EP2340397A1 - Insert de brûleur pour une chambre de combustion d'une turbine à gaz et turbine à gaz - Google Patents

Insert de brûleur pour une chambre de combustion d'une turbine à gaz et turbine à gaz

Info

Publication number
EP2340397A1
EP2340397A1 EP09823099A EP09823099A EP2340397A1 EP 2340397 A1 EP2340397 A1 EP 2340397A1 EP 09823099 A EP09823099 A EP 09823099A EP 09823099 A EP09823099 A EP 09823099A EP 2340397 A1 EP2340397 A1 EP 2340397A1
Authority
EP
European Patent Office
Prior art keywords
combustion chamber
burner
wall
gas turbine
burner insert
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
EP09823099A
Other languages
German (de)
English (en)
Other versions
EP2340397B1 (fr
Inventor
Andreas Böttcher
Andre Kluge
Tobias Krieger
Jürgen MEISL
Kai-Uwe Schildmacher
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.)
Siemens AG
Original Assignee
Siemens AG
Siemens Corp
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 Siemens AG, Siemens Corp filed Critical Siemens AG
Priority to EP09823099.8A priority Critical patent/EP2340397B1/fr
Publication of EP2340397A1 publication Critical patent/EP2340397A1/fr
Application granted granted Critical
Publication of EP2340397B1 publication Critical patent/EP2340397B1/fr
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
    • F23R3/002—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
    • 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
    • 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

Definitions

  • the present invention relates to a combustor liner for a gas turbine combustor having a burner port for inserting a combustor.
  • the invention relates to a gas turbine.
  • annular combustion chambers that is to say of combustion chambers which extend annularly around the turbine rotor
  • a multiplicity of combustion inserts are generally arranged next to one another in the circumferential direction of the annular combustion chamber.
  • the cooling air flowing past the cold side of the burner side then flows into the combustion chamber between the radially outer wall and the radially inner wall of the combustion chamber.
  • cooling air can also be introduced into the combustion chamber by gaps between circumferentially adjacent combustion inserts.
  • Such an annular combustion chamber is described, for example, in EP 1 557 607 A1.
  • a burner insert is shown in Figure 4 in a partially cutaway perspective view. It comprises a burner insert wall 42 with a cold side 43 and a hot side 44, which is to be turned to the combustion chamber interior (the hot side can not be seen in FIG. 4).
  • the cold side 43 communicates with the outlet of the compressor in fluid communication so that compressor air can be bypassed for cooling purposes on the cold side 43 to the temperature of the hot side on one for the material of the burner insert 41 acceptable level.
  • the hot side is also provided with a heat-insulating coating, for example in the form of a ceramic coating, in order to reduce the need for cooling air.

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)
  • Gas Burners (AREA)
  • Pre-Mixing And Non-Premixing Gas Burner (AREA)

Abstract

L'invention concerne un insert de brûleur (41) pour une chambre de combustion (25) de turbine à gaz, avec une paroi d'insert (42) ayant une face froide (43) et une face chaude (44) et une bordure (46) qui délimite la paroi d'insert (42). La bordure (46) possède une arête (51) sur au moins une partie de la circonférence, faisant saillie par rapport à la face froide (43). Une ouverture de brûleur (45) destinée à recevoir un brûleur (27) est formée dans la paroi d'insert (42).
EP09823099.8A 2008-10-29 2009-09-14 Pièce du brûleur pour une chambre de combustion d'une turbine à gaz et turbine à gaz Active EP2340397B1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
EP09823099.8A EP2340397B1 (fr) 2008-10-29 2009-09-14 Pièce du brûleur pour une chambre de combustion d'une turbine à gaz et turbine à gaz

Applications Claiming Priority (3)

Application Number Priority Date Filing Date Title
EP08018907A EP2182285A1 (fr) 2008-10-29 2008-10-29 Pièce du brûleur pour une chambre de combustion d'une turbine à gaz et turbine à gaz
EP09823099.8A EP2340397B1 (fr) 2008-10-29 2009-09-14 Pièce du brûleur pour une chambre de combustion d'une turbine à gaz et turbine à gaz
PCT/EP2009/061854 WO2010049206A1 (fr) 2008-10-29 2009-09-14 Insert de brûleur pour une chambre de combustion d'une turbine à gaz et turbine à gaz

Publications (2)

Publication Number Publication Date
EP2340397A1 true EP2340397A1 (fr) 2011-07-06
EP2340397B1 EP2340397B1 (fr) 2013-07-31

Family

ID=40672584

Family Applications (2)

Application Number Title Priority Date Filing Date
EP08018907A Withdrawn EP2182285A1 (fr) 2008-10-29 2008-10-29 Pièce du brûleur pour une chambre de combustion d'une turbine à gaz et turbine à gaz
EP09823099.8A Active EP2340397B1 (fr) 2008-10-29 2009-09-14 Pièce du brûleur pour une chambre de combustion d'une turbine à gaz et turbine à gaz

Family Applications Before (1)

Application Number Title Priority Date Filing Date
EP08018907A Withdrawn EP2182285A1 (fr) 2008-10-29 2008-10-29 Pièce du brûleur pour une chambre de combustion d'une turbine à gaz et turbine à gaz

Country Status (7)

