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RU2000102271A - COMBINED LIQUID ROCKET ENGINE - Google Patents

COMBINED LIQUID ROCKET ENGINE

Info

Publication number
RU2000102271A
RU2000102271A RU2000102271/06A RU2000102271A RU2000102271A RU 2000102271 A RU2000102271 A RU 2000102271A RU 2000102271/06 A RU2000102271/06 A RU 2000102271/06A RU 2000102271 A RU2000102271 A RU 2000102271A RU 2000102271 A RU2000102271 A RU 2000102271A
Authority
RU
Russia
Prior art keywords
rocket engine
combined liquid
liquid rocket
gas
turbopump
Prior art date
Application number
RU2000102271/06A
Other languages
Russian (ru)
Other versions
RU2183759C2 (en
Inventor
Николай Федорович Иванов
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 RU2000102271A priority Critical patent/RU2183759C2/en
Priority claimed from RU2000102271A external-priority patent/RU2183759C2/en
Publication of RU2000102271A publication Critical patent/RU2000102271A/en
Application granted granted Critical
Publication of RU2183759C2 publication Critical patent/RU2183759C2/en

Links

Claims (1)

Комбинированный жидкостный ракетный двигатель, включающий камеру с трактом регенеративного охлаждения и автономные турбонасосные агрегаты топливных компонентов, первый из которых снабжен приводом по замкнутой безгазогенераторной схеме с дожиганием, второй снабжен приводом по открытой газогенераторной схеме на основных компонентах топлива, отличающийся тем, что выходная полость турбины первого турбонасосного агрегата сообщена газоводом со смесительной головкой газогенератора привода второго турбонасосного агрегата.Combined liquid rocket engine, including a chamber with a regenerative cooling path and autonomous turbopump assemblies of fuel components, the first of which is driven by a closed gas-free generator circuit with afterburning, the second is equipped with an open gas generator drive on the main fuel components, characterized in that the turbine outlet cavity of the first the turbopump unit is communicated by the gas duct to the mixing head of the gas generator of the drive of the second turbopump unit.
RU2000102271A 2000-01-27 2000-01-27 Lox/liquid hydrogen engine RU2183759C2 (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
RU2000102271A RU2183759C2 (en) 2000-01-27 2000-01-27 Lox/liquid hydrogen engine

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
RU2000102271A RU2183759C2 (en) 2000-01-27 2000-01-27 Lox/liquid hydrogen engine

Publications (2)

Publication Number Publication Date
RU2000102271A true RU2000102271A (en) 2001-11-27
RU2183759C2 RU2183759C2 (en) 2002-06-20

Family

ID=20229984

Family Applications (1)

Application Number Title Priority Date Filing Date
RU2000102271A RU2183759C2 (en) 2000-01-27 2000-01-27 Lox/liquid hydrogen engine

Country Status (1)

Country Link
RU (1) RU2183759C2 (en)

Families Citing this family (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
RU2295052C2 (en) * 2005-03-09 2007-03-10 Открытое акционерное общество "Ракетно-космическая корпорация "Энергия" им. С.П. Королева" Liquid propellant rocket power plant
RU2455515C1 (en) * 2011-04-04 2012-07-10 Николай Борисович Болотин Three-stage booster-rocket, liquid propellant rocket engine and roll nozzle block
RU2474719C1 (en) * 2011-12-29 2013-02-10 Николай Борисович Болотин Hydrogen-oxygen liquid propellant rocket engine
RU2755848C1 (en) * 2020-06-23 2021-09-22 Федеральное государственное бюджетное образовательное учреждение высшего образования "Воронежский государственный технический университет" Combined-circuit cryogenic liquid propellant rocket engine (variants)
RU2765219C1 (en) * 2020-11-10 2022-01-26 Акционерное общество "КБхиммаш им. А.М. Исаева" Liquid rocket engine made according to the configuration without afterburning in the chamber

Family Cites Families (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2816417A (en) * 1952-08-13 1957-12-17 Gen Electric Control system for dual rotor pump drives
US3028729A (en) * 1960-04-12 1962-04-10 United Aircraft Corp Rocket fuel system
US3168807A (en) * 1961-08-08 1965-02-09 United Aircraft Corp Nuclear rocket flow control
US4171615A (en) * 1966-04-21 1979-10-23 The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration Supercharged topping rocket propellant feed system
DE3617757C1 (en) * 1986-05-30 1987-07-02 Erno Raumfahrttechnik Gmbh, 2800 Bremen, De
RU2052648C1 (en) * 1989-10-24 1996-01-20 Военная инженерно-космическая академия им.А.Ф.Можайского Method of operating electric rocket engine
RU2095607C1 (en) * 1995-07-19 1997-11-10 Ракетно-космическая корпорация "Энергия" им.С.П.Королева Cryogenic propellant rocket engine

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