IGNITION METHOD OF COMBUSTION CHAMBER OF AIRCRAFT GAS TURBINE ENGINES Russian patent published in 2020 - IPC F02C7/266 

FIELD: aviation.

SUBSTANCE: method of ignition of combustion chambers of aircraft engines consists in that air from compressor is supplied to combustion chamber, air is supplied from secondary circuit of combustion chamber into gap formed between ignition plug and special bushing installed between external housing of combustion chamber and housing of flame tube, air flow after its supply into gap between special bushing and ignition plug housing is simultaneously additionally passed through inner volume of ignition plug, in which ceramic insulator is installed, working end of which forms surface of spark gap on working end of ignition plug, this air flow from this inner cavity of ignition plug housing is brought into gap between housing of ignition plug and special bushing in zone of inner surface of working end face of special bushing, air from gap between special bushing and ignition plug is supplied into inner volume of flame tube parallel to plug axis through working end of special bushing, creating an electric discharge at the working end of the spark plug, feeding fuel sprayed by the injector onto the working end of the plug, air from the gap between the special bushing and the ignition plug is fed into the inner volume of the flame tube only on one side of the working end of the special bushing, facing the engine turbine, perpendicular to the fuel-air mixture movement in the ignition plug location area.

EFFECT: disclosed method of ignition of combustion chamber of aircraft gas turbine engines allows not only to expand the ignition of combustion chambers range and thereby to improve reliability of aircraft gas turbine engines start, but also reduce weight and overall dimensions of ignition systems, increase life of ignition devices, reduce logistics costs in operation.

1 cl, 5 dwg