GAS TURBINE COMBUSTION CHAMBER IGNITER Russian patent published in 2008 - IPC F02C7/266 H01T13/06 

FIELD: engines and pumps.

SUBSTANCE: proposed igniter as arranged inside a sleeve, its end face being provided with an orifice aligned with its inner space and communicating the aforesaid space with turbine combustion chamber. Note that the said sleeve is furnished with an extra space arranged inside the sleeve casing provided with an orifice communicating the said extra space with the sleeve outer surface facing the combustion chamber inlet. Note that the sleeve casing is furnished additionally with, at least, one orifice communicating the said extra space with the sleeve inner space and orifices communicating the extra space with the space formed by the coaxial orifice in the sleeve working end face and the combustion chamber walls on the sleeve working end face side. The igniter spark plug body is made stepwise, the transition from the greater to smaller diameters being made perpendicular to the plug and sleeve axes. The smaller-diameter plug surface is arranged in the sleeve end face orifice. The said plug working end face is arranged between the sleeve working end face inner and outer surfaces. The orifices communicating the extra space with sleeve working end face orifice communicate also with the annular gap formed by the smaller-diameter plug body and the sleeve working end face orifice aligned with the latter.

EFFECT: higher reliability of starting aircraft gas turbine engines.

5 dwg