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FR2865001B1 - Turboreacteur comprenant un bras de raccord de servitudes, et le bras de raccord de servitudes. - Google Patents

Turboreacteur comprenant un bras de raccord de servitudes, et le bras de raccord de servitudes.

Info

Publication number
FR2865001B1
FR2865001B1 FR0400221A FR0400221A FR2865001B1 FR 2865001 B1 FR2865001 B1 FR 2865001B1 FR 0400221 A FR0400221 A FR 0400221A FR 0400221 A FR0400221 A FR 0400221A FR 2865001 B1 FR2865001 B1 FR 2865001B1
Authority
FR
France
Prior art keywords
servitude
connecting arm
turboreactor
arm
servitude connecting
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 - Lifetime
Application number
FR0400221A
Other languages
English (en)
Other versions
FR2865001A1 (fr
Inventor
Jacky Derenes
Georges Mazeaud
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 Moteurs 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
Application filed by SNECMA Moteurs SA filed Critical SNECMA Moteurs SA
Priority to FR0400221A priority Critical patent/FR2865001B1/fr
Priority to CA2492166A priority patent/CA2492166C/fr
Priority to UAA200500229 priority patent/UA85824C2/uk
Priority to US11/031,004 priority patent/US7543442B2/en
Priority to JP2005003400A priority patent/JP4188323B2/ja
Priority to RU2005100180/06A priority patent/RU2388921C2/ru
Priority to EP05300017.0A priority patent/EP1553263B1/fr
Priority to CN2005100041680A priority patent/CN1657757B/zh
Publication of FR2865001A1 publication Critical patent/FR2865001A1/fr
Application granted granted Critical
Publication of FR2865001B1 publication Critical patent/FR2865001B1/fr
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

Links

Classifications

    • 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
    • F01D9/00—Stators
    • F01D9/06—Fluid supply conduits to nozzles or the like
    • F01D9/065—Fluid supply or removal conduits traversing the working fluid flow, e.g. for lubrication-, cooling-, or sealing fluids

Landscapes

  • Engineering & Computer Science (AREA)
  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
FR0400221A 2004-01-12 2004-01-12 Turboreacteur comprenant un bras de raccord de servitudes, et le bras de raccord de servitudes. Expired - Lifetime FR2865001B1 (fr)

Priority Applications (8)

Application Number Priority Date Filing Date Title
FR0400221A FR2865001B1 (fr) 2004-01-12 2004-01-12 Turboreacteur comprenant un bras de raccord de servitudes, et le bras de raccord de servitudes.
UAA200500229 UA85824C2 (uk) 2004-01-12 2005-01-10 Турбовентиляторний двигун і модульна консоль для турбовентиляторного двигуна
US11/031,004 US7543442B2 (en) 2004-01-12 2005-01-10 Turbojet engine comprising a connector arm for ancillary systems, and the connector arm for ancillary systems
CA2492166A CA2492166C (fr) 2004-01-12 2005-01-10 Turboreacteur comprenant un bras de raccord de servitudes, et le bras de raccord de servitudes
JP2005003400A JP4188323B2 (ja) 2004-01-12 2005-01-11 付属部品システム用のコネクタアームを備えたターボジェットエンジン、および付属部品システム用のコネクタアーム
RU2005100180/06A RU2388921C2 (ru) 2004-01-12 2005-01-11 Турбореактивный двигатель, содержащий соединительную лопасть для вспомогательных устройств, и соединительная лопасть для вспомогательных устройств
EP05300017.0A EP1553263B1 (fr) 2004-01-12 2005-01-11 Entretoise pourvue de raccordements des canalisations de service d'un turboréacteur
CN2005100041680A CN1657757B (zh) 2004-01-12 2005-01-12 包括用于副系统的连接器臂的涡轮喷气飞机发动机及用于副系统的连接器臂

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
FR0400221A FR2865001B1 (fr) 2004-01-12 2004-01-12 Turboreacteur comprenant un bras de raccord de servitudes, et le bras de raccord de servitudes.

Publications (2)

Publication Number Publication Date
FR2865001A1 FR2865001A1 (fr) 2005-07-15
FR2865001B1 true FR2865001B1 (fr) 2008-05-09

Family

ID=34586487

Family Applications (1)

Application Number Title Priority Date Filing Date
FR0400221A Expired - Lifetime FR2865001B1 (fr) 2004-01-12 2004-01-12 Turboreacteur comprenant un bras de raccord de servitudes, et le bras de raccord de servitudes.

Country Status (8)

Country Link
US (1) US7543442B2 (fr)
EP (1) EP1553263B1 (fr)
JP (1) JP4188323B2 (fr)
CN (1) CN1657757B (fr)
CA (1) CA2492166C (fr)
FR (1) FR2865001B1 (fr)
RU (1) RU2388921C2 (fr)
UA (1) UA85824C2 (fr)

