DEVICE DETERMINING BOUNDARY OF APPEARANCE OF INSTABILITY OF OPERATION PROCESS IN GAS GENERATOR OF LIQUID-PROPELLANT ROCKET ENGINE Russian patent published in 2002 - IPC

FIELD: rocket engineering. SUBSTANCE: device determining boundary of appearance of instability of operation process in gas generator of liquid-propellant rocket engine has injector head linked by gas supplying line to combustion chamber, system feeding fuel components, system recording measurement of parameters of process of burning. Across outlet from gas generator there installed in sequence: throttling orifice simulating hydraulic resistance of turbine of turbo-driven pump assembly, throttling orifice simulating critical section of main combustion chamber and by-pass conduits laid in parallel and fitted with relief valves communicating spaces of main combustion chamber or gas generator with space of transcritical section of nozzle. EFFECT: reduced time and expenses for adjustment of gas generator of liquid-propellant rocket engine of closed circuit for stability of combustion process, replication of combustion process with high-frequency vibration. 4 cl, 3 dwg