EP2040001A3 - Chambre de combustion annulaire de moteur à turbine à gaz - Google Patents

Chambre de combustion annulaire de moteur à turbine à gaz Download PDF

Info

Publication number
EP2040001A3
EP2040001A3 EP08164751A EP08164751A EP2040001A3 EP 2040001 A3 EP2040001 A3 EP 2040001A3 EP 08164751 A EP08164751 A EP 08164751A EP 08164751 A EP08164751 A EP 08164751A EP 2040001 A3 EP2040001 A3 EP 2040001A3
Authority
EP
European Patent Office
Prior art keywords
chamber
wall
orifices
gas turbine
turbine engine
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
EP08164751A
Other languages
German (de)
English (en)
Other versions
EP2040001B1 (fr
EP2040001A2 (fr
Inventor
Didier Hippolyte Hernandez
Thomas Olivier Marie Noel
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
Application filed by SNECMA SAS filed Critical SNECMA SAS
Publication of EP2040001A2 publication Critical patent/EP2040001A2/fr
Publication of EP2040001A3 publication Critical patent/EP2040001A3/fr
Application granted granted Critical
Publication of EP2040001B1 publication Critical patent/EP2040001B1/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
    • F23R3/42—Continuous combustion chambers using liquid or gaseous fuel characterised by the arrangement or form of the flame tubes or combustion chambers
    • F23R3/50—Combustion chambers comprising an annular flame tube within an annular casing
    • 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
    • F23R2900/00—Special features of, or arrangements for continuous combustion chambers; Combustion processes therefor
    • F23R2900/00012—Details of sealing devices

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Combustion Methods Of Internal-Combustion Engines (AREA)

Abstract

La présente invention porte sur une chambre de combustion annulaire de moteur à turbine à gaz comportant une paroi externe et une paroi interne reliées par une paroi formant fond de chambre les parois délimitant des foyers de combustion d'axes inclinés par rapport à l'axe de la chambre, la paroi (16) de fond de chambre, de forme tronconique, étant percée d'orifices (16s) pour les systèmes d'injection de carburant, les plans des orifices étant perpendiculaires aux axes des foyers de combustion, des déflecteurs de protection thermique centrés sur chacun des orifices (16s) comportant un épaulement par lequel ils sont en appui contre une portion de surface plane le long du pourtour des orifices (16s). La chambre est caractérisé par le fait que la paroi (16) de fond de chambre est conformée en une succession de facettes (16f) planes adjacentes présentant un bord commun, avec une facette par orifice (16s), l'épaulement des déflecteurs étant en appui contre le plan des facettes (16f).
EP08164751.3A 2007-09-21 2008-09-19 Chambre de combustion annulaire de moteur à turbine à gaz Active EP2040001B1 (fr)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
FR0706644A FR2921462B1 (fr) 2007-09-21 2007-09-21 Chambre de combustion annulaire de moteur a turbine a gaz

Publications (3)

Publication Number Publication Date
EP2040001A2 EP2040001A2 (fr) 2009-03-25
EP2040001A3 true EP2040001A3 (fr) 2010-02-17
EP2040001B1 EP2040001B1 (fr) 2018-04-18

Family

ID=39327017

Family Applications (1)

Application Number Title Priority Date Filing Date
EP08164751.3A Active EP2040001B1 (fr) 2007-09-21 2008-09-19 Chambre de combustion annulaire de moteur à turbine à gaz

Country Status (5)

Country Link
US (1) US8156744B2 (fr)
EP (1) EP2040001B1 (fr)
CA (1) CA2639588C (fr)
FR (1) FR2921462B1 (fr)
RU (1) RU2485405C2 (fr)

Families Citing this family (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CH704185A1 (de) * 2010-12-06 2012-06-15 Alstom Technology Ltd Gasturbine sowie verfahren zum rekonditionieren einer solchen gasturbine.
FR2970666B1 (fr) * 2011-01-24 2013-01-18 Snecma Procede de perforation d'au moins une paroi d'une chambre de combustion
GB2491580A (en) * 2011-06-06 2012-12-12 Rolls Royce Plc A method of manufacturing a sheet metal annular combustion chamber
US10260748B2 (en) 2012-12-21 2019-04-16 United Technologies Corporation Gas turbine engine combustor with tailored temperature profile
US10816201B2 (en) 2013-09-13 2020-10-27 Raytheon Technologies Corporation Sealed combustor liner panel for a gas turbine engine
DE102015202570A1 (de) * 2015-02-12 2016-08-18 Rolls-Royce Deutschland Ltd & Co Kg Abdichtung eines Randspalts zwischen Effusionsschindeln einer Gasturbinenbrennkammer
US10816213B2 (en) 2018-03-01 2020-10-27 General Electric Company Combustor assembly with structural cowl and decoupled chamber

Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2673454A1 (fr) * 1991-02-28 1992-09-04 Snecma Chambre de combustion comportant une paroi de fond comprenant une pluralite de troncs de cones partiels.
EP1731839A2 (fr) * 2005-06-07 2006-12-13 Snecma Système de fixation d'un système d'injection sur un fond de chambre de combustion de turboréacteur et procède de fixation
EP1818615A1 (fr) * 2006-02-10 2007-08-15 Snecma Chambre de combustion annulaire d'une turbomachine
EP1826492A1 (fr) * 2006-02-27 2007-08-29 Snecma Agencement pour une chambre de combustion de turboréacteur

Family Cites Families (16)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4222230A (en) * 1978-08-14 1980-09-16 General Electric Company Combustor dome assembly
US4843825A (en) * 1988-05-16 1989-07-04 United Technologies Corporation Combustor dome heat shield
US5463864A (en) * 1993-12-27 1995-11-07 United Technologies Corporation Fuel nozzle guide for a gas turbine engine combustor
US5419115A (en) * 1994-04-29 1995-05-30 United Technologies Corporation Bulkhead and fuel nozzle guide assembly for an annular combustion chamber
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
US6550251B1 (en) * 1997-12-18 2003-04-22 General Electric Company Venturiless swirl cup
US6212870B1 (en) * 1998-09-22 2001-04-10 General Electric Company Self fixturing combustor dome assembly
US6279323B1 (en) * 1999-11-01 2001-08-28 General Electric Company Low emissions combustor
RU2225575C2 (ru) * 2001-12-06 2004-03-10 Межрегиональная общественная организация "Поволжское отделение Российской инженерной академии" Устройство для подвода топлива в камеру сгорания
RU2223488C1 (ru) * 2002-10-25 2004-02-10 Красноярский государственный университет Индикаторный состав для определения меди (ii) в водных растворах
US7121095B2 (en) * 2003-08-11 2006-10-17 General Electric Company Combustor dome assembly of a gas turbine engine having improved deflector plates
US7415826B2 (en) * 2005-07-25 2008-08-26 General Electric Company Free floating mixer assembly for combustor of a gas turbine engine
FR2903171B1 (fr) * 2006-06-29 2008-10-17 Snecma Sa Agencement a liaison par crabot pour chambre de combustion de turbomachine
FR2909748B1 (fr) * 2006-12-07 2009-07-10 Snecma Sa Fond de chambre, procede de realisation de celui-ci, chambre de combustion le comportant et turboreacteur en etant equipe
FR2914399B1 (fr) * 2007-03-27 2009-10-02 Snecma Sa Carenage pour fond de chambre de combustion.

Patent Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2673454A1 (fr) * 1991-02-28 1992-09-04 Snecma Chambre de combustion comportant une paroi de fond comprenant une pluralite de troncs de cones partiels.
EP1731839A2 (fr) * 2005-06-07 2006-12-13 Snecma Système de fixation d'un système d'injection sur un fond de chambre de combustion de turboréacteur et procède de fixation
EP1818615A1 (fr) * 2006-02-10 2007-08-15 Snecma Chambre de combustion annulaire d'une turbomachine
EP1826492A1 (fr) * 2006-02-27 2007-08-29 Snecma Agencement pour une chambre de combustion de turboréacteur

Also Published As

Publication number Publication date
FR2921462B1 (fr) 2012-08-24
US20090077976A1 (en) 2009-03-26
RU2485405C2 (ru) 2013-06-20
CA2639588C (fr) 2016-03-29
RU2008137660A (ru) 2010-03-27
EP2040001B1 (fr) 2018-04-18
FR2921462A1 (fr) 2009-03-27
EP2040001A2 (fr) 2009-03-25
US8156744B2 (en) 2012-04-17
CA2639588A1 (fr) 2009-03-21

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