LIQUID-PROPELLANT ENGINE WITH AFTERBURNING OF EXHAUST TURBINE GAS IN SUPERSONIC PART OF THE NOZZLE AND WITH CONTROLLED THRUST VECTOR

摘要

The invention relates to rocket-space engineering and can be used as sustainer liquid rocket engine of the higher stages of carrier rockets and acceleration blocks of spacecrafts. A liquid rocket engine with afterburning of exhaust turbine generator gas in supersonic part of the nozzle and with controlled thrust vector comprises a combustion chamber with supersonic nozzle, turbo-pump system for supply of fuel components with gas generator and with turbine of active type exhaust collector of which is connected by gas conduit to circular collector of the system for injection of exhaust turbine gas to the nozzle. For afterburning of generator gas and control of thrust vector of chamber of the engine in the wall in supersonic part of the nozzle jets are provided for injection of oxidation component of fuel connected with one circular collector divided with partitions into eight sections that are connected by a system of pipelines to high-pressure main of the engine. For control of thrust vector of the engine each two opposite in diameter sections that are placed in the planes for pitch and yaw control of thrust vector, connected to each other by a pipeline with distributor valve. The inlet branch pipe of each distributor valve is connected by a pipeline to distributor valve for supply of oxidation component to the system for thrust vector control and to intermediate sections of injection of oxidizer for afterburning of generator gas. Advantage of the invention is in increase of functionality of the system for the engine thrust vector control due to use of new pattern of distribution of losses of oxidation fuel component and increase of thrust vector control efficiency.