SMALL GAS TURBINE ENGINE Russian patent published in 2023 - IPC F02K3/00 F23R3/32 F23R3/34 

FIELD: engine building.

SUBSTANCE: invention is related in particular to small-sized gas turbine engines with highly efficient energy indicators. A small engine consists of an inlet device, a centrifugal compressor, a combustion chamber, a turbine, a jet nozzle, fuel supply, cooling and lubrication systems. In the engine, high-pressure air from the compressor is supplied to cool the walls of the flame tube of the combustion chamber, then, heating up due to heat removal from the walls, it enters the combustion chamber through confuser-shaped channels made on the walls of the flame tube in the front part of the combustion chamber, causing the formation of two recirculation zones: primary zone and afterburning zone. The belts of holes for supplying fuel vapor are located on the walls of the fuel supply tubes and are located in the primary zone and the afterburning zone. The fuel-air mixture is formed by mixing fuel vapor with preheated air due to heat removal from the walls of the flame tube.

EFFECT: design of the combustion chamber makes it possible to increase the completeness of combustion to obtain the maximum permissible temperature (energy) to create aircraft thrust, as well as to improve the environmental performance of the engine.

1 cl, 2 dwg