EP0837286A3 - Brennkammer einer Gasturbine mit einem ringförmigen Kopfabschnitt - Google Patents

Brennkammer einer Gasturbine mit einem ringförmigen Kopfabschnitt Download PDF

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Publication number
EP0837286A3
EP0837286A3 EP97114340A EP97114340A EP0837286A3 EP 0837286 A3 EP0837286 A3 EP 0837286A3 EP 97114340 A EP97114340 A EP 97114340A EP 97114340 A EP97114340 A EP 97114340A EP 0837286 A3 EP0837286 A3 EP 0837286A3
Authority
EP
European Patent Office
Prior art keywords
head section
air inlet
ring
inlet openings
gas turbine
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
EP97114340A
Other languages
English (en)
French (fr)
Other versions
EP0837286A2 (de
EP0837286B1 (de
Inventor
Achim Schmid
Manfred Schwithal
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 EP0837286A2 publication Critical patent/EP0837286A2/de
Publication of EP0837286A3 publication Critical patent/EP0837286A3/de
Application granted granted Critical
Publication of EP0837286B1 publication Critical patent/EP0837286B1/de
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
    • F23R3/10—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
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/002—Wall structures

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Spray-Type Burners (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Air Supply (AREA)

Abstract

Brennkammer einer Gasturbine mit einem ringförmigen Kopfabschnitt, innerhalb dessen eine Frontplatte zur Aufnahme von Brennern vorgesehen ist, welche über ringförmig angeordnete Lufteintrittsöffnungen im Kopfabschnitt mit einem Primärluftstrom versorgt werden, wobei die sich bezüglich der Anströmung der Lufteintrittsöffnungen an der Außenseite des Kopfabschnittes bildenden Staupunkte einen Ring beschreiben, innerhalb dessen die Lufteintrittsöffnungen liegen,und wobei die Frontplatte weiterhin über Verschraubungen fixierte, im Brennkammer-Brennraum vorgesehene Hitzeschilder trägt,dadurch gekennzeichnet, daß im Kopfabschnitt Montageöffnungen für die Verschraubungen vorgesehen sind, wobei die sich bezüglich der Anströmung der Montageöffnungen an der Außenseite des Kopfabschnittes bildenden Staupunkte einen Ring beschreiben, der nicht außerhalb des von den Staupunkten der Lufteintrittsöffnungen beschriebenen Ringes liegt.
EP97114340A 1996-10-18 1997-08-20 Brennkammer einer Gasturbine mit einem ringförmigen Kopfabschnitt Expired - Lifetime EP0837286B1 (de)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE19643028 1996-10-18
DE19643028A DE19643028A1 (de) 1996-10-18 1996-10-18 Brennkammer einer Gasturbine mit einem ringförmigen Kopfabschnitt

Publications (3)

Publication Number Publication Date
EP0837286A2 EP0837286A2 (de) 1998-04-22
EP0837286A3 true EP0837286A3 (de) 2000-07-05
EP0837286B1 EP0837286B1 (de) 2002-10-02

Family

ID=7809106

Family Applications (1)

Application Number Title Priority Date Filing Date
EP97114340A Expired - Lifetime EP0837286B1 (de) 1996-10-18 1997-08-20 Brennkammer einer Gasturbine mit einem ringförmigen Kopfabschnitt

Country Status (4)

Country Link
US (1) US5934066A (de)
EP (1) EP0837286B1 (de)
CA (1) CA2218520C (de)
DE (2) DE19643028A1 (de)

