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BRPI0401808A - Dispositivo de fixação de um turbomotor no montante de um avião - Google Patents

Dispositivo de fixação de um turbomotor no montante de um avião

Info

Publication number
BRPI0401808A
BRPI0401808A BR0401808-7A BRPI0401808A BRPI0401808A BR PI0401808 A BRPI0401808 A BR PI0401808A BR PI0401808 A BRPI0401808 A BR PI0401808A BR PI0401808 A BRPI0401808 A BR PI0401808A
Authority
BR
Brazil
Prior art keywords
small connecting
connecting rods
turbomotor
suspension
engine
Prior art date
Application number
BR0401808-7A
Other languages
English (en)
Inventor
Jean-Claude Felix Pasquer
Philippe Loewenstein
Marc Tesniere
Original Assignee
Snecma Moteurs
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 filed Critical Snecma Moteurs
Publication of BRPI0401808A publication Critical patent/BRPI0401808A/pt
Publication of BRPI0401808B1 publication Critical patent/BRPI0401808B1/pt

Links

Classifications

    • 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
    • B64D27/404—Suspension arrangements specially adapted for supporting vertical loads
    • 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
    • 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
    • B64D27/406—Suspension arrangements specially adapted for supporting thrust loads, e.g. thrust links

Landscapes

  • Engineering & Computer Science (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Pivots And Pivotal Connections (AREA)
  • Transmission Devices (AREA)
  • Shafts, Cranks, Connecting Bars, And Related Bearings (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Supercharger (AREA)
  • Clamps And Clips (AREA)
  • Axle Suspensions And Sidecars For Cycles (AREA)

Abstract

"DISPOSITIVO DE FIXAçãO DE UM TURBOMOTOR NO MONTANTE DE UM AVIãO". A presente invenção tem como objetivo uma suspensão ou um dispositivo de fixação traseiro de um turbomotor (1) no montante de um avião que compreende uma virola superior (12) provida de meios de fixação no montante, na qual são articuladas, por segundas ligações (163, 183) com articulação, três pequenas bielas dispostas transversalmente ao eixo longitudinal do motor, uma primeira (16) e uma segunda (18) pequenas bielas de um lado e de outro do eixo do motor e uma terceira pequena biela (17) entre elas duas, as pequenas bielas sendo elas próprias ligadas ao motor por primeiras ligações (161, 181) com articulações. A suspensão é caracterizada pelo fato de que as primeira (16) e segunda (18) pequenas bielas compreendem cada uma delas uma terceira (167, 187) ligação de reserva e que a virola superior (12) é formada por uma viga (120) fixada rigidamente ao montante. A solução da invenção permite a realização de pequenas bielas idênticas e assegurar a intercambiabilidade das mesmas reduzindo assim os riscos de erro na montagem.
BRPI0401808-7B1A 2003-05-27 2004-05-24 Dispositivo de fixação de um turbomotor no montante de um avião BRPI0401808B1 (pt)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
FR0306435A FR2855494B1 (fr) 2003-05-27 2003-05-27 Dispositif d'accrocharge arriere de moteur d'avion

Publications (2)

Publication Number Publication Date
BRPI0401808A true BRPI0401808A (pt) 2005-01-18
BRPI0401808B1 BRPI0401808B1 (pt) 2013-12-31

Family

ID=33104490

Family Applications (1)

Application Number Title Priority Date Filing Date
BRPI0401808-7B1A BRPI0401808B1 (pt) 2003-05-27 2004-05-24 Dispositivo de fixação de um turbomotor no montante de um avião

Country Status (10)

Country Link
US (1) US6988692B2 (pt)
EP (1) EP1481895B1 (pt)
JP (1) JP2004352231A (pt)
BR (1) BRPI0401808B1 (pt)
CA (1) CA2469943C (pt)
DE (1) DE602004002891T2 (pt)
ES (1) ES2276247T3 (pt)
FR (1) FR2855494B1 (pt)
RU (1) RU2346856C2 (pt)
UA (1) UA80689C2 (pt)

