FLUID-PROPELLANT ENGINE WITH AFTERBURNING OF WORKED OUT ON TURBINE GENERATOR GAS AND CONTROLLED THRUST VECTOR

摘要

A liquid-propellant engine with turbo-pump system of supply of two fuel components to chamber of the engine and afterburning of worked out on turbine generator gas in supersonic section of jet comprises a combustion chamber with supersonic nozzle, those have cooling sections with fuel inlet and outlet collectors, a turbo-pump system for supply of fuel components with gas generator that operates on main components of fuel with large excess of fuel, and with turbine of active type exhaust collector of which is connected with gas duct to circular gas collector arranged in the middle section of supersonic nozzle with circular slot for blast of worked out on turbine generator gas, this connects cavity of blast collector to cavity of nozzle, injection jets for injection of oxidation fuel component to nozzle, those are arranged in the wall of the nozzle with uniform arrangement in perimeter of cross section of the nozzle and are combined with one fuel collector that is connected by pipeline to high-pressure mains of oxidation component of fuel. In collector of jet for injection of oxidation fuel component to nozzle four partitions are provided, those divide it into four sections. Axis of symmetry of each section is placed in planes of rocket stage flight control as in pitch and course. Each two opposite in diameter sections of injection are connected to each other with pipeline with flow control device with controlled drive connected to vehicle flight control system. Inlet branch pipe of hydro-distributor is connected to pipeline for supply of oxidation component for afterburning of exhaust generator gas in nozzle.