FR2967399B1 - Nacelle pour turboreacteur double flux d'un aeronef - Google Patents

Nacelle pour turboreacteur double flux d'un aeronef

Info

Publication number
FR2967399B1
FR2967399B1 FR1059393A FR1059393A FR2967399B1 FR 2967399 B1 FR2967399 B1 FR 2967399B1 FR 1059393 A FR1059393 A FR 1059393A FR 1059393 A FR1059393 A FR 1059393A FR 2967399 B1 FR2967399 B1 FR 2967399B1
Authority
FR
France
Prior art keywords
nacelle
aircraft
double flow
turbojet
turbojet double
Prior art date
Legal status (The legal status 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 status listed.)
Active
Application number
FR1059393A
Other languages
English (en)
Other versions
FR2967399A1 (fr
Inventor
Herve Hurlin
Olivier Kerbler
Olivier Gilo
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Safran Nacelles SAS
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
Priority to FR1059393A priority Critical patent/FR2967399B1/fr
Application filed by Aircelle SA filed Critical Aircelle SA
Priority to EP11831835.1A priority patent/EP2640952A2/fr
Priority to PCT/FR2011/052543 priority patent/WO2012066210A2/fr
Priority to US13/640,119 priority patent/US9243587B2/en
Priority to CA2816255A priority patent/CA2816255A1/fr
Priority to CN201180055102.8A priority patent/CN103210200B/zh
Priority to BR112013010648A priority patent/BR112013010648A2/pt
Priority to RU2013126749/06A priority patent/RU2013126749A/ru
Publication of FR2967399A1 publication Critical patent/FR2967399A1/fr
Application granted granted Critical
Publication of FR2967399B1 publication Critical patent/FR2967399B1/fr
Active legal-status Critical Current
Anticipated expiration legal-status Critical

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
    • F02K1/06—Varying effective area of jet pipe or nozzle
    • F02K1/12—Varying effective area of jet pipe or nozzle by means of pivoted flaps
    • F02K1/123—Varying effective area of jet pipe or nozzle by means of pivoted flaps of two series of flaps, both having their flaps hinged at their upstream ends on a fixed structure
    • 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
    • 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
    • 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
    • F02K1/12—Varying effective area of jet pipe or nozzle by means of pivoted flaps
    • 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
    • F02K1/76—Control or regulation of thrust reversers
    • F02K1/763—Control or regulation of thrust reversers with actuating systems or actuating devices; Arrangement of actuators for thrust reversers

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • General Engineering & Computer Science (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Wind Motors (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Springs (AREA)
FR1059393A 2010-11-16 2010-11-16 Nacelle pour turboreacteur double flux d'un aeronef Active FR2967399B1 (fr)

Priority Applications (8)

Application Number Priority Date Filing Date Title
FR1059393A FR2967399B1 (fr) 2010-11-16 2010-11-16 Nacelle pour turboreacteur double flux d'un aeronef
PCT/FR2011/052543 WO2012066210A2 (fr) 2010-11-16 2011-10-28 Nacelle pour un turboréacteur double flux d'un aéronef
US13/640,119 US9243587B2 (en) 2010-11-16 2011-10-28 Nacelle for an aircraft bypass turbojet engine
CA2816255A CA2816255A1 (fr) 2010-11-16 2011-10-28 Nacelle pour un turboreacteur double flux d'un aeronef
EP11831835.1A EP2640952A2 (fr) 2010-11-16 2011-10-28 Nacelle pour un turboréacteur double flux d'un aéronef
CN201180055102.8A CN103210200B (zh) 2010-11-16 2011-10-28 用于飞行器旁通涡轮喷气发动机的发动机舱
BR112013010648A BR112013010648A2 (pt) 2010-11-16 2011-10-28 nacela para um motor turbojato bypass de uma aeronave
RU2013126749/06A RU2013126749A (ru) 2010-11-16 2011-10-28 Гондола двухконтурного турбореактивного двигателя летательного аппарата

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
FR1059393A FR2967399B1 (fr) 2010-11-16 2010-11-16 Nacelle pour turboreacteur double flux d'un aeronef

Publications (2)

Publication Number Publication Date
FR2967399A1 FR2967399A1 (fr) 2012-05-18
FR2967399B1 true FR2967399B1 (fr) 2012-11-02

Family

ID=44115615

Family Applications (1)

Application Number Title Priority Date Filing Date
FR1059393A Active FR2967399B1 (fr) 2010-11-16 2010-11-16 Nacelle pour turboreacteur double flux d'un aeronef

Country Status (8)

Country Link
US (1) US9243587B2 (fr)
EP (1) EP2640952A2 (fr)
CN (1) CN103210200B (fr)
BR (1) BR112013010648A2 (fr)
CA (1) CA2816255A1 (fr)
FR (1) FR2967399B1 (fr)
RU (1) RU2013126749A (fr)
WO (1) WO2012066210A2 (fr)

Families Citing this family (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US9885253B2 (en) 2013-10-07 2018-02-06 Rohr, Inc. Hybrid inner fixed structure with metallic and composite construction
FR3021704B1 (fr) * 2014-05-30 2016-06-03 Aircelle Sa Nacelle pour turboreacteur d'aeronef comprenant une tuyere secondaire a portes rotatives
GB201609071D0 (en) * 2016-05-24 2016-07-06 Rolls Royce Plc Aircraft gas turbine engine nacelle
US10759541B2 (en) 2016-10-14 2020-09-01 Rohr, Inc. Nacelle bifurcation with leading edge structure

Family Cites Families (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2791882A (en) * 1950-09-29 1957-05-14 Westinghouse Electric Corp Variable area nozzle for jet propulsion engine
US2779157A (en) * 1951-02-14 1957-01-29 Rohr Aircraft Corp Nozzle with variable discharge orifice
US3892358A (en) * 1971-03-17 1975-07-01 Gen Electric Nozzle seal
US3988889A (en) * 1974-02-25 1976-11-02 General Electric Company Cowling arrangement for a turbofan engine
US3972475A (en) * 1975-07-31 1976-08-03 United Technologies Corporation Nozzle construction providing for thermal growth
US4994660A (en) * 1989-04-11 1991-02-19 Hitachi, Ltd. Axisymmetric vectoring exhaust nozzle
FR2669679B1 (fr) * 1990-11-28 1994-04-29 Sud Ouest Conception Aeronauti Tuyere d'ejection de gaz pour moteur a reaction et moteur a reaction equipe d'une telle tuyere, en particulier moteur du type a flux separes.
US5806302A (en) * 1996-09-24 1998-09-15 Rohr, Inc. Variable fan exhaust area nozzle for aircraft gas turbine engine with thrust reverser
FR2873757B1 (fr) * 2004-07-28 2006-09-29 Snecma Moteurs Sa Tuyere convergente de turboreacteur
FR2902839B1 (fr) * 2006-06-21 2011-09-30 Aircelle Sa Inverseur de poussee formant une tuyere adaptative

Also Published As

Publication number Publication date
CN103210200A (zh) 2013-07-17
RU2013126749A (ru) 2014-12-27
FR2967399A1 (fr) 2012-05-18
US20130230391A1 (en) 2013-09-05
CN103210200B (zh) 2015-12-09
WO2012066210A2 (fr) 2012-05-24
US9243587B2 (en) 2016-01-26
BR112013010648A2 (pt) 2016-08-09
EP2640952A2 (fr) 2013-09-25
CA2816255A1 (fr) 2012-05-24
WO2012066210A3 (fr) 2012-10-26

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