Patent ID: 8585357
Filing Date: 2013-11-19
Classification: F01D

Abstract:
1. A gas turbine engine having a main axis of rotation defining axial, radial and circumferential directions, a combustor, a static vane ring assembly and a turbine assembly supported within an outer case, the vane ring assembly being axially positioned between the combustor and the turbine assembly for directing combustion gases from the combustor to pass through the turbine assembly, the turbine assembly comprising: an array of circumferentially adjacent blade outer air seal segments forming a static turbine shroud surrounding a turbine rotor; and an array of circumferentially adjacent blade outer air seal support segments forming a static support ring around the turbine shroud, each of the blade outer air seal support segments including at least one radially and outwardly extending front leg at a forward end of the blade outer air seal support segment, the at least one front leg engaging with the outer case, the forward end including a radial surface adjacent to the vane ring assembly and thereby receiving an axial load from the static vane ring assembly, each of the blade outer air seal support segments further including a pair of circumferentially spaced and radially elongated rear prongs at a rearward end of the blade outer air seal support segment, the rear prongs each having only one surface radially abutting the outer case to transfer a moment of force created by said axial load from the vane ring assembly, to the outer case.