LIQUID PROPELLANT ROCKET ENGINE COMBUSTION CHAMBER MIXING HEAD Russian patent published in 1999 - IPC

FIELD: heavy thrust rocket engines. SUBSTANCE: combustion chamber mixing head has equalizing mixing space connected with spaces of cooling unit of injector face, generator gas supply unit and combustion chamber. Channels are made over perimeter of injector face opposite to peripheral nozzles on section whose width does not exceeds diameter of oxidizer nozzle passage area. These channels connect combustion chamber space with injector face cooling unit space. Optimum operating conditions of mixing head are provided when area of channels located at each peripheral nozzle is 0.15-0.2 of area of passage of oxidizer nozzle (for instance, oxygen nozzle). EFFECT: increased economy of operation of combustion chamber, increased thrust specific pulse. 2 cl, 5 dwg