Abstract: A thermal seal and insulating assembly for the low pressure turbine stage of a gas turbine engine having an inner liner and an outer liner which are connected by a 360.degree. ring. The ring serves to insulate a low pressure turbine case which is located radially outward from the outer liner from high temperature fluid flow. The inner liner is integrally connected to a liner extension located at the front of the inner liner. The liner extension deflects thermal fluid flow away from the inner liner. The inner liner and outer liner house a plurality of tubular and axially aligned honeycombed cells which provide a barrier against radiation heat transfer.

Abstract: A clearance control apparatus has a positioning mechanism for controlling clearance between rotor blade tips and a shroud segment of a gas turbine engine casing. The positioning mechanism is supported by the casing, coupled to the shroud segment, and actuatable for moving the shroud segment toward and away from the rotor blade tips to reach a position at which a desired clearance is established. The mechanism includes a shaft and a bellcrank actuating assembly. The shaft is mounted through a passage defined by a mounting structure on the casing for radial movement along a longitudinal axis of the shaft toward and away from the rotor axis and is coupled at its inner end to the shroud segment. The bellcrank actuating assembly is coupled to an outer end of the shaft and mounted to the casing adjacent the shaft for pivotal movement about an axis spaced from and extending transverse to the longitudinal axis of the shaft.