BRPI0720329A2 - " nacela de motor a jato de aeronave " - Google Patents

" nacela de motor a jato de aeronave "

Info

Publication number
BRPI0720329A2
BRPI0720329A2 BRPI0720329-2A2A BRPI0720329A BRPI0720329A2 BR PI0720329 A2 BRPI0720329 A2 BR PI0720329A2 BR PI0720329 A BRPI0720329 A BR PI0720329A BR PI0720329 A2 BRPI0720329 A2 BR PI0720329A2
Authority
BR
Brazil
Prior art keywords
nacela
jet engine
aircraft jet
aircraft
engine
Prior art date
Application number
BRPI0720329-2A2A
Other languages
English (en)
Inventor
Guillaume Bulin
Patrick Oberle
Thierry Surply
Original Assignee
Aibus France
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 Aibus France filed Critical Aibus France
Publication of BRPI0720329A2 publication Critical patent/BRPI0720329A2/pt

Links

Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C7/00—Structures or fairings not otherwise provided for
    • B64C7/02—Nacelles
    • 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
    • F02K1/28—Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto using fluid jets to influence the jet 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
    • F02K1/28—Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto using fluid jets to influence the jet flow
    • F02K1/30—Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto using fluid jets to influence the jet flow for varying effective area of jet pipe or nozzle
    • 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
    • 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
    • F02K3/04—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 plant including ducted fans, i.e. fans with high volume, low pressure outputs, for augmenting the jet thrust, e.g. of double-flow type
    • F02K3/06—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 plant including ducted fans, i.e. fans with high volume, low pressure outputs, for augmenting the jet thrust, e.g. of double-flow type with front fan
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2260/00—Function
    • F05D2260/60—Fluid transfer
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2270/00—Control
    • F05D2270/01—Purpose of the control system
    • F05D2270/17—Purpose of the control system to control boundary layer
    • F05D2270/173—Purpose of the control system to control boundary layer by the Coanda effect
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2270/00—Control
    • F05D2270/01—Purpose of the control system
    • F05D2270/18—Purpose of the control system using fluidic amplifiers or actuators
    • 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

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Jet Pumps And Other Pumps (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Wind Motors (AREA)
BRPI0720329-2A2A 2007-01-02 2007-12-27 " nacela de motor a jato de aeronave " BRPI0720329A2 (pt)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR0700004A FR2910937B1 (fr) 2007-01-02 2007-01-02 Nacelle de reacteur d'aeronef et aeronef comportant une telle nacelle
PCT/FR2007/002176 WO2008102079A2 (fr) 2007-01-02 2007-12-27 Nacelle de réacteur d'aéronef et aéronef comportant une telle nacelle

Publications (1)

Publication Number Publication Date
BRPI0720329A2 true BRPI0720329A2 (pt) 2013-12-24

Family

ID=38123871

Family Applications (1)

Application Number Title Priority Date Filing Date
BRPI0720329-2A2A BRPI0720329A2 (pt) 2007-01-02 2007-12-27 " nacela de motor a jato de aeronave "

Country Status (9)

Country Link
US (1) US8596037B2 (pt)
EP (1) EP2115290B1 (pt)
JP (1) JP5031850B2 (pt)
CN (1) CN101573524B (pt)
BR (1) BRPI0720329A2 (pt)
CA (1) CA2674260C (pt)
FR (1) FR2910937B1 (pt)
RU (1) RU2472959C2 (pt)
WO (1) WO2008102079A2 (pt)

Families Citing this family (24)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US9701415B2 (en) 2007-08-23 2017-07-11 United Technologies Corporation Gas turbine engine with axial movable fan variable area nozzle
US10167813B2 (en) 2007-08-23 2019-01-01 United Technologies Corporation Gas turbine engine with fan variable area nozzle to reduce fan instability
US9494084B2 (en) 2007-08-23 2016-11-15 United Technologies Corporation Gas turbine engine with fan variable area nozzle for low fan pressure ratio
DE102009011924A1 (de) * 2009-03-10 2010-09-16 Rolls-Royce Deutschland Ltd & Co Kg Nebenstromkanal eines Turbofantriebwerks
US8800261B2 (en) * 2010-07-19 2014-08-12 United Technologies Corporation Gas turbine engine with noise attenuating variable area fan nozzle
FR2978126B1 (fr) * 2011-07-22 2013-09-27 Airbus Operations Sas Nacelle pour ensemble propulsif a tuyere a section variable
WO2013126123A1 (en) * 2011-12-08 2013-08-29 United Technologies Corporation Gas turbine engine with axial movable fan variable area nozzle
WO2013141930A1 (en) 2011-12-30 2013-09-26 United Technologies Corporation Gas turbine engine with low fan pressure ratio
WO2013141934A2 (en) * 2011-12-30 2013-09-26 United Technologies Corporation Gas turbine engine with fan variable area nozzle
US10724431B2 (en) * 2012-01-31 2020-07-28 Raytheon Technologies Corporation Buffer system that communicates buffer supply air to one or more portions of a gas turbine engine
US8794009B2 (en) * 2012-01-31 2014-08-05 United Technologies Corporation Gas turbine engine buffer system
US20130192251A1 (en) * 2012-01-31 2013-08-01 Peter M. Munsell Buffer system that communicates buffer supply air to one or more portions of a gas turbine engine
US9593628B2 (en) 2012-01-31 2017-03-14 United Technologies Corporation Gas turbine engine variable area fan nozzle with ice management
US8869508B2 (en) 2012-01-31 2014-10-28 United Technologies Corporation Gas turbine engine variable area fan nozzle control
US20150252751A1 (en) * 2012-09-27 2015-09-10 United Technologies Corporation Geared gas turbine engine integrated with a variable area fan nozzle with reduced noise
US8979018B2 (en) * 2012-11-28 2015-03-17 The Boeing Company System and method for minimizing wave drag through bilaterally asymmetric design
US20140161603A1 (en) * 2012-12-07 2014-06-12 General Electric Company Exhaust diffuser
WO2014143267A1 (en) * 2013-03-15 2014-09-18 United Technologies Corporation Gas turbine engine with low fan noise
FR3011820B1 (fr) * 2013-10-11 2017-03-31 Aircelle Sa Nacelle pour moteur d'aeronef a tuyere de section variable
US9371799B2 (en) * 2014-04-24 2016-06-21 The Boeing Company Thrust-reverser assemblies that utilize active flow-control and systems and methods including the same
FR3021704B1 (fr) * 2014-05-30 2016-06-03 Aircelle Sa Nacelle pour turboreacteur d'aeronef comprenant une tuyere secondaire a portes rotatives
US9951719B2 (en) * 2015-04-13 2018-04-24 United Technologies Corporation Combined inlet laminar and thrust reverser cascade efflux flow control system
FR3082238A1 (fr) * 2018-06-11 2019-12-13 Airbus Operations Tuyere primaire d'un conduit d'ejection primaire d'une turbomachine
US12286941B2 (en) * 2022-04-26 2025-04-29 General Electric Company Reverse thrust turbofan engine

