ADJUSTABLE INLET GUIDE VANE OF GAS TURBINE ENGINE COMPRESSOR Russian patent published in 2019 - IPC F01D17/12 F04D29/56 

FIELD: machine building.

SUBSTANCE: invention relates to design of gas turbine engine (GTE), namely GTE units serving to control and control changes of gas flow located in stator part. In the well-known inlet guide vanes controlled gas turbine compressor comprising guide vanes, each including a fixed post and flap, installed by outer and inner shanks in outer housing and inner ring of compressor, respectively, flaps rotation mechanism, according to the present invention, the flaps turning mechanism is made in the form of an annular casing installed under the inner shanks of the flaps and the annular casing, which is rigidly connected to the stator of the compressor, in which the annular power piston is installed, which is made with possibility of axial displacement, which is limited by the end walls of the annular casing, wherein on outer surface of annular power piston circumferentially radial ledges are made, each of which is pivotally connected to flap inner shank by means of lever, wherein control cavities formed by adjacent ends of annular power piston of annular housing are interconnected with supply and discharge lines of working fluid.

EFFECT: technical results achieved by the claimed invention are reduction of overall dimensions of GTE by elimination of hydraulic cylinders on the outer housing of the compressor, as well as reduction of pressure in the hydraulic system, which increases reliability of the gas turbine engine.

1 cl, 5 dwg