FR3002288B1 - Suspension d'un turboreacteur par double support arriere - Google Patents

Suspension d'un turboreacteur par double support arriere Download PDF

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Publication number
FR3002288B1
FR3002288B1 FR1351414A FR1351414A FR3002288B1 FR 3002288 B1 FR3002288 B1 FR 3002288B1 FR 1351414 A FR1351414 A FR 1351414A FR 1351414 A FR1351414 A FR 1351414A FR 3002288 B1 FR3002288 B1 FR 3002288B1
Authority
FR
France
Prior art keywords
turbojet
suspension
rear support
ring
flow channel
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
FR1351414A
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English (en)
Other versions
FR3002288A1 (fr
Inventor
Francois Robert Bellabal
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 FR1351414A priority Critical patent/FR3002288B1/fr
Priority to PCT/FR2014/050331 priority patent/WO2014128397A1/fr
Priority to US14/768,748 priority patent/US10184401B2/en
Publication of FR3002288A1 publication Critical patent/FR3002288A1/fr
Application granted granted Critical
Publication of FR3002288B1 publication Critical patent/FR3002288B1/fr
Active legal-status Critical Current
Anticipated expiration legal-status Critical

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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
    • F02C7/20—Mounting or supporting of plant; Accommodating heat expansion or creep
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D27/00—Arrangement or mounting of power plants in aircraft; Aircraft characterised by the type or position of power plants
    • B64D27/40—Arrangements for mounting power plants in aircraft
    • 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
    • F01D25/16—Arrangement of bearings; Supporting or mounting bearings in casings
    • F01D25/162—Bearing supports
    • 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
    • F01D25/28—Supporting or mounting arrangements, e.g. for turbine casing
    • 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
    • F02K3/025—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 by-pass flow being at least partly used to create an independent thrust component
    • 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
    • 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
    • F05D2260/00—Function
    • F05D2260/30—Retaining components in desired mutual position
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00—Aeronautics or air transport
    • Y02T50/40—Weight reduction
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00—Aeronautics or air transport
    • Y02T50/60—Efficient propulsion technologies, e.g. for aircraft

Landscapes

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

Abstract

Turboréacteur double flux équipé d'un canal de flux froid de forme cylindrique et comportant à une de ses extrémités axiales un anneau structural apte à recevoir les efforts transmis par le carter d'échappement dudit turboréacteur, ledit anneau comportant au moins un point d'attache apte à transmettre lesdits efforts à la structure d'un aéronef, caractérisé en ce que ledit anneau comporte une pluralité de points d'attache (4g, 4d) positionnés sur sa circonférence, lesdits points formant une figure géométrique à l'intérieur de laquelle passe l'axe de symétrie du canal de flux froid (7). Préférentiellement les points d'attache sont au nombre de deux et diamétralement opposés l'un par rapport à l'autre.
FR1351414A 2013-02-20 2013-02-20 Suspension d'un turboreacteur par double support arriere Active FR3002288B1 (fr)

Priority Applications (3)

Application Number Priority Date Filing Date Title
FR1351414A FR3002288B1 (fr) 2013-02-20 2013-02-20 Suspension d'un turboreacteur par double support arriere
PCT/FR2014/050331 WO2014128397A1 (fr) 2013-02-20 2014-02-17 Suspension d'un turboréacteur par double support arrière
US14/768,748 US10184401B2 (en) 2013-02-20 2014-02-17 Turbojet engine suspension using a double rear support

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
FR1351414A FR3002288B1 (fr) 2013-02-20 2013-02-20 Suspension d'un turboreacteur par double support arriere

Publications (2)

Publication Number Publication Date
FR3002288A1 FR3002288A1 (fr) 2014-08-22
FR3002288B1 true FR3002288B1 (fr) 2022-11-25

Family

ID=48521199

Family Applications (1)

Application Number Title Priority Date Filing Date
FR1351414A Active FR3002288B1 (fr) 2013-02-20 2013-02-20 Suspension d'un turboreacteur par double support arriere

Country Status (3)

Country Link
US (1) US10184401B2 (fr)
FR (1) FR3002288B1 (fr)
WO (1) WO2014128397A1 (fr)

Families Citing this family (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US10985608B2 (en) 2016-12-13 2021-04-20 General Electric Company Back-up power system for a component and method of assembling same
CN111865145A (zh) * 2019-04-26 2020-10-30 南京德朔实业有限公司 电动工具及其控制方法
US11697506B2 (en) * 2020-05-15 2023-07-11 General Electric Company Methods and apparatus for gas turbine bending isolation
GB2610571A (en) 2021-09-08 2023-03-15 Rolls Royce Plc An improved gas turbine engine
GB2610565A (en) * 2021-09-08 2023-03-15 Rolls Royce Plc An improved gas turbine engine

Family Cites Families (17)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4266741A (en) * 1978-05-22 1981-05-12 The Boeing Company Mounting apparatus for fan jet engine having mixed flow nozzle installation
US4458863A (en) * 1980-03-10 1984-07-10 The Boeing Company Strut supported inlet
US4469730A (en) * 1982-12-30 1984-09-04 The Boeing Company Composite base structure and end fitting joint and method
FR2793768B1 (fr) * 1999-05-17 2001-09-07 Aerospatiale Airbus Dispositif de montage sur un mat d'un ensemble propulsif d'aeronef et mat adapte a ce dispositif
GB2375513B (en) * 2001-05-19 2005-03-23 Rolls Royce Plc A mounting arrangement for a gas turbine engine
FR2891254B1 (fr) * 2005-09-29 2007-10-26 Airbus France Sas Ensemble moteur pour aeronef
GB0520850D0 (en) * 2005-10-14 2005-11-23 Rolls Royce Plc Fan static structure
FR2916737B1 (fr) * 2007-06-01 2010-05-28 Airbus France Ensemble moteur pour aeronef a nacelle coulissante.
FR2920138B1 (fr) 2007-08-24 2010-03-12 Airbus France Dispositif d'accrochage de moteur d'aeronef comportant un dispositif de reprise des efforts de poussee a encombrement reduit
FR2928181B1 (fr) 2008-02-28 2010-04-02 Airbus France Ensemble moteur pour aeronef comprenant un turboreacteur avec des structures de renfort reliant le carter de soufflante au carter central.
FR2940359B1 (fr) * 2008-12-18 2014-11-28 Snecma Carter d'echappement pour turbomachine, comportant une ferrure d'accrochage dissociee de la virole exterieure.
US9816441B2 (en) * 2009-03-30 2017-11-14 United Technologies Corporation Gas turbine engine with stacked accessory components
US8313293B2 (en) * 2009-05-15 2012-11-20 Pratt & Whitney Canada Corp. Turbofan mounting system
US8979491B2 (en) 2009-05-15 2015-03-17 Pratt & Whitney Canada Corp. Turbofan mounting arrangement
GB201121971D0 (en) * 2011-12-21 2012-02-01 Rolls Royce Deutschland & Co Kg Accessory mounting for a gas turbine
US9249681B2 (en) * 2012-01-31 2016-02-02 United Technologies Corporation Fan case rub system
FR2999155B1 (fr) * 2012-12-12 2014-11-21 Aircelle Sa Ensemble propulsif pour aeronef

Also Published As

Publication number Publication date
US20150377136A1 (en) 2015-12-31
US10184401B2 (en) 2019-01-22
WO2014128397A1 (fr) 2014-08-28
FR3002288A1 (fr) 2014-08-22

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