BRPI0813603A2 - "nacela para um turbojato e aeronave" - Google Patents

"nacela para um turbojato e aeronave"

Info

Publication number
BRPI0813603A2
BRPI0813603A2 BRPI0813603A BRPI0813603A2 BR PI0813603 A2 BRPI0813603 A2 BR PI0813603A2 BR PI0813603 A BRPI0813603 A BR PI0813603A BR PI0813603 A2 BRPI0813603 A2 BR PI0813603A2
Authority
BR
Brazil
Prior art keywords
nacela
turbojet
aircraft
Prior art date
Application number
Other languages
English (en)
Inventor
Thierry Jacques Albert Le Docte
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 BRPI0813603A2 publication Critical patent/BRPI0813603A2/pt

Links

Classifications

    • 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
    • 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
    • B64D29/06—Attaching of nacelles, fairings or cowlings
    • 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
    • F02K1/08—Varying effective area of jet pipe or nozzle by axially moving or transversely deforming an internal member, e.g. the exhaust cone
    • 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
    • F02K1/08—Varying effective area of jet pipe or nozzle by axially moving or transversely deforming an internal member, e.g. the exhaust cone
    • F02K1/085—Varying effective area of jet pipe or nozzle by axially moving or transversely deforming an internal member, e.g. the exhaust cone by transversely deforming an internal member
    • 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
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
    • Y10T137/00—Fluid handling
    • Y10T137/0536—Highspeed fluid intake means [e.g., jet engine intake]

Landscapes

  • Engineering & Computer Science (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Supercharger (AREA)
BRPI0813603 2007-08-20 2008-06-19 "nacela para um turbojato e aeronave" BRPI0813603A2 (pt)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR0705920A FR2920146B1 (fr) 2007-08-20 2007-08-20 Nacelle a section de sortie adaptable
PCT/FR2008/000859 WO2009024660A1 (fr) 2007-08-20 2008-06-19 Nacelle a section de sortie adaptable

Publications (1)

Publication Number Publication Date
BRPI0813603A2 true BRPI0813603A2 (pt) 2014-12-30

Family

ID=39204058

Family Applications (1)

Application Number Title Priority Date Filing Date
BRPI0813603 BRPI0813603A2 (pt) 2007-08-20 2008-06-19 "nacela para um turbojato e aeronave"

Country Status (8)

Country Link
US (1) US8875518B2 (pt)
EP (1) EP2181041A1 (pt)
CN (1) CN101784449B (pt)
BR (1) BRPI0813603A2 (pt)
CA (1) CA2696792C (pt)
FR (1) FR2920146B1 (pt)
RU (1) RU2469923C2 (pt)
WO (1) WO2009024660A1 (pt)

Families Citing this family (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2966435B1 (fr) * 2010-10-25 2013-04-26 Aircelle Sa Nacelle de turboreacteur a section de sortie de ventilation adaptable
EP3385510B1 (en) * 2011-03-17 2022-02-09 Airbus Canada Limited Partnership Control method for operating a precooler in an aircraft and aircraft engine
FR2978989B1 (fr) * 2011-08-12 2013-07-26 Aircelle Sa Cone d'ejection pour turboreacteur d'aeronef
US10294863B2 (en) 2013-07-09 2019-05-21 United Technologies Corporation Preloaded AFT vent area for low pressure fan ducts
EP3183172B1 (en) 2014-08-20 2018-10-31 Bombardier Inc. Actuated outlet door for aircraft high-temperature exhaust
FR3075865B1 (fr) * 2017-12-21 2020-07-17 Safran Nacelles Ensemble propulsif pour aeronef et procede de ventilation d’une enceinte moteur
FR3099916B1 (fr) * 2019-08-16 2022-08-05 Safran Aircraft Engines Structure interne pour nacelle de turbomachine
US11685539B2 (en) * 2019-09-27 2023-06-27 Rohr, Inc. Passive internal compartment exhaust for an aircraft propulsion system
US11518535B2 (en) * 2019-09-30 2022-12-06 Rohr, Inc. Nacelle cowl deflection limiter
FR3103226B1 (fr) * 2019-11-15 2021-11-12 Airbus Operations Sas Turbomachine d’aeronef comportant une tuyere primaire equipee d’une cale d’usure

