LIQUID PROPELLANT ROCKET ENGINE WITH CONTROLLED VECTOR OF THRUST AND UNIT OF COMBUSTION CHAMBER SUSPENSION

摘要

FIELD: engines and pumps.;SUBSTANCE: liquid propellant rocket engine with controlled thrust vector, comprising power frame, combustion chamber, having head, cylindrical part and nozzle, which is fixed on power frame with the help of suspension unit, providing for possibility of swinging by means of two drives, installed in mutually-perpendicular planes, gas generator and turbopump set, comprising, in its turn, turbine, pump of oxidiser, fuel pump, gas duct, connecting outlet from turbine with head of combustion chamber via suspension unit, at the same time gas generator is fixed to power frame with the help of hinged joint, fixed in its upper point, gas duct is rigidly fixed to power plate, inside gas duct there is a central traction rod fixed by means of ball joint, passing inside suspension unit, other end of which is rigidly connected to perforated plate, installed inside head of combustion chamber, unit of suspension is arranged in the form of upper and lower flanges with flexible element, for instance, bellows, between them. Drives are arranged in the form of hydraulic cylinders, fixed hingedly to power frame, stems of which are fixed to lower ring of suspension unit. Specified tasks are solved in suspension unit of combustion chamber of liquid propellant rocket engine, comprising upper flange, rigidly connected to gas duct and lower flange rigidly connected to head of combustion chamber, and flexible element, for instance, bellows, between them, differing by the fact that inside flexible element there is a central power traction rod installed, one end of which with the help of ball hinged joint is fixed inside on gas duct, and the other one - on perforated plate installed inside head of combustion chamber. Flexible element from inside may be closed by two independent sleeves, installed partially one into the other with gap. Flexible element from outside is closed by two independent sleeves, installed partially one into the other with gap.;EFFECT: simplified suspension unit of liquid propellant rocket engine chamber and improvement of its reliability.;5 cl, 3 dwg