BR112014014261A2 - lacre resistente ao fogo para uma montagem compreendendo im pilão e uma nacela de motor turbojato e montagem de pilão de nacela - Google Patents

lacre resistente ao fogo para uma montagem compreendendo im pilão e uma nacela de motor turbojato e montagem de pilão de nacela

Info

Publication number
BR112014014261A2
BR112014014261A2 BR112014014261A BR112014014261A BR112014014261A2 BR 112014014261 A2 BR112014014261 A2 BR 112014014261A2 BR 112014014261 A BR112014014261 A BR 112014014261A BR 112014014261 A BR112014014261 A BR 112014014261A BR 112014014261 A2 BR112014014261 A2 BR 112014014261A2
Authority
BR
Brazil
Prior art keywords
mounting
pylon
nacelle
fire resistant
turbojet engine
Prior art date
Application number
BR112014014261A
Other languages
English (en)
Inventor
Phi Alexandre
Guillon Jean-Bernard
Phi Stéphane
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 BR112014014261A2 publication Critical patent/BR112014014261A2/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
    • F02C7/28—Arrangement of seals
    • 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
    • F02C7/24—Heat or noise insulation
    • F02C7/25—Fire protection or prevention
    • 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
    • F02K1/805—Sealing devices therefor, e.g. for movable parts of jet pipes or nozzle flaps
    • 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
    • B64D29/00—Power-plant nacelles, fairings, or cowlings

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Gasket Seals (AREA)
BR112014014261A 2012-01-05 2013-01-04 lacre resistente ao fogo para uma montagem compreendendo im pilão e uma nacela de motor turbojato e montagem de pilão de nacela BR112014014261A2 (pt)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR1250111A FR2985501B1 (fr) 2012-01-05 2012-01-05 Joint d'etancheite pour pylone et nacelle de turboreacteur et ensemble de pylone et nacelle de turboreacteur incorporant un tel joint d'etancheite
PCT/FR2013/050015 WO2013102739A1 (fr) 2012-01-05 2013-01-04 Joint d ' étancheité pour pylone et nacelle de turboréacteur et ensemble de pylone et nacelle de turboréacteur incorporant un tel joint d ' étancheité

Publications (1)

Publication Number Publication Date
BR112014014261A2 true BR112014014261A2 (pt) 2017-06-13

Family

ID=47628352

Family Applications (1)

Application Number Title Priority Date Filing Date
BR112014014261A BR112014014261A2 (pt) 2012-01-05 2013-01-04 lacre resistente ao fogo para uma montagem compreendendo im pilão e uma nacela de motor turbojato e montagem de pilão de nacela

Country Status (8)

Country Link
US (1) US20140318149A1 (pt)
EP (1) EP2800693A1 (pt)
CN (1) CN104093632A (pt)
BR (1) BR112014014261A2 (pt)
CA (1) CA2858740A1 (pt)
FR (1) FR2985501B1 (pt)
RU (1) RU2014131660A (pt)
WO (1) WO2013102739A1 (pt)

Families Citing this family (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR3019857B1 (fr) * 2014-04-11 2020-12-25 Aircelle Sa Inverseur de poussee de nacelle de turboreacteur comprenant une commande commune pour les capots mobiles et une tuyere variable
US9896970B2 (en) 2014-11-14 2018-02-20 General Electric Company Method and system for sealing an annulus
US9915225B2 (en) 2015-02-06 2018-03-13 United Technologies Corporation Propulsion system arrangement for turbofan gas turbine engine
US10450898B2 (en) * 2015-02-13 2019-10-22 United Technologies Corporation Track fairing assembly for a turbine engine nacelle
JP6830804B2 (ja) * 2016-12-05 2021-02-17 三菱航空機株式会社 航空機用のファイアシール構造および航空機
CN107878763A (zh) * 2017-10-19 2018-04-06 哈尔滨飞机工业集团有限责任公司 一种双发直升机发动机机舱防火板
US11518535B2 (en) * 2019-09-30 2022-12-06 Rohr, Inc. Nacelle cowl deflection limiter
EP3971401A1 (en) * 2020-05-05 2022-03-23 Rohr, Inc. Aircraft propulsion system nozzle with internal flow passage
US11781506B2 (en) 2020-06-03 2023-10-10 Rtx Corporation Splitter and guide vane arrangement for gas turbine engines

