gas turbine
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US20040083734A1 (en) * 2002-11-05 2004-05-06 Kendall Robert M. Sintered metal fiber liner for gas burners
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US7631503B2 (en) * 2006-09-12 2009-12-15 Pratt & Whitney Canada Corp. Combustor with enhanced cooling access
DE112007002152T5 (en) * 2006-09-14 2009-07-23 Solar Turbines Inc., San Diego Baffle plate dome assembly for a turbine engine
DE102006048842B4 (en) 2006-10-13 2019-10-10 Man Energy Solutions Se Combustion chamber for a gas turbine
US20090199563A1 (en) * 2008-02-07 2009-08-13 Hamilton Sundstrand Corporation Scalable pyrospin combustor
US9587832B2 (en) * 2008-10-01 2017-03-07 United Technologies Corporation Structures with adaptive cooling

Patent Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5509270A (en) * 1994-03-01 1996-04-23 Rolls-Royce Plc Gas turbine engine combustor heatshield
EP1434007A2 (en) * 2002-12-23 2004-06-30 Siemens Westinghouse Power Corporation Gas turbine can annular combustor
EP1605209A1 (en) * 2004-06-07 2005-12-14 Siemens Aktiengesellschaft Combustor with thermo-acoustic vibrations dampening device
US20060059913A1 (en) * 2004-09-21 2006-03-23 Siemens Aktiengesellschaft Combustion chamber for a gas turbine with at least two resonator devices
FR2889732A1 (en) * 2005-08-12 2007-02-16 Snecma Combustion chamber for turbomachine, has annular inner and outer walls including perforations emerging relative to tabs and constituted of holes whose axis forms, with longitudinal axis, angle comprised between preset values
US20070137207A1 (en) * 2005-12-20 2007-06-21 Mancini Alfred A Pilot fuel injector for mixer assembly of a high pressure gas turbine engine

Also Published As

Publication number Publication date
JP2011094949A (en) 2011-05-12
CA2714259C (en) 2012-11-20
DE102009046066A1 (en) 2011-05-12
US20110265483A1 (en) 2011-11-03
JP5160616B2 (en) 2013-03-13
CA2714259A1 (en) 2011-04-28
US9140452B2 (en) 2015-09-22
EP2317227A2 (en) 2011-05-04
EP2317227B1 (en) 2019-10-02

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