ADJUSTABLE INLET GUIDE VANE ASSEMBLY OF GAS TURBINE ENGINE COMPRESSOR Russian patent published in 2017 - IPC F01D17/16 F04D29/56 

FIELD: engine devices and pumps.

SUBSTANCE: adjustable inlet guide vane of the gas turbine engine compressor consists of an outer body, an inner ring and guide vanes arranged between them consisting of fixed posts and rotary flaps. The outer body is made of separate segments equal to the number of fixed posts. The inner surface segments of the outer body form a flow section. The inner ring has profiled grooves and holes for the flaps. The fixed posts and flaps are mounted for turning by means of cylindrical trunnions in holes of the outer body and inner ring. The segments of the outer body have flanges with mating surfaces bent along the posts profile and slots for fixed posts. The fixed posts have holes for bolt joint on the upper part of the profile and are installed in grooves of the outer body segments and into the profile grooves of the inner ring and fixed by bolt connection through holes in the flanges of the outer base segments and glue joint in the inner ring slots. In the inner ring, the posts can be fixed with plate locks. The upper trunnions of the rotary flaps are mounted in bushes of clamps secured by bolt or rivet connection on the flanges of the outer body adjacent segments.

EFFECT: reduced weight reduction and simplified design of the inlet guide vane of the gas turbine engine compressor.

3 cl, 4 dwg