ES2155970T3 - Estatorreactor de geometria evolutiva para aeronave. - Google Patents

Estatorreactor de geometria evolutiva para aeronave.

Info

Publication number
ES2155970T3
ES2155970T3 ES97400336T ES97400336T ES2155970T3 ES 2155970 T3 ES2155970 T3 ES 2155970T3 ES 97400336 T ES97400336 T ES 97400336T ES 97400336 T ES97400336 T ES 97400336T ES 2155970 T3 ES2155970 T3 ES 2155970T3
Authority
ES
Spain
Prior art keywords
statorreactor
combustion chamber
aircraft
geometry
allows
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 - Lifetime
Application number
ES97400336T
Other languages
English (en)
Inventor
Alain Chevalier
Marc Bouchez
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.)
Aerospatiale Matra
Original Assignee
Aerospatiale Matra
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 Aerospatiale Matra filed Critical Aerospatiale Matra
Application granted granted Critical
Publication of ES2155970T3 publication Critical patent/ES2155970T3/es
Anticipated expiration legal-status Critical
Expired - Lifetime 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
    • F02K7/00—Plants in which the working fluid is used in a jet only, i.e. the plants not having a turbine or other engine driving a compressor or a ducted fan; Control thereof
    • F02K7/10—Plants in which the working fluid is used in a jet only, i.e. the plants not having a turbine or other engine driving a compressor or a ducted fan; Control thereof characterised by having ram-action compression, i.e. aero-thermo-dynamic-ducts or ram-jet engines
    • 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)
  • Nozzles (AREA)
  • Combustion Methods Of Internal-Combustion Engines (AREA)
  • Fuel-Injection Apparatus (AREA)
  • Electrical Control Of Air Or Fuel Supplied To Internal-Combustion Engine (AREA)
  • Fluidized-Bed Combustion And Resonant Combustion (AREA)
  • Pressure-Spray And Ultrasonic-Wave- Spray Burners (AREA)
  • Toys (AREA)

Abstract

LA INVENCION SE REFIERE A UN ESTATORREACTOR PARA AERONAVE CON VUELO SUPERSONICO Y/O HIPERSONICO, DESTINADO A FUNCIONAR SOBRE UNA GRAN BANDA DE VELOCIDADES, QUE LLEVA, UNA ENTRADA (4) DE COMBURANTE, UN DISPOSITIVO DE INYECCION (5) DE COMBUSTIBLE; Y UN CUERPO (3) DE ESTATORREACTOR QUE, POR UNA PARTE, COMPRENDE UNA CAMARA DE COMBUSTION (6) Y UNA TOBERA DE ESCAPE (7) Y QUE, POR OTRA PARTE, PRESENTA, AL MENOS EN UNA ZONA DE TRANSICION (9) ENTRE LA CAMARA DE COMBUSTION Y LA TOBERA DE ESCAPE, UNA GEOMETRIA EVOLUTIVA QUE PERMITE MODIFICAR PROGRESIVAMENTE SU SECCION LONGITUDINAL. SEGUN LA INVENCION, DICHO CUERPO (3) DEL ESTATORREACTOR LLEVA AL MENOS UNA ABERTURA CONTROLABLE (11) SUSCEPTIBLE DE ESTABLECER CON EL EXTERIOR UNA COMUNICACION CON DICHA CAMARA DE COMBUSTION, Y QUE PERMITE INTRODUCIR UNA CORRIENTE DE AIRE EXTERIOR EN DICHA ZONA DE TRANSICION 89).
ES97400336T 1996-03-01 1997-02-14 Estatorreactor de geometria evolutiva para aeronave. Expired - Lifetime ES2155970T3 (es)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
FR9602603A FR2745606B1 (fr) 1996-03-01 1996-03-01 Statoreacteur a geometrie evolutive pour aeronef

Publications (1)

Publication Number Publication Date
ES2155970T3 true ES2155970T3 (es) 2001-06-01

Family

ID=9489759

Family Applications (1)

Application Number Title Priority Date Filing Date
ES97400336T Expired - Lifetime ES2155970T3 (es) 1996-03-01 1997-02-14 Estatorreactor de geometria evolutiva para aeronave.

