BR112013002143A2 - motor turbo lateral - Google Patents

motor turbo lateral

Info

Publication number
BR112013002143A2
BR112013002143A2 BR112013002143A BR112013002143A BR112013002143A2 BR 112013002143 A2 BR112013002143 A2 BR 112013002143A2 BR 112013002143 A BR112013002143 A BR 112013002143A BR 112013002143 A BR112013002143 A BR 112013002143A BR 112013002143 A2 BR112013002143 A2 BR 112013002143A2
Authority
BR
Brazil
Prior art keywords
turbo engine
casing
primary structure
side turbo
pressure
Prior art date
Application number
BR112013002143A
Other languages
English (en)
Inventor
François Robert Bellabal
Original Assignee
Snecma
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 filed Critical Snecma
Publication of BR112013002143A2 publication Critical patent/BR112013002143A2/pt

Links

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; ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D27/00—Arrangement or mounting of power plant in aircraft; Aircraft characterised thereby
    • B64D27/02—Aircraft characterised by the type or position of power plant
    • B64D27/16—Aircraft characterised by the type or position of power plant of jet type
    • B64D27/20—Aircraft characterised by the type or position of power plant of jet type within or attached to fuselage
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02K—JET-PROPULSION PLANTS
    • F02K1/00—Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto
    • F02K1/78—Other construction of jet pipes
    • F02K1/80—Couplings or connections
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02K—JET-PROPULSION PLANTS
    • F02K1/00—Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto
    • F02K1/78—Other construction of jet pipes
    • F02K1/82—Jet pipe walls, e.g. liners
    • 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
    • F05D2230/00—Manufacture
    • F05D2230/60—Assembly methods
    • F05D2230/64—Assembly methods using positioning or alignment devices for aligning or centring, e.g. pins
    • F05D2230/642—Assembly methods using positioning or alignment devices for aligning or centring, e.g. pins using maintaining alignment while permitting differential dilatation
    • 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
    • F05D2260/94—Functionality given by mechanical stress related aspects such as low cycle fatigue [LCF] of high cycle fatigue [HCF]
    • 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
    • F05D2260/94—Functionality given by mechanical stress related aspects such as low cycle fatigue [LCF] of high cycle fatigue [HCF]
    • F05D2260/941—Functionality given by mechanical stress related aspects such as low cycle fatigue [LCF] of high cycle fatigue [HCF] particularly aimed at mechanical or thermal stress reduction

Abstract

motor turbo lateral.a invenção se refere ao motor turbo que tem uma capa externa no alojamento intermediário (13) conectada na suspensão frontal e uma estrutura primária conectada na suspensão traseira; a capa e a estrutura primária são mantidas em relação coaxial por brações (35a-35f) com pelo menos alguns deles que são formados e/ou dispostos para deformarem em resposta à pressão do motor turbo ao criar um torque de deformação entre a capa e a estrutura primária em oposição à tensão oposta gerada pela mesma pressão.
BR112013002143A 2010-07-30 2011-07-15 motor turbo lateral BR112013002143A2 (pt)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR1056337A FR2963390B1 (fr) 2010-07-30 2010-07-30 Turboreacteur lateral perfectionne pour limiter ses deformations
PCT/FR2011/051693 WO2012013889A1 (fr) 2010-07-30 2011-07-15 Turboreacteur lateral perfectionne pour limiter ses deformations

Publications (1)

Publication Number Publication Date
BR112013002143A2 true BR112013002143A2 (pt) 2016-05-24

Family

ID=43805705

Family Applications (1)

Application Number Title Priority Date Filing Date
BR112013002143A BR112013002143A2 (pt) 2010-07-30 2011-07-15 motor turbo lateral

Country Status (8)

Country Link
US (1) US9366186B2 (pt)
EP (1) EP2598738B1 (pt)
CN (1) CN103038485B (pt)
BR (1) BR112013002143A2 (pt)
CA (1) CA2806165A1 (pt)
FR (1) FR2963390B1 (pt)
RU (1) RU2587029C2 (pt)
WO (1) WO2012013889A1 (pt)

Families Citing this family (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2988777B1 (fr) * 2012-03-29 2014-04-25 Snecma Propulsion Solide Integration de pieces d'arriere-corps de moteur aeronautique
FR2994941B1 (fr) * 2012-09-06 2015-08-07 Airbus Operations Sas Ensemble propulsif pour aeronef comprenant un carenage structural.
FR3010048B1 (fr) * 2013-09-04 2017-03-31 Snecma Structure de liaison moteur-nacelle a cales de liaison
FR3010049B1 (fr) * 2013-09-04 2017-03-31 Snecma Structure de liaison moteur-nacelle a secteurs de virole pivotants
FR3047075B1 (fr) * 2016-01-27 2018-02-23 Safran Aircraft Engines Piece de revolution pour banc d'essai de turbine ou pour turbomachine, banc d'essais de turbines comprenant ladite piece, et procede les utilisant
CN112709613B (zh) * 2020-12-30 2023-01-17 中国航发沈阳发动机研究所 一种航空发动机侧向辅助安装节结构

