GB1291473A - Improvements in rocket combustion chambers or thrust nozzles - Google Patents

Improvements in rocket combustion chambers or thrust nozzles

Info

Publication number
GB1291473A
GB1291473A GB5934369A GB5934369A GB1291473A GB 1291473 A GB1291473 A GB 1291473A GB 5934369 A GB5934369 A GB 5934369A GB 5934369 A GB5934369 A GB 5934369A GB 1291473 A GB1291473 A GB 1291473A
Authority
GB
United Kingdom
Prior art keywords
nozzle
combustion chamber
ring manifold
frusto
wall
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
GB5934369A
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 GB1291473A publication Critical patent/GB1291473A/en
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

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Gasket Seals (AREA)
  • Testing Of Engines (AREA)

Abstract

1291473 Rocket combustion chamber and nozzle MESSERSCHMITT-BÍLKOWBLOHM GmbH 4 Dec 1969 [16 Jan 1969] 59343/69 Heading F1J The invention relates to means for connecting the coolant inlet ring manifold to the wall of a rocket combustion chamber or thrust nozzle, the wall of the combustion chamber or nozzle being formed of a material such as copper which is softer than that of the ring manifold. The abutting surfaces of the combustion chamber or nozzle and of the ring manifold are of frustoconical form. The thrust nozzle shown comprises a wall 1 formed with cooling bores 1α and an end flange 2 of T-section and having a frusto-conical surface 11b. A ring manifold member 5 formed with an annular passage 6 and radial passage 12α, also with an internal frusto-conical surface 11α is formed with an annular recess 4 in which is received the portion 3α of the flange 2. An annular clamp member 7 having a tongue portion 10 is secured to the member 5 by studs 8 and nuts 9, the tongue portion 10 engaging the underside of the portion 3b of the flange 2 whereby the frusto-conical surfaces 11α, 11b are held together in sealed relation upon tightening of the nuts 9.
GB5934369A 1969-01-16 1969-12-04 Improvements in rocket combustion chambers or thrust nozzles Expired GB1291473A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
DE19696901525 DE6901525U (en) 1969-01-16 1969-01-16 DEVICE FOR CONNECTING THE COOLANT INLET RING TO THE WALL OF A ROCKET COMBUSTION CHAMBER OR THROTTLE NOZZLE

Publications (1)

Publication Number Publication Date
GB1291473A true GB1291473A (en) 1972-10-04

Family

ID=6599076

Family Applications (1)

Application Number Title Priority Date Filing Date
GB5934369A Expired GB1291473A (en) 1969-01-16 1969-12-04 Improvements in rocket combustion chambers or thrust nozzles

Country Status (3)

Country Link
DE (1) DE6901525U (en)
FR (1) FR2028419A1 (en)
GB (1) GB1291473A (en)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN114412667A (en) * 2021-12-20 2022-04-29 上海空间推进研究所 Connecting system of engine combustion chamber and spray pipe extension section and machining method thereof

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE2519538C2 (en) * 1975-05-02 1982-12-30 Messerschmitt-Bölkow-Blohm GmbH, 8000 München Connection between the coolant inlet ring and the combustion chamber or thrust nozzle wall of a rocket engine

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN114412667A (en) * 2021-12-20 2022-04-29 上海空间推进研究所 Connecting system of engine combustion chamber and spray pipe extension section and machining method thereof
CN114412667B (en) * 2021-12-20 2023-06-23 上海空间推进研究所 Connecting system for engine combustion chamber and jet pipe extension section and processing method thereof

Also Published As

Publication number Publication date
FR2028419A1 (en) 1970-10-09
DE6901525U (en) 1970-07-09

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