Country Status (8)

Country Link
US (1) US5894722A (es)
EP (1) EP0793011B1 (es)
JP (1) JP3930599B2 (es)
CA (1) CA2198419C (es)
DE (1) DE69704585T2 (es)
ES (1) ES2155970T3 (es)
FR (1) FR2745606B1 (es)
RU (1) RU2125172C1 (es)

Families Citing this family (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2813344B1 (fr) * 2000-08-28 2002-11-29 Aerospatiale Matra Missiles Systeme d'obturation pour un orifice d'un conduit, en particulier pour un orifice d'une voie d'introduction d'air dans la chambre de combustion d'un statoreacteur
US7216474B2 (en) * 2004-02-19 2007-05-15 Aerojet-General Corporation Integrated air inlet system for multi-propulsion aircraft engines
RU2315878C1 (ru) * 2006-04-25 2008-01-27 Иркутское высшее военное авиационное инженерное училище (военный институт) Сверхзвуковое входное устройство
US20140331682A1 (en) 2012-11-08 2014-11-13 Mark Bovankovich High-speed-launch ramjet booster
US9656760B2 (en) * 2013-11-07 2017-05-23 Sikorsky Aircraft Corporation Variable geometry helicopter engine inlet
CN104863715B (zh) * 2015-04-16 2016-08-17 南京航空航天大学 一种矩形进口二元高超声速变几何进气道、其设计方法以及工作方法
JP6628246B2 (ja) * 2016-03-28 2020-01-08 三菱重工業株式会社 スクラムジェットエンジン、飛しょう体
CN112627990B (zh) * 2020-12-23 2021-11-19 华中科技大学 一种直接驱动组合发动机流道调节结构及其控制方法
US11434018B1 (en) * 2021-11-27 2022-09-06 Airbus Defence and Space GmbH Switchable air inlet device for engine air

Family Cites Families (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR1110011A (fr) * 1954-08-20 1956-02-06 Perfectionnements apportés aux stato-réacteurs pour aérodynes, notamment à ceux pour vol à vitesse supersonique
US3143852A (en) * 1961-09-08 1964-08-11 John M Alderson Ram jet engine
US3279194A (en) * 1962-08-14 1966-10-18 Garrett Corp Aerothermodynamic duct and control means therefor
FR1496091A (fr) * 1966-04-20 1967-09-29 Snecma Tuyère d'éjection pour propulseurs à plusieurs flux moteurs, notamment à deux flux moteurs
US3514956A (en) * 1968-03-11 1970-06-02 William R Bray Injector-ram jet engine
RU1093062C (ru) * 1982-12-30 1994-08-30 ЦАГИ им.профессора Н.Е.Жуковского Эжекторный увеличитель тяги турбореактивного двигателя
GB2222635B (en) * 1987-10-24 1992-05-27 British Aerospace Propulsion units for aerospace vehicles
RU2028488C1 (ru) * 1988-06-30 1995-02-09 Блинчевский Мнахем Яковлевич Прямоточный двигатель
US5054288A (en) * 1988-10-24 1991-10-08 The Boeing Company Bypass duct for a hypersonic propulsion system

Also Published As

Publication number Publication date
EP0793011B1 (fr) 2001-04-18
US5894722A (en) 1999-04-20
FR2745606A1 (fr) 1997-09-05
CA2198419C (fr) 2005-02-22
EP0793011A1 (fr) 1997-09-03
JPH09324701A (ja) 1997-12-16
JP3930599B2 (ja) 2007-06-13
RU2125172C1 (ru) 1999-01-20
CA2198419A1 (fr) 1997-09-01
FR2745606B1 (fr) 1998-04-30
DE69704585T2 (de) 2001-08-30
DE69704585D1 (de) 2001-05-23

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