Family Cites Families (19)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3778185A (en) * 1972-08-28 1973-12-11 United Aircraft Corp Composite strut joint construction
US4266741A (en) * 1978-05-22 1981-05-12 The Boeing Company Mounting apparatus for fan jet engine having mixed flow nozzle installation
FR2469566A1 (fr) * 1979-11-12 1981-05-22 Snecma Perfectionnements aux dispositifs de fixation de turboreacteurs multiflux
US4428189A (en) * 1980-04-02 1984-01-31 United Technologies Corporation Case deflection control in aircraft gas turbine engines
RU1501456C (ru) * 1987-06-11 1995-02-09 Авиационный комплекс им.С.В.Ильюшина Силовая установка летательного аппарата
US5224341A (en) * 1992-01-06 1993-07-06 United Technologies Corporation Separable fan strut for a gas turbofan powerplant
US5174525A (en) * 1991-09-26 1992-12-29 General Electric Company Structure for eliminating lift load bending in engine core of turbofan
GB0021696D0 (en) 2000-09-05 2000-10-18 Univ Manchester Impact absorber device
US7370467B2 (en) 2003-07-29 2008-05-13 Pratt & Whitney Canada Corp. Turbofan case and method of making
US7594404B2 (en) 2006-07-27 2009-09-29 United Technologies Corporation Embedded mount for mid-turbine frame
US7559747B2 (en) * 2006-11-22 2009-07-14 Pratt & Whitney Canada Corp. Turbine exhaust strut airfoil profile
US7857594B2 (en) 2006-11-28 2010-12-28 Pratt & Whitney Canada Corp. Turbine exhaust strut airfoil profile
US7762087B2 (en) 2006-12-06 2010-07-27 United Technologies Corporation Rotatable integrated segmented mid-turbine frames
WO2008150202A1 (en) 2007-06-08 2008-12-11 Volvo Aero Corporation A structure for transferring loads at a gas turbine engine, and an engine and an aircraft with such a structure
FR2928180B1 (fr) * 2008-02-28 2010-04-02 Airbus France Ensemble moteur pour aeronef comprenant une structure annulaire de transfert d'efforts entourant le carter central d'un turboreacteur.
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.
FR2928136B1 (fr) * 2008-02-28 2010-04-02 Airbus France Ensemble moteur pour aeronef comprenant des attaches moteur deportees vers le bas sur le carter de soufflante.
US8784051B2 (en) 2008-06-30 2014-07-22 Pratt & Whitney Canada Corp. Strut for a gas turbine engine
FR2940359B1 (fr) * 2008-12-18 2014-11-28 Snecma Carter d'echappement pour turbomachine, comportant une ferrure d'accrochage dissociee de la virole exterieure.

Also Published As

Publication number Publication date
US9366186B2 (en) 2016-06-14
FR2963390A1 (fr) 2012-02-03
CA2806165A1 (fr) 2012-02-02
WO2012013889A1 (fr) 2012-02-02
RU2587029C2 (ru) 2016-06-10
EP2598738B1 (fr) 2018-04-25
RU2013108875A (ru) 2014-09-10
FR2963390B1 (fr) 2012-08-31
CN103038485A (zh) 2013-04-10
US20130125560A1 (en) 2013-05-23
EP2598738A1 (fr) 2013-06-05
CN103038485B (zh) 2016-01-20

Similar Documents

Publication Publication Date Title
BR112013002143A2 (pt) motor turbo lateral
BR112014030903A2 (pt) máquina de bebida com inibidor de vibração
BRPI0616578A8 (pt) estribo de afixação de turborreator para aeronave, e, aeronave
BR112012013274A2 (pt) acoplamento magnético permanente
BRPI0413772A (pt) painel de isolamento substancialmente plano e método para a construção de um painel de isolamento substancialmente plano
BR112013018530A2 (pt) estrutura da carroceria dianteira do veículo
BR112014029711A2 (pt) amortecedor para um conjunto de rotor de turbina de um motor de turbina a gás e motor de turbina a gás
BR112013020396A2 (pt) veículo de lado a lado
BR112015005328A2 (pt) estrutura de seção dianteira de veículo
BRPI0516069A (pt) empenagem vertical para aeronave munida dessa empenagem
BR112014000983A2 (pt) montagem de invólucro
BR112013008475A2 (pt) atuador linear eletromagnético
BR112014019021A8 (pt) Retardador hidrodinâmico
BR112013029870A2 (pt) máquina dínamo-elétrica
BR112018074201A2 (pt) estrutura de montagem para dispositivo de conversão de energia
BR112014013811A2 (pt) sistema mecânico que compreende uma peça de desgaste e um suporte, e balde que compreende pelo menos tal sistema mecânico
BR112016024620A2 (pt) aparelhagem elétrica com montagem segura
BR112015012327A2 (pt) configuração de estrutura para veículos
BR112015015228A2 (pt) engrenagem com um eixo
BR112015030653A2 (pt) módulo de ligação, trocador de calor e conjunto trocador de calor correspondente
BR112013006678A2 (pt) estrutura de carroceria de veículo
BRPI0605508A (pt) métodos para estabilização de composições oftálmicas
BR112013006465A2 (pt) montagem de propulsão de aeronave.
BR112012002429A2 (pt) polipeptídeos de porphyromonas gingivalis
BR112014014612A8 (pt) montagem de palhetas guias de compressor de turbomáquina

Legal Events

Date Code Title Description
B08F Application fees: dismissal - article 86 of industrial property law
B08K Lapse as no evidence of payment of the annual fee has been furnished to inpi (acc. art. 87)