SEAL

摘要

A turbofan gas turbine engine ( 10 ) comprises a compressor rotor ( 24 ) carrying a plurality of circumferentially spaced radially extending rotor blades ( 26 ) and a casing ( 28 ) surrounding the compressor rotor ( 24 ) and compressor rotor blades ( 26 ). A compressor rotor blade tip seal ( 48 ) comprises an annular member ( 30 ) secured to and arranged within the casing ( 28 ). The annular member ( 40 ) has a plurality of circumferentially spaced axially extending corrugations ( 32 ) and a plurality of radially spaced circumferentially extending corrugations ( 34 ). A lining ( 40 ) is secured to and arranged within the annular member ( 30 ). The lining ( 40 ) is spaced radially from the tips ( 27 ) of the compressor rotor blades ( 26 ) to form a clearance ( 29 ). An actuator ( 56 ) is provided to move the annular member ( 30 ) and lining ( 40 ) radially to control the size of the clearance ( 29 ).