Families Citing this family (18)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US6779268B1 (en) * 2003-05-13 2004-08-24 General Electric Company Outer and inner cowl-wire wrap to one piece cowl conversion
US7748221B2 (en) 2006-11-17 2010-07-06 Pratt & Whitney Canada Corp. Combustor heat shield with variable cooling
US7681398B2 (en) 2006-11-17 2010-03-23 Pratt & Whitney Canada Corp. Combustor liner and heat shield assembly
US7721548B2 (en) 2006-11-17 2010-05-25 Pratt & Whitney Canada Corp. Combustor liner and heat shield assembly
GB0705458D0 (en) * 2007-03-22 2007-05-02 Rolls Royce Plc A Location ring arrangement
US7845174B2 (en) * 2007-04-19 2010-12-07 Pratt & Whitney Canada Corp. Combustor liner with improved heat shield retention
US9291102B2 (en) 2011-09-07 2016-03-22 Siemens Energy, Inc. Interface ring for gas turbine fuel nozzle assemblies
DE102013007443A1 (de) * 2013-04-30 2014-10-30 Rolls-Royce Deutschland Ltd & Co Kg Brennerdichtung für Gasturbinen-Brennkammerkopf und Hitzeschild
FR3011317B1 (fr) * 2013-10-01 2018-02-23 Safran Aircraft Engines Chambre de combustion pour turbomachine a admission d'air homogene au travers de systemes d'injection
DE102014213302A1 (de) * 2014-07-09 2016-01-14 Rolls-Royce Deutschland Ltd & Co Kg Brennkammer einer Gasturbine mit verschraubtem Brennkammerkopf
FR3026827B1 (fr) * 2014-10-01 2019-06-07 Safran Aircraft Engines Chambre de combustion de turbomachine
DE102015213629A1 (de) 2015-07-20 2017-01-26 Rolls-Royce Deutschland Ltd & Co Kg Abdeckteil und Brennkammerbaugruppe für eine Gasturbine
US10767863B2 (en) * 2015-07-22 2020-09-08 Rolls-Royce North American Technologies, Inc. Combustor tile with monolithic inserts
DE102015224990A1 (de) * 2015-12-11 2017-06-14 Rolls-Royce Deutschland Ltd & Co Kg Verfahren zur Montage einer Brennkammer eines Gasturbinentriebwerks
DE102015224988A1 (de) * 2015-12-11 2017-06-14 Rolls-Royce Deutschland Ltd & Co Kg Verfahren zur Montage einer Brennkammer eines Gasturbinentriebwerks
DE102017201349A1 (de) 2017-01-27 2018-08-02 Rolls-Royce Deutschland Ltd & Co Kg Brennkammeranordnung einer Gasturbine
DE102017207392A1 (de) * 2017-05-03 2018-11-08 Siemens Aktiengesellschaft Silobrennkammer und Verfahren zum Umrüsten einer solchen
GB201715366D0 (en) 2017-09-22 2017-11-08 Rolls Royce Plc A combustion chamber

Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO1996004510A1 (de) * 1994-08-01 1996-02-15 Bmw Rolls-Royce Gmbh Hitzeschild für eine gasturbinen-brennkammer
WO1996027765A1 (de) * 1995-03-08 1996-09-12 Bmw Rolls-Royce Gmbh Hitzeschild-anordnung für eine gasturbinen-brennkammer
US5941076A (en) * 1996-07-25 1999-08-24 Snecma-Societe Nationale D'etude Et De Construction De Moteurs D'aviation Deflecting feeder bowl assembly for a turbojet engine combustion chamber

Family Cites Families (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4870818A (en) * 1986-04-18 1989-10-03 United Technologies Corporation Fuel nozzle guide structure and retainer for a gas turbine engine
US4934145A (en) * 1988-10-12 1990-06-19 United Technologies Corporation Combustor bulkhead heat shield assembly
US5181377A (en) * 1991-04-16 1993-01-26 General Electric Company Damped combustor cowl structure
US5289677A (en) * 1992-12-16 1994-03-01 United Technologies Corporation Combined support and seal ring for a combustor
US5323601A (en) * 1992-12-21 1994-06-28 United Technologies Corporation Individually removable combustor liner panel for a gas turbine engine
US5419115A (en) * 1994-04-29 1995-05-30 United Technologies Corporation Bulkhead and fuel nozzle guide assembly for an annular combustion chamber

Patent Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO1996004510A1 (de) * 1994-08-01 1996-02-15 Bmw Rolls-Royce Gmbh Hitzeschild für eine gasturbinen-brennkammer
WO1996027765A1 (de) * 1995-03-08 1996-09-12 Bmw Rolls-Royce Gmbh Hitzeschild-anordnung für eine gasturbinen-brennkammer
US5941076A (en) * 1996-07-25 1999-08-24 Snecma-Societe Nationale D'etude Et De Construction De Moteurs D'aviation Deflecting feeder bowl assembly for a turbojet engine combustion chamber

Also Published As

Publication number Publication date
CA2218520C (en) 2007-03-13
DE19643028A1 (de) 1998-04-23
US5934066A (en) 1999-08-10
EP0837286A2 (de) 1998-04-22
CA2218520A1 (en) 1998-04-18
EP0837286B1 (de) 2002-10-02
DE59708367D1 (de) 2002-11-07

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