GAS TURBINE ENGINE AND METHOD OF ITS OPERATION Russian patent published in 2015 - IPC F01D25/16 F02C7/06 F01D11/02 

FIELD: engines and pumps.

SUBSTANCE: gas turbine engine comprises rotor radial outer and inner stator parts with compressor air channel extending there between, circular clearance between rotor and radially inner stator part as well as discharge pipe. Rotor comprises fluid bearing rotor part while radially inner stator part comprises stator part. Circular clearance makes circular air channel communicated with compressor air channel. Cross-section of circular air channel decreases in airflow direction in first part and increases in second part. Discharge pipeline air inlet extending through second part of circular air channel is arranged axially between second part of circular air channel second part and fluid bearing. In operation of said engine, rotor is driven relative to radially outer and inner walls of stator part. Compressed air is forced via compressor air channel into circular air channel composed by the part of circular gap between rotor and radially inner stator part.

EFFECT: ruled out fluid ingress from bearing chamber into compressor air channel.

15 cl, 2 dwg