Patent ID: 8011883

Claim:
A zero running clearance system for gas turbine engines, comprising: at least one first rotor assembly of a gas turbine engine compressor rotatable around a rotational axis, each first rotor assembly having a plurality of blades with each blade having a tip; at least one first stator assembly of said gas turbine engine compressor disposed adjacent said at least one first rotor assembly; at least one first shroud segment having blade seal surfaces disposed radially outside of said at least one first rotor assembly; at least one second rotor assembly of a gas turbine engine turbine rotatable around said rotational axis, each second rotor assembly having a plurality of blades with each blade having a tip; at least one second stator assembly of said gas turbine engine turbine disposed adjacent said at least one second rotor assembly; at least one second shroud segment having blade seal surfaces disposed radially outside of said at least one second rotor assembly, wherein said blade tips and said blade seal surfaces have mating geometries and a clearance distance extending between said blade tips and said blade seal surfaces; an actuator selectively operable to move said at least one first rotor assembly and said at least one second rotor assembly to alter said clearance distance; and means for controlling said actuator at a response rate sufficient to alter said clearance distance.