Gas turbine engine blade tip clearance apparatus and method

摘要

A gas turbine engine is provided that includes one or more rotor assemblies (30), one or more shroud segments (52), and an actuator (58). The rotor assemblies (30) are rotatable around an axially extending rotational axis (22), and each rotor assembly (30) has a plurality of blades (32). Each blade (32) has a blade tip (42). The one or more shroud segments (52) each has a blade seal surface (54) disposed radially outside of the one or more rotor assemblies (30). The blade tips (42) and blade seal surfaces (54) (collectively referred to as the blade seal surface) have mating conical geometries and a clearance distance (56) extending between the blade tips (42) and blade seal surface (54). The blade tips (42) and blade seal surface (54) are disposed at an angle relative to the axial centerline of the engine, which angle is greater than zero. The actuator (58) is selectively operable to axially move one or both of the shroud segments (52) and rotor assemblies (30) relative to the other of the shroud segments (52) and rotor assemblies (30) to alter the clearance distance (56).