FIELD: aircraft industry.
SUBSTANCE: proposed aircraft ramjet engine has air intake and combustion chamber arranged in succession. Inlet of combustion chamber is combined with air supply duct. It has also gas generator whose outlet is connected by fuel duct with inlet of injector forming fuel jets directed into combustion chamber. Engine is furnished also with transfer zone in form of constant-section chamber located after combustion chamber. At least one injector is located in end of combustion chamber, and fuel jet formed by injector has at outlet supersonic velocity with component counter main gas flow forming de Laval nozzle in form of free boundary layer between main flow and fuel-air jets. Walls of combustion chamber are made widening, with half-angle of diversion within 5° and 15°.
EFFECT: increased efficiency of operation of aircraft ramjet engines.
4 cl, 4 dwg
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