Family Cites Families (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR703607A (fr) 1930-10-11 1931-05-04 Sacs, pochettes, sachets ou autres en papier ou matière analogue
FR905687A (fr) 1943-02-17 1945-12-11 Ig Farbenindustrie Ag Amollissants
GB1131224A (en) * 1964-10-31 1968-10-23 Pioneer Oilsealing & Moulding Improvements in and relating to labyrinth seals
GB1591193A (en) * 1978-03-29 1981-06-17 Fyson & Son Ltd C J R Idler roller assemblies for conveyors
US5088775A (en) * 1990-07-27 1992-02-18 General Electric Company Seal ring with flanged end portions
DE4237886A1 (de) * 1992-09-11 1994-03-17 Mtu Muenchen Gmbh Einrichtung zur Abdichtung fluidisch unterschiedlich druckbeaufschlagter Räume zwischen relativ zueinander beweglichen Gehäusen, insbesondere von Flugtriebwerken
US5910094A (en) * 1996-09-10 1999-06-08 The Boeing Company Aircraft labyrinth fire seal
FR2909974B1 (fr) * 2006-12-13 2009-02-06 Aircelle Sa Nacelle pour turboreacteur double flux

Also Published As

Publication number Publication date
EP2800693A1 (fr) 2014-11-12
FR2985501B1 (fr) 2013-12-27
WO2013102739A1 (fr) 2013-07-11
CN104093632A (zh) 2014-10-08
RU2014131660A (ru) 2016-02-27
CA2858740A1 (fr) 2013-07-11
FR2985501A1 (fr) 2013-07-12
US20140318149A1 (en) 2014-10-30

Similar Documents

Publication Publication Date Title
BR112014014261A2 (pt) lacre resistente ao fogo para uma montagem compreendendo im pilão e uma nacela de motor turbojato e montagem de pilão de nacela
BR112014008570A2 (pt) reversor de empuxo para uma nacela de um motor turbojato e nacela para uma aeronave turbojato
BR112014009939A2 (pt) dispositivo de reversão de empuxo para uma nacela de motor turbojato e nacela de um motor turbojato
BR112014028731A2 (pt) reversor de empuxo para uma nacela de motor turbojato e nacela de motor turbojato.
BR112014004264A2 (pt) nacela e montagem traseira da mesma para motor turbojato
SG11201403706WA (en) Low noise turbine for geared turbofan engine
SG11201403015WA (en) Geared turbofan gas turbine engine architecture
SG11201402667QA (en) Geared turbofan gas turbine engine architecture
SG11201403012PA (en) Geared turbofan gas turbine engine architecture
BR112014001679A2 (pt) cone de escape para motor turbojato de aeronave
SG11201402823TA (en) Geared turbofan gas turbine engine architecture
BR112013014444A2 (pt) nacela para um motor turbojato de fluxo secundário e aeronave incluindo uma asa e uma nacela
SG11201402824RA (en) Geared turbofan gas turbine engine architecture
SG11201403011RA (en) Geared turbofan gas turbine engine architecture
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
BR112014017430A8 (pt) reversor de empuxo do tipo cascata para um motor turbojato de aeronaves e nacela oara um motor turbojato de aeronaves
EP2805022A4 (en) GAS TURBINE AND AUBES SYSTEM
BR112013023410A2 (pt) dispositivo de travamento e nacela de motor turbojato compreendendo pelo menos uma carenagem movente
BR112013023408A2 (pt) montagem de vedação para uma nacela de turbojato e nacela de motor turbojato
BR112014026258A2 (pt) conjunto de recipiente, método para montar um conjunto de recipiente e motor de turbina a gás
BR112015005181A2 (pt) dispositivo reversor de empuxo para uma nacela de motor turbojato e nacela de motor turbojato.
BR112015003808A2 (pt) aparelho de invólucro para um motor de turbina a gás e aparelho de hélice para um motor de turbina a gás
BR112014010136A2 (pt) reversor de empuxo para uma nacela de motor turbojato de aeronave e nacela
BRPI0822127A2 (pt) Nacela para motor turbojato e aeronave
BR112014032381A2 (pt) conjunto de ventoinha, motor de turbina a gás e método para montar um conjunto de vedação

Legal Events

Date Code Title Description
B08F Application dismissed because of non-payment of annual fees [chapter 8.6 patent gazette]

Free format text: REFERENTE A 4A ANUIDADE.

B08K Patent lapsed as no evidence of payment of the annual fee has been furnished to inpi [chapter 8.11 patent gazette]
B350 Update of information on the portal [chapter 15.35 patent gazette]