Patent ID: 7341426

Claim:
A gas turbine engine compressor, comprising: one or more rotor assemblies rotatable around an axially extending rotational axis, each rotor assembly having a plurality of blades with each blade having a blade tip; one or more shroud segments having blade seal surfaces disposed radially outside of the one or more rotor assemblies; wherein the blade tips and blade seal surfaces have mating conical geometries and a clearance distance extending between the blade tips and blade seal surfaces; and an actuator selectively operable to axially move one or both of the shroud segments and rotor assemblies relative to the other of the shroud segments and rotor assemblies to alter the clearance distance, wherein the actuator includes a screw thread device disposed in connection with the one or more rotor assemblies, wherein one or both of the shroud segments and rotor assemblies move axially relative to the other of the shroud segments and rotor assemblies when at least a portion of the screw thread device rotates.