BR112012031008A2 - pá em cascata automontada para um reversor de empuxo em cascata para uma nacela de motor turbojato de avião, cascata e montagem da mesma.. - Google Patents

pá em cascata automontada para um reversor de empuxo em cascata para uma nacela de motor turbojato de avião, cascata e montagem da mesma..

Info

Publication number
BR112012031008A2
BR112012031008A2 BR112012031008A BR112012031008A BR112012031008A2 BR 112012031008 A2 BR112012031008 A2 BR 112012031008A2 BR 112012031008 A BR112012031008 A BR 112012031008A BR 112012031008 A BR112012031008 A BR 112012031008A BR 112012031008 A2 BR112012031008 A2 BR 112012031008A2
Authority
BR
Brazil
Prior art keywords
cascade
self
downstream
thrust reverser
shovel
Prior art date
Application number
BR112012031008A
Other languages
English (en)
Inventor
Guy Bernard Vauchel
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 BR112012031008A2 publication Critical patent/BR112012031008A2/pt

Links

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02K—JET-PROPULSION PLANTS
    • F02K3/00—Plants including a gas turbine driving a compressor or a ducted fan
    • F02K3/02—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber
    • F02K3/025—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber the by-pass flow being at least partly used to create an independent thrust component
    • 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

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)
  • Turbine Rotor Nozzle Sealing (AREA)

Abstract

pá em cascata automontada para um reversor de empulxo em cascata para uma nacela de motor turbojato de avião, cascata emontagem da mesma. a invenção refere-se a uma cascata automontada (61) para um reversor de empuxo de uma nacela de motor a jato de avião, a referida cascata compreendendo uma porção a montante (612), provida com um meio de anexação a montante para anexar a cascata a uma estrutura estacionária da nacela, e, além disso, compreendendo uma porção a jusante oposta (613) sobre a qual o meio de conexão a jusante (617,620), posicionado apenas sobre a referida porção a jusante eprojetada para conectar a cascata a pelo menos uma cascata adjante, são providos de modo que duas cascatas adjacentes estão diretamente conectadas entre si apenas nas respectivas porções a jusante das mesmas. a referida porção a jusante corresponde a uma área estendendo-se a partir da borda lateral e jusante aolongo de umcomprimento menor ou igual a n vezes o comprimento da última cavidade localizada ao longo da referida borda lateral a jusante, em que n é menor que 3. a presente invenção édeuso no campo de nacelas de motor a jato de avião.
BR112012031008A 2010-06-08 2011-06-01 pá em cascata automontada para um reversor de empuxo em cascata para uma nacela de motor turbojato de avião, cascata e montagem da mesma.. BR112012031008A2 (pt)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR1054473A FR2960918B1 (fr) 2010-06-08 2010-06-08 Grille de deviation du type autosupporte pour inverseur de poussee
PCT/FR2011/051259 WO2011154644A1 (fr) 2010-06-08 2011-06-01 Grille de déviation du type autosupporté pour inverseur de poussée

Publications (1)

Publication Number Publication Date
BR112012031008A2 true BR112012031008A2 (pt) 2016-10-25

Family

ID=43513753

Family Applications (1)

Application Number Title Priority Date Filing Date
BR112012031008A BR112012031008A2 (pt) 2010-06-08 2011-06-01 pá em cascata automontada para um reversor de empuxo em cascata para uma nacela de motor turbojato de avião, cascata e montagem da mesma..

Country Status (8)

Country Link
US (1) US9410502B2 (pt)
EP (1) EP2580459B1 (pt)
CN (1) CN102933829A (pt)
BR (1) BR112012031008A2 (pt)
CA (1) CA2801603A1 (pt)
FR (1) FR2960918B1 (pt)
RU (1) RU2572153C2 (pt)
WO (1) WO2011154644A1 (pt)

