FR2309729A1 - Cooling medium collection ring for rocket propulsion - having connecting flange with one sided dove tail joint to prevent displacement - Google Patents

Cooling medium collection ring for rocket propulsion - having connecting flange with one sided dove tail joint to prevent displacement

Info

Publication number
FR2309729A1
FR2309729A1 FR7611709A FR7611709A FR2309729A1 FR 2309729 A1 FR2309729 A1 FR 2309729A1 FR 7611709 A FR7611709 A FR 7611709A FR 7611709 A FR7611709 A FR 7611709A FR 2309729 A1 FR2309729 A1 FR 2309729A1
Authority
FR
France
Prior art keywords
collection ring
cooling medium
sided
connecting flange
prevent displacement
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.)
Granted
Application number
FR7611709A
Other languages
French (fr)
Other versions
FR2309729B1 (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)

Abstract

The combustion chamber cooling medium collection ring is made of high grade steel and fixed to the combustion chamber wall by means of an annular flange (18) showing a semi-dovetail joint (30). The joint either side of the cooling channel (24) is additionally sealed by a brazing seam (26). Alternatively the collection ring is made in two parts and the flange has a full dovetail. The first part of the collection ring is fixed to the flange by an internal brazing seam and the second part after welding to the first part is clamped up to the first part by a series of pinch bolts.
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 true FR2309729A1 (en) 1976-11-26
FR2309729B1 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)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
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

Families Citing this family (4)

* 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)
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

Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR1187946A (en) * 1956-11-09 1959-09-17 Armstrong Siddeley Motors Ltd Combustion chamber
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
FR2058274A1 (en) * 1969-08-14 1971-05-28 Messerschmitt Boelkow Blohm
FR2250899A1 (en) * 1973-11-13 1975-06-06 Messerschmitt Boelkow Blohm

Family Cites Families (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
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

Patent Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR1187946A (en) * 1956-11-09 1959-09-17 Armstrong Siddeley Motors Ltd Combustion chamber
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
FR2058274A1 (en) * 1969-08-14 1971-05-28 Messerschmitt Boelkow Blohm
FR2250899A1 (en) * 1973-11-13 1975-06-06 Messerschmitt Boelkow Blohm

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
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

Also Published As

Publication number Publication date
DE2519538C2 (en) 1982-12-30
JPS51133613A (en) 1976-11-19
FR2309729B1 (en) 1980-04-18
DE2519538A1 (en) 1976-11-18

Similar Documents

Publication Publication Date Title
FR2333964A1 (en) PROPULSION TUBE FOR GAS TURBINE ENGINE
FR2309729A1 (en) Cooling medium collection ring for rocket propulsion - having connecting flange with one sided dove tail joint to prevent displacement
GB1517418A (en) Sealed flange joint
GB1188103A (en) Steam Generator and Method of Making the Same
ES426222A1 (en) Apparatus for welding a flange to a pipe
GB1329497A (en) Internal combustion engine gas seal
GB1418739A (en) Method for making a branch connection to a pipe under pressure
FR2395401A1 (en) COMBUSTION CHAMBER FOR A GAS TURBINE
GB1138636A (en) Improvements in solid fuel rocket propulsion units
GB1454888A (en) Centre housing for a rotary piston internal combustion engine
GB1327151A (en) Branch-connecting piece for a plastics pipe line and a pipe connection comprising a branch-connecting piece
ES306254A1 (en) Tube joints
GB1286925A (en) Method of assembling a junction piece to a planetary cooler tube on a rotary kiln
FR2456217A1 (en) MOTOR-ROCKET
GB1164725A (en) A Telescopic Conduit Connected Between the Exhaust of an Internal Combustion Engine and an Exhaust Gas Turbine
FR2320808A1 (en) Flash butt welding large dia. pipes for pipelines - using manipulator running inside pipes for centering and clamping (OE151176)
GB1305516A (en)
GB1142235A (en) Improvements in conduit flanges
FR2411351A1 (en) Pipes clamp on coupling arrangement - uses end flanged tubular parts, and clamping ring with groove having sloping side wall for forming wedging action between flanges
GB1491391A (en) Engine having an oil cooled seal
FR2227784A5 (en) Jointing seal for large dia. concrete undersea piping - has compensation for misalignment of pipe ends
GB1496128A (en) Explosive joining of pipes in liquid environments
FR2279967A1 (en) Tubular mast for lighting installations - has sections joined using internal mating wedge blocks held by bolts
GB1355874A (en) Insert for use in the exploxive welding or expansion processes of tubes
FR2454856A1 (en) Explosion welding of tube in heat exchanger tube plate - using explosive with reduced detonation speed in direction of propagation

Legal Events

Date Code Title Description
ST Notification of lapse