Families Citing this family (21)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2869874B1 (fr) * 2004-05-04 2006-06-23 Snecma Moteurs Sa Moteur d'avion avec des moyens de suspension a la structure d'un avion
FR2883839B1 (fr) * 2005-03-29 2007-06-29 Snecma Moteurs Sa Suspension arriere de turboreacteur
US20070057128A1 (en) * 2005-09-14 2007-03-15 Honeywell International, Inc. Auxiliary power unit case flange to plate adapter
FR2891245B1 (fr) * 2005-09-26 2007-10-26 Airbus France Sas Procede de montage d'un moteur d'aeronef sur une structure rigide d'un mat d'accrochage du moteur
FR2891243B1 (fr) * 2005-09-26 2009-04-03 Airbus France Sas Mat d'accrochage de moteur pour aeronef
FR2891253B1 (fr) * 2005-09-28 2007-10-26 Airbus France Sas Attache arriere d'un moteur d'aeronef a deux manilles
GB0603539D0 (en) * 2006-02-22 2006-04-05 Airbus Uk Ltd Control surface failsafe drop link
FR2914907B1 (fr) * 2007-04-16 2009-10-30 Snecma Sa Suspension souple avec peigne pour turbomoteur
FR2915175B1 (fr) * 2007-04-20 2009-07-17 Airbus France Sa Mat d'accrochage de moteur pour aeronef disposant d'une poutre d'attache moteur arriere deportee du caisson
US7762509B2 (en) * 2007-10-18 2010-07-27 United Technologies Corp. Gas turbine engine systems involving rotatable annular supports
US8950702B2 (en) * 2008-01-18 2015-02-10 United Technologies Corporation Pylon and engine mount configuration
DE102008021431A1 (de) * 2008-04-29 2009-11-12 Airbus Deutschland Gmbh Flugzeug mit einer Energie-Versorgungsvorrichtung
FR2933070B1 (fr) * 2008-06-25 2010-08-20 Snecma Systeme propulsif d'aeronef
FR2959210B1 (fr) * 2010-04-21 2013-08-23 Snecma Palonnier de suspension de turboreacteur d'aeronef et suspension avec accroche-soufflante ainsi equipee
FR2974065B1 (fr) * 2011-04-14 2013-05-10 Snecma Procede de montage d'un moteur d'aeronef sur un pylone et attache moteur pour la mise en oeuvre d'un tel procede.
FR2989952B1 (fr) 2012-04-27 2014-04-18 Aircelle Sa Nacelle de turboreacteur a section aval
EP3024729B1 (en) 2013-07-26 2022-04-27 MRA Systems, LLC Aircraft engine pylon
US10464685B2 (en) * 2015-01-07 2019-11-05 Lord Corporation Aircraft engine mount
FR3041935B1 (fr) * 2015-10-05 2017-12-15 Airbus Operations Sas Ensemble moteur pour aeronef comprenant au moins deux attaches moteur arriere decalees axialement l'une de l'autre
FR3053660A1 (fr) * 2016-07-08 2018-01-12 Airbus Operations Attache moteur d'aeronef comprenant au moins un ecrou transversal et aeronef comprenant ladite attache moteur
FR3086925B1 (fr) * 2018-10-08 2020-09-11 Safran Aircraft Engines Ensemble de suspension pour une turbomachine

