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FR3042023B1 - Chambre de combustion annulaire pour turbomachine - Google Patents

Chambre de combustion annulaire pour turbomachine Download PDF

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Publication number
FR3042023B1
FR3042023B1 FR1559491A FR1559491A FR3042023B1 FR 3042023 B1 FR3042023 B1 FR 3042023B1 FR 1559491 A FR1559491 A FR 1559491A FR 1559491 A FR1559491 A FR 1559491A FR 3042023 B1 FR3042023 B1 FR 3042023B1
Authority
FR
France
Prior art keywords
combustion chamber
injectors
injector
turbomachine
annular 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.)
Expired - Fee Related
Application number
FR1559491A
Other languages
English (en)
Other versions
FR3042023A1 (fr
Inventor
Stephane PASCAUD
Guillaume TALIERCIO
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 Helicopter Engines SAS
Original Assignee
Safran Helicopter Engines SAS
Turbomeca SA
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 to FR1559491A priority Critical patent/FR3042023B1/fr
Application filed by Safran Helicopter Engines SAS, Turbomeca SA filed Critical Safran Helicopter Engines SAS
Priority to KR1020187009802A priority patent/KR20180063120A/ko
Priority to CA3000922A priority patent/CA3000922A1/fr
Priority to CN201680058929.7A priority patent/CN108139077B/zh
Priority to US15/765,823 priority patent/US10895383B2/en
Priority to EP16787502.0A priority patent/EP3359880B1/fr
Priority to PCT/FR2016/052539 priority patent/WO2017060605A1/fr
Priority to JP2018517607A priority patent/JP2018534518A/ja
Priority to RU2018116261A priority patent/RU2718375C2/ru
Priority to PL16787502T priority patent/PL3359880T3/pl
Publication of FR3042023A1 publication Critical patent/FR3042023A1/fr
Application granted granted Critical
Publication of FR3042023B1 publication Critical patent/FR3042023B1/fr
Expired - Fee Related 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
    • F23R3/06—Arrangement of apertures along the flame tube
    • 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
    • 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
    • F23R3/42—Continuous combustion chambers using liquid or gaseous fuel characterised by the arrangement or form of the flame tubes or combustion chambers
    • F23R3/54—Reverse-flow combustion chambers
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2240/00—Components
    • F05D2240/35—Combustors or associated equipment

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)
  • Turbine Rotor Nozzle Sealing (AREA)

Abstract

Chambre de combustion annulaire (10) comportant une première paroi annulaire (12) et une deuxième paroi annulaire (13) coaxiales autour d'un axe (X), un fond de chambre (14) reliant les première et deuxième parois (12, 13), et une pluralité d'injecteurs (16), la première paroi (12) comportant des premiers trous (18) d'alimentation en air en aval des injecteurs (16), la chambre de combustion (10) étant caractérisée en ce que pour au moins un premier desdits injecteurs (16), au moins quatre des premiers trous (18) ayant en commun le premier injecteur comme injecteur le plus proche sont situés le long d'une courbe (C) strictement convexe, en vue radiale, la concavité de la courbe étant tournée vers le premier injecteur (16).
FR1559491A 2015-10-06 2015-10-06 Chambre de combustion annulaire pour turbomachine Expired - Fee Related FR3042023B1 (fr)

Priority Applications (10)

Application Number Priority Date Filing Date Title
FR1559491A FR3042023B1 (fr) 2015-10-06 2015-10-06 Chambre de combustion annulaire pour turbomachine
RU2018116261A RU2718375C2 (ru) 2015-10-06 2016-10-04 Кольцевая камера сгорания для газотурбинного двигателя
CN201680058929.7A CN108139077B (zh) 2015-10-06 2016-10-04 用于涡轮发动机的环形燃烧腔室
US15/765,823 US10895383B2 (en) 2015-10-06 2016-10-04 Ring-shaped combustion chamber for a turbine engine
EP16787502.0A EP3359880B1 (fr) 2015-10-06 2016-10-04 Chambre de combustion annulaire pour turbomachine
PCT/FR2016/052539 WO2017060605A1 (fr) 2015-10-06 2016-10-04 Chambre de combustion annulaire pour turbomachine
KR1020187009802A KR20180063120A (ko) 2015-10-06 2016-10-04 터빈 엔진용 환상 연소실
CA3000922A CA3000922A1 (fr) 2015-10-06 2016-10-04 Chambre de combustion annulaire pour turbomachine
PL16787502T PL3359880T3 (pl) 2015-10-06 2016-10-04 Pierścieniowa komora spalania do maszyny wirowej
JP2018517607A JP2018534518A (ja) 2015-10-06 2016-10-04 タービンエンジン用環状燃焼室

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR1559491A FR3042023B1 (fr) 2015-10-06 2015-10-06 Chambre de combustion annulaire pour turbomachine
FR1559491 2015-10-06

