Apparatus for controlling rotor blade tip clearances in a gas turbine engine

摘要

A compressor (40) for a gas turbine engine includes a rotor assembly (42) comprising 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 portion of a radially inner flowpath surface through the compressor. A casing (80) extends circumferentially around the rotor assembly. The casing includes at least a first ring (41) and a second ring (82). The first ring includes a radially inner surface defining a portion of a radially outer flowpath surface through the compressor. The first ring inner surface is spaced radially outwardly from the plurality of rotor blade tips. The said second ring is coupled to the first ring by a fastener assembly (86). The first ring radially inner surface facilitates substantially insulating the fastener assembly from the compressor flowpath.