General Electric Company
Thermal isolation structure for rotating turbine frame

Abstract:

The present disclosure is directed to a gas turbine engine defining a radial direction, a circumferential direction, an axial centerline along a longitudinal direction, and wherein the gas turbine engine defines an upstream end and a downstream end along the longitudinal direction. The gas turbine engine includes a first turbine rotor comprising an inner shroud, an outer shroud outward of the inner shroud in the radial direction, at least one connecting airfoil coupling the inner shroud and the outer shroud at least partially along the radial direction, and an outer band outward of the outer shroud in the radial direction and extended at least partially in the circumferential direction, and a plurality of connecting members couples the outer shroud and the outer band.