DE2356572C3 - Flüssigkeitsgekühlte Raketenbrennkammer mit Schubdüse - Google Patents

Flüssigkeitsgekühlte Raketenbrennkammer mit Schubdüse

Info

Publication number
DE2356572C3
DE2356572C3 DE2356572A DE2356572A DE2356572C3 DE 2356572 C3 DE2356572 C3 DE 2356572C3 DE 2356572 A DE2356572 A DE 2356572A DE 2356572 A DE2356572 A DE 2356572A DE 2356572 C3 DE2356572 C3 DE 2356572C3
Authority
DE
Germany
Prior art keywords
thrust nozzle
combustion chamber
cooling circuit
thrust
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
Application number
DE2356572A
Other languages
German (de)
English (en)
Other versions
DE2356572B2 (de
DE2356572A1 (de
Inventor
Helmut Dipl.-Ing. Dederra
Guenther Dr.-Ing. Schmidt
Juergen Dipl.-Ing. Stanke
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.)
Airbus Defence and Space GmbH
Original Assignee
Messerschmitt Bolkow Blohm AG
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 Messerschmitt Bolkow Blohm AG filed Critical Messerschmitt Bolkow Blohm AG
Priority to DE2356572A priority Critical patent/DE2356572C3/de
Priority to IN2450/CAL/74A priority patent/IN142651B/en
Priority to US05/522,990 priority patent/US4055044A/en
Priority to FR7437281A priority patent/FR2250899B1/fr
Priority to JP49129644A priority patent/JPS5823496B2/ja
Publication of DE2356572A1 publication Critical patent/DE2356572A1/de
Publication of DE2356572B2 publication Critical patent/DE2356572B2/de
Application granted granted Critical
Publication of DE2356572C3 publication Critical patent/DE2356572C3/de
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
    • F02K9/00—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
    • F02K9/42—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof using liquid or gaseous propellants
    • F02K9/60—Constructional parts; Details not otherwise provided for
    • F02K9/62—Combustion or thrust chambers
    • F02K9/64—Combustion or thrust chambers having cooling arrangements
    • 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
    • F02K9/972—Fluid cooling arrangements for nozzles

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Testing Of Engines (AREA)
DE2356572A 1973-11-13 1973-11-13 Flüssigkeitsgekühlte Raketenbrennkammer mit Schubdüse Expired DE2356572C3 (de)

Priority Applications (5)

Application Number Priority Date Filing Date Title
DE2356572A DE2356572C3 (de) 1973-11-13 1973-11-13 Flüssigkeitsgekühlte Raketenbrennkammer mit Schubdüse
IN2450/CAL/74A IN142651B (enExample) 1973-11-13 1974-11-07
US05/522,990 US4055044A (en) 1973-11-13 1974-11-11 Rocket engine construction and connection for closed and opened fluid cooling circuits for the walls thereof
FR7437281A FR2250899B1 (enExample) 1973-11-13 1974-11-12
JP49129644A JPS5823496B2 (ja) 1973-11-13 1974-11-12 スイシンノズル オユウスル エキレイシキロケツトネンシヨウシツ

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
DE2356572A DE2356572C3 (de) 1973-11-13 1973-11-13 Flüssigkeitsgekühlte Raketenbrennkammer mit Schubdüse

Publications (3)

Publication Number Publication Date
DE2356572A1 DE2356572A1 (de) 1975-05-15
DE2356572B2 DE2356572B2 (de) 1978-08-10
DE2356572C3 true DE2356572C3 (de) 1979-03-29

Family

ID=5897956

Family Applications (1)

Application Number Title Priority Date Filing Date
DE2356572A Expired DE2356572C3 (de) 1973-11-13 1973-11-13 Flüssigkeitsgekühlte Raketenbrennkammer mit Schubdüse

Country Status (5)

Country Link
US (1) US4055044A (enExample)
JP (1) JPS5823496B2 (enExample)
DE (1) DE2356572C3 (enExample)
FR (1) FR2250899B1 (enExample)
IN (1) IN142651B (enExample)

