Patent ID: 8152450
Filing Date: 2012-04-10
Classification: F01D

Abstract:
1. A gas turbine engine comprising: a rotor disk with a plurality of rotor blades secured to the rotor disk, the rotor disk having a floating air seal forming surface on a side of the rotor disk that is substantially perpendicular to a rotating axis of the rotor disk; a stator located adjacent to the rotor disk; an annular groove formed within the stator and opening toward the floating seal forming surface of the rotor disk; an annular floating piston axially movable within the annular groove of the stator; the annular floating piston having an annular groove formed on a side facing the floating air seal forming surface of the rotor disk; the annular floating piston having a fluid pressure reacting surface on an opposite side to the annular groove; and, the annular floating piston having a fluid passage connecting the fluid pressure reacting surface to the annular groove to supply a fluid pressure and form a fluid cushion for the floating air seal.