JET TURBINE ENGINE Russian patent published in 2015 - IPC F01D25/16 F02C7/06 F02C7/47 

FIELD: engines and pumps.

SUBSTANCE: jet turbine engine comprises a fan (2) with an inlet bell mouth (3) on the runner (4) and an angular-contact thrust bearing (5) with labyrinth seals of an oil cavity (7), and also a low pressure compressor (8) and a high pressure compressor (9). From the front side of labyrinth seals the ring cavity of high pressure cooling air and a ring cavity of the high pressure heat air are located in series. The ring cavity of the cooling air at the outlet through the labyrinth seals is connected to the oil cavity, and at the inlet - through the pipes located in channels of the oil cavity support, an open header and a pipe in the oil cavity - with the peripheral cavity (17) of the air-gas channel (18) of the low pressure compressor (8) at its outlet (19). The ring cavity of the heat air is connected at the outlet with the air cavities (23) of the inlet bell mouth (3), and at the outlet - through the break of the open header and the pipe (25) in the oil cavity of the angular-contact thrust bearing of the fan - with the air-gas channel (26) at the outlet (27) of the high pressure compressor (9).

EFFECT: improvement of the engine reliability due to anti-icing heating of the fan bell mouth and improvement of efficiency of labyrinth seal of the oil cavity of the angular-contact thrust bearing of the fan.

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