BR112015012652A2 - Sistema reversor de empuxo e método para reversão de empuxo - Google Patents

Sistema reversor de empuxo e método para reversão de empuxo

Info

Publication number
BR112015012652A2
BR112015012652A2 BR112015012652A BR112015012652A BR112015012652A2 BR 112015012652 A2 BR112015012652 A2 BR 112015012652A2 BR 112015012652 A BR112015012652 A BR 112015012652A BR 112015012652 A BR112015012652 A BR 112015012652A BR 112015012652 A2 BR112015012652 A2 BR 112015012652A2
Authority
BR
Brazil
Prior art keywords
thrust
cascade
translation
rear direction
engine
Prior art date
Application number
BR112015012652A
Other languages
English (en)
Inventor
Roy Stuart Alan
Michael Cosgrove James
Original Assignee
Gen Electric
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 Gen Electric filed Critical Gen Electric
Publication of BR112015012652A2 publication Critical patent/BR112015012652A2/pt

Links

Classifications

    • 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
    • F02K1/54—Nozzles having means for reversing jet thrust
    • F02K1/64—Reversing fan flow
    • F02K1/70—Reversing fan flow using thrust reverser flaps or doors mounted on the fan housing
    • F02K1/72—Reversing fan flow using thrust reverser flaps or doors mounted on the fan housing the aft end of the fan housing being movable to uncover openings in the fan housing for the reversed flow
    • 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
    • F02K1/54—Nozzles having means for reversing jet thrust
    • F02K1/64—Reversing fan flow
    • 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
    • F02K1/54—Nozzles having means for reversing jet thrust
    • F02K1/64—Reversing fan flow
    • F02K1/70—Reversing fan flow using thrust reverser flaps or doors mounted on the fan housing
    • 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

Abstract

SISTEMA REVERSOR DE EMPUXO, MOTOR TURBOFAN A GÁS E MÉTODO PARA REVERSÃO DE EMPUXO. Trata-se de um sistema reversar de empuxo e operação adequados para motores turbofan de alta derivação. O sistema reversar de empuxo inclui um sistema em cascata adaptado para ser transladado com uma carenagem de translação na direção traseira de um motor para expor uma abertura circunferencial. O sistema em cascata é distribuído a partir de uma posição acondicionada enquanto a carenagem de translação e o sistema em cascata são transladados na direção traseira. Durante a implantação do sistema em cascata, a extremidade dianteira do mesmo translada na direção traseira e uma extremidade traseira do mesmo translada, inicialmente, na direção traseira e gira, então, de modo subsequente, sobre a extremidade dianteira de forma que a translação do segmento em cascata na direção traseira faça com que o segmento em cascata se mova para uma posição implantada e desvie o ar de derivação para dentro de um duto de derivação do motor através de uma abertura circunferencial.
BR112015012652A 2012-11-30 2013-11-18 Sistema reversor de empuxo e método para reversão de empuxo BR112015012652A2 (pt)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
US13/690,065 US9016040B2 (en) 2012-11-30 2012-11-30 Thrust reverser system with translating-rotating cascade and method of operation
PCT/US2013/070566 WO2014123595A2 (en) 2012-11-30 2013-11-18 Thrust reverser system with translating rotating cascade and method of operation

Publications (1)

Publication Number Publication Date
BR112015012652A2 true BR112015012652A2 (pt) 2017-10-03

Family

ID=50824058

Family Applications (1)

Application Number Title Priority Date Filing Date
BR112015012652A BR112015012652A2 (pt) 2012-11-30 2013-11-18 Sistema reversor de empuxo e método para reversão de empuxo

Country Status (7)

Country Link
US (1) US9016040B2 (pt)
EP (1) EP2925991B1 (pt)
JP (1) JP2016506470A (pt)
CN (1) CN104822930B (pt)
BR (1) BR112015012652A2 (pt)
CA (1) CA2891594C (pt)
WO (1) WO2014123595A2 (pt)

