EP1746348A3 - Turbomachine à distribution angulaire de l'air - Google Patents

Turbomachine à distribution angulaire de l'air Download PDF

Info

Publication number
EP1746348A3
EP1746348A3 EP06117022.1A EP06117022A EP1746348A3 EP 1746348 A3 EP1746348 A3 EP 1746348A3 EP 06117022 A EP06117022 A EP 06117022A EP 1746348 A3 EP1746348 A3 EP 1746348A3
Authority
EP
European Patent Office
Prior art keywords
annular
section
inclination
turbomachine
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
EP06117022.1A
Other languages
German (de)
English (en)
Other versions
EP1746348A2 (fr
EP1746348B1 (fr
Inventor
Michel Buret
Michel Cazalens
Didier Hernandez
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 EP1746348A2 publication Critical patent/EP1746348A2/fr
Publication of EP1746348A3 publication Critical patent/EP1746348A3/fr
Application granted granted Critical
Publication of EP1746348B1 publication Critical patent/EP1746348B1/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
    • F23R3/02—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
    • F23R3/12—Air inlet arrangements for primary air inducing a vortex
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23C—METHODS OR APPARATUS FOR COMBUSTION USING FLUID FUEL OR SOLID FUEL SUSPENDED IN  A CARRIER GAS OR AIR 
    • F23C5/00—Disposition of burners with respect to the combustion chamber or to one another; Mounting of burners in combustion apparatus
    • F23C5/08—Disposition of burners
    • F23C5/32—Disposition of burners to obtain rotating flames, i.e. flames moving helically or spirally
    • 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
    • F23R2900/00—Special features of, or arrangements for continuous combustion chambers; Combustion processes therefor
    • F23R2900/03042—Film cooled combustion chamber walls or domes

Landscapes

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

Abstract

Ensemble de turbomachine comportant une section annulaire de compression, un carter formé d'une enveloppe annulaire externe (204) et d'une enveloppe annulaire interne (206) fixée à l'intérieur de l'enveloppe externe à l'aide d'une pluralité de bras radiaux de maintien (208), une section annulaire de combustion logée à l'intérieur du carter, et une section annulaire de turbine. L'air issu de la section de compression présente un mouvement giratoire avec une inclinaison par rapport à un axe longitudinal (X-X) de la turbomachine, et la section de combustion comporte des moyens de distribution angulaire de l'air pour donner aux gaz issus de la section de combustion un mouvement giratoire avec une inclinaison égale ou supérieure à celle de l'air issu de la section de compression, lesdits moyens de distribution étant formés par les bras de maintien (208) qui présentent chacun une inclinaison par rapport à l'axe longitudinal (X-X) de la turbomachine égale ou supérieure à celle de l'air issu de la section de compression.
EP06117022.1A 2005-07-18 2006-07-12 Turbomachine à distribution angulaire de l'air Active EP1746348B1 (fr)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
FR0507578A FR2888631B1 (fr) 2005-07-18 2005-07-18 Turbomachine a distribution angulaire de l'air

Publications (3)

Publication Number Publication Date
EP1746348A2 EP1746348A2 (fr) 2007-01-24
EP1746348A3 true EP1746348A3 (fr) 2013-05-01
EP1746348B1 EP1746348B1 (fr) 2015-06-10

Family

ID=36001030

Family Applications (1)

Application Number Title Priority Date Filing Date
EP06117022.1A Active EP1746348B1 (fr) 2005-07-18 2006-07-12 Turbomachine à distribution angulaire de l'air

Country Status (4)

Country Link
US (1) US7549294B2 (fr)
EP (1) EP1746348B1 (fr)
FR (1) FR2888631B1 (fr)
RU (1) RU2415342C2 (fr)