Families Citing this family (29)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE2519538C2 (de) * 1975-05-02 1982-12-30 Messerschmitt-Bölkow-Blohm GmbH, 8000 München Verbindung zwischen dem Kühlmittel-Zulaufring und der Brennkammer-oder Schubdüsenwand eines Raketentriebwerks
DE2743983C2 (de) * 1977-09-30 1982-11-11 Messerschmitt-Bölkow-Blohm GmbH, 8000 München Flüssigkeitsraketentriebwerk in Nebenstrombauart für den Betrieb im luftleeren Raum
DE2949522C2 (de) * 1979-12-08 1982-01-28 Messerschmitt-Bölkow-Blohm GmbH, 8000 München Gekühlte Schubdüse für ein Raketentriebwerk
DE3535779C1 (en) * 1985-10-07 1987-04-09 Messerschmitt Boelkow Blohm Arrangement for the cooling of rocket engine walls
DE3618038A1 (de) * 1986-05-28 1987-12-03 Messerschmitt Boelkow Blohm Stuetzstruktur fuer fluessigkeitsgekuehlte expansionsduesen
DE3710984A1 (de) * 1987-04-01 1988-10-13 Messerschmitt Boelkow Blohm Vakuumduesen-auslassring
FR2639404B1 (fr) * 1988-11-21 1994-04-15 Propulsion Ste Europeenne Divergent de moteur-fusee a tuyere annulaire complementaire
US5269132A (en) * 1992-10-29 1993-12-14 E-Systems, Inc. Method and apparatus for controlling infrared emissions
DE4315256A1 (de) * 1993-05-07 1994-11-10 Mtu Muenchen Gmbh Einrichtung zur Verteilung sowie Zu- und Abführung eines Kühlmittels an einer Wand eines Turbo-, insbesondere Turbo-Staustrahltriebwerks
DE19505357C1 (de) * 1995-02-17 1996-05-23 Daimler Benz Aerospace Ag Verfahren zur Kühlung von Triebwerkswänden und Wandstruktur zur Durchführung desselben
WO1997014875A1 (en) * 1995-10-17 1997-04-24 Westinghouse Electric Corporation Gas turbine regenerative cooled combustor
JP3310900B2 (ja) * 1997-04-15 2002-08-05 三菱重工業株式会社 燃焼器尾筒の冷却構造
DE10141108B4 (de) * 2001-08-22 2005-06-30 Eads Space Transportation Gmbh Raketentriebwerk mit geschlossenen Triebwerkskreislauf mit modularer Zuführung der Turbinenabgase
WO2003052255A1 (en) * 2001-12-18 2003-06-26 Volvo Aero Corporation A component for being subjected to high thermal load during operation and a method for manufacturing such a component
US6802179B2 (en) * 2002-12-02 2004-10-12 Aerojet-General Corporation Nozzle with spiral internal cooling channels
US7343732B2 (en) * 2003-03-04 2008-03-18 Aerojet-General Corporation Rocket engine chamber with layered internal wall channels
US20060032212A1 (en) * 2004-08-10 2006-02-16 The Boeing Company Lightweight rocket engine combustion chamber and associated method
US7997510B2 (en) * 2006-07-24 2011-08-16 Thomas Clayton Pavia Systems, methods and apparatus for propulsion
US7793506B2 (en) * 2006-08-11 2010-09-14 Wyle Laboratories, Inc. Emission controlled engine exhaust static test stand
US20100229565A1 (en) * 2006-12-19 2010-09-16 Arne Boman Wall of a rocket engine
US20120060464A1 (en) * 2007-07-24 2012-03-15 James Robert Grote Systems, methods and apparatus for propulsion
FR2923269B1 (fr) * 2007-11-06 2011-06-17 Centre Nat Etd Spatiales Tuyere propulsive de detente d'un jet supersonique de gaz
KR100959793B1 (ko) 2007-12-31 2010-05-28 한국항공우주연구원 액체로켓엔진용 양방향 재생냉각 연소실 및 이의 모사시험장치
US20090288390A1 (en) * 2008-05-23 2009-11-26 Thomas Clayton Pavia Simplified thrust chamber recirculating cooling system
CN104948347B (zh) * 2014-03-31 2017-02-15 北京航天动力研究所 一种具有均流功能的推力室集合器
DE102020124530A1 (de) * 2020-09-21 2022-03-24 Arianegroup Gmbh Brennkammerabschnitt mit integriertem Leitblech und Verfahren zum Herstellen eines Brennkammerabschnitts
CN113266492B (zh) * 2021-04-16 2022-03-15 北京星际荣耀空间科技股份有限公司 发动机推力室、火箭发动机、液体火箭
CN113530718A (zh) * 2021-08-31 2021-10-22 西安航天动力研究所 一种火箭发动机推力室热试用身部模块
CN114483381B (zh) * 2021-12-21 2023-08-11 西北工业大学 一种使用组合动密封的变结构发动机喷管

Family Cites Families (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2935841A (en) * 1956-06-18 1960-05-10 Bell Aircraft Corp Thrust chamber with integrated cooling and structural members
US3048966A (en) * 1958-12-15 1962-08-14 Snecma Rocket propulsion method
US3267664A (en) * 1963-03-19 1966-08-23 North American Aviation Inc Method of and device for cooling
FR1391927A (fr) * 1964-01-29 1965-03-12 Monsieur Le Ministre Des Armee Chambre de combustion avec tuyère pour moteurs fusées à liquides
GB1089055A (en) * 1965-07-20 1967-11-01 Bristol Siddeley Engines Ltd Combined combustion chamber and propulsive unit for a rocket engine
GB1220223A (en) * 1967-01-16 1971-01-20 Messerschmitt Boelkow Blohm A liquid cooled rocket combustion chamber with thrust nozzle
US3605412A (en) * 1968-07-09 1971-09-20 Bolkow Gmbh Fluid cooled thrust nozzle for a rocket
US3597923A (en) * 1969-10-02 1971-08-10 Michael Simon Rocket propulsion system

Also Published As

Publication number Publication date
DE2356572B2 (de) 1978-08-10
IN142651B (enExample) 1977-08-06
JPS5823496B2 (ja) 1983-05-16
FR2250899A1 (enExample) 1975-06-06
US4055044A (en) 1977-10-25
FR2250899B1 (enExample) 1980-12-26
JPS5079614A (enExample) 1975-06-28
DE2356572A1 (de) 1975-05-15

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Legal Events

Date Code Title Description
C3 Grant after two publication steps (3rd publication)
8320 Willingness to grant licences declared (paragraph 23)