FIELD: motors and pumps.
SUBSTANCE: invention relates to aviation and rocket engineering and may be used for airplanes or other aircrafts power plant development operating on air jet engines. Gas liquid jet engine contains inlet device, external circuit, internal circuit represented with gas turbine engine and combination chamber for both circuits. According to the invention, the external circuit of the engine is combined with the external circuit of power plant (engine nacelle) and profiled geometric elements located in circuit nozzles. Mixed gases are intensified to supersonic modes at combination chamber inlet. The combination chamber exceeds diametrical dimensions of maximum external circuit channel diameter. The combination chamber is provided with supersonic mixed gas flow converter into subsonic flow. The converter is represented with cylindrical channel with cross section area corresponding to the critical cross section when speed is smoothly transmitted into subsonic flow through the sound speed. The converter is a place of surge formation during direct shock wave transfer into the subsonic flow within the expanding nozzle, which is implemented as exhaust diffuser.
EFFECT: reduction of specific fuel consumption by principle change of engine design.
1 dwg
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