GB792909A - Rocket motor cooling systems - Google Patents

Rocket motor cooling systems

Info

Publication number
GB792909A
GB792909A GB1711853A GB1711853A GB792909A GB 792909 A GB792909 A GB 792909A GB 1711853 A GB1711853 A GB 1711853A GB 1711853 A GB1711853 A GB 1711853A GB 792909 A GB792909 A GB 792909A
Authority
GB
United Kingdom
Prior art keywords
combustion chamber
coolant
heat exchanger
pumped
kerosene
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
GB1711853A
Inventor
Frank Bernard Halford
Arthur Valentine Cleaver
George Edward Preece
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
De Havilland Engine Co 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 De Havilland Engine Co Ltd filed Critical De Havilland Engine Co Ltd
Priority to GB1711853A priority Critical patent/GB792909A/en
Publication of GB792909A publication Critical patent/GB792909A/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
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2260/00—Function
    • F05D2260/20—Heat transfer, e.g. cooling
    • F05D2260/205—Cooling fluid recirculation, i.e. after cooling one or more components is the cooling fluid recovered and used elsewhere for other purposes
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2260/00—Function
    • F05D2260/20—Heat transfer, e.g. cooling
    • F05D2260/232—Heat transfer, e.g. cooling characterized by the cooling medium

Abstract

792,909. Generating combustion products under pressure. DE HAVILLAND ENGINE CO., Ltd. May 19, 1954 [June 19, 1953], No. 17118/53. Class 51 (1). [Also in Group XXVI] A cooling system for the combustion chamber of a rocket motor using liquid propellants comprises a cooling jacket around the combustion chamber, means for circulating a liquid coolant through this jacket, and a heat exchanger through which the coolant is also circulated and wherein the coolant gives up heat to a propellant liquid. In Fig. 1 water from a tank 20 is pumped by a pump 19 through a cooling jacket 11 surrounding the combustion chamber 10 and through a heat exchanger 18 where it gives up heat to an oxidant, e.g. hydrogen peroxide, pumped from a tank 14 through the heat exchanger to the combustion chamber. A fuel, e.g. kerosene, is pumped by a pump 17 from a tank 16 to the combustion chamber. The pressure of the coolant may be low in relation to the injection pressure of the propellant liquids. In a modification, Fig. 2 (not shown), kerosene is used as the coolant as well as a fuel and the pump 17 is connected to a point on the cooling system between the cooling jacket 11 and the heat exchanger 18 so that a small proportion of the kerosene circulating in the coolant circuit is tapped off and injected into the combustion chamber.
GB1711853A 1953-06-19 1953-06-19 Rocket motor cooling systems Expired GB792909A (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
GB1711853A GB792909A (en) 1953-06-19 1953-06-19 Rocket motor cooling systems

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GB1711853A GB792909A (en) 1953-06-19 1953-06-19 Rocket motor cooling systems

Publications (1)

Publication Number Publication Date
GB792909A true GB792909A (en) 1958-04-02

Family

ID=10089582

Family Applications (1)

Application Number Title Priority Date Filing Date
GB1711853A Expired GB792909A (en) 1953-06-19 1953-06-19 Rocket motor cooling systems

Country Status (1)

Country Link
GB (1) GB792909A (en)

Cited By (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3137132A (en) * 1961-11-15 1964-06-16 Space Age Materials Corp Internally cooled rocket nozzle
US3516254A (en) * 1967-09-11 1970-06-23 United Aircraft Corp Closed-loop rocket propellant cycle
WO1995026467A2 (en) * 1994-03-29 1995-10-05 Igor Urban Bipropellant rocket motor
EP0916835A1 (en) * 1997-11-14 1999-05-19 TRW Inc. Closed loop cooled rocket engine
EP2693033A1 (en) * 2011-03-31 2014-02-05 Mitsubishi Heavy Industries, Ltd. Aircraft/spacecraft fluid cooling system and aircraft/spacecraft fluid cooling device
FR2994731A1 (en) * 2012-08-22 2014-02-28 Snecma COOLING PROCESS
CN106567791A (en) * 2016-11-08 2017-04-19 上海宇航系统工程研究所 Forced circulation precooling system
RU2687548C1 (en) * 2018-07-31 2019-05-14 Российская Федерация, от имени которой выступает Государственная корпорация по космической деятельности "РОСКОСМОС" Device for regenerative cooling of supersonic part of liquid rocket engine nozzle

