Patent ID: 8961115
Filing Date: 2015-02-24
Classification: F01D,F05D

Abstract:
1. A gas turbine engine section comprising: a rotor carrying a plurality of blades, said blades each having a radially outer tip; a blade outer air seal positioned radially outwardly of said tips of said blades, said blade outer air seal being provided by at least a plurality of circumferentially spaced segments, said circumferentially spaced segments being operable to slide circumferentially relative to each other to adjust an inner diameter of an inner surface of said blade outer air seal segments; an actuator for actuating said blade outer air seal segments to slide relative to each other to control a clearance between the inner periphery of said blade outer air seal segments and an outer periphery of the tips; and said actuator expands or contracts along an axis generally parallel to a rotational axis of said rotor to in turn cause said blade outer air seal segments to slide circumferentially.