Families Citing this family (16)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2007102807A1 (fr) * 2006-03-06 2007-09-13 United Technologies Corporation Chambre de combustion annulaire à flux en biais pour moteur à turbine
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
US7798765B2 (en) * 2007-04-12 2010-09-21 United Technologies Corporation Out-flow margin protection for a gas turbine engine
US7594401B1 (en) * 2008-04-10 2009-09-29 General Electric Company Combustor seal having multiple cooling fluid pathways
FR2931515B1 (fr) * 2008-05-22 2014-07-18 Snecma Turbomachine avec diffuseur
US8104288B2 (en) * 2008-09-25 2012-01-31 Honeywell International Inc. Effusion cooling techniques for combustors in engine assemblies
FR2945854B1 (fr) * 2009-05-19 2015-08-07 Snecma Vrille melangeuse pour un injecteur de carburant dans une chambre de combustion d'une turbine a gaz et dispositif de combustion correspondant
FR2955375B1 (fr) * 2010-01-18 2012-06-15 Turbomeca Dispositif d'injection et chambre de combustion de turbomachine equipee d'un tel dispositif d'injection
DE102010023816A1 (de) 2010-06-15 2011-12-15 Rolls-Royce Deutschland Ltd & Co Kg Gasturbinenbrennkammeranordnung
FR2964725B1 (fr) * 2010-09-14 2012-10-12 Snecma Carenage aerodynamique pour fond de chambre de combustion
DE102011108887A1 (de) 2011-07-28 2013-01-31 Rolls-Royce Deutschland Ltd & Co Kg Gasturbinenzentripetalringbrennkammer sowie Verfahren zur Strömungsführung
US20150323185A1 (en) * 2014-05-07 2015-11-12 General Electric Compamy Turbine engine and method of assembling thereof
JP6456481B2 (ja) * 2014-08-26 2019-01-23 シーメンス エナジー インコーポレイテッド ガスタービンエンジン内の音響共鳴器用のフィルム冷却孔配列
DE102017100984B4 (de) 2017-01-19 2019-03-07 Karlsruher Institut für Technologie Gasturbinenbrennkammeranordnung
US10823422B2 (en) * 2017-10-17 2020-11-03 General Electric Company Tangential bulk swirl air in a trapped vortex combustor for a gas turbine engine
US11181269B2 (en) 2018-11-15 2021-11-23 General Electric Company Involute trapped vortex combustor assembly

Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR1173468A (fr) * 1956-04-03 1959-02-25 Bristol Aero Engines Ltd Perfectionnements aux chambres de combustion
DE1145438B (de) * 1958-12-15 1963-03-14 Bristol Siddeley Engines Ltd Brenneinrichtung
US4996838A (en) * 1988-10-27 1991-03-05 Sol-3 Resources, Inc. Annular vortex slinger combustor
EP0590297A1 (fr) * 1992-09-26 1994-04-06 Asea Brown Boveri Ag Chambre de combustion de turbine à gaz
DE19541303A1 (de) * 1995-11-06 1997-05-28 Siemens Ag Gasturbine

Family Cites Families (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4638628A (en) * 1978-10-26 1987-01-27 Rice Ivan G Process for directing a combustion gas stream onto rotatable blades of a gas turbine

Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR1173468A (fr) * 1956-04-03 1959-02-25 Bristol Aero Engines Ltd Perfectionnements aux chambres de combustion
DE1145438B (de) * 1958-12-15 1963-03-14 Bristol Siddeley Engines Ltd Brenneinrichtung
US4996838A (en) * 1988-10-27 1991-03-05 Sol-3 Resources, Inc. Annular vortex slinger combustor
EP0590297A1 (fr) * 1992-09-26 1994-04-06 Asea Brown Boveri Ag Chambre de combustion de turbine à gaz
DE19541303A1 (de) * 1995-11-06 1997-05-28 Siemens Ag Gasturbine

Also Published As

Publication number Publication date
FR2888631A1 (fr) 2007-01-19
EP1746348A2 (fr) 2007-01-24
EP1746348B1 (fr) 2015-06-10
FR2888631B1 (fr) 2010-12-10
RU2415342C2 (ru) 2011-03-27
RU2006125657A (ru) 2008-01-27
US7549294B2 (en) 2009-06-23
US20070012048A1 (en) 2007-01-18

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