FIELD: space.
SUBSTANCE: invention relates to aerospace engineering and can be used in rocket propulsion units operating on heavy hydrocarbon fuel with system without afterburning generator gas. Method for stabilization of combustion process in combustion chamber of liquid-propellant engine, which consists in two-stage heat supply at forced movement of medium, wherein additional controlled heat flow is fed into combustion chamber of rocket engine in the form of jet of high-temperature combustion products with the help of flash-type prechamber. Device for stabilization of combustion processes in combustion chamber of liquid-propellant engine, comprising housing, in which electric spark plug is installed, bushing, in which there is a fuel supply cavity, a fuel manifold, a mixing element, inside which a reaction cavity is formed, which narrows to the combustion chamber outlet, wherein the device located in the center of the combustion chamber above the jet unit of the rocket engine, comprises an antechamber, a prechamber body, which consists of a fire and power wall, the presence of a confusor and nozzles, nozzle unit, fuel supply to prechamber is carried out along two different lines. In the fire wall and in the part of the confusor there are belts of perforated holes providing tangential fuel supply, and axes of which do not intersect the axis of the prechamber. Device is equipped with external and internal cooling system and includes assembled collectors, cooling paths with corrugations and longitudinal ribs.
EFFECT: invention provides a stable working process in a wide range of throttling, preventing occurrence of a self-oscillatory process.
4 cl, 1 dwg
