EP1731839A3 - System for fixing an injection system to the dome of turbine combustion chamber and method of fixation - Google Patents

System for fixing an injection system to the dome of turbine combustion chamber and method of fixation Download PDF

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Publication number
EP1731839A3
EP1731839A3 EP06115000.9A EP06115000A EP1731839A3 EP 1731839 A3 EP1731839 A3 EP 1731839A3 EP 06115000 A EP06115000 A EP 06115000A EP 1731839 A3 EP1731839 A3 EP 1731839A3
Authority
EP
European Patent Office
Prior art keywords
fixing
combustion chamber
dome
fixation
injection system
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
EP06115000.9A
Other languages
German (de)
French (fr)
Other versions
EP1731839A2 (en
EP1731839B1 (en
Inventor
Didier Hippolyte Hernandez
Romain Nicolas Lunel
Christophe Pieussergues
David Pinchon
Guillaume Sevi
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.)
Safran Aircraft Engines SAS
Original Assignee
SNECMA SAS
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 FR0551518A external-priority patent/FR2886714B1/en
Application filed by SNECMA SAS filed Critical SNECMA SAS
Publication of EP1731839A2 publication Critical patent/EP1731839A2/en
Publication of EP1731839A3 publication Critical patent/EP1731839A3/en
Application granted granted Critical
Publication of EP1731839B1 publication Critical patent/EP1731839B1/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
    • 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
    • F23R3/283—Attaching or cooling of fuel injecting means including supports for fuel injectors, stems, or lances
    • 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
    • F23R3/60—Support structures; Attaching or mounting means

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Fuel-Injection Apparatus (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Combustion Methods Of Internal-Combustion Engines (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Abstract

Système de fixation d'un système d'injection sur un fond de chambre de combustion de turboréacteur. Il comprend un déflecteur (20) brasé sur le fond de chambre (22). Le déflecteur comporte une partie annulaire (32) ayant un chant (42) formant un épaulement de retenue dirigé vers l'avant du turboréacteur et le système d'injection (2) comporte une collerette (44) sur laquelle est formé un épaulement de retenue (46), dirigé vers l'arrière du turboréacteur et prenant appui contre l'épaulement de retenue (42) du déflecteur (20).

Figure imgaf001
System for fixing an injection system on a turbojet combustion chamber bottom. It comprises a deflector (20) brazed to the chamber floor (22). The deflector comprises an annular portion (32) having a lip (42) forming a retaining shoulder directed towards the front of the turbojet and the injection system (2) comprises a flange (44) on which is formed a retaining shoulder (46), directed towards the rear of the turbojet and bearing against the retaining shoulder (42) of the deflector (20).
Figure imgaf001
EP06115000.9A 2005-06-07 2006-06-06 System for fixing an injection system to the dome of turbine combustion chamber and method of fixation Active EP1731839B1 (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR0551518A FR2886714B1 (en) 2005-06-07 2005-06-07 ANTI-ROTARY INJECTION SYSTEM FOR TURBO-REACTOR
FR0552929A FR2886715B1 (en) 2005-06-07 2005-09-28 SYSTEM FOR FASTENING AN INJECTION SYSTEM ON A TURBOREACTOR COMBUSTION CHAMBER BOTTOM AND METHOD OF FASTENING

Publications (3)

Publication Number Publication Date
EP1731839A2 EP1731839A2 (en) 2006-12-13
EP1731839A3 true EP1731839A3 (en) 2013-05-08
EP1731839B1 EP1731839B1 (en) 2015-08-05

Family

ID=36972884

Family Applications (1)

Application Number Title Priority Date Filing Date
EP06115000.9A Active EP1731839B1 (en) 2005-06-07 2006-06-06 System for fixing an injection system to the dome of turbine combustion chamber and method of fixation

Country Status (5)

Country Link
US (1) US7673460B2 (en)
EP (1) EP1731839B1 (en)
JP (1) JP4875928B2 (en)
CA (1) CA2548869C (en)
RU (1) RU2406935C2 (en)

