RU2001111151A - LIQUID ROCKET ENGINE WITH TURBO PUMP SUPPLY OF CRYOGENIC FUEL - Google Patents

LIQUID ROCKET ENGINE WITH TURBO PUMP SUPPLY OF CRYOGENIC FUEL

Info

Publication number
RU2001111151A
RU2001111151A RU2001111151/06A RU2001111151A RU2001111151A RU 2001111151 A RU2001111151 A RU 2001111151A RU 2001111151/06 A RU2001111151/06 A RU 2001111151/06A RU 2001111151 A RU2001111151 A RU 2001111151A RU 2001111151 A RU2001111151 A RU 2001111151A
Authority
RU
Russia
Prior art keywords
rocket engine
liquid rocket
cryogenic fuel
turbine
condensate pump
Prior art date
Application number
RU2001111151/06A
Other languages
Russian (ru)
Other versions
RU2202703C2 (en
Inventor
Аркадий Алексеевич Бахмутов
Владислав Тимофеевич Буканов
Игорь Алексеевич Клепиков
Вячеслав Васильевич Мирошкин
Владимир Иосифович Прищепа
Татьяна Яковлевна Ромасенко
Original Assignee
Аркадий Алексеевич Бахмутов
Владислав Тимофеевич Буканов
Игорь Алексеевич Клепиков
Вячеслав Васильевич Мирошкин
Владимир Иосифович Прищепа
Татьяна Яковлевна Ромасенко
Filing date
Publication date
Application filed by Аркадий Алексеевич Бахмутов, Владислав Тимофеевич Буканов, Игорь Алексеевич Клепиков, Вячеслав Васильевич Мирошкин, Владимир Иосифович Прищепа, Татьяна Яковлевна Ромасенко filed Critical Аркадий Алексеевич Бахмутов
Priority to RU2001111151/06A priority Critical patent/RU2202703C2/en
Priority claimed from RU2001111151/06A external-priority patent/RU2202703C2/en
Publication of RU2001111151A publication Critical patent/RU2001111151A/en
Application granted granted Critical
Publication of RU2202703C2 publication Critical patent/RU2202703C2/en

Links

Claims (3)

1. Жидкостный ракетный двигатель с турбонасосной подачей криогенного топлива, включающий камеру с форсуночной головкой и охлаждаемым корпусом, турбонасосный агрегат из паровой турбины и насосов подачи окислителя, горючего и конденсата отработавшего пара, причем вход турбины соединен с выходом насоса конденсата через первую магистраль, включающую охлаждающий тракт камеры, а выход турбины сообщен с входом насоса конденсата через вторую магистраль с теплообменником-конденсатором для охлаждения отработавшего пара криогенным топливным компонентом, отличающийся тем, что во второй магистрали размещен эжектор с высоконапорным соплом, подключенным к выходу насоса конденсата.1. A liquid rocket engine with a turbopump supply of cryogenic fuel, including a chamber with a nozzle head and a cooled casing, a turbopump assembly from a steam turbine and oxidizer, fuel and exhaust condensate pumps, the turbine inlet being connected to the condensate pump outlet through a first line including a cooling the path of the chamber, and the turbine output is communicated with the condensate pump inlet through the second line with a heat exchanger-condenser for cooling the exhaust steam with a cryogenic fuel component, characterized in that in the second line there is an ejector with a high-pressure nozzle connected to the outlet of the condensate pump. 2. Жидкостный ракетный двигатель по п. 1, отличающийся тем, что эжектор размещен между выходом теплообменника-конденсатора и входом насоса конденсата. 2. A liquid rocket engine according to claim 1, characterized in that the ejector is located between the output of the heat exchanger-condenser and the inlet of the condensate pump. 3. Жидкостный ракетный двигатель по п. 1, отличающийся тем, что эжектор размещен между выходом турбины и входом теплообменника-конденсатора. 3. A liquid rocket engine according to claim 1, characterized in that the ejector is located between the output of the turbine and the input of the heat exchanger-condenser.
RU2001111151/06A 2001-04-26 2001-04-26 Liquid-propellant rocket engine with turbopump delivery of cryogenic propellant RU2202703C2 (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
RU2001111151/06A RU2202703C2 (en) 2001-04-26 2001-04-26 Liquid-propellant rocket engine with turbopump delivery of cryogenic propellant

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
RU2001111151/06A RU2202703C2 (en) 2001-04-26 2001-04-26 Liquid-propellant rocket engine with turbopump delivery of cryogenic propellant

Publications (2)

Publication Number Publication Date
RU2001111151A true RU2001111151A (en) 2003-03-10
RU2202703C2 RU2202703C2 (en) 2003-04-20

Family

ID=20248869

Family Applications (1)

Application Number Title Priority Date Filing Date
RU2001111151/06A RU2202703C2 (en) 2001-04-26 2001-04-26 Liquid-propellant rocket engine with turbopump delivery of cryogenic propellant

Country Status (1)

Country Link
RU (1) RU2202703C2 (en)

Families Citing this family (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
RU2481489C1 (en) * 2012-03-05 2013-05-10 Николай Борисович Болотин Turbo-pump unit of rocket engine
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

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