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BRPI0401809A - Dispositivo de fixação dianteiro de motor de avião - Google Patents

Dispositivo de fixação dianteiro de motor de avião

Info

Publication number
BRPI0401809A
BRPI0401809A BR0401809-5A BRPI0401809A BRPI0401809A BR PI0401809 A BRPI0401809 A BR PI0401809A BR PI0401809 A BRPI0401809 A BR PI0401809A BR PI0401809 A BRPI0401809 A BR PI0401809A
Authority
BR
Brazil
Prior art keywords
hand
fastening device
aircraft engine
engine front
front fastening
Prior art date
Application number
BR0401809-5A
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 BRPI0401809A publication Critical patent/BRPI0401809A/pt
Publication of BRPI0401809B1 publication Critical patent/BRPI0401809B1/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
    • 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
    • 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)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Connection Of Plates (AREA)
  • Vibration Prevention Devices (AREA)
  • Toys (AREA)

Abstract

"DISPOSITIVO DE FIXAçãO DIANTEIRO DE MOTOR DE AVIãO". A presente invenção tem como objetivo uma suspensão ou um dispositivo de fixação, em especial dianteiro, de um turbomotor (1) no montante de um avião que compreende uma virola superior (12, 12<39>) provida de meios de fixação no montante, uma primeira (16) e uma segunda (18) bielas ligadas cada uma delas com o motor por um lado por uma primeira ligação com articulação (161, 181; 161<39>, 181<39>) e com a virola (12, 12<39>) por outro lado por uma segunda ligação com articulação (165, 185; 165<39>, 185<39>). O dispositivo é caracterizado pelo fato de que cada biela (16, 18) compreende uma terceira ligação (167, 187; 167<39>, 187<39>) de reserva. A invenção permite a realização de elementos com a mesma forma. Assegura-se desse modo uma intercambiabilidade entre esses elementos e uma redução dos custos de produção e de gestão. Por outro lado são reduzidos os riscos de erro na montagem.
BRPI0401809-5B1A 2003-05-27 2004-05-24 dispositivo de fixaÇço dianteiro de motor de aviço BRPI0401809B1 (pt)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
FR0306436A FR2855495B1 (fr) 2003-05-27 2003-05-27 Dispositif d'accrochage avant de moteur d'avion

Publications (2)

Publication Number Publication Date
BRPI0401809A true BRPI0401809A (pt) 2005-01-18
BRPI0401809B1 BRPI0401809B1 (pt) 2013-09-24

Family

ID=33104491

Family Applications (1)

Application Number Title Priority Date Filing Date
BRPI0401809-5B1A BRPI0401809B1 (pt) 2003-05-27 2004-05-24 dispositivo de fixaÇço dianteiro de motor de aviço

Country Status (10)

Country Link
US (1) US7165743B2 (pt)
EP (1) EP1481896B1 (pt)
JP (1) JP4272106B2 (pt)
BR (1) BRPI0401809B1 (pt)
CA (1) CA2469868C (pt)
DE (1) DE602004006463T2 (pt)
ES (1) ES2285378T3 (pt)
FR (1) FR2855495B1 (pt)
RU (1) RU2346855C2 (pt)
UA (1) UA85533C2 (pt)

