SMALL-SIZE TURBOJET ENGINE WITH ANNULAR EVAPORATIVE COMBUSTION CHAMBER AND TWO-ZONE FUEL SUPPLY Russian patent published in 2025 - IPC F02K3/00 F23R3/32 F23R3/34 

FIELD: mechanical engineering.

SUBSTANCE: invention relates to engine building and, in particular, to small-size gas turbine engines with high efficiency. Small-size engine consists of inlet device, centrifugal compressor, evaporation combustion chamber with two-zone fuel supply, turbine, 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, being heated 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 formation of a circulating flow in the primary zone, from which combustion products enter the afterburning zone, then into the mixing zone to form the temperature field and exit the combustion chamber into the turbine. Fuel feed tubes of two types have different lengths for supply of fuel to the primary zone and to the after-burning zone. Belts of holes for supply of fuel vapours are located on walls of fuel supply tubes and are arranged in primary zone and after-burning zone. Fuel-air mixture is formed due to mixing of fuel vapours with air. A portion of the air is used to cool the walls of the blades of the nozzle apparatus located in the region of high temperatures.

EFFECT: such design of combustion chamber allows to increase completeness of combustion to obtain maximum allowable temperature (energy) for creation of aircraft thrust, as well as to increase ecological properties of the engine.

1 cl, 3 dwg