FR1419313A - Tuyère d'éjection de réacteur à section de surface variable - Google Patents

Tuyère d'éjection de réacteur à section de surface variable

Info

Publication number
FR1419313A
FR1419313A FR421A FR421A FR1419313A FR 1419313 A FR1419313 A FR 1419313A FR 421 A FR421 A FR 421A FR 421 A FR421 A FR 421A FR 1419313 A FR1419313 A FR 1419313A
Authority
FR
France
Prior art keywords
ejection nozzle
variable area
area reactor
reactor ejection
variable
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.)
Expired
Application number
FR421A
Other languages
English (en)
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.)
General Electric Co
Original Assignee
General Electric Co
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 General Electric Co filed Critical General Electric Co
Application granted granted Critical
Publication of FR1419313A publication Critical patent/FR1419313A/fr
Expired legal-status Critical Current

Links

Classifications

    • 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
    • F02K3/068—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 being characterised by a short axial length relative to the diameter
    • 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
    • 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
    • F02K1/10—Varying effective area of jet pipe or nozzle by distorting the 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
    • F02K1/645—Reversing fan flow using inflatable diaphragms

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)
  • Control Of Turbines (AREA)
FR421A 1963-12-30 1964-12-30 Tuyère d'éjection de réacteur à section de surface variable Expired FR1419313A (fr)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US334137A US3279192A (en) 1963-12-30 1963-12-30 Variable area exhaust nozzle

Publications (1)

Publication Number Publication Date
FR1419313A true FR1419313A (fr) 1965-11-26

Family

ID=23305755

Family Applications (1)

Application Number Title Priority Date Filing Date
FR421A Expired FR1419313A (fr) 1963-12-30 1964-12-30 Tuyère d'éjection de réacteur à section de surface variable

Country Status (3)

Country Link
US (1) US3279192A (fr)
FR (1) FR1419313A (fr)
GB (1) GB1083738A (fr)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2523650A1 (fr) * 1982-03-17 1983-09-23 Centre Nat Etd Spatiales Dispositif deployable de prolongement de tuyere de moteur fusee
CN115559827A (zh) * 2022-10-25 2023-01-03 北京动力机械研究所 一种双模喷管