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US10077739B2 (en) * 2014-04-24 2018-09-18 Rohr, Inc. Dual actuation system for cascade and thrust reverser panel for an integral cascade variable area fan nozzle
US9534562B2 (en) * 2014-04-25 2017-01-03 Rohr, Inc. System and apparatus for a thrust reverser
US10612490B2 (en) 2014-04-25 2020-04-07 Rohr, Inc. Drag link assembly including buried drag link fitting
US9945324B2 (en) * 2014-11-06 2018-04-17 Rohr, Inc. Sleeve linkage for thrust reverser
US10309343B2 (en) * 2014-11-06 2019-06-04 Rohr, Inc. Split sleeve hidden door thrust reverser
US9784214B2 (en) * 2014-11-06 2017-10-10 Rohr, Inc. Thrust reverser with hidden linkage blocker doors
FR3031727B1 (fr) * 2015-01-21 2019-07-12 Safran Nacelles Dispositif d’inversion de poussee a grilles mobiles et berceau pour nacelle pour mat du type corps
US10378479B2 (en) 2015-10-19 2019-08-13 General Electric Company Variable effective area fan nozzle
US10247136B2 (en) * 2015-12-03 2019-04-02 General Electric Company Thrust reverser system for a gas turbine engine
US20170167438A1 (en) * 2015-12-11 2017-06-15 General Electric Company Gas Turbine Engine
FR3047522B1 (fr) * 2016-02-04 2018-03-16 Safran Aircraft Engines Ensemble propulsif pour aeronef
US10655564B2 (en) 2016-05-13 2020-05-19 Rohr, Inc. Thrust reverser system with hidden blocker doors
US9976696B2 (en) 2016-06-21 2018-05-22 Rohr, Inc. Linear actuator with multi-degree of freedom mounting structure
FR3055669B1 (fr) * 2016-09-05 2018-09-28 Airbus Operations Systeme d'inverseur de poussee limitant les perturbations aerodynamiques en configuration inactive
US11473527B2 (en) * 2016-09-28 2022-10-18 The Boeing Company Nacelle with tangential restraint
US20180128206A1 (en) * 2016-11-09 2018-05-10 General Electric Company Gas turbine engine
FR3059368A1 (fr) * 2016-11-28 2018-06-01 Airbus Operations Nacelle d'un turboreacteur comportant un volet inverseur
US11022071B2 (en) 2016-12-21 2021-06-01 The Boeing Company Load distribution panel assembly, system and method
FR3062371B1 (fr) * 2017-01-31 2019-03-29 Airbus Nacelle d'un turboreacteur comportant un volet inverseur
FR3062637B1 (fr) * 2017-02-07 2020-07-10 Airbus Operations (S.A.S.) Nacelle de turboreacteur comportant un mecanisme d'entrainement d'inverseur de poussee
ES2819128T3 (es) * 2017-03-03 2021-04-15 MTU Aero Engines AG Contorneo de una plataforma de una rejilla de paletas
US10415503B2 (en) 2017-03-10 2019-09-17 Spirit Aerosystems, Inc. Cascade pivot door-type thrust reverser for turbofan engine
CN108661821B (zh) * 2017-03-31 2022-03-18 Mra系统有限责任公司 反推力器组件及操作方法
FR3067406B1 (fr) * 2017-06-13 2019-07-12 Airbus Operations Systeme d'inverseur de poussee presentant des perturbations aerodynamiques limitees
US10436112B2 (en) * 2017-06-26 2019-10-08 The Boeing Company Translating turning vanes for a nacelle inlet
US10343786B2 (en) * 2017-06-28 2019-07-09 General Electric Company System and method of operating a ducted fan propulsion system during aircraft taxi
US10578055B2 (en) * 2017-08-10 2020-03-03 Mra Systems, Llc Turbine engine thrust reverser stop
US11047308B2 (en) 2018-06-29 2021-06-29 The Boeing Company Acoustic panel for thrust reversers
US10794328B2 (en) * 2018-07-06 2020-10-06 Rohr, Inc. Thrust reverser with blocker door folding linkage
FR3090048A1 (fr) * 2018-12-13 2020-06-19 Airbus Operations Turboreacteur double flux comportant une serie de lames rotatives pour obturer la veine du flux secondaire
FR3092145A1 (fr) * 2019-01-24 2020-07-31 Airbus Operations Turboreacteur double flux comportant une serie de lames rotatives pour obturer la veine du flux secondaire
FR3094757A1 (fr) * 2019-04-04 2020-10-09 Airbus Operations Turboreacteur comportant une nacelle equipee d’un systeme inverseur et une grille de cascades mobile
FR3095015A1 (fr) * 2019-04-09 2020-10-16 Airbus Operations Turboreacteur double flux comportant une serie de lames rotatives pour obturer la veine du flux secondaire
FR3102511B1 (fr) * 2019-10-25 2022-08-26 Safran Nacelles Inverseur de poussée à volets commandés par un mécanisme doté de guignols aéronautiques
US11840987B2 (en) * 2022-04-05 2023-12-12 General Electric Company Cascade thrust reverser assembly for a gas turbine engine

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Also Published As

Publication number Publication date
US9016040B2 (en) 2015-04-28
EP2925991B1 (en) 2019-09-04
CA2891594C (en) 2020-09-22
EP2925991A2 (en) 2015-10-07
CN104822930A (zh) 2015-08-05
CA2891594A1 (en) 2014-08-14
WO2014123595A2 (en) 2014-08-14
CN104822930B (zh) 2017-09-22
WO2014123595A8 (en) 2015-06-25
WO2014123595A3 (en) 2014-11-06
US20140150403A1 (en) 2014-06-05
JP2016506470A (ja) 2016-03-03

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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]
B11B Dismissal acc. art. 36, par 1 of ipl - no reply within 90 days to fullfil the necessary requirements
B350 Update of information on the portal [chapter 15.35 patent gazette]