Family Cites Families (20)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2224707B (en) * 1988-11-12 1992-06-10 Rolls Royce Plc Improvements in or relating to engine mounting integrity
US5176339A (en) * 1991-09-30 1993-01-05 Lord Corporation Resilient pivot type aircraft mounting
US5275357A (en) * 1992-01-16 1994-01-04 General Electric Company Aircraft engine mount
US5320307A (en) * 1992-03-25 1994-06-14 General Electric Company Aircraft engine thrust mount
US5351930A (en) * 1992-08-11 1994-10-04 Lord Corporation Mounting for engines and the like
US5303880A (en) * 1992-10-28 1994-04-19 General Electric Company Aircraft engine pin mount
US5649417A (en) * 1995-03-24 1997-07-22 The Boeing Company Fail-safe engine mount system
US5620154A (en) * 1995-05-03 1997-04-15 The Boeing Company Three link failsafe engine mount
US5860623A (en) * 1995-05-03 1999-01-19 The Boeing Company Three link failsafe engine mount
US5725181A (en) * 1996-05-01 1998-03-10 The Boeing Company Aircraft engine thrust mount
FR2770486B1 (fr) * 1997-11-06 2000-01-28 Aerospatiale Dispositif d'accrochage d'un moteur sur un aeronef
FR2774358B1 (fr) * 1998-02-04 2000-04-21 Aerospatiale Dispositif d'accrochage d'un moteur d'aeronef
US6189830B1 (en) * 1999-02-26 2001-02-20 The Boeing Company Tuned engine mounting system for jet aircraft
US6330995B1 (en) * 2000-02-29 2001-12-18 General Electric Company Aircraft engine mount
FR2806699B1 (fr) * 2000-03-22 2002-05-10 Aerospatiale Matra Airbus Dispositif de reprise de poussee apte a relier un turbomoteur et un mat d'aeronef
FR2820402B1 (fr) * 2001-02-08 2003-05-02 Eads Airbus Sa Dispositif d'accrochage d'un moteur sur un aeronef
FR2828167B1 (fr) * 2001-07-31 2003-11-21 Airbus France Dispositif d'accrochage d'un moteur sur un aeronef
FR2830516B1 (fr) * 2001-10-04 2004-01-02 Snecma Moteurs Suspension de turboreacteur
US6607165B1 (en) * 2002-06-28 2003-08-19 General Electric Company Aircraft engine mount with single thrust link
US6843449B1 (en) * 2004-02-09 2005-01-18 General Electric Company Fail-safe aircraft engine mounting system

Also Published As

Publication number Publication date
ES2276247T3 (es) 2007-06-16
RU2346856C2 (ru) 2009-02-20
US6988692B2 (en) 2006-01-24
DE602004002891D1 (de) 2006-12-07
JP2004352231A (ja) 2004-12-16
EP1481895B1 (fr) 2006-10-25
FR2855494A1 (fr) 2004-12-03
CA2469943C (fr) 2012-01-03
CA2469943A1 (fr) 2004-11-27
FR2855494B1 (fr) 2006-09-22
US20040251379A1 (en) 2004-12-16
DE602004002891T2 (de) 2007-09-06
UA80689C2 (en) 2007-10-25
BRPI0401808B1 (pt) 2013-12-31
EP1481895A1 (fr) 2004-12-01
RU2004116111A (ru) 2005-11-10

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Legal Events

Date Code Title Description
B11A Dismissal acc. art.33 of ipl - examination not requested within 36 months of filing
B04C Request for examination: application reinstated [chapter 4.3 patent gazette]
B25D Requested change of name of applicant approved

Owner name: SNECMA (FR)

Free format text: ALTERADO DE: SNECMA MOTEURS

B09A Decision: intention to grant [chapter 9.1 patent gazette]
B16A Patent or certificate of addition of invention granted [chapter 16.1 patent gazette]

Free format text: PRAZO DE VALIDADE: 20 (VINTE) ANOS CONTADOS A PARTIR DE 24/05/2004, OBSERVADAS AS CONDICOES LEGAIS.

B21F Lapse acc. art. 78, item iv - on non-payment of the annual fees in time

Free format text: REFERENTE A 15A ANUIDADE.

B24J Lapse because of non-payment of annual fees (definitively: art 78 iv lpi, resolution 113/2013 art. 12)

Free format text: EM VIRTUDE DA EXTINCAO PUBLICADA NA RPI 2516 DE 26-03-2019 E CONSIDERANDO AUSENCIA DE MANIFESTACAO DENTRO DOS PRAZOS LEGAIS, INFORMO QUE CABE SER MANTIDA A EXTINCAO DA PATENTE E SEUS CERTIFICADOS, CONFORME O DISPOSTO NO ARTIGO 12, DA RESOLUCAO 113/2013.