BR112013008450A2 - nacela de motor turbojato compreendendo uma seção posterior tendo uma estrutura interna - Google Patents

nacela de motor turbojato compreendendo uma seção posterior tendo uma estrutura interna

Info

Publication number
BR112013008450A2
BR112013008450A2 BR112013008450A BR112013008450A BR112013008450A2 BR 112013008450 A2 BR112013008450 A2 BR 112013008450A2 BR 112013008450 A BR112013008450 A BR 112013008450A BR 112013008450 A BR112013008450 A BR 112013008450A BR 112013008450 A2 BR112013008450 A2 BR 112013008450A2
Authority
BR
Brazil
Prior art keywords
engine compartment
section
turbojet engine
rear section
internal structure
Prior art date
Application number
BR112013008450A
Other languages
English (en)
Inventor
Guy Bernard Vauchel
Laurence Lemains
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 BR112013008450A2 publication Critical patent/BR112013008450A2/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
    • F01D25/24—Casings; Casing parts, e.g. diaphragms, casing fastenings
    • 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
    • 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
    • B64D33/00—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for
    • B64D33/04—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for of exhaust outlets or jet pipes
    • 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
    • F02K1/38—Introducing air inside the jet
    • F02K1/383—Introducing air inside the jet with retractable elements
    • 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
    • F02K1/46—Nozzles having means for adding air to the jet or for augmenting the mixing region between the jet and the ambient air, e.g. for silencing
    • 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)
  • Mechanical Engineering (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • General Engineering & Computer Science (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Movable Scaffolding (AREA)

Abstract

nacela de motor turbojato compreendendo uma seção posterior tendo uma estrutura interna. a presente invenção se refere a uma nacela de motor turbojato (1) compreendendo uma seção posterior (4) tendo uma estrutura interna (9), destinada a cercar uma parte posterior (5) de um compartimento de motor e para delimitar, com um tubo de jato de ejeção (6), uma seção transversal de saída (11) para ventilação (10) do compartimento do motor, caracterizada pelo fato de que compreende pelo menos um elemento móvel (15,151,152, 153, 154, 155, 156, 158, 159) associado com pelo menos um meio de controle correspondente, referido elemento móvel sendo capaz de se mover entre uma posição afastada, em que a seção transversal de saída para ventilação está em uma posição máxima e engrenada, em que o elemento móvel reduz pelo menos parcialmente a seção transversal de saída para ventilação em comparação com a posição retraída, referidos meios de controle sendo capazes de moverem o elemento móvel entre as posições retraída e engrenada.
BR112013008450A 2010-10-25 2011-10-03 nacela de motor turbojato compreendendo uma seção posterior tendo uma estrutura interna BR112013008450A2 (pt)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR1058712A FR2966435B1 (fr) 2010-10-25 2010-10-25 Nacelle de turboreacteur a section de sortie de ventilation adaptable
PCT/FR2011/052297 WO2012056138A1 (fr) 2010-10-25 2011-10-03 Nacelle de turboréacteur à section de sortie de ventilation adaptable

Publications (1)

Publication Number Publication Date
BR112013008450A2 true BR112013008450A2 (pt) 2016-06-28

Family

ID=44123494

Family Applications (1)

Application Number Title Priority Date Filing Date
BR112013008450A BR112013008450A2 (pt) 2010-10-25 2011-10-03 nacela de motor turbojato compreendendo uma seção posterior tendo uma estrutura interna

Country Status (8)

Country Link
US (1) US9670798B2 (pt)
EP (1) EP2632798B1 (pt)
CN (1) CN103180209A (pt)
BR (1) BR112013008450A2 (pt)
CA (1) CA2813559A1 (pt)
FR (1) FR2966435B1 (pt)
RU (1) RU2573686C2 (pt)
WO (1) WO2012056138A1 (pt)

