GB853495A - Improvements in or relating to liquid propellent rocket motors - Google Patents

Improvements in or relating to liquid propellent rocket motors

Info

Publication number
GB853495A
GB853495A GB2884157A GB2884157A GB853495A GB 853495 A GB853495 A GB 853495A GB 2884157 A GB2884157 A GB 2884157A GB 2884157 A GB2884157 A GB 2884157A GB 853495 A GB853495 A GB 853495A
Authority
GB
United Kingdom
Prior art keywords
duct
combustion chamber
liquid
pump
liquid oxygen
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
GB2884157A
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.)
ALLAN BARKER BRITISH
Original Assignee
ALLAN BARKER BRITISH
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 ALLAN BARKER BRITISH filed Critical ALLAN BARKER BRITISH
Priority to GB2884157A priority Critical patent/GB853495A/en
Publication of GB853495A publication Critical patent/GB853495A/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
    • F02K9/44—Feeding propellants
    • F02K9/46—Feeding propellants using pumps
    • F02K9/48—Feeding propellants using pumps driven by a gas turbine fed by propellant combustion gases or fed by vaporized propellants or other gases

Abstract

853,495. Generating combustion products under pressure. BARKER, A. Sept. 15, 1958 [Sept. 13, 1957], No. 28841/57. Class 51 (1). [Also in Group XXVI] In a liquid propellant type of rocket, the combustion chamber is cooled by means of liquid oxygen which is stored at its boiling point but which does not become gaseous when it comes into contact with the wall of the combustion chamber. The rocket motor shown comprises a combustion chamber 14 having a cooling jacket space 6 therearound. Liquid oxygen is supplied from an inlet 3 to the first stage 2 of the pump 1 where its pressure, is increased to about 350 lb. per square inch, the liquid then passing to the second stage 5 where its pressure is increased to about 700 1b. per square inch. The high-pressure liquid oxygen then flows through duct 9 to the combustion chamber cooling space 6, being discharged therefrom as a liquid through duct 10. A portion of the liquid then passes through an expansion valve 11 to a gas and liquid separator 12. The gaseous oxygen discharges through duct 15 and into the combustion chamber 14 through nozzles 16, 17 where it takes part in the oombustion process. Liquid oxygen from the separator 12 flows through duct 13 into which liquid oxygen from the first stage 2 of the pump 1 is discharged and then passes through the second stage 5 of the pump and thence as described above. The second portion of the liquid oxygen from the duct 10 flows through duct 18 where it divides, some flowing through duct 19 to the nozzle 16 where it is atomized by gaseous oxygen flowing through duct 15 to the rocket combustion chamber 14. The remainder of the liquid oxygen flowing through duct 18 enters the auxiliary combustion chamber 20 to which fuel is also supplied through duct 24 and nozzle 23. Combustion gases from the auxiliary chamber 20 are utilized to drive the turbine 7 and finally discharge through duct 21 into'the rocket combustion chamber 14. The turbine 7 drives the liquid oxygen pump 2, 5 also the fuel pump 8, a portion of the fuel from the pump passing to the auxiliary combustion chamber 20, the remainder flowing through duct 25 and nozzle 17 to the rocket combustion chamber.
GB2884157A 1957-09-13 1957-09-13 Improvements in or relating to liquid propellent rocket motors Expired GB853495A (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
GB2884157A GB853495A (en) 1957-09-13 1957-09-13 Improvements in or relating to liquid propellent rocket motors

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GB2884157A GB853495A (en) 1957-09-13 1957-09-13 Improvements in or relating to liquid propellent rocket motors

Publications (1)

Publication Number Publication Date
GB853495A true GB853495A (en) 1960-11-09

Family

ID=10282021

Family Applications (1)

Application Number Title Priority Date Filing Date
GB2884157A Expired GB853495A (en) 1957-09-13 1957-09-13 Improvements in or relating to liquid propellent rocket motors

Country Status (1)

Country Link
GB (1) GB853495A (en)

Cited By (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE1222319B (en) * 1964-10-15 1966-08-04 Boelkow Gmbh Fuel delivery system for liquid rocket engines
US3516251A (en) * 1967-06-03 1970-06-23 Rolls Royce Rocket engine
US4621492A (en) * 1985-01-10 1986-11-11 The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration Low loss injector for liquid propellant rocket engines
EP0242196A1 (en) * 1986-04-16 1987-10-21 The Marconi Company Limited Thrusters
EP0244215A1 (en) * 1986-05-02 1987-11-04 The Marconi Company Limited Gas thruster
US4894986A (en) * 1988-05-11 1990-01-23 Royal Ordnance Bipropellant rocket engines
CN106673930A (en) * 2015-11-09 2017-05-17 北京卫星环境工程研究所 Application of basic metal or hydride thereof as chemical propellant in low earth orbit
CN115324773A (en) * 2022-10-13 2022-11-11 中国人民解放军63921部队 Full open expansion cycle engine

Cited By (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE1222319B (en) * 1964-10-15 1966-08-04 Boelkow Gmbh Fuel delivery system for liquid rocket engines
US3516251A (en) * 1967-06-03 1970-06-23 Rolls Royce Rocket engine
US4621492A (en) * 1985-01-10 1986-11-11 The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration Low loss injector for liquid propellant rocket engines
EP0242196A1 (en) * 1986-04-16 1987-10-21 The Marconi Company Limited Thrusters
EP0244215A1 (en) * 1986-05-02 1987-11-04 The Marconi Company Limited Gas thruster
US4894986A (en) * 1988-05-11 1990-01-23 Royal Ordnance Bipropellant rocket engines
CN106673930A (en) * 2015-11-09 2017-05-17 北京卫星环境工程研究所 Application of basic metal or hydride thereof as chemical propellant in low earth orbit
CN115324773A (en) * 2022-10-13 2022-11-11 中国人民解放军63921部队 Full open expansion cycle engine

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