Publications (2)

Publication Number Publication Date
FR3042023A1 FR3042023A1 (fr) 2017-04-07
FR3042023B1 true FR3042023B1 (fr) 2020-06-05

Family

ID=54979773

Family Applications (1)

Application Number Title Priority Date Filing Date
FR1559491A Expired - Fee Related FR3042023B1 (fr) 2015-10-06 2015-10-06 Chambre de combustion annulaire pour turbomachine

Country Status (10)

Country Link
US (1) US10895383B2 (fr)
EP (1) EP3359880B1 (fr)
JP (1) JP2018534518A (fr)
KR (1) KR20180063120A (fr)
CN (1) CN108139077B (fr)
CA (1) CA3000922A1 (fr)
FR (1) FR3042023B1 (fr)
PL (1) PL3359880T3 (fr)
RU (1) RU2718375C2 (fr)
WO (1) WO2017060605A1 (fr)

Family Cites Families (19)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3671171A (en) 1970-11-27 1972-06-20 Avco Corp Annular combustors
CA2076102C (fr) 1991-09-23 2001-12-18 Stephen John Howell Chambre de combustion a bague de projection
FR2690977B1 (fr) 1992-05-06 1995-09-01 Snecma Chambre de combustion comportant des passages reglables d'admission de comburant primaire.
EP0700498B1 (fr) * 1993-06-01 1998-10-21 Pratt & Whitney Canada, Inc. Injecteur radial de carburant, a entrainement d'air
FR2751054B1 (fr) 1996-07-11 1998-09-18 Snecma Chambre de combustion anti-nox a injection de carburant de type annulaire
US6155056A (en) * 1998-06-04 2000-12-05 Pratt & Whitney Canada Corp. Cooling louver for annular gas turbine engine combustion chamber
US6367262B1 (en) * 2000-09-29 2002-04-09 General Electric Company Multiple annular swirler
FR2856467B1 (fr) * 2003-06-18 2005-09-02 Snecma Moteurs Chambre de combustion annulaire de turbomachine
US7509809B2 (en) * 2005-06-10 2009-03-31 Pratt & Whitney Canada Corp. Gas turbine engine combustor with improved cooling
FR2903169B1 (fr) * 2006-06-29 2011-11-11 Snecma Dispositif d'injection d'un melange d'air et de carburant, chambre de combustion et turbomachine munies d'un tel dispositif
FR2911667B1 (fr) * 2007-01-23 2009-10-02 Snecma Sa Systeme d'injection de carburant a double injecteur.
US8171634B2 (en) * 2007-07-09 2012-05-08 Pratt & Whitney Canada Corp. Method of producing effusion holes
FR2919380B1 (fr) * 2007-07-26 2013-10-25 Snecma Chambre de combustion d'une turbomachine.
US8616004B2 (en) 2007-11-29 2013-12-31 Honeywell International Inc. Quench jet arrangement for annular rich-quench-lean gas turbine combustors
FR2941287B1 (fr) * 2009-01-19 2011-03-25 Snecma Paroi de chambre de combustion de turbomachine a une seule rangee annulaire d'orifices d'entree d'air primaire et de dilution
US8171740B2 (en) * 2009-02-27 2012-05-08 Honeywell International Inc. Annular rich-quench-lean gas turbine combustors with plunged holes
FR2948988B1 (fr) 2009-08-04 2011-12-09 Snecma Chambre de combustion de turbomachine comprenant des orifices d'entree d'air ameliores
US9080770B2 (en) * 2011-06-06 2015-07-14 Honeywell International Inc. Reverse-flow annular combustor for reduced emissions
CN204460285U (zh) 2014-12-03 2015-07-08 中国航空工业集团公司金城南京机电液压工程研究中心 一种环形回流燃烧室火焰筒

Also Published As

Publication number Publication date
US10895383B2 (en) 2021-01-19
CA3000922A1 (fr) 2017-04-13
JP2018534518A (ja) 2018-11-22
CN108139077B (zh) 2020-09-15
FR3042023A1 (fr) 2017-04-07
EP3359880B1 (fr) 2019-08-21
US20180299127A1 (en) 2018-10-18
WO2017060605A1 (fr) 2017-04-13
RU2018116261A3 (fr) 2020-01-21
RU2018116261A (ru) 2019-11-07
PL3359880T3 (pl) 2019-12-31
EP3359880A1 (fr) 2018-08-15
RU2718375C2 (ru) 2020-04-02
CN108139077A (zh) 2018-06-08
KR20180063120A (ko) 2018-06-11

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Year of fee payment: 2

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Effective date: 20170407

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Owner name: SAFRAN HELICOPTER ENGINES, FR

Effective date: 20180717

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Effective date: 20220605