发明名称 LIQUID PROPELLANT ROCKET ENGINE
摘要 FIELD: engines and pumps.SUBSTANCE: proposed engine comprises combustion chamber, gas generator, turbopump unit, booster turbopump with gas turbine and heat exchanger. In compliance with this invention, heat exchanges cold inlet is communicated with oxidizer pump outlet. heat exchanges cold outlet is connected via booster turbopump gas feed line with turbopump turbine inlet. Turbine outlet is connected with oxidizer inlet line.EFFECT: ruled out high-temperature power gas as booster turbopump turbine drive working fluid.1 dwg
申请公布号 RU2551712(C1) 申请公布日期 2015.05.27
申请号 RU20140111549 申请日期 2014.03.25
申请人 OTKRYTOE AKTSIONERNOE OBSHCHESTVO "KONSTRUKTORSKOE BJURO KHIMAVTOMATIKI" 发明人 VOVCHARENKO KONSTANTIN IVANOVICH;EFIMOCHKIN ALEKSANDR FROLOVICH;ELISEEV ALEKSANDR VLADIMIROVICH
分类号 F02K9/42 主分类号 F02K9/42
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