FIELD: aircraft industry.
SUBSTANCE: invention relates to compressors of gas-turbine engines of aircraft and ground application. According to invention, in compressor of gas-turbine engine with vanes of turbine guide vane assembly installed by outer trunnions in outer housing, inner bushings are interference-fitted on outer trunnions of vanes adjoining by outer ring radial rib on root to boss of trunnion and outer bushings installed with clearance and interference-fitted into outer housing in ring radial rib from outer side of outer bushing, thus forming radial-thrust sliding bearing at H/d=2.5-3.5; D/d=1.2-1.8; d/l=7-15 where H is height on inner bushing; d is outer diameter of vane outer trunnion; D is diameter of ring radial rib of inner bushing; l is thickness of wall of inner bushing.
EFFECT: improved reliability and increased efficiency of compressor of gas-turbine engine.
2 dwg
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