Families Citing this family (14)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2993921B1 (fr) 2012-07-26 2014-07-18 Snecma Procede pour ameliorer les performances du systeme d'ejection d'un turbomoteur d'aeronef a double flux separes, systeme d'ejection et turbomoteur correspondants.
US9347397B2 (en) * 2012-08-02 2016-05-24 United Technologies Corporation Reflex annular vent nozzle
EP3019724B1 (en) * 2013-07-09 2018-04-11 United Technologies Corporation Preloaded aft vent area for low pressure fan ducts
US20150267644A1 (en) * 2014-03-19 2015-09-24 The Boeing Company Integrated Primary Nozzle
US10197007B2 (en) 2016-01-14 2019-02-05 General Electric Company Method and system for controlling core cowl vent area
PL420340A1 (pl) * 2017-01-30 2018-08-13 General Electric Company Redukowanie fali uderzeniowej dyszy ujściowej
FR3077847B1 (fr) * 2018-02-09 2020-02-14 Safran Nacelles Inverseur de poussee a volets pour ensemble propulsif d’aeronef
US10794327B2 (en) 2018-03-21 2020-10-06 Honeywell International Inc. Systems and methods for thrust reverser with temperature and fluid management
US11002222B2 (en) 2018-03-21 2021-05-11 Honeywell International Inc. Systems and methods for thrust reverser with temperature and fluid management
DE102018123573B4 (de) * 2018-09-25 2021-04-29 Rolls-Royce Deutschland Ltd & Co Kg Druckausgleichsklappenbaugruppe
FR3097016B1 (fr) * 2019-06-06 2021-07-23 Safran Aircraft Engines Structure de confluence d’une veine primaire et d’une veine secondaire dans une turbomachine a double flux
FR3098253B1 (fr) * 2019-07-02 2021-09-17 Safran Aircraft Engines Turbomachine à double flux comprenant une tuyère compacte
FR3099916B1 (fr) 2019-08-16 2022-08-05 Safran Aircraft Engines Structure interne pour nacelle de turbomachine
US11518535B2 (en) * 2019-09-30 2022-12-06 Rohr, Inc. Nacelle cowl deflection limiter

Family Cites Families (14)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3003311A (en) * 1957-07-17 1961-10-10 Havilland Engine Co Ltd Adjustable propulsion nozzles
US3391869A (en) * 1966-05-23 1968-07-09 Rohr Corp Variable cone area convergentdivergent nozzle system
FR1504543A (fr) * 1966-07-28 1967-12-08 Snecma Perfectionnements aux turboréacteurs et autres réacteurs à double flux
US4825644A (en) * 1987-11-12 1989-05-02 United Technologies Corporation Ventilation system for a nacelle
US5284012A (en) * 1991-05-16 1994-02-08 General Electric Company Nacelle cooling and ventilation system
US5623820A (en) * 1995-02-03 1997-04-29 The Boeing Company Flow control apparatus for gas turbine engine installation pressure relief doors
US6751944B2 (en) * 2001-10-23 2004-06-22 The Nordam Group, Inc. Confluent variable exhaust nozzle
FR2890696B1 (fr) * 2005-09-12 2010-09-17 Airbus France Turbomoteur a bruit de jet attenue
FR2892152B1 (fr) * 2005-10-19 2007-11-23 Airbus France Sas Turbomoteur a bruit de jet attenue
FR2896276B1 (fr) * 2006-01-19 2008-02-15 Airbus France Sas Turbomoteur a double flux pourvu d'un prerefroidisseur.
US7614210B2 (en) * 2006-02-13 2009-11-10 General Electric Company Double bypass turbofan
GB0607773D0 (en) * 2006-04-20 2006-05-31 Rolls Royce Plc A gas turbine engine
FR2920146B1 (fr) * 2007-08-20 2009-10-30 Aircelle Sa Nacelle a section de sortie adaptable
FR2939768B1 (fr) * 2008-12-12 2011-09-09 Aircelle Sa Trappe de surpression destinee a etre montee sur une paroi d'une nacelle de turboreacteur

Also Published As

Publication number Publication date
US9670798B2 (en) 2017-06-06
RU2573686C2 (ru) 2016-01-27
EP2632798B1 (fr) 2017-05-31
CA2813559A1 (fr) 2012-05-03
CN103180209A (zh) 2013-06-26
WO2012056138A1 (fr) 2012-05-03
RU2013122962A (ru) 2014-12-10
EP2632798A1 (fr) 2013-09-04
US20130236294A1 (en) 2013-09-12
FR2966435B1 (fr) 2013-04-26
FR2966435A1 (fr) 2012-04-27

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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]