DE68923602T2 - Rakentendüse mit ringförmiger Zusatzdüse. - Google Patents

Rakentendüse mit ringförmiger Zusatzdüse.

Info

Publication number
DE68923602T2
DE68923602T2 DE68923602T DE68923602T DE68923602T2 DE 68923602 T2 DE68923602 T2 DE 68923602T2 DE 68923602 T DE68923602 T DE 68923602T DE 68923602 T DE68923602 T DE 68923602T DE 68923602 T2 DE68923602 T2 DE 68923602T2
Authority
DE
Germany
Prior art keywords
nozzle
ring
shaped additional
rocket
rocket nozzle
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 - Fee Related
Application number
DE68923602T
Other languages
English (en)
Other versions
DE68923602D1 (de
Inventor
Claude E Bonniot
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
EUROPEENNE DE PROPULSION SURESNES FR Ste
Societe Europeenne de Propulsion SEP 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 EUROPEENNE DE PROPULSION SURESNES FR Ste, Societe Europeenne de Propulsion SEP SA filed Critical EUROPEENNE DE PROPULSION SURESNES FR Ste
Application granted granted Critical
Publication of DE68923602D1 publication Critical patent/DE68923602D1/de
Publication of DE68923602T2 publication Critical patent/DE68923602T2/de
Anticipated expiration legal-status Critical
Expired - Fee Related 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
    • F02K9/00—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
    • F02K9/97—Rocket nozzles
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02K—JET-PROPULSION PLANTS
    • F02K9/00—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
    • F02K9/80—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof characterised by thrust or thrust vector control
    • F02K9/82—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof characterised by thrust or thrust vector control by injection of a secondary fluid into the rocket exhaust gases
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02K—JET-PROPULSION PLANTS
    • F02K9/00—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
    • F02K9/80—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof characterised by thrust or thrust vector control
    • F02K9/88—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof characterised by thrust or thrust vector control using auxiliary rocket nozzles
    • 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
    • F05D2250/00—Geometry
    • F05D2250/30—Arrangement of components
    • F05D2250/32—Arrangement of components according to their shape
    • F05D2250/324—Arrangement of components according to their shape divergent

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Jet Pumps And Other Pumps (AREA)
DE68923602T 1988-11-21 1989-11-21 Rakentendüse mit ringförmiger Zusatzdüse. Expired - Fee Related DE68923602T2 (de)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
FR8815122A FR2639404B1 (fr) 1988-11-21 1988-11-21 Divergent de moteur-fusee a tuyere annulaire complementaire

Publications (2)

Publication Number Publication Date
DE68923602D1 DE68923602D1 (de) 1995-08-31
DE68923602T2 true DE68923602T2 (de) 1996-01-11

Family

ID=9372050

Family Applications (1)

Application Number Title Priority Date Filing Date
DE68923602T Expired - Fee Related DE68923602T2 (de) 1988-11-21 1989-11-21 Rakentendüse mit ringförmiger Zusatzdüse.

Country Status (6)

Country Link
US (1) US5067316A (de)
EP (1) EP0370887B1 (de)
JP (1) JPH0331567A (de)
CA (1) CA2003271A1 (de)
DE (1) DE68923602T2 (de)
FR (1) FR2639404B1 (de)

