FIELD: engine building.
SUBSTANCE: invention relates to rocket jet engines. The universal rocket engine (URE) for a cruise missile, subsonic, supersonic and hypersonic plane, spaceplane, comprises a system for forming and injecting high-pressure gaseous or liquid fuel, an apparatus for injection of an oxidising mixture and water; a narrowing adjustable air intake with a rectangular or triangular cross-section; an adjustable nozzle; a multi-sectional combustion chamber with a system for simultaneous ignition along the entire length of the combustion chamber. Installed in the sections of the combustion chamber are frontal valves with an axis of rotation and a spring mechanism located on said axis. The engine comprises a back retractable valve with an axis of rotation.
EFFECT: achieved upon implementation of the invention are an increase in the thermodynamic efficiency and a reduction in the specific fuel consumption due to the increase in the amplitude of pressure pulsations, increase in the degree of compression and flow mass of the air in the combustion chamber, increase in the combustion rate of the combustible mixture, use of detonation modes of combustion of the fuel.
7 cl, 35 dwg