Country Link
US (1) US9074771B2 (fr)
EP (2) EP2182285A1 (fr)
JP (1) JP5349605B2 (fr)
CN (1) CN102203509B (fr)
ES (1) ES2426395T3 (fr)
RU (1) RU2530684C2 (fr)
WO (1) WO2010049206A1 (fr)

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DE102012204103A1 (de) * 2012-03-15 2013-09-19 Siemens Aktiengesellschaft Hitzeschildelement für einen Verdichterluftbypass um die Brennkammer
US9322560B2 (en) * 2012-09-28 2016-04-26 United Technologies Corporation Combustor bulkhead assembly
US20150033746A1 (en) * 2013-08-02 2015-02-05 Solar Turbines Incorporated Heat shield with standoffs
US9534786B2 (en) * 2014-08-08 2017-01-03 Pratt & Whitney Canada Corp. Combustor heat shield
US10267521B2 (en) 2015-04-13 2019-04-23 Pratt & Whitney Canada Corp. Combustor heat shield
DE102016206188A1 (de) * 2016-04-13 2017-10-19 Rolls-Royce Deutschland Ltd & Co Kg Brennkammerschindel einer Gasturbine
DE102016224632A1 (de) * 2016-12-09 2018-06-14 Rolls-Royce Deutschland Ltd & Co Kg Plattenförmiges Bauteil einer Gasturbine sowie Verfahren zu dessen Herstellung
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
US11009230B2 (en) 2018-02-06 2021-05-18 Raytheon Technologies Corporation Undercut combustor panel rail
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
US20190285276A1 (en) * 2018-03-14 2019-09-19 United Technologies Corporation Castellated combustor panels
DE102018212394B4 (de) 2018-07-25 2024-03-28 Rolls-Royce Deutschland Ltd & Co Kg Brennkammerbaugruppe mit Strömungsleiteinrichtung aufweisendem Wandelement
US11015807B2 (en) * 2019-01-30 2021-05-25 Pratt & Whitney Canada Corp. Combustor heat shield cooling
EP3964753A1 (fr) * 2020-09-07 2022-03-09 Siemens Energy Global GmbH & Co. KG Joint d'étanchéité destiné à l'utilisation dans un élément pare-chaleur

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GB2107448B (en) * 1980-10-21 1984-06-06 Rolls Royce Gas turbine engine combustion chambers
US4914918A (en) * 1988-09-26 1990-04-10 United Technologies Corporation Combustor segmented deflector
GB9018014D0 (en) * 1990-08-16 1990-10-03 Rolls Royce Plc Gas turbine engine combustor
GB2287310B (en) * 1994-03-01 1997-12-03 Rolls Royce Plc Gas turbine engine combustor heatshield
US5419115A (en) * 1994-04-29 1995-05-30 United Technologies Corporation Bulkhead and fuel nozzle guide assembly for an annular combustion chamber
DE4427222A1 (de) * 1994-08-01 1996-02-08 Bmw Rolls Royce Gmbh Hitzeschild für eine Gasturbinen-Brennkammer
US6032457A (en) * 1996-06-27 2000-03-07 United Technologies Corporation Fuel nozzle guide
US5974805A (en) * 1997-10-28 1999-11-02 Rolls-Royce Plc Heat shielding for a turbine combustor
US6164074A (en) * 1997-12-12 2000-12-26 United Technologies Corporation Combustor bulkhead with improved cooling and air recirculation zone
US6751961B2 (en) * 2002-05-14 2004-06-22 United Technologies Corporation Bulkhead panel for use in a combustion chamber of a gas turbine engine
US6792757B2 (en) * 2002-11-05 2004-09-21 Honeywell International Inc. Gas turbine combustor heat shield impingement cooling baffle
RU31818U1 (ru) * 2002-11-21 2003-08-27 ОАО Самарский научно-технический комплекс им. Н.Д. Кузнецова Газотурбинный двигатель НК-37, компрессор, камера сгорания, турбина
US7080515B2 (en) 2002-12-23 2006-07-25 Siemens Westinghouse Power Corporation Gas turbine can annular combustor
ATE483138T1 (de) 2004-01-21 2010-10-15 Siemens Ag Brenner mit gekühltem bauteil, gasturbine sowie verfahren zur kühlung des bauteils
RU52982U1 (ru) * 2005-08-03 2006-04-27 ЭКОЛ спол. с.р.о. Горелка для сжигания с низкими эмиссиями вредных веществ и система горелок
EP1767855A1 (fr) 2005-09-27 2007-03-28 Siemens Aktiengesellschaft Chambre de combustion et turbine à gaz
RU52992U1 (ru) 2005-10-24 2006-04-27 Ираклий Отарович Чиквиладзе Радиатор двигателя внутреннего сгорания гоночного автомобиля
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Also Published As

Publication number Publication date
EP2340397B1 (fr) 2013-07-31
JP2012506991A (ja) 2012-03-22
EP2182285A1 (fr) 2010-05-05
US20110197590A1 (en) 2011-08-18
RU2011121647A (ru) 2012-12-10
US9074771B2 (en) 2015-07-07
ES2426395T3 (es) 2013-10-23
WO2010049206A1 (fr) 2010-05-06
RU2530684C2 (ru) 2014-10-10
JP5349605B2 (ja) 2013-11-20
CN102203509A (zh) 2011-09-28
CN102203509B (zh) 2014-07-09

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