GAS TURBINE ENGINE ANNULAR COMBUSTION CHAMBER Russian patent published in 2018 - IPC F23R3/50 F23R3/46 

FIELD: motors and pumps.

SUBSTANCE: invention relates to combustion chambers of gas turbine engines using liquid fuel, preferably aircraft engines. Annular combustion chamber of the gas turbine engine comprises a flame tube, a front device, a fairing with an open front central part and a diffuser. Diffuser comprises an outer wall, an inner wall and two annular baffles therebetween, forming three annular passages inside the diffuser to supply air to the combustion chamber. Each partition consists of a main section, an entrance area and an exit section. Edges of the entrance sections of the partitions are made sharp. Output sections of the partitions protrude against the walls of the diffuser and have a shape that prevents the escape of air flow and formation of backward current zones in the wake behind them. Surfaces of the main sections of the partitions have a conical shape. Edges of the open front of the fairing lie on the continuation of the forming surfaces of the main sections of the partitions.

EFFECT: invention is aimed at reducing the formation of nitrogen oxides by burning fuel in the combustion chamber of a gas turbine engine.

3 cl, 2 dwg