Patent attributes
A zero running clearance system for gas turbine engines includes a gas turbine engine compressor having one or more first rotor assemblies and one or more first stator assemblies disposed adjacent the one or more first rotor assemblies; a gas turbine engine turbine having one or more second rotor assemblies and one or more second stator assemblies disposed adjacent the one or more second rotor assemblies; one or more shroud segments having blade seal surfaces disposed radially outside of the tips of blades of both the first and second rotor assemblies and a clearance distance extending between the blade tips and blade seal surfaces; and, an actuator selectively operable to axially move the first and said second rotor assemblies to alter the clearance distance.
