BLADE RING OF STATOR OF AXIAL COMPRESSOR OF GAS-TURBINE ENGINE Russian patent published in 1998 - IPC

FIELD: gas-turbine engines. SUBSTANCE: proposed blade ring is intended for compressors of gas-turbine engines. Double-support blades of blade form are fitted on the ends with shoulders and tails entering location grooves. One of them on side of outer shell contacts spring-loaded rest. Shoulders and tails of each blade are lined with damping material. Location grooves for fixing of blades are displaced with reference to one another in circumferential and axial directions ( in parallel to longitudinal axis of compressor ) by constant values of angle α and distance l correspondingly. Maintainability of compressor under operational conditions with minimal time by replacement of failed blades is enhanced thanks to simplified design of fixing of blade ends in location grooves of shells of body of compressor and to installation of spring-loaded rests. EFFECT: enhanced maintainability of compressor. 4 cl, 3 dwg