FIELD: engines and pumps.
SUBSTANCE: stator (1) of a gas turbine engine compressor is made with rotary guide blades (7), (9) and (10) and rotary thrust rings (23), (24) and (25) connected with them via levers (19), (20) and (21). Thrust rings comprise radial support screws (26), in the heads of which at the side of the stator there are inserts (29) from composite material. In rotary thrust rings (23), (24) and (25) there are support surfaces (29) opposite to the heads of the support screws (26). On support screws there are bushings (27), support surfaces (28) of which are arranged opposite to support surfaces (29) of the rotary thrust rings (23), (24) and (25). Between support surfaces of the rotary thrust rings and bushings there are springs (30). The sum of the distance h between the external surface of thrust rings and a washer (33), installed on the rod of the screw (26), and the distance k between the inner surface of thrust rings and coupled end surface of the head of the support screw is at least equal to the value H of protrusion of a composite insert (31) from the seat of the support screw head.
EFFECT: by increasing evenness of rotation of guide blades, exclusion of gaps in couplings and accordingly reduced deformation of rotary thrust rings of a drive, and also wear of blade rotation mechanism parts, increased reliability and resource of a compressor stator.
3 dwg
