ADJUSTABLE INLET GUIDING APPARATUS OF THE COMPRESSOR OF A GAS TURBINE ENGINE Russian patent published in 2022 - IPC F01D17/12 F04D29/56 

FIELD: engine building.

SUBSTANCE: invention relates to the field of aviation engine building, namely, to a design of an adjustable inlet guiding apparatus (IGA) of the compressor of a gas turbine engine (GTE). The adjustable inlet guiding apparatus of the compressor of a gas turbine engine comprises an outer body 1 and an inner ring 2 with guiding blades installed in between, made in the form of fixed racks 3 secured in the outer body 1 and the inner ring 2, and rotary flaps 4 with upper 5 and lower 6 shanks installed in bearings 7 and 8 in the corresponding matching holes of the outer body 1 and the inner ring 2. The drive of the rotary flaps 4 is made in the form of an electric reducer motor 10 installed in the inner ring 2, provided with a cylindrical gear 11 on the output shaft for transmitting rotation to the sector of the cylindrical gear 9, installed on the lower shank 6 of the rotary flap 4, through an intermediate gear 18 and the gear rings of the internal engagement wheel 17 and the flat gear wheel 16, made on the inner cage 15 of an angular contact ball bearing 12 with a detachable outer cage.

EFFECT: creation of an adjustable IGA of the compressor of a GTE.

1 cl, 2 dwg