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BRPI0402464A - Suspensão de turbomotor a um montante de avião - Google Patents

Suspensão de turbomotor a um montante de avião

Info

Publication number
BRPI0402464A
BRPI0402464A BR0402464-8A BRPI0402464A BRPI0402464A BR PI0402464 A BRPI0402464 A BR PI0402464A BR PI0402464 A BRPI0402464 A BR PI0402464A BR PI0402464 A BRPI0402464 A BR PI0402464A
Authority
BR
Brazil
Prior art keywords
hardware
rocker
suspension
connecting means
airplane
Prior art date
Application number
BR0402464-8A
Other languages
English (en)
Inventor
Philippe Loewenstein
Frederic Jean-Marc Darcy
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 BRPI0402464A publication Critical patent/BRPI0402464A/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)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Supercharger (AREA)
  • Clamps And Clips (AREA)
  • Load-Engaging Elements For Cranes (AREA)

Abstract

"SUSPENSãO DE TURBOMOTOR A UM MONTANTE DE AVIãO". A presente invenção tem como objetivo uma suspensão de turbomotor a um montante de avião que compreende uma ferragem (12) disposta para ser fixada ao montante, um balancim (15; 15<39>) fixado em sua parte central (150; 150<39>) na ferragem por um primeiro meio de ligação (150-130) com um eixo de pivotamento (136; 136<39>) e duas bielas (20, 22; 20<39>, 22<39>) de compensação de impulsão ligadas cada uma delas na parte de trás ao balancim por um segundo meio de ligação (200-155, 220-157; 200<39>-155<39>, 220<39>-157<39>) e que compreendem na extremidade dianteira meios de fixação ao motor, caracterizada pelo fato de que o primeiro meio de ligação (150-130) é constituído por dois ramos paralelos (151, 153) distantes um do outro na parte central (150) do balancim, que operam junto com uma aba de fixação (130) solidária da ferragem por intermédio de um eixo de pivotamento e o balancim (15, 15<39>) compreende dois terceiros meios de ligação laterais de reserva (155-135, 157-137; 155<39>-135<39>, 157<39>-137<39>), com a ferragem (12, 12<39>). A invenção permite a realização de uma montagem simplificada cuja segurança é melhorada.
BR0402464-8A 2003-06-30 2004-06-29 Suspensão de turbomotor a um montante de avião BRPI0402464A (pt)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
FR0307893A FR2856656B1 (fr) 2003-06-30 2003-06-30 Suspension arriere de moteur d'avion avec bielles de reprise de poussee et palonnier en forme de boomerang

Publications (1)

Publication Number Publication Date
BRPI0402464A true BRPI0402464A (pt) 2005-05-24

Family

ID=33427637

Family Applications (1)

Application Number Title Priority Date Filing Date
BR0402464-8A BRPI0402464A (pt) 2003-06-30 2004-06-29 Suspensão de turbomotor a um montante de avião

Country Status (9)

Country Link
US (1) US7021585B2 (pt)
EP (1) EP1493663B1 (pt)
JP (1) JP2005022641A (pt)
BR (1) BRPI0402464A (pt)
CA (1) CA2472312A1 (pt)
DE (1) DE602004000283T2 (pt)
ES (1) ES2253728T3 (pt)
FR (1) FR2856656B1 (pt)
RU (1) RU2004119904A (pt)

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FR2924094B1 (fr) * 2007-11-23 2010-01-15 Snecma Turboreacteur suspendu a un pylone d'aeronef
FR2924684B1 (fr) 2007-12-07 2010-01-01 Snecma Suspension d'un turboreacteur a un aeronef
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US8826641B2 (en) * 2008-01-28 2014-09-09 United Technologies Corporation Thermal management system integrated pylon
US8167237B2 (en) 2008-03-21 2012-05-01 United Technologies Corporation Mounting system for a gas turbine engine
DE102008021431A1 (de) * 2008-04-29 2009-11-12 Airbus Deutschland Gmbh Flugzeug mit einer Energie-Versorgungsvorrichtung
US8695920B2 (en) 2008-06-02 2014-04-15 United Technologies Corporation Gas turbine engine with low stage count low pressure turbine
US8511605B2 (en) 2008-06-02 2013-08-20 United Technologies Corporation Gas turbine engine with low stage count low pressure turbine
US8807477B2 (en) 2008-06-02 2014-08-19 United Technologies Corporation Gas turbine engine compressor arrangement
US20140174056A1 (en) 2008-06-02 2014-06-26 United Technologies Corporation Gas turbine engine with low stage count low pressure turbine
US8800914B2 (en) 2008-06-02 2014-08-12 United Technologies Corporation Gas turbine engine with low stage count low pressure turbine
US8128021B2 (en) * 2008-06-02 2012-03-06 United Technologies Corporation Engine mount system for a turbofan gas turbine engine
GB0810585D0 (en) * 2008-06-11 2008-07-16 Rolls Royce Plc Engine mounting arrangement
GB0810589D0 (en) * 2008-06-11 2008-07-16 Rolls Royce Plc Engine mounting arrangement
GB0810791D0 (en) * 2008-06-13 2008-07-23 Rolls Royce Plc Thrust mounting arrangement
GB0902909D0 (en) * 2009-02-23 2009-04-08 Rolls Royce Plc A thrust mount arrangement for an aircraft engine
FR2952150B1 (fr) * 2009-11-02 2012-02-24 Airbus Operations Sas Bielle structurale comportant un mode filtrant des vibrations
FR2959210B1 (fr) * 2010-04-21 2013-08-23 Snecma Palonnier de suspension de turboreacteur d'aeronef et suspension avec accroche-soufflante ainsi equipee
KR101828921B1 (ko) * 2010-06-14 2018-02-13 로오드 코포레이션 헬리콥터 엔진 장착 시스템 및 방법
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
US20130074517A1 (en) * 2011-09-23 2013-03-28 United Technologies Corporation Gas turbine engine mount assembly
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FR3041996B1 (fr) 2015-10-05 2017-10-27 Snecma Systeme de suspension de deux modules d'un ensemble propulsif
CN109562841B (zh) 2016-08-08 2022-03-18 洛德公司 用于飞机发动机的安装系统、装置和方法
FR3058986B1 (fr) * 2016-11-21 2021-04-16 Airbus Operations Sas Attache arriere d'un moteur d'aeronef comportant des temoins de rupture
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FR3086924B1 (fr) * 2018-10-08 2021-02-12 Safran Aircraft Engines Turbomachine comportant des moyens de suspension
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Also Published As

Publication number Publication date
US7021585B2 (en) 2006-04-04
ES2253728T3 (es) 2006-06-01
CA2472312A1 (fr) 2004-12-30
JP2005022641A (ja) 2005-01-27
FR2856656A1 (fr) 2004-12-31
RU2004119904A (ru) 2005-12-10
DE602004000283D1 (de) 2006-02-02
EP1493663B1 (fr) 2005-12-28
FR2856656B1 (fr) 2006-12-01
US20050067528A1 (en) 2005-03-31
DE602004000283T2 (de) 2006-08-31
EP1493663A1 (fr) 2005-01-05

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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
B11Y Definitive dismissal - extension of time limit for request of examination expired [chapter 11.1.1 patent gazette]