Family Cites Families (33)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB1058933A (en) * 1963-10-02 1967-02-15 Bristol Siddeley Engines Ltd Improvements in jet propulsion nozzles
US3598318A (en) * 1970-04-10 1971-08-10 Boeing Co Movable acoustic splitter for nozzle area control and thrust reversal
GB1318748A (en) * 1970-08-11 1973-05-31 Secr Defence Gas turgine ducted fan engines for aircraft
US3721389A (en) * 1971-06-10 1973-03-20 Boeing Co Exit nozzle assemblies for gas turbine power plants
FR2260697B1 (pt) * 1974-02-11 1976-06-25 Snecma
GB1605260A (en) * 1974-09-07 1986-11-12 Rolls Royce Gas turbine engines
US4232513A (en) * 1977-10-19 1980-11-11 Rolls-Royce Limited Pressure relief panel for aircraft powerplant
US4271666A (en) * 1979-08-20 1981-06-09 Avco Corporation Integral infrared radiation suppressor for a turbofan engine
US4825644A (en) * 1987-11-12 1989-05-02 United Technologies Corporation Ventilation system for a nacelle
US4961588A (en) * 1989-01-31 1990-10-09 Westinghouse Electric Corp. Radial seal
US5054281A (en) * 1989-09-25 1991-10-08 Rohr Industries, Inc. Gas turbine engine compartment vent system
DE4008956A1 (de) * 1990-03-20 1991-09-26 Messerschmitt Boelkow Blohm Einlaufsystem fuer ueber- oder hyperschallflugzeuge
US5174525A (en) * 1991-09-26 1992-12-29 General Electric Company Structure for eliminating lift load bending in engine core of turbofan
US5524846A (en) * 1993-12-21 1996-06-11 The Boeing Company Fire protection system for airplanes
US5778659A (en) * 1994-10-20 1998-07-14 United Technologies Corporation Variable area fan exhaust nozzle having mechanically separate sleeve and thrust reverser actuation systems
US5577381A (en) * 1994-12-06 1996-11-26 United Technologies Corporation Exhaust nozzle cooling scheme for gas turbine engine
US5623820A (en) * 1995-02-03 1997-04-29 The Boeing Company Flow control apparatus for gas turbine engine installation pressure relief doors
US5632493A (en) * 1995-05-04 1997-05-27 Eg&G Sealol, Inc. Compliant pressure balanced seal apparatus
FR2734319B1 (fr) * 1995-05-15 1997-07-18 Aerospatiale Dispositif pour prelever et refroidir de l'air chaud au niveau d'un moteur d'aeronef
GB2308866B (en) * 1996-01-04 1999-09-08 Rolls Royce Plc Ducted fan gas turbine engine with secondary duct
US5887822A (en) * 1997-03-28 1999-03-30 The Boeing Company Segmented engine flow control device
US5906097A (en) * 1997-03-28 1999-05-25 The Boeing Company Engine flow control device
US6487848B2 (en) * 1998-11-06 2002-12-03 United Technologies Corporation Gas turbine engine jet noise suppressor
US7578132B2 (en) * 2001-03-03 2009-08-25 Rolls-Royce Plc Gas turbine engine exhaust nozzle
CA2460598C (en) * 2001-10-23 2012-12-18 The Nordam Group, Inc. Confluent variable exhaust nozzle
US7188417B2 (en) * 2002-06-28 2007-03-13 United Technologies Corporation Advanced L-channel welded nozzle design
US7010905B2 (en) * 2003-02-21 2006-03-14 The Nordam Group, Inc. Ventilated confluent exhaust nozzle
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
US8434309B2 (en) * 2006-10-12 2013-05-07 United Technologies Corporation Translating core cowl having aerodynamic flap sections
FR2960216B1 (fr) * 2010-05-19 2013-02-15 Aircelle Sa Element d'aerodynamisme pour une nacelle d'aeronef
US9555871B2 (en) * 2012-03-05 2017-01-31 The Boeing Company Two-surface sandwich structure for accommodating in-plane expansion of one of the surfaces relative to the opposing surface

Also Published As

Publication number Publication date
US20110214747A1 (en) 2011-09-08
FR2920146A1 (fr) 2009-02-27
WO2009024660A1 (fr) 2009-02-26
RU2469923C2 (ru) 2012-12-20
US8875518B2 (en) 2014-11-04
CA2696792C (fr) 2015-10-06
EP2181041A1 (fr) 2010-05-05
CN101784449B (zh) 2015-01-07
FR2920146B1 (fr) 2009-10-30
CN101784449A (zh) 2010-07-21
CA2696792A1 (fr) 2009-02-26
RU2010109801A (ru) 2011-09-27

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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]