GAS TURBINE ENGINE Russian patent published in 2009 - IPC F02C7/36 

FIELD: engines and pumps.

SUBSTANCE: invention relates to engine production, particularly, to aircraft gas turbine engine and gas turbine plants drive assemblies. The proposed gas turbine engine comprises low-pressure compressor shaft, high-pressure compressor shaft, driving gear wheel transmitting torque from the high-pressure compressor shat to the central drive via a splined joint. Note that the low-pressure compressor shaft accommodates a sleeve with labyrinth seal knife edges, while the driving gear wheel accommodates a sleeve with sealing coating to form with the said gear wheel circular radial chambers communicating with the inlet chamber arranged between the said chambers and with the central drive chamber via the holes furnished in the sleeve with sealing coating and those of driving gear wheel and high-pressure compressor shaft. In operation, oil vapours coming from the central drive chamber into circular inlet chamber get accumulated of the surface in the form of oil film due to action of centrifugal force produced by running rotors. Accumulated oil flows, via radial holes, into the chamber from which it is uniformly distributed over the splined-joint gaps to lube the splines and to flow out into the circular chamber. Now, the oil is forced through radial holes into the chamber.

EFFECT: continuous lubrication of splines preventing their premature wear-out.

2 dwg