Cited By (13)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3137132A (en) * 1961-11-15 1964-06-16 Space Age Materials Corp Internally cooled rocket nozzle
US3516254A (en) * 1967-09-11 1970-06-23 United Aircraft Corp Closed-loop rocket propellant cycle
WO1995026467A2 (en) * 1994-03-29 1995-10-05 Igor Urban Bipropellant rocket motor
WO1995026467A3 (en) * 1994-03-29 1995-11-09 Igor Urban Bipropellant rocket motor
EP0916835A1 (en) * 1997-11-14 1999-05-19 TRW Inc. Closed loop cooled rocket engine
US6052987A (en) * 1997-11-14 2000-04-25 Trw Inc. Non-propellant fluid cooled space craft rocket engine
EP2693033A1 (en) * 2011-03-31 2014-02-05 Mitsubishi Heavy Industries, Ltd. Aircraft/spacecraft fluid cooling system and aircraft/spacecraft fluid cooling device
EP2693033A4 (en) * 2011-03-31 2015-01-14 Mitsubishi Heavy Ind Ltd Aircraft/spacecraft fluid cooling system and aircraft/spacecraft fluid cooling device
US9476654B2 (en) 2011-03-31 2016-10-25 Mitsubishi Heavy Industries, Ltd. Aircraft/spacecraft fluid cooling system and aircraft/spacecraft fluid cooling method
FR2994731A1 (en) * 2012-08-22 2014-02-28 Snecma COOLING PROCESS
WO2014044939A1 (en) * 2012-08-22 2014-03-27 Snecma Cooling method
CN106567791A (en) * 2016-11-08 2017-04-19 上海宇航系统工程研究所 Forced circulation precooling system
RU2687548C1 (en) * 2018-07-31 2019-05-14 Российская Федерация, от имени которой выступает Государственная корпорация по космической деятельности "РОСКОСМОС" Device for regenerative cooling of supersonic part of liquid rocket engine nozzle

Similar Documents

Publication Publication Date Title
US2505798A (en) Liquid fuel jet propulsion system
GB793689A (en) Rocket motors
GB792909A (en) Rocket motor cooling systems
US3013384A (en) Jet atomic system
GB1099989A (en) An auxiliary unit for starting jet-propulsion engines and for generating electrical energy
US3782112A (en) Hybrid generator
GB1104447A (en) Improvements in or relating to rocket motors
GB899030A (en) Improvements relating to propellant systems for rockets
GB1211841A (en) Fluid propulsion mechanisms for rockets
GB1048276A (en) Improvements in or relating to steam generation and apparatus therefor
GB1486000A (en) Method and apparatus for converting heat energy into mechanical energy
GB919506A (en) Improvements in vapourized fuel systems of jet propulsion engines
GB761896A (en) Improvements in and relating to rocket motors
SE8200783L (en) FUEL SYSTEM FOR MARINE DIESEL ENGINES
US2938482A (en) Solid propellant starter for liquid fuel monopropellant torpedo propulsion system
GB765670A (en) Minimising fire risk when operating rockets, gas-generators or the like
DITTMAN et al. Hydrogen-oxygen internal combustion engine may approach the thermal efficiency of fuel cells for space power systems applications
JPS529708A (en) Injector for rocket engine
STUDHALTER Discussion of engine system and component design of the j-2 high-energy liquid propellant rocket engine which uses liquid hydrogen as the fuel
SU973888A1 (en) Power unit
GB932980A (en) Combustion chambers for liquid fuels
GB834090A (en) Improvements relating to cooling arrangements for internal combustion engines
Sanders et al. 41. Dynamics and Control of Chemical Rockets
BATTERTON et al. Experimental test results of a generalized parameter fuel control(Performance tests of hydromechanical fuel control system for J-85 engine)
GB1050377A (en)