FR2932227B1 - Turboreacteur double flux - Google Patents

Turboreacteur double flux

Info

Publication number
FR2932227B1
FR2932227B1 FR0853807A FR0853807A FR2932227B1 FR 2932227 B1 FR2932227 B1 FR 2932227B1 FR 0853807 A FR0853807 A FR 0853807A FR 0853807 A FR0853807 A FR 0853807A FR 2932227 B1 FR2932227 B1 FR 2932227B1
Authority
FR
France
Prior art keywords
turbojet
double flow
ifd
high pressure
pressure compressor
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.)
Active
Application number
FR0853807A
Other languages
English (en)
Other versions
FR2932227A1 (fr
Inventor
Romuald Gentils
Stephane Rousselin
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
Priority to FR0853807A priority Critical patent/FR2932227B1/fr
Priority to US12/475,619 priority patent/US8419352B2/en
Publication of FR2932227A1 publication Critical patent/FR2932227A1/fr
Application granted granted Critical
Publication of FR2932227B1 publication Critical patent/FR2932227B1/fr
Active legal-status Critical Current
Anticipated expiration legal-status Critical

Links

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02K—JET-PROPULSION PLANTS
    • F02K3/00—Plants including a gas turbine driving a compressor or a ducted fan
    • F02K3/02—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber
    • F02K3/04—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber the plant including ducted fans, i.e. fans with high volume, low pressure outputs, for augmenting the jet thrust, e.g. of double-flow type
    • F02K3/06—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber the plant including ducted fans, i.e. fans with high volume, low pressure outputs, for augmenting the jet thrust, e.g. of double-flow type with front fan
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/24—Casings; Casing parts, e.g. diaphragms, casing fastenings
    • F01D25/26—Double casings; Measures against temperature strain in casings

Landscapes

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

Abstract

L'invention concerne un turboréacteur double flux qui comporte un capot externe OFD et un capot interne IFD (122) entre lesquels circule le flux secondaire, et un compresseur haute pression (116) comprenant un carter externe (124). De façon caractéristique, le capot interne IFD (122) est fixé sur le carter externe (124). Application à un turboréacteur avec compresseur haute pression (116) de type axialo-centrifuge.
FR0853807A 2008-06-09 2008-06-09 Turboreacteur double flux Active FR2932227B1 (fr)

Priority Applications (2)

Application Number Priority Date Filing Date Title
FR0853807A FR2932227B1 (fr) 2008-06-09 2008-06-09 Turboreacteur double flux
US12/475,619 US8419352B2 (en) 2008-06-09 2009-06-01 Bypass turbojet

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
FR0853807A FR2932227B1 (fr) 2008-06-09 2008-06-09 Turboreacteur double flux

Publications (2)

Publication Number Publication Date
FR2932227A1 FR2932227A1 (fr) 2009-12-11
FR2932227B1 true FR2932227B1 (fr) 2011-07-01

Family

ID=40097241

Family Applications (1)

Application Number Title Priority Date Filing Date
FR0853807A Active FR2932227B1 (fr) 2008-06-09 2008-06-09 Turboreacteur double flux

Country Status (2)

Country Link
US (1) US8419352B2 (fr)
FR (1) FR2932227B1 (fr)

Families Citing this family (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2952126B1 (fr) * 2009-11-04 2011-12-23 Snecma Turbomachine a double flux pour aeronef, comprenant des moyens structuraux de rigidification du carter central
US9062603B2 (en) 2012-06-20 2015-06-23 United Technologies Corporation Four bar drive mechanism for bleed system
US9091209B2 (en) 2012-06-20 2015-07-28 United Technologies Corporation Four bar bracket
WO2014137430A1 (fr) 2013-03-08 2014-09-12 Rolls-Royce North American Technologies, Inc. Compresseur centrifuge de moteur à turbine à gaz doté d'un joint entre deux parties de diffuseur
US20180135525A1 (en) * 2016-11-14 2018-05-17 Pratt & Whitney Canada Corp. Gas turbine engine tangential orifice bleed configuration

