LIQUID-PROPELLANT ROCKET ENGINE Russian patent published in 2010 - IPC F02K9/64 

Abstract RU 2396453 C1

FIELD: engines and pumps.

SUBSTANCE: proposed engine comprises oxidiser and fuel pumps, turbine to drive said pumps, chamber with cooling circuit with its outlet communicated with turbine inlet. In compliance with proposed invention, cooling circuit inlet communicates with oxidiser pump outlet, while chamber cooling circuit outlet accommodates temperature gauge connected with engine control system. Chamber cooling circuit, in contact with oxidiser, is made from copper alloys. Filter made from copper alloys is arranged at chamber cooling circuit inlet.

EFFECT: simplified design, reduced operating costs and expanded range of applicable fuels.

3 cl, 1 dwg

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Authors

Vovcharenko Konstantin Ivanovich

Garbera Stanislav Nikolaevich

Gorokhov Viktor Dmitrievich

Efimochkin Aleksandr Frolovich

Lipljavyj Igor' Vasil'Evich

Orlov Vadim Aleksandrovich

Rachuk Vladimir Sergeevich

Shostak Aleksandr Viktorovich

Dates

2010-08-10Published

2009-01-22Filed