METHOD FOR ARRANGEMENT OF WORKING PROCESS IN STRAIGHT-FLOW AIR-JET ENGINE WITH CONTINUOUS-DETONATION COMBUSTION CHAMBER AND DEVICE FOR IMPLEMENTATION THEREOF Russian patent published in 2020 - IPC F02K7/10 F02K7/14 

FIELD: physics.

SUBSTANCE: invention relates to methods of operating a working process in air-jet engines with continuous-detonation combustion and devices for their implementation, particularly for high-speed unmanned aerial vehicles. Method of working process organization in straight-flow air-jet engine with continuous-detonation combustion includes acceleration of aircraft to supersonic speed providing for beginning of autonomous flight of aircraft with such engine, partial deceleration of incoming supersonic air flow in skew races of seal and in wall boundary layer before arrival in annular combustion chamber, continuous supply of fuel to mixing zone with air, formation of detonation-capable mixture of fuel and air. Further, continuous-detonation combustion of fuel mixture is initiated, flow of detonation products from annular combustion chamber through annular nozzle with supersonic speed with formation of jet stream and creation of reactive thrust. Approaching supersonic air flow is first partially inhibited in skew jumps of the seal and in the wall boundary layer, and then accelerated in the fan of rarefaction waves with partial recovery of parameters of incoming supersonic air flow and enters the straight-flow air-jet engine in the form of weakly retarded supersonic air flow. One part of air is directed into annular combustion chamber. Other part, including wall boundary layer, is directed around annular combustion chamber to provide cooling of walls of annular combustion chamber and to prevent gas-dynamic effect of continuous-detonation combustion of fuel mixture and air in the annular combustion chamber for the course of weakly retarded supersonic air flow at the inlet of the straight-flow air-jet engine. Method is implemented in the device including a supersonic air intake, a central body, an annular combustion chamber with a belt of nozzles of fuel supply, a gas-dynamic insulator located between the annular combustion chamber and the external wall of the rear cone of the central body.

EFFECT: invention provides the possibility of autonomous flight with low Mach number.

7 cl, 2 dwg