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US8104262B2 (en) * 2006-10-12 2012-01-31 United Technologies Corporation Dual function cascade integrated variable area fan nozzle and thrust reverser
FR2987600B1 (fr) * 2012-03-02 2014-02-28 Aircelle Sa Nacelle aplatie de turboreacteur
GB201219366D0 (en) 2012-10-29 2012-12-12 Rolls Royce Deutschland & Co Kg Aeroengine thrust reverser arrangement
FR3007465B1 (fr) 2013-06-21 2015-06-05 Aircelle Sa Dispositif de commande pour inverseur de poussee de turboreacteur, realisant un blocage de l'inverseur
US9347398B2 (en) * 2013-10-07 2016-05-24 Rohr, Inc. Actuator support system and apparatus
US9771894B2 (en) 2013-10-07 2017-09-26 Rohr, Inc. Radially connected cascade grids
CN104712455B (zh) * 2013-12-12 2017-07-04 中航商用航空发动机有限责任公司 涡扇发动机的反推力装置和用于该反推力装置的反推叶栅
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
US10309343B2 (en) * 2014-11-06 2019-06-04 Rohr, Inc. Split sleeve hidden door thrust reverser
FR3047522B1 (fr) * 2016-02-04 2018-03-16 Safran Aircraft Engines Ensemble propulsif pour aeronef
EP3228854B1 (en) 2016-04-06 2019-10-02 Rolls-Royce plc Aircraft gas turbine engine nacelle
RU2666889C1 (ru) * 2017-03-16 2018-09-12 Акционерное общество "Объединенная двигателестроительная корпорация" (АО "ОДК") Отклоняющая решетка реверсивного устройства наружного корпуса двигателя
US10598127B2 (en) * 2017-08-15 2020-03-24 Spirit Aerosystems, Inc. Method of fabricating a thrust reverser cascade assembly
US11073032B2 (en) * 2018-07-25 2021-07-27 Rohr, Inc. Cascade array vanes with assembly features
US20190375136A1 (en) * 2018-06-08 2019-12-12 The Boeing Company Cascade assembly for a jet engine thrust reverser
FR3095676B1 (fr) 2019-05-03 2021-04-09 Safran Aircraft Engines Grille d’inverseur de poussée incluant un traitement acoustique
CN113879557A (zh) * 2020-07-02 2022-01-04 中国航发商用航空发动机有限责任公司 反推叶栅装置制造方法、制造工装及反推叶栅装置
CN113530706B (zh) * 2021-08-18 2022-08-05 中国航发贵阳发动机设计研究所 一种发动机尾喷管的外调节片与主动调节片的连接结构

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GB1052963A (pt) * 1963-09-30
US3262270A (en) * 1965-06-07 1966-07-26 Gen Electric Thrust reverser
US3262268A (en) * 1965-06-07 1966-07-26 Gen Electric Thrust reverser
US3794246A (en) * 1973-04-11 1974-02-26 Aeronca Inc Thrust reversing cascade assembly
US4030290A (en) * 1974-11-06 1977-06-21 The Boeing Company Jet engine thrust reverser
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US4067094A (en) * 1976-04-26 1978-01-10 Harry Feick Co., Inc. Load bearing vane structure for thrust reversal
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US4778110A (en) * 1982-09-30 1988-10-18 Rohr Industries, Inc. Modular composite cascade assembly
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US5507143A (en) * 1993-04-13 1996-04-16 The Boeing Company Cascade assembly for use in a thrust-reversing mechanism
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UA28120C2 (uk) * 1998-06-03 2000-10-16 Державне Підприємство "Запорізьке Машинобудівне Конструкторське Бюро "Прогрес" Імені Академіка О.Г.Івченка" Решітка аеродинамічних профілів пристрою реверсування тяги реактивного двигуна
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Also Published As

Publication number Publication date
CN102933829A (zh) 2013-02-13
FR2960918B1 (fr) 2012-05-25
RU2012156113A (ru) 2014-07-20
US20130266423A1 (en) 2013-10-10
RU2572153C2 (ru) 2015-12-27
CA2801603A1 (fr) 2011-12-15
FR2960918A1 (fr) 2011-12-09
US9410502B2 (en) 2016-08-09
EP2580459A1 (fr) 2013-04-17
WO2011154644A1 (fr) 2011-12-15
EP2580459B1 (fr) 2016-05-11

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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]