Family Cites Families (14)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3357176A (en) * 1965-09-22 1967-12-12 Williams Res Corp Twin spool gas turbine engine with axial and centrifugal compressors
US3823553A (en) * 1972-12-26 1974-07-16 Gen Electric Gas turbine with removable self contained power turbine module
US4112677A (en) * 1977-01-31 1978-09-12 Avco Corporation Thrust spoiler for turbofan engine
DE3315914A1 (de) 1983-05-02 1984-11-08 MTU Motoren- und Turbinen-Union München GmbH, 8000 München Gasturbinentriebwerk mit einrichtungen zur schaufelspaltminimierung
US5237817A (en) * 1992-02-19 1993-08-24 Sundstrand Corporation Gas turbine engine having low cost speed reduction drive
US5619850A (en) * 1995-05-09 1997-04-15 Alliedsignal Inc. Gas turbine engine with bleed air buffer seal
US6488469B1 (en) * 2000-10-06 2002-12-03 Pratt & Whitney Canada Corp. Mixed flow and centrifugal compressor for gas turbine engine
US6647730B2 (en) * 2001-10-31 2003-11-18 Pratt & Whitney Canada Corp. Turbine engine having turbine cooled with diverted compressor intermediate pressure air
US6935840B2 (en) * 2002-07-15 2005-08-30 Pratt & Whitney Canada Corp. Low cycle fatigue life (LCF) impeller design concept
EP1777378A3 (fr) * 2003-07-29 2011-03-09 Pratt & Whitney Canada Corp. Enveloppe de réacteur à double flux et procédé de fabrication
JP2005226584A (ja) * 2004-02-13 2005-08-25 Honda Motor Co Ltd コンプレッサ及びガスタービンエンジン
US7059136B2 (en) * 2004-08-27 2006-06-13 General Electric Company Air turbine powered accessory
JP4279245B2 (ja) * 2004-12-06 2009-06-17 本田技研工業株式会社 ガスタービンエンジン
US8057157B2 (en) * 2007-10-22 2011-11-15 General Electric Company System for delivering air from a multi-stage compressor to a turbine portion of a gas turbine engine

Also Published As

Publication number Publication date
FR2932227A1 (fr) 2009-12-11
US8419352B2 (en) 2013-04-16
US20100047059A1 (en) 2010-02-25

Similar Documents

Publication Publication Date Title
FR2932227B1 (fr) Turboreacteur double flux
EP1531236A3 (fr) Boîtier de compresseur de turbine à gaz avec des orifices de soutirage
FR3034129B1 (fr) Aube mobile de turbine a conception amelioree pour turbomachine d'aeronef
EP1566524A3 (fr) Refroidissement de la carcasse d'enveloppe de turbine
FR2928180B1 (fr) Ensemble moteur pour aeronef comprenant une structure annulaire de transfert d'efforts entourant le carter central d'un turboreacteur.
RU2006114259A (ru) Устройство герметизации камеры газотурбинного двигателя, и оборудованный им двигатель летательного аппарата
CA2400151A1 (fr) Secteur d'entretoise de support d'anneau de stator de la turbine haute pression d'une turbomachine avec rattrapage de jeux
ATE458672T1 (de) Abdeckstruktur für einen lufteinlass
FR3051016B1 (fr) Dispositif de degivrage d'un bec de separation de turbomachine aeronautique
WO2008030214A3 (fr) Joint d'étanchéité de bride à ressort de turbine
RU2010116161A (ru) Камера сгорания
EP4234989A3 (fr) Dispositif de couplage de fluide de translation
EP3249171A3 (fr) Ensemble joint d'étanchéité
FR3066552B1 (fr) Assemblage sur un arbre de turbomachine d'un disque aubage monobloc et d'un rotor de compresseur basse pression a au moins deux etages d'aubes mobiles
EP2629014A3 (fr) Butée de guidage de chemise de combustion et procédé d'assemblage d'une chambre de combustion
FR3095830B1 (fr) Module de turbomachine equipe d’un dispositif de maintien de lamelles d’etancheite
WO2016185336A1 (fr) Compresseur à spirale
FR3080887B1 (fr) Systeme de refroidissement d'un moteur avec deux thermostats et integrant un circuit selon un cycle de rankine
EP1433924A3 (fr) Chambre de combustion de turbine à gaz
PL406855A1 (pl) Zespół unieruchamiający łożysko i sposób jego montażu
FR3099801B1 (fr) Ensemble pour une turbine de turbomachine
FR3055655B1 (fr) Carter intermediaire de turbine de turbomachine
FR3035447B1 (fr) Turbomoteur pour un aeronef equipe d'un centreur a activation automatique
FR3063403B1 (fr) Moteur electrique d'un aeronef comprenant un systeme de refroidissement a ailettes monobloc avec le stator
FR3062679B1 (fr) Virole de reduction de la surpression au voisinage du joint amont d'une enceinte de palier de turboreacteur

Legal Events

Date Code Title Description
PLFP Fee payment

Year of fee payment: 9

PLFP Fee payment

Year of fee payment: 10

PLFP Fee payment

Year of fee payment: 11

CD Change of name or company name

Owner name: SAFRAN AIRCRAFT ENGINES, FR

Effective date: 20170719

PLFP Fee payment

Year of fee payment: 13

PLFP Fee payment

Year of fee payment: 14

PLFP Fee payment

Year of fee payment: 15

PLFP Fee payment

Year of fee payment: 16