FR2971015B1 - Tuyere d'ejection pour turboreacteur d'avion a double flux separes a capot secondaire deployable et corps central retractable - Google Patents

Tuyere d'ejection pour turboreacteur d'avion a double flux separes a capot secondaire deployable et corps central retractable

Info

Publication number
FR2971015B1
FR2971015B1 FR1150769A FR1150769A FR2971015B1 FR 2971015 B1 FR2971015 B1 FR 2971015B1 FR 1150769 A FR1150769 A FR 1150769A FR 1150769 A FR1150769 A FR 1150769A FR 2971015 B1 FR2971015 B1 FR 2971015B1
Authority
FR
France
Prior art keywords
turboreactor
central body
ejection tube
secondary cover
separate flows
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
FR1150769A
Other languages
English (en)
Other versions
FR2971015A1 (fr
Inventor
Sebastien Jean Paul Aeberli
Guillaume Bodard
Alexandre Alfred Gaston Vuillemin
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 Aircraft Engines SAS
Original Assignee
SNECMA SAS
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 SNECMA SAS filed Critical SNECMA SAS
Priority to FR1150769A priority Critical patent/FR2971015B1/fr
Priority to US13/362,826 priority patent/US20120192543A1/en
Publication of FR2971015A1 publication Critical patent/FR2971015A1/fr
Application granted granted Critical
Publication of FR2971015B1 publication Critical patent/FR2971015B1/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
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
    • F02C7/24—Heat or noise insulation
    • 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
    • F02K1/09—Varying effective area of jet pipe or nozzle by axially moving an external member, e.g. a shroud
    • 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
    • F05D2260/96—Preventing, counteracting or reducing vibration or noise
    • 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)
  • Structures Of Non-Positive Displacement Pumps (AREA)
FR1150769A 2011-02-01 2011-02-01 Tuyere d'ejection pour turboreacteur d'avion a double flux separes a capot secondaire deployable et corps central retractable Active FR2971015B1 (fr)

Priority Applications (2)

Application Number Priority Date Filing Date Title
FR1150769A FR2971015B1 (fr) 2011-02-01 2011-02-01 Tuyere d'ejection pour turboreacteur d'avion a double flux separes a capot secondaire deployable et corps central retractable
US13/362,826 US20120192543A1 (en) 2011-02-01 2012-01-31 Exhaust nozzle for a bypass airplane turbojet having a deployable secondary cover and a retractable central body

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
FR1150769A FR2971015B1 (fr) 2011-02-01 2011-02-01 Tuyere d'ejection pour turboreacteur d'avion a double flux separes a capot secondaire deployable et corps central retractable

Publications (2)

Publication Number Publication Date
FR2971015A1 FR2971015A1 (fr) 2012-08-03
FR2971015B1 true FR2971015B1 (fr) 2015-02-27

Family

ID=44548899

Family Applications (1)

Application Number Title Priority Date Filing Date
FR1150769A Active FR2971015B1 (fr) 2011-02-01 2011-02-01 Tuyere d'ejection pour turboreacteur d'avion a double flux separes a capot secondaire deployable et corps central retractable

Country Status (2)

Country Link
US (1) US20120192543A1 (fr)
FR (1) FR2971015B1 (fr)

Families Citing this family (11)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20140161603A1 (en) * 2012-12-07 2014-06-12 General Electric Company Exhaust diffuser
EP2959148B1 (fr) 2013-02-20 2019-05-22 Rolls-Royce North American Technologies, Inc. Turbine à gaz dotée d'un passage de dérivation configurable
US20160123178A1 (en) 2013-05-31 2016-05-05 General Electric Company Dual-mode plug nozzle
GB201609071D0 (en) * 2016-05-24 2016-07-06 Rolls Royce Plc Aircraft gas turbine engine nacelle
GB201811780D0 (en) 2018-07-19 2018-09-05 Rolls Royce Plc Exhaust nozzle assembly
US11313320B2 (en) 2020-02-27 2022-04-26 Rolls-Royce North American Technologies Inc. Exhaust nozzle with centerbody support structure for a gas turbine engine
US11274630B2 (en) 2020-02-27 2022-03-15 Rolls-Royce North American Technologies Inc. Exhaust nozzle with vane support structure for a gas turbine engine
US11408368B2 (en) 2020-03-31 2022-08-09 Rolls-Royce North American Technologies Inc. Reconfigurable exhaust nozzle for a gas turbine engine
US11286878B2 (en) 2020-03-31 2022-03-29 Rolls-Royce North American Technologies Inc. Variable area nozzle exhaust system with integrated thrust reverser
US11834189B2 (en) * 2020-04-09 2023-12-05 Gulfstream Aerospace Corporation Exhaust nozzle assembly, propulsion system employing the exhaust nozzle assembly, and aircraft employing the propulsion system
WO2022255956A1 (fr) * 2021-06-02 2022-12-08 Cogan Yasin Système de propulsion d'air de moteur à réaction

Family Cites Families (14)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3655009A (en) * 1969-09-18 1972-04-11 Rohr Corp Method and apparatus for suppressing the noise of a fan-jet engine
US3841091A (en) * 1973-05-21 1974-10-15 Gen Electric Multi-mission tandem propulsion system
US4819425A (en) * 1982-03-18 1989-04-11 The Boeing Company Primary-secondary ventilated flow mixer nozzle for high bypass turbo fan jet propulsion system
US4537026A (en) * 1982-04-07 1985-08-27 Rolls-Royce Inc. Variable area nozzles for turbomachines
US4527388A (en) * 1982-07-12 1985-07-09 The Garrett Corporation Jet propulsion apparatus and methods
DE4012212A1 (de) * 1990-04-14 1991-10-24 Mtu Muenchen Gmbh Duese fuer ein hyperschalltriebwerk
DE4222947C2 (de) * 1992-07-11 1995-02-02 Deutsche Aerospace Strahltriebwerk
US5722233A (en) * 1993-06-23 1998-03-03 The Nordam Group, Inc. Turbofan engine exhaust mixing area modification for improved engine efficiency and noise reduction
WO1996012881A1 (fr) * 1994-10-20 1996-05-02 United Technologies Corporation Buse d'evacuation d'air de ventilation, a section de superficie variable
US5826794A (en) * 1997-02-28 1998-10-27 The Boeing Company Aircraft scoop ejector nozzle
GB0205701D0 (en) * 2002-03-12 2002-04-24 Rolls Royce Plc Variable area nozzle
US20070214795A1 (en) * 2006-03-15 2007-09-20 Paul Cooker Continuous real time EGT margin control
FR2904372B1 (fr) * 2006-07-26 2008-10-31 Snecma Sa Tuyere d'ejection des gaz pour turbomachine a double flux ayant une section d'ejection ou de col variable par deplacement du capot secondaire
FR2914020B1 (fr) * 2007-03-23 2009-04-24 Airbus France Sas Procede pour reduire les emissions sonores a l'arriere d'un turbomoteur et turbomoteur perfectionne par le procede

Also Published As

Publication number Publication date
FR2971015A1 (fr) 2012-08-03
US20120192543A1 (en) 2012-08-02

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