GAS PASSAGE OF LIQUID PROPELLANT ROCKET ENGINE Russian patent published in 2002 - IPC

FIELD: rocketry. SUBSTANCE: gas passage of liquid propellant rocket engine of closed layout is installed between turbine of turbopump set and injector unit of combustion chamber head being made in form of curvilinear diffuser with mixing straightening grid installed before injector unit of combustion chamber head. Gas passage has additional nozzle straightening grid in form of set of small-size nozzles installed behind turbine of turbopump set. EFFECT: provision of additional head at starting and speeding up in gas passage behind turbine for elimination of sharp overspeeding of turbopump set exceeding maximum tolerable values. 3 cl, 2 dwg