Families Citing this family (33)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3482783A (en) * 1966-08-12 1969-12-09 Goodyear Aerospace Corp Expandable nozzle
US3442082A (en) * 1966-12-19 1969-05-06 Adolphe C Peterson Turbine gas generator and work propulsion system for aircraft and other vehicles
US3596465A (en) * 1970-03-12 1971-08-03 Nasa Inflatable transpiration cooled nozzle
US3637140A (en) * 1970-09-03 1972-01-25 Goodyear Aerospace Corp Pneumatically actuated variable area inlet or exhaust nozzle
US3756026A (en) * 1971-04-23 1973-09-04 Rohr Corp Propulsion flow modulating system
US3812672A (en) * 1972-02-10 1974-05-28 Cci Aerospace Corp Supercharged ejector ramjet aircraft engine
GB1418665A (en) * 1972-04-27 1975-12-24 Rolls Royce Fluid flow ducts
US3967443A (en) * 1972-04-27 1976-07-06 Rolls-Royce (1971) Limited Turbofan engine with flexible, variable area nozzle
GB2292125B (en) * 1981-10-13 1996-07-10 Rolls Royce Nozzle capable of varying the direction of discharge of fluid therefrom
AU2443884A (en) * 1983-02-15 1984-08-23 Commonwealth Of Australia, The Thrust augmentor
FR2565293B1 (fr) * 1984-06-04 1986-10-17 Aerospatiale Ensemble dilueur-deviateur de jet pour turbomoteur d'aerodyne
FR2628790A1 (fr) * 1988-03-16 1989-09-22 Snecma Propulseur combine turbofusee aerobie
US5060550A (en) * 1991-02-19 1991-10-29 The United States Of America As Represented By The Secretary Of The Navy Rocket nozzle snubber
US5664415A (en) * 1994-06-01 1997-09-09 Lockheed Fort Worth Company After-burning turbo-fan engine with a fixed geometry exhaust nozzle having a variable flow coefficient
US6647707B2 (en) * 2000-09-05 2003-11-18 Sudarshan Paul Dev Nested core gas turbine engine
US6981365B1 (en) * 2001-12-28 2006-01-03 Sierra Engineering Incorporated Supersonic revolving nozzle
US6899513B2 (en) * 2003-07-07 2005-05-31 Pratt & Whitney Canada Corp. Inflatable compressor bleed valve system
WO2006060006A1 (fr) * 2004-12-01 2006-06-08 United Technologies Corporation Cone arriere non metallique de moteur a turbine de bout
EP2074302A1 (fr) 2006-10-12 2009-07-01 United Technologies Corporation Capot central ondulé pour moteur à turbine à gaz
WO2008045057A1 (fr) * 2006-10-12 2008-04-17 United Technologies Corporation Tuyère à surface de dérivation variable, du type à vessie
US9010126B2 (en) * 2008-02-20 2015-04-21 United Technologies Corporation Gas turbine engine with variable area fan nozzle bladder system
US20110147533A1 (en) * 2009-12-21 2011-06-23 Honeywell International Inc. Morphing ducted fan for vertical take-off and landing vehicle
DE102011106959A1 (de) * 2011-07-08 2013-01-10 Rolls-Royce Deutschland Ltd & Co Kg Fluggasturbine mit variabler Nebenstromdüse
US9416752B2 (en) * 2012-02-28 2016-08-16 Pratt & Whitney Canada Corp. Gas turbine exhaust having reduced jet noise
US9989009B2 (en) 2012-10-31 2018-06-05 The Boeing Company Methods and apparatus for sealing variable area fan nozzles of jet engines
US9352843B2 (en) * 2012-12-31 2016-05-31 United Technologies Corporation Gas turbine engine having fan rotor driven by turbine exhaust and with a bypass
EP2829690A1 (fr) * 2013-07-23 2015-01-28 Alstom Technology Ltd Ensemble de maintenance pouvant s'adapter à l'intérieur d'un moteur à turbine à gaz
WO2015088606A2 (fr) * 2013-12-13 2015-06-18 United Technologies Corporation Architecture pour un système de propulsion axialement compact et à performances élevées
US9297333B2 (en) 2014-08-26 2016-03-29 The Boeing Company Variable geometry inlet for a ducted fan and method of assembling same
JP2018508692A (ja) * 2015-02-11 2018-03-29 エムアールエイ・システムズ・エルエルシー 可変面積ノズルを有するタービンエンジン
DE102015206095A1 (de) * 2015-04-02 2016-10-06 Rolls-Royce Deutschland Ltd & Co Kg Fluggasturbine mit variabler Nebenstromdüse
RU2644721C2 (ru) * 2016-06-23 2018-02-13 Федеральное государственное унитарное предприятие "Центральный институт авиационного моторостроения имени П.И. Баранова" Авиационная силовая установка
US12018615B2 (en) * 2022-10-31 2024-06-25 Pratt & Whitney Canada Corp. Systems and methods for controlling an air flow rate for a propulsion system air intake

Family Cites Families (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2737019A (en) * 1953-08-14 1956-03-06 Louis S Billman Variable area convergent-divergent diffuser
US3060679A (en) * 1958-10-24 1962-10-30 Gen Electric Powerplant

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2523650A1 (fr) * 1982-03-17 1983-09-23 Centre Nat Etd Spatiales Dispositif deployable de prolongement de tuyere de moteur fusee
EP0091841A1 (fr) * 1982-03-17 1983-10-19 Centre National D'etudes Spatiales Dispositif déployable de prolongement de tuyère de moteur fusée
US4480437A (en) * 1982-03-17 1984-11-06 Centre National D'etudes Spatiales Unfoldable device for extending the nozzle of a rocket engine
CN115559827A (zh) * 2022-10-25 2023-01-03 北京动力机械研究所 一种双模喷管

Also Published As

Publication number Publication date
US3279192A (en) 1966-10-18
GB1083738A (en) 1967-09-20

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