TURBO ENGINE AND METHOD FOR OPERATION THEREOF Russian patent published in 2018 - IPC F02C5/10 F02K7/04 F02K3/10 

FIELD: engine building.

SUBSTANCE: invention relates to a turbojet engine and method of its operation. Single-shaft turbojet engine contains a compressor, a turbine, the main continuous-detonation combustion chamber with fuel supply channels, fuel injectors and initiator of detonation, gas-dynamic damper, nozzle apparatus and turbine. Four continuous-detonation combustion chambers are located in the exhaust cavity of the engine, having the form of closed circular sectors, the input of each of which is connected to the air channel of the external circuit. Main combustion chamber inlet is connected to the air duct of the internal circuit. Bypass ratio of the engine is equal to or greater than one. On the motor shaft there is an electric machine connected to the battery pack. Ring piezoelectric generator consisting of two parts separated by a buffer is also connected to the battery pack. Around the inner surfaces of the main and exhaust combustion chambers, annular cooling shirts with permeable matrix nozzles and fuel injector units are installed. To cool the outer surfaces of four exhaust combustion chambers in places in contact with the hot gas stream coming out of the turbine, an annular cooling cavity with matrix nozzles and a fuel injector block is installed. Engine has an automatic control system that includes a computer, associated with the control channel, fuel control valves, controlled air dampers, temperature and pressure sensors.

EFFECT: invention is aimed at improving the thermodynamic efficiency of the engine, thrust, reducing the weight and size characteristics, and expanding the range of variation of the thrust vector.

2 cl, 5 dwg