Family Cites Families (16)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3024602A (en) * 1952-04-22 1962-03-13 Snecma Arrangements for deflecting the jet expelled from a discharge nozzle or from a reaction-propulsion unit
GB1019203A (en) * 1964-06-18 1966-02-02 Rolls Royce Jet nozzle
FR1479705A (fr) * 1966-05-11 1967-05-05 Bristol Siddeley Engines Ltd Perfectionnements aux moteurs comportant une turbine à gaz
GB1357370A (en) * 1971-09-24 1974-06-19 Rolls Royce Ducted fan gas turbine jet propulsion engine with thrust control means
GB1418905A (en) * 1972-05-09 1975-12-24 Rolls Royce Gas turbine engines
GB1506588A (en) * 1975-10-11 1978-04-05 Rolls Royce Gas turbine engine power plants for aircraft
US5090196A (en) * 1989-07-21 1992-02-25 The Boeing Company Ducted fan type gas turbine engine power plants
US5904320A (en) * 1994-07-14 1999-05-18 Northrop Gunman Corporation Blockerless thrust reverser
US5655360A (en) * 1995-05-31 1997-08-12 General Electric Company Thrust reverser with variable nozzle
US6112512A (en) * 1997-08-05 2000-09-05 Lockheed Martin Corporation Method and apparatus of pulsed injection for improved nozzle flow control
RU21220U1 (ru) * 2001-06-01 2001-12-27 Федеральное государственное унитарное предприятие "Завод им. В.Я. Климова" - дочернее предприятие ФГУП "РСК "МиГ" Регулируемое сопло с отклоняемым вектором тяги турбореактивного двигателя
US7093793B2 (en) * 2003-08-29 2006-08-22 The Nordam Group, Inc. Variable cam exhaust nozzle
US7174704B2 (en) * 2004-07-23 2007-02-13 General Electric Company Split shroud exhaust nozzle
FR2883604B1 (fr) * 2005-03-23 2010-03-12 Snecma Moteurs Systeme de deviation d'un flux de gaz dans une tuyere
RU56490U1 (ru) * 2005-11-18 2006-09-10 Государственное образовательное учреждение высшего профессионального образования Московский авиационный институт (государственный технический университет) Регулируемое щелевое сопло
FR2906573B1 (fr) * 2006-09-29 2008-11-21 Airbus France Sas Nacelle de reacteur d'aeronef et aeronef comportant une telle nacelle

Also Published As

Publication number Publication date
CA2674260C (en) 2015-02-10
FR2910937A1 (fr) 2008-07-04
WO2008102079A3 (fr) 2008-11-13
CA2674260A1 (en) 2008-08-28
US8596037B2 (en) 2013-12-03
EP2115290A2 (fr) 2009-11-11
RU2009129524A (ru) 2011-02-10
EP2115290B1 (fr) 2012-09-05
US20090277155A1 (en) 2009-11-12
CN101573524A (zh) 2009-11-04
JP2010514987A (ja) 2010-05-06
WO2008102079A2 (fr) 2008-08-28
JP5031850B2 (ja) 2012-09-26
FR2910937B1 (fr) 2009-04-03
RU2472959C2 (ru) 2013-01-20
CN101573524B (zh) 2012-05-30

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Legal Events

Date Code Title Description
B25A Requested transfer of rights approved

Owner name: AIRBUS OPERATIONS SAS (FR)

B08F Application dismissed because of non-payment of annual fees [chapter 8.6 patent gazette]

Free format text: REFERENTE A 11A ANUIDADE.

B08K Patent lapsed as no evidence of payment of the annual fee has been furnished to inpi [chapter 8.11 patent gazette]

Free format text: EM VIRTUDE DO ARQUIVAMENTO PUBLICADO NA RPI 2495 DE 30-10-2018 E CONSIDERANDO AUSENCIA DE MANIFESTACAO DENTRO DOS PRAZOS LEGAIS, INFORMO QUE CABE SER MANTIDO O ARQUIVAMENTO DO PEDIDO DE PATENTE, CONFORME O DISPOSTO NO ARTIGO 12, DA RESOLUCAO 113/2013.