Families Citing this family (24)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20060032974A1 (en) * 2004-08-16 2006-02-16 Honeywell International Inc. Modular installation kit for auxiliary power unit
US7624581B2 (en) * 2005-12-21 2009-12-01 General Electric Company Compact booster bleed turbofan
FR2905975B1 (fr) * 2006-09-20 2008-12-05 Snecma Sa Conduite de soufflante pour une turbomachine.
US20080072566A1 (en) * 2006-09-27 2008-03-27 Pratt & Whitney Canada Corp. Bleed holes oriented with gaspath and flared for noise reduction
FR2919347B1 (fr) * 2007-07-26 2009-11-20 Snecma Enveloppe externe de conduite de soufflante dans une turbomachine.
FR2919344B1 (fr) * 2007-07-26 2013-08-16 Snecma Turboreacteur a double flux comprenant une conduite de soufflante a un seul bras de passage de servitudes.
FR2933070B1 (fr) * 2008-06-25 2010-08-20 Snecma Systeme propulsif d'aeronef
FR2937301B1 (fr) * 2008-10-22 2010-12-10 Snecma Avion a groupes motopropulseurs partiellement encastres dans le fuselage
US9478896B2 (en) 2011-12-22 2016-10-25 Rolls-Royce Plc Electrical connectors
GB2497807B (en) 2011-12-22 2014-09-10 Rolls Royce Plc Electrical harness
GB2498006B (en) 2011-12-22 2014-07-09 Rolls Royce Plc Gas turbine engine systems
GB2497809B (en) * 2011-12-22 2014-03-12 Rolls Royce Plc Method of servicing a gas turbine engine
FR2996070B1 (fr) * 2012-09-21 2018-09-21 Snecma Systeme de guidage de cable dans une veine de turbomachine
WO2014051658A1 (fr) 2012-09-26 2014-04-03 United Technologies Corporation Ensemble joint pour une structure statique d'un moteur à turbine à gaz
US9376935B2 (en) 2012-12-18 2016-06-28 Pratt & Whitney Canada Corp. Gas turbine engine mounting ring
FR3015569B1 (fr) * 2013-12-19 2019-01-25 Safran Aircraft Engines Carter pour un ensemble propulsif
FR3034465B1 (fr) * 2015-04-03 2017-05-05 Snecma Turbomoteur comportant deux flux de ventilation distincts
FR3036437B1 (fr) * 2015-05-22 2017-05-05 Snecma Ensemble de turbomachine pour lubrifier un support de palier
US10727656B2 (en) * 2017-11-08 2020-07-28 Raytheon Technologies Corporation Igniter cable conduit for gas turbine engine
US11230995B2 (en) 2017-11-08 2022-01-25 Raytheon Technologies Corporation Cable conduit for turbine engine bypass
GB201820505D0 (en) * 2018-12-17 2019-01-30 Rolls Royce Connector system
FR3097258B1 (fr) * 2019-06-14 2021-07-02 Safran Aircraft Engines Systeme de passage de servitudes a encombrement optimise des servitudes et a montage simplifie
FR3110547B1 (fr) * 2020-05-20 2022-04-22 Safran Nacelles Nacelle pour ensemble propulsif à très grand taux de dilution, comprenant une structure interne avant amovible et structurelle
FR3156488B1 (fr) * 2023-12-12 2025-11-07 Safran Aircraft Engines Systeme de passage de fluides pour une cloison d’une turbomachine et turbomachine comportant un tel systeme

Family Cites Families (11)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3841089A (en) * 1973-02-20 1974-10-15 Ltv Aerospace Corp Fuel reclaiming system
RU1254798C (ru) * 1983-11-15 1995-06-27 Запорожское машиностроительное конструкторское бюро "Прогресс" Устройство для дренажа топлива из камеры сгорания газотурбинного двигателя
US4987736A (en) * 1988-12-14 1991-01-29 General Electric Company Lightweight gas turbine engine frame with free-floating heat shield
US5174110A (en) * 1991-10-17 1992-12-29 United Technologies Corporation Utility conduit enclosure for turbine engine
US5313780A (en) * 1992-12-07 1994-05-24 General Electric Company Free-riding oil tube damper
US5292227A (en) * 1992-12-10 1994-03-08 General Electric Company Turbine frame
US5746574A (en) * 1997-05-27 1998-05-05 General Electric Company Low profile fluid joint
US6125627A (en) * 1998-08-11 2000-10-03 Allison Advanced Development Company Method and apparatus for spraying fuel within a gas turbine engine
US6619917B2 (en) * 2000-12-19 2003-09-16 United Technologies Corporation Machined fan exit guide vane attachment pockets for use in a gas turbine
RU2199670C1 (ru) * 2001-07-16 2003-02-27 Открытое Акционерное Общество "А. Люлька-Сатурн" Регулируемый входной направляющий аппарат компрессора газотурбинного двигателя
US7370467B2 (en) * 2003-07-29 2008-05-13 Pratt & Whitney Canada Corp. Turbofan case and method of making

Also Published As

Publication number Publication date
FR2865001A1 (fr) 2005-07-15
JP2005201266A (ja) 2005-07-28
CN1657757A (zh) 2005-08-24
EP1553263A1 (fr) 2005-07-13
RU2388921C2 (ru) 2010-05-10
UA85824C2 (uk) 2009-03-10
CA2492166A1 (fr) 2005-07-12
US20050247043A1 (en) 2005-11-10
EP1553263B1 (fr) 2016-05-18
US7543442B2 (en) 2009-06-09
CA2492166C (fr) 2012-06-19
CN1657757B (zh) 2011-05-04
JP4188323B2 (ja) 2008-11-26
RU2005100180A (ru) 2006-06-20

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