RU2015109344A - Rocket Engine - RD - Google Patents

Rocket Engine - RD Download PDF

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Publication number
RU2015109344A
RU2015109344A RU2015109344A RU2015109344A RU2015109344A RU 2015109344 A RU2015109344 A RU 2015109344A RU 2015109344 A RU2015109344 A RU 2015109344A RU 2015109344 A RU2015109344 A RU 2015109344A RU 2015109344 A RU2015109344 A RU 2015109344A
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RU
Russia
Prior art keywords
gas
throttle
fuel
tank
oxidizer
Prior art date
Application number
RU2015109344A
Other languages
Russian (ru)
Other versions
RU2643282C2 (en
Inventor
Николай Михайлович Пикулев
Original Assignee
Николай Михайлович Пикулев
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 Николай Михайлович Пикулев filed Critical Николай Михайлович Пикулев
Priority to RU2015109344A priority Critical patent/RU2643282C2/en
Publication of RU2015109344A publication Critical patent/RU2015109344A/en
Application granted granted Critical
Publication of RU2643282C2 publication Critical patent/RU2643282C2/en

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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02K—JET-PROPULSION PLANTS
    • F02K9/00—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
    • F02K9/42—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof using liquid or gaseous propellants
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23Q—IGNITION; EXTINGUISHING-DEVICES
    • F23Q3/00—Igniters using electrically-produced sparks

Abstract

Ракетный двигатель, содержащий газогенератор, связанный газоводами с теплообменником и смесительной головкой камеры сгорания, связанной через дроссель с баками горючего и окислителя, снабженный системой автоматического запуска и управления, отличающийся тем, что газогенератор оснащен запальным устройством со свечей зажигания, форсункой, соединенной с воздушным баллоном (180 ат.), баком горючего, а также двумя инжекторами с форсунками, один из которых присоединен через дроссель к баку с горючим, другой через дроссель к баку с окислителем, при этом оба инжектора через газозаборники соединены с полостью высокого давления газогенератора, а третий газозаборник через предохранительный клапан соединен с теплообменником, который трубами связан с баком горючего и окислителя.A rocket engine containing a gas generator, connected by gas ducts to a heat exchanger and a mixing head of a combustion chamber, connected through a throttle to fuel and oxidizer tanks, equipped with an automatic start-up and control system, characterized in that the gas generator is equipped with an ignition device with a spark plug, an injector connected to an air cylinder (180 at.), A fuel tank, as well as two injectors with nozzles, one of which is connected through a throttle to a fuel tank, the other through a throttle to a tank with an oxidizer, in this case, both injectors are connected through the gas inlets to the high-pressure cavity of the gas generator, and the third gas inlet is connected through a safety valve to the heat exchanger, which is connected by pipes to the fuel and oxidizer tank.

Claims (1)

Ракетный двигатель, содержащий газогенератор, связанный газоводами с теплообменником и смесительной головкой камеры сгорания, связанной через дроссель с баками горючего и окислителя, снабженный системой автоматического запуска и управления, отличающийся тем, что газогенератор оснащен запальным устройством со свечей зажигания, форсункой, соединенной с воздушным баллоном (180 ат.), баком горючего, а также двумя инжекторами с форсунками, один из которых присоединен через дроссель к баку с горючим, другой через дроссель к баку с окислителем, при этом оба инжектора через газозаборники соединены с полостью высокого давления газогенератора, а третий газозаборник через предохранительный клапан соединен с теплообменником, который трубами связан с баком горючего и окислителя. A rocket engine containing a gas generator, connected by gas ducts to a heat exchanger and a mixing head of a combustion chamber, connected through a throttle to fuel and oxidizer tanks, equipped with an automatic start-up and control system, characterized in that the gas generator is equipped with an ignition device with a spark plug, an injector connected to an air cylinder (180 at.), A fuel tank, as well as two injectors with nozzles, one of which is connected through a throttle to a fuel tank, the other through a throttle to a tank with an oxidizer, in this case, both injectors are connected through the gas inlets to the high-pressure cavity of the gas generator, and the third gas inlet is connected through a safety valve to the heat exchanger, which is connected by pipes to the fuel and oxidizer tank.
RU2015109344A 2015-03-17 2015-03-17 Rocket engine RU2643282C2 (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
RU2015109344A RU2643282C2 (en) 2015-03-17 2015-03-17 Rocket engine

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
RU2015109344A RU2643282C2 (en) 2015-03-17 2015-03-17 Rocket engine

Publications (2)

Publication Number Publication Date
RU2015109344A true RU2015109344A (en) 2016-10-10
RU2643282C2 RU2643282C2 (en) 2018-01-31

Family

ID=57122262

Family Applications (1)

Application Number Title Priority Date Filing Date
RU2015109344A RU2643282C2 (en) 2015-03-17 2015-03-17 Rocket engine

Country Status (1)

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RU (1) RU2643282C2 (en)

Family Cites Families (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JP3012329B2 (en) * 1991-06-27 2000-02-21 ティー アール ダブリュ インコーポレーテッド High performance dual mode integral propulsion system
DE4305154C1 (en) * 1993-02-19 1994-05-26 Deutsche Aerospace Coaxial fuel injectors for combustion chamber in rocket - has central body and sleeve, opening in plane of combustion chamber end face, and flow divider
RU2084767C1 (en) * 1994-07-25 1997-07-20 Малое инновационное предприятие Научно-исследовательского института тепловых процессов "Теплоэн" Ignition device
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)

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RU2643282C2 (en) 2018-01-31

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