FR2309729B1 - - Google Patents

Info

Publication number
FR2309729B1
FR2309729B1 FR7611709A FR7611709A FR2309729B1 FR 2309729 B1 FR2309729 B1 FR 2309729B1 FR 7611709 A FR7611709 A FR 7611709A FR 7611709 A FR7611709 A FR 7611709A FR 2309729 B1 FR2309729 B1 FR 2309729B1
Authority
FR
France
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
FR7611709A
Other languages
French (fr)
Other versions
FR2309729A1 (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.)
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
Publication of FR2309729A1 publication Critical patent/FR2309729A1/en
Application granted granted Critical
Publication of FR2309729B1 publication Critical patent/FR2309729B1/fr
Granted 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

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Gasket Seals (AREA)
  • Connection Of Plates (AREA)
FR7611709A 1975-05-02 1976-04-21 Cooling medium collection ring for rocket propulsion - having connecting flange with one sided dove tail joint to prevent displacement Granted FR2309729A1 (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
DE19752519538 DE2519538C2 (en) 1975-05-02 1975-05-02 Connection between the coolant inlet ring and the combustion chamber or thrust nozzle wall of a rocket engine

Publications (2)

Publication Number Publication Date
FR2309729A1 FR2309729A1 (en) 1976-11-26
FR2309729B1 true FR2309729B1 (en) 1980-04-18

Family

ID=5945560

Family Applications (1)

Application Number Title Priority Date Filing Date
FR7611709A Granted FR2309729A1 (en) 1975-05-02 1976-04-21 Cooling medium collection ring for rocket propulsion - having connecting flange with one sided dove tail joint to prevent displacement

Country Status (3)

Country Link
JP (1) JPS51133613A (en)
DE (1) DE2519538C2 (en)
FR (1) FR2309729A1 (en)

Families Citing this family (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE10237381B4 (en) 2002-08-12 2005-06-23 Eads Space Transportation Gmbh Combustion structure and method for its production
RU2465483C1 (en) * 2011-03-31 2012-10-27 Федеральное государственное унитарное предприятие "Государственный космический научно-производственный центр имени М.В. Хруничева" (ФГУП "ГКНПЦ им. М.В. Хруничева") Manufacturing method of nozzle of combustion chamber of liquid-propellant engine (lpe)
RU2519003C1 (en) * 2013-04-09 2014-06-10 Открытое акционерное общество "Конструкторское бюро химавтоматики" Method of fabrication of liquid-propellant rocket engine combustion chamber nozzle
CN107940157B (en) * 2017-11-20 2020-07-24 西安航天动力研究所 Regenerative cooling gas guide pipe and processing method thereof
CN108979900A (en) * 2018-08-29 2018-12-11 北京航天动力研究所 A kind of collection pendular ring in liquid rocket engine thrust chamber body portion

Family Cites Families (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE1071421B (en) * 1956-11-09 1959-12-17 Armstrong Siddeley Motors Ltd., Coventry, Warwickshire (Großbritannien) Combustion chamber for gas turbines or rocket motors
FR1232288A (en) * 1957-06-21 1960-10-06 Bristol Siddeley Engines Ltd Improvements to combustion chambers
US3001726A (en) * 1959-06-23 1961-09-26 United Aircraft Corp Manifold attachment
US3062566A (en) * 1959-06-25 1962-11-06 United Aircraft Corp Manifold attachment to tubular wall
DE1751180A1 (en) * 1968-04-18 1971-04-29 Messerschmitt Boelkow Blohm Design and arrangement of an inlet ring or outlet collecting ring for thrust nozzles or combustion chambers of rocket engines, in particular liquid rocket engines
DE6901525U (en) * 1969-01-16 1970-07-09 Messerschmitt Boelkow Blohm DEVICE FOR CONNECTING THE COOLANT INLET RING TO THE WALL OF A ROCKET COMBUSTION CHAMBER OR THROTTLE NOZZLE
DE1941296B2 (en) * 1969-08-14 1971-09-30 Messerschmitt Bolkow Blohm GmbH, 8000 München COMBUSTION CHAMBER WITH THROTTLE NOZZLE, REGENERATIVELY COOLED BY A LIQUID MEDIUM
DE2356572C3 (en) * 1973-11-13 1979-03-29 Messerschmitt-Boelkow-Blohm Gmbh, 8000 Muenchen Liquid-cooled rocket combustion chamber with thrust nozzle

Also Published As

Publication number Publication date
JPS51133613A (en) 1976-11-19
FR2309729A1 (en) 1976-11-26
DE2519538C2 (en) 1982-12-30
DE2519538A1 (en) 1976-11-18

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Legal Events

Date Code Title Description
ST Notification of lapse