DE602006005027D1 - Vorrichtung zur Abstützung und Einlassung von Röhre und Kabeln in einem Turbotriebwerk - Google Patents

Vorrichtung zur Abstützung und Einlassung von Röhre und Kabeln in einem Turbotriebwerk

Info

Publication number
DE602006005027D1
DE602006005027D1 DE602006005027T DE602006005027T DE602006005027D1 DE 602006005027 D1 DE602006005027 D1 DE 602006005027D1 DE 602006005027 T DE602006005027 T DE 602006005027T DE 602006005027 T DE602006005027 T DE 602006005027T DE 602006005027 D1 DE602006005027 D1 DE 602006005027D1
Authority
DE
Germany
Prior art keywords
cables
supporting
turbocharged engine
fitting tubes
tubes
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
DE602006005027T
Other languages
English (en)
Inventor
Georges Mazeaud
Didier Jean-Louis Yvon
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 DE602006005027D1 publication Critical patent/DE602006005027D1/de
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
    • 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)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
DE602006005027T 2005-06-29 2006-06-23 Vorrichtung zur Abstützung und Einlassung von Röhre und Kabeln in einem Turbotriebwerk Active DE602006005027D1 (de)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
FR0506612A FR2887931B1 (fr) 2005-06-29 2005-06-29 Dispositif de support et de logement de servitudes dans un turboreacteur a double flux

Publications (1)

Publication Number Publication Date
DE602006005027D1 true DE602006005027D1 (de) 2009-03-19

Family

ID=35929691

Family Applications (1)

Application Number Title Priority Date Filing Date
DE602006005027T Active DE602006005027D1 (de) 2005-06-29 2006-06-23 Vorrichtung zur Abstützung und Einlassung von Röhre und Kabeln in einem Turbotriebwerk

Country Status (5)

Country Link
US (1) US7805949B2 (de)
EP (1) EP1741879B1 (de)
DE (1) DE602006005027D1 (de)
FR (1) FR2887931B1 (de)
RU (1) RU2324832C2 (de)

Families Citing this family (23)

* 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
US20080078162A1 (en) * 2006-09-28 2008-04-03 Guy Lefebvre Turbine exhaust case cowling for a gas turbine engine
FR2932233B1 (fr) * 2008-06-06 2012-09-28 Aircelle Sa Carter pour rotor de turbomachine
FR2933130B1 (fr) * 2008-06-25 2012-02-24 Snecma Carter structural pour turbomachine
US9121351B2 (en) * 2008-10-30 2015-09-01 Rolls-Royce North American Technologies, Inc. Gas turbine engine accessory system
US8966911B2 (en) * 2009-12-29 2015-03-03 Rolls-Royce North American Technologies, Inc. Turbofan engine with HP and LP power off-takes
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
GB2497807B (en) 2011-12-22 2014-09-10 Rolls Royce Plc Electrical harness
US9478896B2 (en) 2011-12-22 2016-10-25 Rolls-Royce Plc Electrical connectors
GB201306482D0 (en) * 2013-04-10 2013-05-22 Rolls Royce Plc Mounting arrangement
FR3005992B1 (fr) * 2013-05-24 2015-05-22 Snecma Dispositif de passage de servitudes pour une turbomachine
FR3008912B1 (fr) * 2013-07-29 2017-12-15 Snecma Carter de turbomachine et procede de fabrication
FR3010049B1 (fr) * 2013-09-04 2017-03-31 Snecma Structure de liaison moteur-nacelle a secteurs de virole pivotants
FR3015625B1 (fr) * 2013-12-20 2015-12-11 Snecma Bras de guidage d'elements de forme allongee, en particulier pour une turbomachine
US10900371B2 (en) 2017-07-27 2021-01-26 Rolls-Royce North American Technologies, Inc. Abradable coatings for high-performance systems
US10858950B2 (en) 2017-07-27 2020-12-08 Rolls-Royce North America Technologies, Inc. Multilayer abradable coatings for high-performance systems
FR3077846B1 (fr) * 2018-02-14 2020-03-13 Safran Aircraft Engines Virole exterieure de carter intermediaire pour turbomachine d'aeronef a double flux, comprenant des dispositifs ameliores d'etancheite a l'air et de resistance au feu
GB201808853D0 (en) * 2018-05-31 2018-07-18 Rolls Royce Plc A gas turbine engine bleed duct
GB201808852D0 (en) 2018-05-31 2018-07-18 Rolls Royce Plc Gas turbine engine
FR3096743B1 (fr) 2019-05-28 2021-05-07 Safran Aircraft Engines Paroi coupe-feu et procédé d’ouverture de celle-ci
US11047251B2 (en) 2019-07-17 2021-06-29 Rolls-Royce Corporation Routing for electrical communication in gas turbine engines
FR3117173A1 (fr) 2020-12-09 2022-06-10 Safran Aircraft Engines Ensemble propulsif d’aéronef et procédé d’adaptation d’un ensemble propulsif

Family Cites Families (14)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2827760A (en) * 1951-04-18 1958-03-25 Bristol Aero Engines Ltd Combined anti-icing and generator cooling arrangement for a gas turbine engine
US3571977A (en) * 1969-06-27 1971-03-23 Boeing Co Access and pressure release door latch mechanism
US3777489A (en) * 1972-06-01 1973-12-11 Gen Electric Combustor casing and concentric air bleed structure
US5012639A (en) * 1989-01-23 1991-05-07 United Technologies Corporation Buffer region for the nacelle of a gas turbine engine
US5123242A (en) * 1990-07-30 1992-06-23 General Electric Company Precooling heat exchange arrangement integral with mounting structure fairing of gas turbine engine
GB2267736B (en) * 1992-06-09 1995-08-09 Gen Electric Segmented turbine flowpath assembly
US5292227A (en) * 1992-12-10 1994-03-08 General Electric Company Turbine frame
US6012735A (en) * 1994-06-13 2000-01-11 Textron Automotive Company Trim panel having air bag door
US6581874B2 (en) * 2000-09-27 2003-06-24 Lord Corporation Mounting assembly for an aircraft auxiliary power unit and method
US6942452B2 (en) * 2002-12-17 2005-09-13 Pratt & Whitney Canada Corp. Grommeted bypass duct penetration
GB0315894D0 (en) * 2003-07-08 2003-08-13 Rolls Royce Plc Aircraft engine arrangement
US7083144B2 (en) * 2004-08-18 2006-08-01 The Boeing Company Apparatus and methods for support of propulsion systems interconnect members
US7124572B2 (en) * 2004-09-14 2006-10-24 Honeywell International, Inc. Recuperator and turbine support adapter for recuperated gas turbine engines
US7607308B2 (en) * 2005-12-08 2009-10-27 General Electric Company Shrouded turbofan bleed duct

Also Published As

Publication number Publication date
US20070084216A1 (en) 2007-04-19
RU2006123032A (ru) 2008-01-20
US7805949B2 (en) 2010-10-05
EP1741879A1 (de) 2007-01-10
FR2887931B1 (fr) 2007-08-17
EP1741879B1 (de) 2009-01-28
RU2324832C2 (ru) 2008-05-20
FR2887931A1 (fr) 2007-01-05

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Legal Events

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8364 No opposition during term of opposition