Families Citing this family (43)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2862612B1 (fr) * 2003-11-25 2006-02-17 Airbus France Dispositif d'accrochage d'un moteur sous une voilure d'aeronef
US20060032974A1 (en) * 2004-08-16 2006-02-16 Honeywell International Inc. Modular installation kit for auxiliary power unit
FR2883839B1 (fr) * 2005-03-29 2007-06-29 Snecma Moteurs Sa Suspension arriere de turboreacteur
FR2883940B1 (fr) * 2005-03-31 2008-10-10 Airbus France Sas Bielle structurale creuse et procede de fabrication d'une telle bielle
US20070057128A1 (en) * 2005-09-14 2007-03-15 Honeywell International, Inc. Auxiliary power unit case flange to plate adapter
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
GB2443554A (en) * 2006-11-06 2008-05-07 Goodrich Corp Aircraft cargo monitoring system
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
FR2918644B1 (fr) * 2007-07-09 2009-10-23 Airbus France Sas Mat d'accrochage de moteur pour aeronef disposant d'un palonnier articule en quatre points.
FR2924094B1 (fr) * 2007-11-23 2010-01-15 Snecma Turboreacteur suspendu a un pylone d'aeronef
US8950702B2 (en) * 2008-01-18 2015-02-10 United Technologies Corporation Pylon and engine mount configuration
FR2926536B1 (fr) * 2008-01-23 2010-07-30 Snecma Accrochage d'un systeme propulsif a un element de structure d'un aeronef
US8672260B2 (en) * 2009-12-02 2014-03-18 United Technologies Corporation Single plane mount system for gas turbine engine
EP2580119B1 (en) * 2010-06-14 2017-03-08 LORD Corporation A helicopter engine mounting system and methods
FR2965549B1 (fr) * 2010-10-01 2013-07-05 Airbus Operations Sas Dispositif de reprise de poussee a bielles pour mat d'accrochage d'un moteur d'aeronef, integrant trois rotules alignees
FR2965796B1 (fr) 2010-10-07 2013-06-07 Snecma Suspension d'un moteur a un mat d'aeronef comportant un arceau de suspension
ES2398861B1 (es) * 2010-10-08 2014-04-29 Airbus Operations, S.L. Concepto de unión intercambiable para un cono de un fuselaje trasero de un avión.
FR2973339B1 (fr) * 2011-03-29 2014-08-22 Snecma Dispositif de suspension d'une turbomachine a un avion
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.
US20130074517A1 (en) * 2011-09-23 2013-03-28 United Technologies Corporation Gas turbine engine mount assembly
US9016623B2 (en) * 2011-11-30 2015-04-28 The Boeing Company Jam protection and alleviation for control surface linkage mechanisms
CN103318415B (zh) * 2012-03-21 2015-10-14 中国航空工业集团公司沈阳发动机设计研究所 一种航空发动机安装维护用升降装置
FR2997142B1 (fr) * 2012-10-18 2014-12-05 Epsilon Composite Procede de realisation d'un embout goupille d'une piece longitudinale, embout ainsi obtenu
FR3000467A1 (fr) * 2012-12-28 2014-07-04 Airbus Operations Sas Manille a trois points a capacite de filtrage de vibrations et attache moteur d'aeronef equipee d'une telle manille
CN103101628B (zh) * 2013-02-06 2015-05-27 中国商用飞机有限责任公司 一种与飞机吊挂一体化的前安装节
US8979020B2 (en) 2013-06-07 2015-03-17 Pratt & Whitney Canada Corp. Mounting system for mounting engine nacelle components and associated method
US10144524B2 (en) * 2013-06-14 2018-12-04 Rohr, Inc. Assembly for mounting a turbine engine to a pylon
US10266273B2 (en) 2013-07-26 2019-04-23 Mra Systems, Llc Aircraft engine pylon
FR3032180B1 (fr) * 2015-01-30 2018-05-18 Airbus Operations Ensemble propulsif comportant un turboreacteur et un mat d'accrochage permettant une nouvelle distribution des efforts entre le turboreacteur et la voilure
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
FR3059645B1 (fr) * 2016-12-02 2018-12-07 Safran Aircraft Engines Dispositif de suspension pour turbomachine
CN107521706A (zh) * 2017-07-28 2017-12-29 中国航空工业集团公司西安飞机设计研究所 发动机辅助安装接头
DE102017129060A1 (de) 2017-12-06 2019-06-06 Rolls-Royce Deutschland Ltd & Co Kg Integrierte Tragstruktur für ein Flugzeugtriebwerk und dessen Zubehörkomponenten
FR3081836B1 (fr) 2018-06-01 2020-11-06 Airbus Operations Sas Ensemble propulsif d'aeronef et procede de verification de l'integrite d'une attache moteur de l'ensemble propulsif
FR3086924B1 (fr) * 2018-10-08 2021-02-12 Safran Aircraft Engines Turbomachine comportant des moyens de suspension
US11479104B2 (en) 2019-07-24 2022-10-25 Honeywell International Inc. System and method for gas turbine engine mount with seal
FR3102976B1 (fr) * 2019-11-13 2023-11-24 Safran Aircraft Engines Avion à suspension instrumentée
US11821253B2 (en) * 2020-11-12 2023-11-21 The Boeing Company Aircraft door common stop fitting
US20240124147A1 (en) * 2022-10-13 2024-04-18 General Electric Company Gas turbine engine mount
CN117020611B (zh) * 2023-09-01 2024-03-19 昆山帕捷汽车零部件有限公司 一种发动机连接杆上螺栓和卡环的预锁紧的装配机

Family Cites Families (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
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
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
FR2828167B1 (fr) * 2001-07-31 2003-11-21 Airbus France Dispositif d'accrochage d'un moteur sur un aeronef

Also Published As

Publication number Publication date
UA85533C2 (ru) 2009-02-10
ES2285378T3 (es) 2007-11-16
CA2469868C (fr) 2012-10-02
DE602004006463D1 (de) 2007-06-28
RU2004116113A (ru) 2005-11-10
FR2855495A1 (fr) 2004-12-03
FR2855495B1 (fr) 2006-11-24
JP2004352233A (ja) 2004-12-16
RU2346855C2 (ru) 2009-02-20
EP1481896B1 (fr) 2007-05-16
EP1481896A1 (fr) 2004-12-01
DE602004006463T2 (de) 2008-01-17
JP4272106B2 (ja) 2009-06-03
US20040251381A1 (en) 2004-12-16
CA2469868A1 (fr) 2004-11-27
BRPI0401809B1 (pt) 2013-09-24
US7165743B2 (en) 2007-01-23

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Legal Events

Date Code Title Description
B25D Requested change of name of applicant approved

Owner name: SNECMA (FR)

Free format text: ALTERADO DE: SNECMA MOTEURS

B07A Application suspended after technical examination (opinion) [chapter 7.1 patent gazette]
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.

B21A Patent or certificate of addition expired [chapter 21.1 patent gazette]

Free format text: PATENTE EXTINTA EM 24/05/2024