Gas turbine engine blade tip clearance apparatus and method

摘要

A zero running clearance system for gas turbine engines includes a gas turbine engine compressor (14) having one or more first rotor assemblies (30) and one or more first stator assemblies (28) disposed adjacent the one or more first rotor assemblies (30); a gas turbine engine turbine (18) having one or more second rotor assemblies (104) and one or more second stator assemblies (102) disposed adjacent the one or more second rotor assemblies (104); one or more shroud segments (80) having blade seal surfaces (120) disposed radially outside of the tips of blades of both the first and second rotor assemblies (30;104) and a clearance distance extending between the blade tips and blade seal surfaces; and, an actuator (58) selectively operable to axially move the first and said second rotor assemblies (30;104) to alter the clearance distance.