GAS TURBINE ENGINE COMBUSTION CHAMBER Russian patent published in 2023 - IPC F23R3/12 

FIELD: aircraft engine construction.

SUBSTANCE: invention relates to aircraft engine construction, in particular to gas turbine engines with combustion chambers with radial fuel supply via a sawing disc on the rotor shaft. A gas turbine engine annular combustion chamber contains a casing, a flame tube with a number of apertures for supplying air in the combustion zone and a mixing zone for reducing gas temperature before the turbine atomizing disk on the fuel supply rotor shaft, an ignition plug, an annular collector connected via a pipe to the connector of additional air in an atomizing disk cavity is installed in the basis of a flame tube.

EFFECT: invention provides possibility to reduce engine starting time by means of quality fuel atomizing and mixing with additional air (or oxygen) in the ignition zones, and stabilizing fuel-air mixture combustion during engine starting.

1 cl, 1 dwg