RU95112367A - Liquid cryogenic propellant rocket engine - Google Patents

Liquid cryogenic propellant rocket engine

Info

Publication number
RU95112367A
RU95112367A RU95112367/06A RU95112367A RU95112367A RU 95112367 A RU95112367 A RU 95112367A RU 95112367/06 A RU95112367/06 A RU 95112367/06A RU 95112367 A RU95112367 A RU 95112367A RU 95112367 A RU95112367 A RU 95112367A
Authority
RU
Russia
Prior art keywords
oxidizer
turbopump
fuel
turbine
cryogenic
Prior art date
Application number
RU95112367/06A
Other languages
Russian (ru)
Other versions
RU2095607C1 (en
Inventor
В.В. Копылов
М.Н. Сыровец
Original Assignee
Ракетно-космическая корпорация "Энергия" им.С.П.Королева
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 Ракетно-космическая корпорация "Энергия" им.С.П.Королева filed Critical Ракетно-космическая корпорация "Энергия" им.С.П.Королева
Priority to RU95112367A priority Critical patent/RU2095607C1/en
Publication of RU95112367A publication Critical patent/RU95112367A/en
Application granted granted Critical
Publication of RU2095607C1 publication Critical patent/RU2095607C1/en

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Abstract

FIELD: liquid-propellant rocket engines. SUBSTANCE: propellant components are cryogenic oxidizer - liquid oxygen and hydrocarbon fuel. Liquid-propellant rocket engine includes combustion chamber with nozzle, cryogenic oxidizer and fuel turbopumps with oxidizer and fuel service mains provided with drive turbines and gas generator equipped with cooling jacket which is connected to oxidizer service main. Outlet of gas generator is connected with inlet of turbine of fuel turbopump and outlet of cooling jacket of gas generator is connected with inlet of turbine of oxidizer turbopump whose outlet is connected to inlet of oxidizer turbopump through heat exchanger mounted in oxidizer service main. Cryogenic oxidizer delivered to cooling jacket of gas generator is gasified due to heat exchange with generator gas and is used as working medium for oxidizer turbopump. EFFECT: enhanced efficiency of cooling generator gas; burning of propellant at optimal ratio of components; avoidance of thermal action of gas on turbine blades; reduced amount of burnt propellant.

Claims (1)

Жидкостный ракетный двигатель на криогенном топливе, содержащий камеру сгорания с соплом, турбонасос криогенного окислителя и турбонасос углеводородного горючего с расходными магистралями окислителя и горючего, газогенератор, выход которого соединен с входом турбины, связанной с турбонасосом горючего и имеющей выхлопной патрубок, отличающийся тем, что он снабжен второй турбиной, связанной с турбонасосом криогенного окислителя, а газогенератор снабжен рубашкой охлаждения, подключенной через отсечной клапан к расходной магистрали окислителя, при этом выход из рубашки охлаждения газогенератора соединен с входом второй турбины, выход которой через теплообменник, установленный на расходной магистрали окислителя, подключен к расходной магистрали перед турбонасосом криогенного окислителя.A liquid cryogenic fuel rocket engine containing a combustion chamber with a nozzle, a cryogenic oxidizer turbopump and a hydrocarbon fuel turbopump with oxidizer and fuel supply lines, a gas generator whose output is connected to a turbine inlet connected to a fuel turbopump and having an exhaust pipe, characterized in that equipped with a second turbine connected to the cryogenic oxidizer turbine pump, and the gas generator is equipped with a cooling jacket connected through an shut-off valve to the flow line ok numerator, wherein the output of the gasifier cooling jacket is connected to the inlet of the second turbine outlet through which the heat exchanger is mounted on the flow of oxidant line is connected to the flow line before cryogenic oxidizer turbo pump.
RU95112367A 1995-07-19 1995-07-19 Cryogenic propellant rocket engine RU2095607C1 (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
RU95112367A RU2095607C1 (en) 1995-07-19 1995-07-19 Cryogenic propellant rocket engine

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
RU95112367A RU2095607C1 (en) 1995-07-19 1995-07-19 Cryogenic propellant rocket engine

Publications (2)

Publication Number Publication Date
RU95112367A true RU95112367A (en) 1997-06-27
RU2095607C1 RU2095607C1 (en) 1997-11-10

Family

ID=20170252

Family Applications (1)

Application Number Title Priority Date Filing Date
RU95112367A RU2095607C1 (en) 1995-07-19 1995-07-19 Cryogenic propellant rocket engine

Country Status (1)

Country Link
RU (1) RU2095607C1 (en)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN111502865A (en) * 2020-04-16 2020-08-07 西安航天动力研究所 Test run method of open-cycle liquid oxygen kerosene engine system

Families Citing this family (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
RU2155273C1 (en) * 1999-08-18 2000-08-27 Открытое акционерное общество "НПО Энергомаш им.акад. В.П. Глушко" Liquid cryogenic propellant rocket engine with closed loop of turbine drive of turbopump unit (versions)
DE19958310C2 (en) * 1999-12-03 2002-01-17 Daimler Chrysler Ag Rocket engine for liquid fuels with a closed engine circuit
FR2941019A1 (en) 2009-01-09 2010-07-16 Snecma PUMP WITH AXIAL BALANCING DEVICE
FR2984452B1 (en) * 2011-12-14 2014-06-13 Snecma PRESSURIZATION DEVICE AND METHOD
FR3000995B1 (en) * 2013-01-11 2015-07-24 Snecma ERGOL SUPPLY CIRCUIT AND COOLING METHOD
FR3000996B1 (en) * 2013-01-11 2016-06-17 Snecma SYSTEM AND METHOD FOR FEEDING A ROCKER ENGINE
FR3009586B1 (en) * 2013-08-06 2015-08-28 Snecma ENGINE FEEDING DEVICE IN ERGOL
RU2612512C1 (en) * 2016-03-29 2017-03-09 Владислав Юрьевич Климов Liquid propellant rocket engine
CN111502864B (en) * 2020-04-16 2021-07-20 西安航天动力研究所 Open-cycle liquid oxygen kerosene engine system and use method thereof

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN111502865A (en) * 2020-04-16 2020-08-07 西安航天动力研究所 Test run method of open-cycle liquid oxygen kerosene engine system
CN111502865B (en) * 2020-04-16 2021-05-04 西安航天动力研究所 Test run method of open-cycle liquid oxygen kerosene engine system

Also Published As

Publication number Publication date
RU2095607C1 (en) 1997-11-10

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