METHOD OF IGNITING AIRCRAFT GAS TURBINE COMBUSTION CHAMBER Russian patent published in 2012 - IPC F02C7/266 H01T13/16 

FIELD: engines and pumps.

SUBSTANCE: air is fed from compressor into combustion chamber. Air is fed from combustion chamber secondary circuit into clearance between ignition plug and special sleeve arranged between combustion chamber outer casing and fire tube casing. Air is fed from clearance between special sleeve and ignition plug into fire tube inner chamber in parallel with plug axis via special sleeve work end. Electric discharge is initiated at ignition plug work end and fuel sprayed by nozzle is fed to plug work end. Air from aforesaid clearance is fed into fire tube only from special sleeve work end one side facing engine turbine, perpendicular to fuel-mix direction in the area of ignition plug.

EFFECT: higher reliability, decreased weight and dimensions.

6 dwg