BR112013013245A2 - estrutura interna para uma nacela para um motor de turbina de uma aeronave e nacela para um motor de turbina de uma aeronave - Google Patents

estrutura interna para uma nacela para um motor de turbina de uma aeronave e nacela para um motor de turbina de uma aeronave

Info

Publication number
BR112013013245A2
BR112013013245A2 BR112013013245A BR112013013245A BR112013013245A2 BR 112013013245 A2 BR112013013245 A2 BR 112013013245A2 BR 112013013245 A BR112013013245 A BR 112013013245A BR 112013013245 A BR112013013245 A BR 112013013245A BR 112013013245 A2 BR112013013245 A2 BR 112013013245A2
Authority
BR
Brazil
Prior art keywords
nacelle
turbine engine
aircraft turbine
internal structure
aircraft
Prior art date
Application number
BR112013013245A
Other languages
English (en)
Inventor
Hervé Hurlin
Olivier Gilo
Olivier Kerbler
Original Assignee
Aircelle Sa
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 Aircelle Sa filed Critical Aircelle Sa
Publication of BR112013013245A2 publication Critical patent/BR112013013245A2/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
    • 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
    • F02K1/06—Varying effective area of jet pipe or nozzle
    • F02K1/08—Varying effective area of jet pipe or nozzle by axially moving or transversely deforming an internal member, e.g. the exhaust cone
    • F02K1/085—Varying effective area of jet pipe or nozzle by axially moving or transversely deforming an internal member, e.g. the exhaust cone by transversely deforming an internal member
    • 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)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Wind Motors (AREA)
BR112013013245A 2010-12-20 2011-11-30 estrutura interna para uma nacela para um motor de turbina de uma aeronave e nacela para um motor de turbina de uma aeronave BR112013013245A2 (pt)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR1060816A FR2969122B1 (fr) 2010-12-20 2010-12-20 Structure interne pour une nacelle pour un turboreacteur double flux d'un aeronef
PCT/FR2011/052825 WO2012085379A1 (fr) 2010-12-20 2011-11-30 Structure interne pour une nacelle d'un aéronef

Publications (1)

Publication Number Publication Date
BR112013013245A2 true BR112013013245A2 (pt) 2016-09-13

Family

ID=44263030

Family Applications (1)

Application Number Title Priority Date Filing Date
BR112013013245A BR112013013245A2 (pt) 2010-12-20 2011-11-30 estrutura interna para uma nacela para um motor de turbina de uma aeronave e nacela para um motor de turbina de uma aeronave

Country Status (8)

Country Link
US (1) US9382845B2 (pt)
EP (1) EP2655191A1 (pt)
CN (1) CN103261026B (pt)
BR (1) BR112013013245A2 (pt)
CA (1) CA2821402A1 (pt)
FR (1) FR2969122B1 (pt)
RU (1) RU2572000C2 (pt)
WO (1) WO2012085379A1 (pt)

Families Citing this family (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102015100602A1 (de) * 2015-01-15 2016-07-21 Brandenburgische Technische Universität Cottbus-Senftenberg Variable Kerntriebwerksverkleidung für Turbofan-Triebwerke mit hohem Nebenstromverhältnis
CN106934074B (zh) * 2015-12-29 2020-07-31 中国航发商用航空发动机有限责任公司 全局最优涡扇发动机进气道减噪设计方法
CN108019295B (zh) * 2017-12-15 2021-03-30 中国航发沈阳发动机研究所 一种航空发动机扰流降噪装置
US11028725B2 (en) * 2018-12-13 2021-06-08 Raytheon Technologies Corporation Adaptive morphing engine geometry
US11440671B2 (en) * 2019-01-24 2022-09-13 Amazon Technologies, Inc. Adjustable motor fairings for aerial vehicles