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* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US7628019B2 (en) * 2005-03-21 2009-12-08 United Technologies Corporation Fuel injector bearing plate assembly and swirler assembly
FR2893390B1 (en) * 2005-11-15 2011-04-01 Snecma BOTTOM OF COMBUSTION CHAMBER WITH VENTILATION
FR2897923B1 (en) * 2006-02-27 2008-06-06 Snecma Sa ANNULAR COMBUSTION CHAMBER WITH REMOVABLE BACKGROUND
FR2903169B1 (en) * 2006-06-29 2011-11-11 Snecma DEVICE FOR INJECTING A MIXTURE OF AIR AND FUEL, COMBUSTION CHAMBER AND TURBOMACHINE HAVING SUCH A DEVICE
FR2910115B1 (en) * 2006-12-19 2012-11-16 Snecma DEFLECTOR FOR BOTTOM OF COMBUSTION CHAMBER, COMBUSTION CHAMBER WHERE IT IS EQUIPPED AND TURBOREACTOR COMPRISING THEM
FR2918443B1 (en) * 2007-07-04 2009-10-30 Snecma Sa COMBUSTION CHAMBER COMPRISING THERMAL PROTECTION DEFLECTORS OF BOTTOM BOTTOM AND GAS TURBINE ENGINE BEING EQUIPPED
FR2921462B1 (en) * 2007-09-21 2012-08-24 Snecma ANNULAR COMBUSTION CHAMBER FOR A GAS TURBINE ENGINE
FR2921464B1 (en) * 2007-09-24 2014-03-28 Snecma ARRANGEMENT OF INJECTION SYSTEMS IN A COMBUSTION CHAMBER BOTTOM OF AN AIRCRAFT ENGINE
DE102007050276A1 (en) * 2007-10-18 2009-04-23 Rolls-Royce Deutschland Ltd & Co Kg Lean premix burner for a gas turbine engine
FR2929690B1 (en) * 2008-04-03 2012-08-17 Snecma Propulsion Solide COMBUSTION CHAMBER SECTORIZED IN CMC FOR GAS TURBINE
FR2932251B1 (en) * 2008-06-10 2011-09-16 Snecma COMBUSTION CHAMBER FOR A GAS TURBINE ENGINE COMPRISING CMC DEFLECTORS
US8327648B2 (en) * 2008-12-09 2012-12-11 Pratt & Whitney Canada Corp. Combustor liner with integrated anti-rotation and removal feature
US9127842B2 (en) 2009-05-27 2015-09-08 Siemens Aktiengesellschaft Burner, operating method and assembly method
JP4815513B2 (en) * 2009-07-06 2011-11-16 川崎重工業株式会社 Gas turbine combustor
FR2963061B1 (en) * 2010-07-26 2012-07-27 Snecma FUEL INJECTION SYSTEM FOR TURBO-REACTOR AND METHOD FOR ASSEMBLING SUCH AN INJECTION SYSTEM
FR2964177B1 (en) * 2010-08-27 2012-08-24 Snecma AIRCRAFT ENGINE COMBUSTION CHAMBER AND METHOD OF FIXING AN INJECTION SYSTEM IN AN AIRCRAFT ENGINE COMBUSTION CHAMBER
FR2971038B1 (en) * 2011-01-31 2013-02-08 Snecma INJECTION DEVICE FOR A TURBOMACHINE COMBUSTION CHAMBER
GB201107095D0 (en) * 2011-04-28 2011-06-08 Rolls Royce Plc A head part of an annular combustion chamber
FR2986856B1 (en) * 2012-02-15 2018-05-04 Safran Aircraft Engines DEVICE FOR INJECTING AIR AND FUEL FOR A COMBUSTION CHAMBER OF A TURBOMACHINE
US9021812B2 (en) * 2012-07-27 2015-05-05 Honeywell International Inc. Combustor dome and heat-shield assembly
FR3026827B1 (en) * 2014-10-01 2019-06-07 Safran Aircraft Engines TURBOMACHINE COMBUSTION CHAMBER
GB2543803B (en) * 2015-10-29 2019-10-30 Rolls Royce Plc A combustion chamber assembly
US10473332B2 (en) * 2016-02-25 2019-11-12 General Electric Company Combustor assembly
DE102017217328A1 (en) * 2017-09-28 2019-03-28 Rolls-Royce Deutschland Ltd & Co Kg Axial extension nozzle for a combustion chamber of an engine
US11280492B2 (en) * 2018-08-23 2022-03-22 General Electric Company Combustor assembly for a turbo machine
US11466858B2 (en) * 2019-10-11 2022-10-11 Rolls-Royce Corporation Combustor for a gas turbine engine with ceramic matrix composite sealing element
FR3103540B1 (en) * 2019-11-26 2022-01-28 Safran Aircraft Engines Fuel injection system of a turbomachine, combustion chamber comprising such a system and associated turbomachine

Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4216652A (en) * 1978-06-08 1980-08-12 General Motors Corporation Integrated, replaceable combustor swirler and fuel injector
US6212870B1 (en) * 1998-09-22 2001-04-10 General Electric Company Self fixturing combustor dome assembly
US6502400B1 (en) * 2000-05-20 2003-01-07 General Electric Company Combustor dome assembly and method of assembling the same

Family Cites Families (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0153842B1 (en) * 1984-02-29 1988-07-27 LUCAS INDUSTRIES public limited company Combustion equipment
FR2572463B1 (en) * 1984-10-30 1989-01-20 Snecma INJECTION SYSTEM WITH VARIABLE GEOMETRY.
US5117637A (en) * 1990-08-02 1992-06-02 General Electric Company Combustor dome assembly
JPH04116316A (en) * 1990-09-05 1992-04-16 Jisedai Koukuuki Kiban Gijutsu Kenkyusho:Kk Swirler of combustion apparatus
US6442940B1 (en) * 2001-04-27 2002-09-03 General Electric Company Gas-turbine air-swirler attached to dome and combustor in single brazing operation
US6782620B2 (en) * 2003-01-28 2004-08-31 General Electric Company Methods for replacing a portion of a combustor dome assembly
FR2859272B1 (en) * 2003-09-02 2005-10-14 Snecma Moteurs AIR / FUEL INJECTION SYSTEM IN A TURBOMACHINE COMBUSTION CHAMBER HAVING MEANS FOR GENERATING COLD PLASMA

Patent Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4216652A (en) * 1978-06-08 1980-08-12 General Motors Corporation Integrated, replaceable combustor swirler and fuel injector
US6212870B1 (en) * 1998-09-22 2001-04-10 General Electric Company Self fixturing combustor dome assembly
US6502400B1 (en) * 2000-05-20 2003-01-07 General Electric Company Combustor dome assembly and method of assembling the same

Also Published As

Publication number Publication date
RU2006119912A (en) 2007-12-20
CA2548869C (en) 2014-05-20
EP1731839A2 (en) 2006-12-13
EP1731839B1 (en) 2015-08-05
JP4875928B2 (en) 2012-02-15
RU2406935C2 (en) 2010-12-20
JP2006343092A (en) 2006-12-21
CA2548869A1 (en) 2006-12-07
US7673460B2 (en) 2010-03-09
US20070084215A1 (en) 2007-04-19

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