COMPRESSOR OF DOUBLE-FLOW GAS TURBINE ENGINE Russian patent published in 2019 - IPC F01D17/16 F04D29/56 

FIELD: aviation; engines.

SUBSTANCE: invention relates to aircraft engine building, particularly, to design of high-pressure compressors of double-flow gas turbine engine. Compressor of double-flow gas turbine engine comprises body of adjustable guide vanes, intermediate housing, control mechanism of rotary blades of adjustable guide vanes, at least one power cylinder. Intermediate housing comprises: posts, gas flow separator, outer rim. Power cylinder is arranged above the outer rim of the intermediate housing and is connected to the control mechanism of the rotary blades of the adjustable guiding devices by means of a transmitting element. Transmitting element is made in the form of a double-arm lever, between which arms a bushing is installed, which is installed on the axis located above the external rim of the intermediate housing across the longitudinal middle surface of the rack. Both arms of double-arm lever and longitudinal axis of power cylinder are made in one plane. One of arms of the double-arm lever is installed with gaps in the through holes, one of which is made in the outer rim of the intermediate housing directly above the post, and the other one – in the wall of the gas flow separator, besides, on external rim of intermediate housing there is installed and rigidly fixed sealing cover in contact with bushing.

EFFECT: invention allows to increase the reliability, service life and efficiency of the compressor.

2 cl, 3 dwg