Family Cites Families (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4196856A (en) * 1977-11-25 1980-04-08 The Boeing Company Variable geometry convergent divergent exhaust nozzle
US20070000232A1 (en) * 2005-06-29 2007-01-04 General Electric Company Gas turbine engine and method of operating same
EP2074307B1 (en) * 2006-10-12 2011-01-26 United Technologies Corporation Translating core cowl having aerodynamic flap sections
FR2907853B1 (fr) * 2006-10-27 2011-12-16 Snecma Tuyere d'ejection des gaz pour turbomachine a double flux ayant une section d'ejection ou de col variable par deploiement de creneaux
FR2916737B1 (fr) * 2007-06-01 2010-05-28 Airbus France Ensemble moteur pour aeronef a nacelle coulissante.
FR2925607B1 (fr) * 2007-12-21 2013-05-10 Aircelle Sa Nacelle pour moteur d'aeronef a tuyere de section variable
GB0820175D0 (en) * 2008-11-05 2008-12-10 Rolls Royce Plc A gas turbine engine variable area exhuast nozzle

Also Published As

Publication number Publication date
US20140140830A1 (en) 2014-05-22
FR2969122B1 (fr) 2012-12-28
US9382845B2 (en) 2016-07-05
CN103261026B (zh) 2015-11-25
FR2969122A1 (fr) 2012-06-22
CN103261026A (zh) 2013-08-21
CA2821402A1 (fr) 2012-06-28
WO2012085379A1 (fr) 2012-06-28
RU2572000C2 (ru) 2015-12-27
RU2013132646A (ru) 2015-01-27
EP2655191A1 (fr) 2013-10-30

Similar Documents

Publication Publication Date Title
BR112014008570A2 (pt) reversor de empuxo para uma nacela de um motor turbojato e nacela para uma aeronave turbojato
BR112013014444A2 (pt) nacela para um motor turbojato de fluxo secundário e aeronave incluindo uma asa e uma nacela
BR112014009939A2 (pt) dispositivo de reversão de empuxo para uma nacela de motor turbojato e nacela de um motor turbojato
BR112012002777A2 (pt) dispositivo de reversor de empuxo para uma nacela de motor turbojato
BR112013005595A2 (pt) aparelho de propulsão e motor de turbina a gás de aeronave
BRPI0821929A2 (pt) Nacela para motor turbojato
BR112014001679A2 (pt) cone de escape para motor turbojato de aeronave
BR112014015552A8 (pt) estrutura de motor de turbina a gás composta e método para a produção de uma estrutura composta de componente de motor de turbina a gás
BR112014004264A2 (pt) nacela e montagem traseira da mesma para motor turbojato
BR112014028731A2 (pt) reversor de empuxo para uma nacela de motor turbojato e nacela de motor turbojato.
BR112014017430A2 (pt) reversor de empuxo do tipo cascata para um motor turbojato de aeronaves e nacela oara um motor turbojato de aeronaves
BRPI0821504A2 (pt) nacela para motor de avião
BRPI0822127A2 (pt) Nacela para motor turbojato e aeronave
BR112013023410A2 (pt) dispositivo de travamento e nacela de motor turbojato compreendendo pelo menos uma carenagem movente
BR112013011673A2 (pt) injetor de combustível para um motor de turbina a gás e método de operação de um motor de turbina a gás
BRPI1007029A2 (pt) conjunto de suspensão para motor turbojato de aeronaves
GB2503713B (en) Engine assembly with an Exhaust Driven Turbine
BR112014010136A2 (pt) reversor de empuxo para uma nacela de motor turbojato de aeronave e nacela
EP2520783A4 (en) COMBUSTION ENGINE WITH A TURBOLADER
BR112014014068A2 (pt) estrutura de entrada de ar para uma nacela de motor turbojato e nacela de motor turbojato
BR112013016130A2 (pt) método para reparar pelo menos uma porção de um painel acústico para uma nacela de um motor turbojato de aeronave e painel acústico.
BR112014014261A2 (pt) lacre resistente ao fogo para uma montagem compreendendo im pilão e uma nacela de motor turbojato e montagem de pilão de nacela
GB2504168B (en) Power take-off system for an internal combustion engine
BR112014006998A2 (pt) conjunto de propulsão de aeronave compreendendo um motor turbojato
BR112014015279A8 (pt) porta para um reversor de empuxo do tipo porta, reversor de empuxo do tipo porta e nacela para motor turbojato

Legal Events

Date Code Title Description
B08F Application dismissed because of non-payment of annual fees [chapter 8.6 patent gazette]
B08K Patent lapsed as no evidence of payment of the annual fee has been furnished to inpi [chapter 8.11 patent gazette]