COMBUSTION CHAMBER OF A GAS TURBINE ENGINE Russian patent published in 2022 - IPC F23R3/38 

FIELD: engine building.

SUBSTANCE: invention relates to gas turbine engines (GTE) and can be used in annular combustion chambers of aircraft GTE. Combustion chamber of a gas turbine engine containing a compressor and a compressor turbine, comprises a rotating nozzle secured on the rotor of the turbocharger. Additionally installed in the combustion chamber is a deflector assembly consisting of two disk-type deflectors: a stationary one with fixed blades and a rotating one with mobile blades. The stationary deflector has a smooth curved shape and is attached to the front wall of the combustion chamber with the inner annular surface thereof. The rotating deflector is attached to the cylindrical surface of the rotating nozzle with the inner annular surface thereof, and holes are made thereon to ensure inflow of air into the inner cavity of the deflector assembly. Blades are located on the peripheral parts of the inner surfaces of both deflectors along the circumferences in the radial direction. Two rows of radial holes are made on the cylindrical surface of the rotating nozzle, the peripheral part of the stationary deflector is located in the plane of rotation of the left row of radial holes, and the mobile blades of the rotating deflector are located in the plane of rotation of the right row of radial holes.

EFFECT: uniformity of the resulting fuel-air mixture, increase in the completeness of fuel combustion, reduction of hazardous atmospheric emissions, fuel conservation.

1 cl, 2 dwg