Families Citing this family (16)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US6293091B1 (en) 1999-04-22 2001-09-25 Trw Inc. Axisymmetrical annular plug propulsion system for integrated rocket/ramjet or rocket/scramjet
FR2816990B1 (fr) 2000-11-22 2003-02-21 Snecma Moteurs Dispositif de reduction ou suppression de decollement de jet dans les tuyeres de moteur-fusee et tuyere comprenant le dispositif
US6568171B2 (en) 2001-07-05 2003-05-27 Aerojet-General Corporation Rocket vehicle thrust augmentation within divergent section of nozzle
US7823376B2 (en) * 2005-09-13 2010-11-02 Aerojet-General Corporation Thrust augmentation in plug nozzles and expansion-deflection nozzles
FR2923269B1 (fr) * 2007-11-06 2011-06-17 Centre Nat Etd Spatiales Tuyere propulsive de detente d'un jet supersonique de gaz
JP4672747B2 (ja) * 2008-03-18 2011-04-20 三菱重工業株式会社 ロケットノズル及びロケットエンジン燃焼ガス流れの制御方法
US8192158B1 (en) * 2008-12-12 2012-06-05 Mainstream Engineering Corp. Apparatus and method to increase total-to-static pressure ratio across a turbine
US8794902B1 (en) 2010-01-26 2014-08-05 II Daniel K. Van Ness System and method to improve the exhaust pressure across a RAM air turbine through secondary flow mixing
US9217392B2 (en) * 2011-12-12 2015-12-22 Curtis E. Graber Vortex cannon with enhanced ring vortex generation
RU2631370C1 (ru) * 2016-05-04 2017-09-21 Акционерное общество "Конструкторское бюро химавтоматики" Жидкостный ракетный двигатель с секторами дефлектора на срезе сопла
US10414521B1 (en) 2018-04-17 2019-09-17 Hardy Engineering & Manufacturing, Inc. Nuclear rocket engine with pebble fuel source
US10414520B1 (en) 2018-04-17 2019-09-17 Hardy Engineering & Manufacturing, Inc. Fuel retention reactor for nuclear rocket engine
US11732677B2 (en) * 2021-02-22 2023-08-22 Raytheon Company Ring-shaped booster rocket
US11852103B2 (en) * 2021-02-22 2023-12-26 Raytheon Company Ring-shaped booster rocket
CN113153581B (zh) * 2021-04-28 2022-11-15 哈尔滨工程大学 一种使用可延展材料包覆充流管道结构的柔性双钟型喷管
CN113944565B (zh) * 2021-10-19 2022-06-28 中国科学院工程热物理研究所 一种用于改善振动特性的尾喷管结构

Family Cites Families (17)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3216653A (en) * 1962-07-09 1965-11-09 Bertin & Cie Ejectors and piping systems operating with a divergent fluid wall
US3013384A (en) * 1955-07-15 1961-12-19 Jr Bonnie Smith Jet atomic system
US3121457A (en) * 1956-12-11 1964-02-18 Lummus Co Burner assembly for synthesis gas generators
FR1182810A (fr) * 1957-09-16 1959-06-30 Snecma Perfectionnements aux tuyères d'éjection à section réglable
US3267664A (en) * 1963-03-19 1966-08-23 North American Aviation Inc Method of and device for cooling
US3520139A (en) * 1964-06-11 1970-07-14 Curtiss Wright Corp Nozzle coolant supply system
GB1233061A (de) * 1968-07-15 1971-05-26
US4004416A (en) * 1970-03-16 1977-01-25 United Technologies Corporation Infra-red suppressor for use with turbo-shaft engine
US3815356A (en) * 1971-03-10 1974-06-11 Trw Inc Foam cooling and acoustic damping of exhaust gases produced by an internal combustion engine
US3925982A (en) * 1973-09-11 1975-12-16 Martin Marietta Corp Fluid-dynamic shock ring for controlled flow separation in a rocket engine exhaust nozzle
DE2356572C3 (de) * 1973-11-13 1979-03-29 Messerschmitt-Boelkow-Blohm Gmbh, 8000 Muenchen Flüssigkeitsgekühlte Raketenbrennkammer mit Schubdüse
US4242865A (en) * 1978-01-25 1981-01-06 Curtiss-Wright Corporation Turbojet afterburner engine with two-position exhaust nozzle
JPS58501940A (ja) * 1981-11-18 1983-11-17 モス，ハンス 消音型ガス噴出用噴射ノズル
US4489889A (en) * 1982-11-08 1984-12-25 Thiokol Corporation Extendible nozzle exit cone
DE3427169A1 (de) * 1984-07-24 1986-01-30 Messerschmitt-Bölkow-Blohm GmbH, 8012 Ottobrunn Raketentriebwerk fuer raumfluege
DE3710984A1 (de) * 1987-04-01 1988-10-13 Messerschmitt Boelkow Blohm Vakuumduesen-auslassring
FR2618488B1 (fr) * 1987-07-20 1989-12-15 Europ Propulsion Divergent a rupture de galbe pour tuyere de moteur-fusee

Also Published As

Publication number Publication date
CA2003271A1 (fr) 1990-05-21
FR2639404B1 (fr) 1994-04-15
US5067316A (en) 1991-11-26
DE68923602D1 (de) 1995-08-31
EP0370887B1 (de) 1995-07-26
EP0370887A1 (de) 1990-05-30
FR2639404A1 (fr) 1990-05-25
JPH0331567A (ja) 1991-02-12

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Legal Events

Date Code Title Description
8364 No opposition during term of opposition
8327 Change in the person/name/address of the patent owner

Owner name: SOCIETE NATIONALE D'ETUDE ET DE CONSTRUCTION DE MO

8339 Ceased/non-payment of the annual fee