GB1089055A - Combined combustion chamber and propulsive unit for a rocket engine - Google Patents

Combined combustion chamber and propulsive unit for a rocket engine

Info

Publication number
GB1089055A
GB1089055A GB3077865A GB3077865A GB1089055A GB 1089055 A GB1089055 A GB 1089055A GB 3077865 A GB3077865 A GB 3077865A GB 3077865 A GB3077865 A GB 3077865A GB 1089055 A GB1089055 A GB 1089055A
Authority
GB
United Kingdom
Prior art keywords
tubes
upstream
divergent
manifold
combustion section
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
GB3077865A
Inventor
Edward George David Andrews
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.)
Bristol Siddeley Engines Ltd
Original Assignee
Bristol Siddeley Engines Ltd
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 Bristol Siddeley Engines Ltd filed Critical Bristol Siddeley Engines Ltd
Priority to GB3077865A priority Critical patent/GB1089055A/en
Priority to DE1966B0067171 priority patent/DE1988818U/en
Priority to FR70176A priority patent/FR1487149A/en
Publication of GB1089055A publication Critical patent/GB1089055A/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)
  • Testing Of Engines (AREA)

Abstract

1,089,055. Rocket engines; combustion chambers. BRISTOL SIDDELEY ENGINES Ltd. July 15, 1966 [July 20, 1965], No.30778/65. Headings F1J and F1L. A rocket engine comprises a combustion section 6 to which an oxidant and liquid fuel are supplied and a convergent-divergent propulsion nozzle. A first cooling jacket surrounds the combustion section, the throat and the upstream portion of the divergent portion of the nozzle, and a second cooling jacket surrounds the downstream portion of the divergent part of the nozzle. The first cooling jacket has an inlet arranged to communicate with a source of oxidant and an outlet leading to the combustion section, while the second cooling jacket has an inlet which communicates with a source of liquid fuel and an outlet leading to the combustion section. In the rocket engine shown, the wall of the combustion section 6, the convergent portion, the throat and the upstream part of the divergent portion of the propulsion nozzle comprises a series of tubes 1, 2 which are secured together as by welding, the tubes 1 at their upstream ends communicating with a manifold 7 to which oxidant such as hydrogen peroxide is supplied through duct 8. The oxidant flows downstream through the tubes 1 to the manifold 11 then upstream through the tubes 2 to the space 10 thence through the catalyst assembly 4, the decomposition products discharging from the space 20 through the passages 19 in the end wall 5 into the combustion space 6. The downstream part 12 of the divergent portion of the nozzle comprises a series of tubes 13 connected at their downstream ends to a manifold 15 to which liquid fuel is supplied, and at their upstream ends to a manifold 14 from which the pre-heated fuel passes through duct 17 and 18 and thence through orifices 21 into the combustion space.
GB3077865A 1965-07-20 1965-07-20 Combined combustion chamber and propulsive unit for a rocket engine Expired GB1089055A (en)

Priority Applications (3)

Application Number Priority Date Filing Date Title
GB3077865A GB1089055A (en) 1965-07-20 1965-07-20 Combined combustion chamber and propulsive unit for a rocket engine
DE1966B0067171 DE1988818U (en) 1965-07-20 1966-07-19 COMBUSTION CHAMBER FOR A ROCKET ENGINE.
FR70176A FR1487149A (en) 1965-07-20 1966-07-20 Rocket engine combustion chamber

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GB3077865A GB1089055A (en) 1965-07-20 1965-07-20 Combined combustion chamber and propulsive unit for a rocket engine

Publications (1)

Publication Number Publication Date
GB1089055A true GB1089055A (en) 1967-11-01

Family

ID=10313000

Family Applications (1)

Application Number Title Priority Date Filing Date
GB3077865A Expired GB1089055A (en) 1965-07-20 1965-07-20 Combined combustion chamber and propulsive unit for a rocket engine

Country Status (2)

Country Link
DE (1) DE1988818U (en)
GB (1) GB1089055A (en)

Cited By (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4055044A (en) * 1973-11-13 1977-10-25 Messerschmitt-Bolkow-Blohm Gmbh Rocket engine construction and connection for closed and opened fluid cooling circuits for the walls thereof
GB2196392A (en) * 1986-10-14 1988-04-27 Gen Electric Multiple-propellant propulsion apparatus & method
GB2196391A (en) * 1986-10-14 1988-04-27 Gen Electric Prolpusion apparatus & method
US4817890A (en) * 1986-10-14 1989-04-04 General Electric Company Multiple-propellant air vehicle and propulsion system
US4840025A (en) * 1986-10-14 1989-06-20 General Electric Company Multiple-propellant air vehicle and propulsion system
WO1993003962A2 (en) * 1991-08-21 1993-03-04 Trw Inc. Satellite propulsion and power system
EP3597897A1 (en) * 2018-07-17 2020-01-22 ArianeGroup GmbH Combustion chamber structure, particularly for a rocket engine
CN114876671A (en) * 2022-03-21 2022-08-09 西安航天动力研究所 Hydrogen peroxide thrust chamber and engine

Cited By (16)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4055044A (en) * 1973-11-13 1977-10-25 Messerschmitt-Bolkow-Blohm Gmbh Rocket engine construction and connection for closed and opened fluid cooling circuits for the walls thereof
GB2196391B (en) * 1986-10-14 1991-06-26 Gen Electric Rocket propulsion system.
GB2196392B (en) * 1986-10-14 1991-06-26 Gen Electric Rocket propulsion system.
US4811556A (en) * 1986-10-14 1989-03-14 General Electric Company Multiple-propellant air vehicle and propulsion system
US4817890A (en) * 1986-10-14 1989-04-04 General Electric Company Multiple-propellant air vehicle and propulsion system
US4840025A (en) * 1986-10-14 1989-06-20 General Electric Company Multiple-propellant air vehicle and propulsion system
US4841723A (en) * 1986-10-14 1989-06-27 General Electric Company Multiple-propellant air vehicle and propulsion system
GB2196391A (en) * 1986-10-14 1988-04-27 Gen Electric Prolpusion apparatus & method
GB2196392A (en) * 1986-10-14 1988-04-27 Gen Electric Multiple-propellant propulsion apparatus & method
US5417049A (en) * 1990-04-19 1995-05-23 Trw Inc. Satellite propulsion and power system
US5572865A (en) * 1990-04-19 1996-11-12 Trw Inc. Satellite propulsion and power system
WO1993003962A3 (en) * 1991-08-21 1993-04-29 Trw Inc Satellite propulsion and power system
WO1993003962A2 (en) * 1991-08-21 1993-03-04 Trw Inc. Satellite propulsion and power system
EP3597897A1 (en) * 2018-07-17 2020-01-22 ArianeGroup GmbH Combustion chamber structure, particularly for a rocket engine
US11525420B2 (en) 2018-07-17 2022-12-13 Arianegroup Gmbh Combustion chamber structure, particularly for a rocket engine
CN114876671A (en) * 2022-03-21 2022-08-09 西安航天动力研究所 Hydrogen peroxide thrust chamber and engine

Also Published As

Publication number Publication date
DE1988818U (en) 1968-07-04

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