COMBUSTION STABILIZATION DEVICE FOR THRUST CHAMBER OF LIQUID PROPELLANT ROCKET ENGINE

摘要

PROBLEM TO BE SOLVED: To simplify a system of a liquid propellant rocket engine, increase the reliability of the engine and reduce the period of time of and the cost of manufacture, by adopting the endoergic cooling method. SOLUTION: A combustion stabilization device for a thrust chamber of the liquid propellant rocket engine comprises a hollow hub member the upper and lower portions of which are opened, a plurality of blade rib members each of which keeps one end detachably connected to an outer surface of the hub member, and a hollow blade connecting member the upper and lower portions of which are opened. The other ends of the blade rib members are connected to an inner side of the blade connecting member. COPYRIGHT: (C)2005,JPO&NCIPI