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RU2000111347A - LIQUID ROCKET ENGINE - Google Patents

LIQUID ROCKET ENGINE

Info

Publication number
RU2000111347A
RU2000111347A RU2000111347/06A RU2000111347A RU2000111347A RU 2000111347 A RU2000111347 A RU 2000111347A RU 2000111347/06 A RU2000111347/06 A RU 2000111347/06A RU 2000111347 A RU2000111347 A RU 2000111347A RU 2000111347 A RU2000111347 A RU 2000111347A
Authority
RU
Russia
Prior art keywords
input
condenser
combustion chamber
rocket engine
pump
Prior art date
Application number
RU2000111347/06A
Other languages
Russian (ru)
Other versions
RU2182984C2 (en
Inventor
Руслан Эдуардович Катков
Николай Николаевич Тупицын
Игорь Петрович Чикаев
Original Assignee
Открытое акционерное общество "Ракетно-космическая корпорация "Энергия" им. С.П. Королева"
Filing date
Publication date
Application filed by Открытое акционерное общество "Ракетно-космическая корпорация "Энергия" им. С.П. Королева" filed Critical Открытое акционерное общество "Ракетно-космическая корпорация "Энергия" им. С.П. Королева"
Priority to RU2000111347A priority Critical patent/RU2182984C2/en
Priority claimed from RU2000111347A external-priority patent/RU2182984C2/en
Publication of RU2000111347A publication Critical patent/RU2000111347A/en
Application granted granted Critical
Publication of RU2182984C2 publication Critical patent/RU2182984C2/en

Links

Claims (1)

Жидкостный ракетный двигатель, включающий в себя камеру сгорания с регенеративным трактом охлаждения, насосы подачи компонентов - горючего и окислителя с турбиной на одном валу, отличающийся тем, что в него введен конденсатор, вход которого по линии хладагента соединен со входом в камеру сгорания и со входом в тракт регенеративного охлаждения камеры сгорания, выход из конденсатора по линии теплоносителя соединен со входом в насос одного из компонентов, а выход из насоса того же компонента сообщен со входом конденсатора по линии хладагента, причем второй вход конденсатора сообщен с выходом турбины, при этом выход насоса другого компонента сообщен со входом в камеру сгорания.A liquid-propellant rocket engine including a combustion chamber with a regenerative cooling path, pumps for supplying components - fuel and an oxidizer with a turbine on one shaft, characterized in that a condenser is introduced into it, the input of which is connected through the refrigerant line to the input to the combustion chamber and to the input into the path of regenerative cooling of the combustion chamber, the outlet of the condenser through the coolant line is connected to the pump inlet of one of the components, and the outlet of the pump of the same component is connected to the condenser inlet through the refrigerant line and, and the second input of the condenser is in communication with the output of the turbine, while the output of the pump of the other component is communicated with the entrance to the combustion chamber.
RU2000111347A 2000-05-06 2000-05-06 Liquid-propellant rocket engine RU2182984C2 (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
RU2000111347A RU2182984C2 (en) 2000-05-06 2000-05-06 Liquid-propellant rocket engine

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
RU2000111347A RU2182984C2 (en) 2000-05-06 2000-05-06 Liquid-propellant rocket engine

Publications (2)

Publication Number Publication Date
RU2000111347A true RU2000111347A (en) 2002-04-20
RU2182984C2 RU2182984C2 (en) 2002-05-27

Family

ID=20234321

Family Applications (1)

Application Number Title Priority Date Filing Date
RU2000111347A RU2182984C2 (en) 2000-05-06 2000-05-06 Liquid-propellant rocket engine

Country Status (1)

Country Link
RU (1) RU2182984C2 (en)

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB202020283D0 (en) 2020-12-21 2021-02-03 Tokamak Energy Ltd Divertor cooling

Family Cites Families (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3049870A (en) * 1960-04-14 1962-08-21 United Aircraft Corp Rocket propellant cycle
US3516254A (en) * 1967-09-11 1970-06-23 United Aircraft Corp Closed-loop rocket propellant cycle
DE3506826A1 (en) * 1985-02-27 1986-08-28 Messerschmitt-Bölkow-Blohm GmbH, 8012 Ottobrunn Method for the operation of a liquid-fuelled rocket engine and rocket engine for implementing the method
FR2640322A1 (en) * 1988-12-09 1990-06-15 Europ Propulsion ROCKET OR COMBINED MOTOR FOR A SPATIAL VEHICLE WITH ESSENTIALLY CLOSED AUXILIARY HYDRAULIC CIRCUIT
RU2095607C1 (en) * 1995-07-19 1997-11-10 Ракетно-космическая корпорация "Энергия" им.С.П.Королева Cryogenic propellant rocket engine
RU2095608C1 (en) * 1995-08-17 1997-11-10 Ракетно-космическая корпорация "Энергия" им.С.П.Королева Liquid-propellant rocket engine
US6052987A (en) * 1997-11-14 2000-04-25 Trw Inc. Non-propellant fluid cooled space craft rocket engine
RU2148181C1 (en) * 1998-10-12 2000-04-27 Открытое акционерное общество "Ракетно-космическая корпорация "Энергия" им.С.П.Королева" Liquid-propellant rocket power plant

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