METHOD AND DEVICE FOR CONTROLLING ROTOR BLADE TIP CLEARANCE IN GAS TURBINE ENGINE

摘要

PROBLEM TO BE SOLVED: To provide a method and a device for assembling a compressor of a gas turbine engine. SOLUTION: A compressor 40 for a gas turbine engine 10 includes a rotor assembly 42 having a plurality of circumferentially-spaced apart rotor blades 50. Each of the blades extends radially outwardly from a radially inner rim 58 to a tip 60. Each rim defines a part of a radially inner flowpath surface through the compressor. A casing 80 extends circumferentially around the rotor assembly. The casing includes a first ring 41 and a second ring 82. The first ring includes a radially inner surfaces 102 defining a part of a radially outer flowpath surface through the compressor. The inner surfaces of the first ring are spaced radially outwardly from the plurality of the rotor blade tips. The second ring is coupled to the first ring by a fastener assembly 86. The radially inner surfaces of the first ring substantially separate the fastener assembly from the flowpath of the compressor. COPYRIGHT: (C)2005,JPO&NCIPI