FIELD: engines and pumps.
SUBSTANCE: liquid propellant rocket engine with controlled thrust vector, which contains power frame, combustion chamber having head, cylindrical part and nozzle fixed on power frame by means of suspension assembly, drives attached to power ring made on combustion chamber, gas generator and turbine pump unit, with turbine, oxidiser pump, gas line connecting the turbine outlet to combustion chambers head through suspension assembly; at that, roll nozzles are grouped into blocks in pairs and mounted on ring header installed in lower part of the nozzle the diameter of which is more than the nozzle cross section diameter; to ring header there connected is gas-generator gas extraction pipeline the other end of which is connected to gas line; ring header is fixed by means of two hinged rods to turbine pump unit and by means of two hinged rods to damping bracket installed on extraction pipeline of gas-generator gas. In the area of critical section of combustion chamber, concentrically to it and with a gap there installed is additional power ring to which through damping support there attached is extraction pipeline of gas-generator gas, and two hinged rods are attached, the ends of which are connected to ring header. To each roll nozzle there supplied from fuel pump is fuel supply tube; at that, each of them is equipped with start-up cut-off valve. All roll nozzles are equipped with ignition device. Block of roll nozzles includes two roll nozzles combined into one assembly; at that, pair of roll nozzles is installed opposite and equipped with three-way valve installed between them; three-way valve is equipped with the drive connected to the shaft.
EFFECT: higher efficiency.
5 cl, 5 dwg
