FIELD: engines and pumps.
SUBSTANCE: liquid propellant rocket engine comprising a combustion chamber, a turbopump set, a drainage cavity connected with a drainage pipeline, at the same time the drainage cavity is located between an oxidant pump and a turbine, and the drainage pipeline is equipped with a gas ejector, at the same time the gas ejector is connected by a pipeline with a cavity downstream the turbine. The pipeline comprises a valve and a throttle.
EFFECT: increased efficiency of a system of LPRE cavities draining and removal of fuel components from them.
2 cl, 2 dwg
| Title | Year | Author | Number |
|---|---|---|---|
| LIQUID PROPELLANT ROCKET ENGINE | 2014 |
|
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|
RU2386844C1 |
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|
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|
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| THREE-COMPONENT LIQUID ROCKET ENGINE AND METHOD OF ITS OPERATION | 2010 |
|
RU2443894C1 |
| MULTISTAGE CARRIER ROCKET, METHOD OF ITS LAUNCHING, FOUR-COMPONENT ROCKET ENGINE AND FOUR COMPONENT GAS GENERATOR | 2009 |
|
RU2397116C1 |
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|
RU2300657C1 |
| MULTI-STAGE | 2008 |
|
RU2390476C1 |
| THREE-COMPONENT LIQUID PROPELLANT ROCKET ENGINE AND METHOD OF ITS OPERATION | 2008 |
|
RU2382223C1 |
| LIQUID-PROPELLANT ROCKET ENGINE | 2006 |
|
RU2302547C1 |
