LIQUID-FUEL ROCKET ENGINE WITH AFTERBURNING OF OXIDATION TURBOGAS

摘要

A liquid-fuel rocket engine (LFRE) with afterburning of oxidation turbogas comprises a chamber, a turbopump assembly with turbine, oxidizer pump and fuel pump, an oxidizer booster pump, lines of oxidizer and gas generator fuel and fuel line of the chamber, there start-shutoff valves are placed, gas line between the turbine and chamber. Additionally to design are included control devices: differential analyzer of pressure drop and pressure controller. At that one of the cavities of differential signaler of pressure drop is connected to input mains of oxidizer booster pump, the other – to output one, and pressure signaler is placed in any place of gas mains. Such technical solution provides switch off of LFRE without destruction of construction of turbine and gas mains that connects turbine and chamber in the case of working out oxidizer, makes it possible to eliminate non-stable self-switch off of LFRE I the case of fuel working out.