STATOR OF GAS TURBINE ENGINE COMPRESSOR Russian patent published in 2002 - IPC

FIELD: aviation industry; gas turbine engines of aircraft and ground application. SUBSTANCE: according to invention, in stator of compressor of gas turbine engine provided with turnable vanes of guide vane assemblies and turnable vanes angular position pickups, each connected with drive mechanism through system of levers with driving and additional tie-rods interconnected by pin, pin is made eccentricity, with ratio of length of driving lever to pin eccentricity being 20- 100. Ring multifaces rib is made on border between elbows of pin. Projections of lock holding pin relative to driving lever in angular position are found on tops and faces of rib. EFFECT: improved reliability of compressor stator owing to provision of agreement between vane turning range of guide vane assembly and range of turnable vane angular position pickup rotor. 5 dwg