BR112012011414A2 - estrutura anular metálica, montagem para turbomáquina de aeronave, e, turbomáquina de aeronave - Google Patents

estrutura anular metálica, montagem para turbomáquina de aeronave, e, turbomáquina de aeronave

Info

Publication number
BR112012011414A2
BR112012011414A2 BR112012011414A BR112012011414A BR112012011414A2 BR 112012011414 A2 BR112012011414 A2 BR 112012011414A2 BR 112012011414 A BR112012011414 A BR 112012011414A BR 112012011414 A BR112012011414 A BR 112012011414A BR 112012011414 A2 BR112012011414 A2 BR 112012011414A2
Authority
BR
Brazil
Prior art keywords
aircraft turbomachine
assembly
metal annular
annular frame
branches
Prior art date
Application number
BR112012011414A
Other languages
English (en)
Other versions
BR112012011414B1 (pt
Inventor
Guilhem Seize
Thomas Alain Christian Vincent
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 BR112012011414A2 publication Critical patent/BR112012011414A2/pt
Publication of BR112012011414B1 publication Critical patent/BR112012011414B1/pt

Links

Classifications

    • 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
    • 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
    • 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
    • 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
    • Y02T50/60—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)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Connection Of Plates (AREA)

Abstract

estrutura anular metálica, montagem para turbomáquina de aeronave, e, turbomáquina de aeronave. a invenção refere-se a uma estrutura anular metálica (50) de conexão entre duas peças, para turbomáquina de aeronave, apresentando em qualquer semisseção dois ramos primários e uma base 962) formando um primeiro u (64) abrindo-se radicalmente em relação a um eixo longitudinal (40, bem como dois ramos secundários formando com um dos dois ramos primários um segundo u (68) abrindo-se longitudinalmente. de acordo com a invenção, os ramos primários e secundários bem como a base (62) do primeiro u são realizados de uma única peça.
BR112012011414-0A 2009-11-12 2010-11-10 Montagem para turbomáquina de aeronave, e, turbomáquina de aeronave BR112012011414B1 (pt)

Applications Claiming Priority (3)

Application Number Priority Date Filing Date Title
FR0957969 2009-11-12
FR0957969A FR2952403B1 (fr) 2009-11-12 2009-11-12 Structure annulaire metallique de raccord pour turbomachine d'aeronef
PCT/EP2010/067183 WO2011058041A1 (fr) 2009-11-12 2010-11-10 Structure annulaire metallique de raccord pour turbomachine d'aeronef

Publications (2)

Publication Number Publication Date
BR112012011414A2 true BR112012011414A2 (pt) 2016-05-03
BR112012011414B1 BR112012011414B1 (pt) 2020-06-16

Family

ID=42261982

Family Applications (1)

Application Number Title Priority Date Filing Date
BR112012011414-0A BR112012011414B1 (pt) 2009-11-12 2010-11-10 Montagem para turbomáquina de aeronave, e, turbomáquina de aeronave

Country Status (9)

Country Link
US (1) US9169743B2 (pt)
EP (1) EP2499341B1 (pt)
JP (1) JP5635114B2 (pt)
CN (1) CN102597429B (pt)
BR (1) BR112012011414B1 (pt)
CA (1) CA2780548C (pt)
FR (1) FR2952403B1 (pt)
RU (1) RU2566617C2 (pt)
WO (1) WO2011058041A1 (pt)

Families Citing this family (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR3055655B1 (fr) * 2016-09-06 2019-04-05 Safran Aircraft Engines Carter intermediaire de turbine de turbomachine
US10975730B2 (en) * 2019-07-02 2021-04-13 Raytheon Technologies Corporation Duct assembly for a gas turbine engine

Family Cites Families (12)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3655223A (en) * 1969-09-17 1972-04-11 Gen Motors Corp Casing joint
GB2119859A (en) * 1982-05-06 1983-11-23 Rolls Royce Exhaust mixer for bypass gas turbine aeroengine
US4534167A (en) * 1982-12-27 1985-08-13 The Boeing Company Inlet cowl attachment for jet engine
FR2610673B1 (fr) * 1987-02-05 1991-03-15 Snecma Turboreacteur multiflux a couronne externe de redresseur de soufflante frettee sur le carter
US5127793A (en) * 1990-05-31 1992-07-07 General Electric Company Turbine shroud clearance control assembly
US5251435A (en) * 1991-10-30 1993-10-12 General Electric Company Reverser inner cowl with integral bifurcation walls and core cowl
US5292227A (en) * 1992-12-10 1994-03-08 General Electric Company Turbine frame
SI9520011A (en) * 1994-08-19 1996-10-31 Majnaric Technologies Inc Method and apparatus for erecting building structures
US6092987A (en) * 1998-02-27 2000-07-25 United Technologies Corporation Stator assembly for a rotary machine
FR2896481B1 (fr) * 2006-01-23 2009-12-04 Aircelle Sa Systeme de fixation pour element constitutif d'une nacelle de turboreacteur
US20090067993A1 (en) * 2007-03-22 2009-03-12 Roberge Gary D Coated variable area fan nozzle
US8438859B2 (en) * 2008-01-08 2013-05-14 Rolls-Royce North American Technologies, Inc. Integrated bypass engine structure

Also Published As

Publication number Publication date
CA2780548C (fr) 2017-07-11
FR2952403A1 (fr) 2011-05-13
FR2952403B1 (fr) 2012-01-13
RU2566617C2 (ru) 2015-10-27
BR112012011414B1 (pt) 2020-06-16
JP2013510986A (ja) 2013-03-28
US9169743B2 (en) 2015-10-27
CN102597429B (zh) 2014-11-19
WO2011058041A1 (fr) 2011-05-19
RU2012124073A (ru) 2013-12-20
EP2499341B1 (fr) 2016-04-13
CA2780548A1 (fr) 2011-05-19
US20120219415A1 (en) 2012-08-30
EP2499341A1 (fr) 2012-09-19
JP5635114B2 (ja) 2014-12-03
CN102597429A (zh) 2012-07-18

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BR112012011414A2 (pt) estrutura anular metálica, montagem para turbomáquina de aeronave, e, turbomáquina de aeronave

Legal Events

Date Code Title Description
B06F Objections, documents and/or translations needed after an examination request according [chapter 6.6 patent gazette]
B06U Preliminary requirement: requests with searches performed by other patent offices: procedure suspended [chapter 6.21 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 10/11/2010, OBSERVADAS AS CONDICOES LEGAIS.