[특허]Liquid-propellant rocket engine with turbine gas afterburning

[미국특허] Liquid-propellant rocket engine with turbine gas afterburning 원문보기

IPC분류정보
국가/구분	United States(US) Patent 등록
국제특허분류(IPC7판)	F02K-009/48 F02K-009/52
출원번호	US-0393435 (1999-09-10)
우선권정보	RU0100839 (1999-01-21)
발명자 / 주소	Katorgin Boris Ivanovich,RUX Chvanov Vladimir Konstantinovich,RUX Derkach Gennady Grigorievich,RUX Movchan Jury Vasilievich,RUX Chelkis Felix Jurievich,RUX Semenov Vadim Iliich,RUX Tolsti
출원인 / 주소	Otkrytoe Aktsionernoe Obschestvo Nauchno-Proizvodstvennoe Obiedinenie "Energomash" Imeni Akademika V.P. Glushko, RUX
대리인 / 주소	Blakely Sokoloff Taylor & Zafman
인용정보	피인용 횟수 : 23 인용 특허 : 3

초록 ▼

The engine comprises a chamber, fuel and oxidizer booster pumps, a turbopump unit, a gas generator, an electrically driven thrust regulator, and a fuel throttle. A programmable starting and ignition system is introduced, which includes a fuel tank, connected to the thrust regulator, and a first ampoule with starting fuel, an output of which through a starting/cut-off valve is connected to fuel injectors of the gas generator. The aforesaid tank is also connected through a second ampoule to the starting fuel and by a jet to autonomous ignition injectors located in the space of the combustion chamber of the engine. An inclined Archimedian screw pump with a gas turbine as an actuator and an oxidizing gas as a working medium is used as an oxidizer booster pump. The gas is discharged after its use in a turbine into an outlet manifold of the booster pump. A heat exchanger, in which the gas used for rocket tank pressurization is heated, is mounted on a pipeline feeding the gas to the aforesaid gas turbine of the booster pump actuator.

대표청구항 ▼

[ What is claimed is:] [1.]1. A liquid-propellant rocket engine with turbine gas afterburning comprising:a combustion chamber, inside which a mixing head for a working mixture is mounted and in which ignition injectors are provided;booster prepumps--a fuel booster pump and an oxidizer booster pump, mounted at an engine inlet;a turbopump unit comprising a turbine, a single-stage oxidizer pump and a two-stage fuel pump, which are made as centrifugal inclined Archimedian screw pumps and inlet main lines of which are connected to said booster prepumps respectively, an outlet of the first stage of the two-stage fuel pump is connected through a throttle sequentially to cooling passages of said chamber and through a start cut-off valve further to the mixing head of said combustion chamber;a gas generator mixing head with injectors of which through an oxidizer start/cut-off valve is connected to an outlet of said oxidizer turbopump unit and through a thrust regulator is connected to an outlet of the second stage of the two-stage fuel pump of said turbopump unit, an outlet of the gas generator is connected to an inlet into said turbine of the turbopump unit, and through a gas feed line is connected to an inlet of said mixing head of the combustion chamber;a programmable start and ignition device made with a starting tank with fuel, the tank being connected through a first check valve to said thrust regulator controlled by an electric drive, a first ampoule with starting fuel, an outlet of which through a start/cut-off valve is connected to injectors of said mixing head of the gas generator, wherein said starting tank is connected through a second check valve, a second ampoule with starting fuel and a jet to ignition injectors of the combustion chamber, and through a fill check valve is connected to a main fuel feed line to an input of the fuel pump.

이 특허에 인용된 특허 (3) 인용/피인용 타임라인 분석

Meng Sen Y. (Reseda CA), Heat induced high pressure lox pump rocket engine cycle.
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Foust Robert R., Rocket engine auxiliary power system.
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Stewart Warner L. (Parma Heights OH) Ginsburg Ambrose (South Euclid OH) Hartmann Melvin J. (Westlake OH), Supercharged topping rocket propellant feed system.
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이 특허를 인용한 특허 (23) 인용/피인용 타임라인 분석

Beck, Philip; Kutter, Bernard; Zegler, Frank, Airborne gas storage and supply system.
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Fisher, Steven C., Bi-propellant injector with flame-holding zone igniter.
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Fowler,Robert B.; Joyner,Claude R., Booster rocket engine using gaseous hydrocarbon in catalytically enhanced gas generator cycle.
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Fisher, Steven C., Coaxial ignition assembly.
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Yu, Tai, Compact cyclone combustion torch igniter.
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Knight, Andrew F., Cool gas generator and ultra-safe rocket engine.
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Greene,William D., Dual expander cycle rocket engine with an intermediate, closed-cycle heat exchanger.
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Hewitt, Ross A., Expander cycle rocket engine with staged combustion and heat exchange.
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Kline, Korey R.; Smith, Kevin W.; Cesaroni, Anthony Joseph, Flame holder for a hybrid rocket motor.
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Kline, Korey R.; Smith, Kevin W., Hybrid rocket motor having a precombustion chamber.
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Kline, Korey R.; Smith, Kevin W., Hybrid rocket motor having a precombustion chamber.
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Kline, Korey R.; Smith, Kevin W.; Bales, Thomas O., Hybrid rocket motor using a turbopump to pressurize a liquid propellant constituent.
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Kline, Korey R.; Smith, Kevin W.; Schmidt, Eric E.; Bales, Thomas O., Hybrid rocket motor using a turbopump to pressurize a liquid propellant constituent.
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Gudmundson, Chris, Hydrogen based combined steam cycle apparatus.
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Jensen, Jeff; Claflin, Scott, Igniter/thruster with catalytic decomposition chamber.
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Johnson, Gabriel L; Sexton, Thomas D, Johnson Sexton cycle rocket engine.
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Chris Udo Maeding DE, Liquid fuel rocket engine with a closed flow cycle.
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Giffin, Rollin George, Methods and systems for operating oxidizer systems.
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Horn, Mark D.; Walczuk, Thomas M., Piezo-resonance igniter and ignition method for propellant liquid rocket engine.
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Horn, Mark D.; Walczuk, Thomas M., Piezo-resonance igniter and ignition method for propellant liquid rocket engine.
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Mango, Frank S., Propellant management system and method for multiple booster rockets.
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Balepin, Vladimir V., Rocket engine.
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Fisher, Steven C.; Brodeur, Tim, Sequence diagram system.
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IPC	Description
A	생활필수품
A62	인명구조; 소방(사다리 E06C)
A62B	인명구조용의 기구, 장치 또는 방법(특히 의료용에 사용되는 밸브 A61M 39/00; 특히 물에서 쓰이는 인명구조 장치 또는 방법 B63C 9/00; 잠수장비 B63C 11/00; 특히 항공기에 쓰는 것, 예. 낙하산, 투출좌석 B64D; 특히 광산에서 쓰이는 구조장치 E21F 11/00)
A62B-1/08	.. 윈치 또는 풀리에 제동기구가 있는 것

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[미국특허] Liquid-propellant rocket engine with turbine gas afterburning 원문보기