Patent ID: 8894359

Claim:
A gas turbine engine comprising: an outer case comprising a turbine exhaust case defining a central longitudinal axis, the exhaust case having an upstream exhaust case flange, a downstream exhaust case flange, and an outer case surface between the upstream and downstream exhaust case flanges extending circumferentially around the central longitudinal axis, the upstream and downstream exhaust case flanges extending radially outward from the outer case surface; a thermal barrier/cooling system for controlling a temperature of the outer case, the thermal barrier/cooling system including: an internal insulating layer supported on an inner case surface opposite the outer case surface and spanning axially from the upstream exhaust case flange to the downstream exhaust case flange, the internal insulating layer extending circumferentially along the inner case surface and providing a thermal resistance to radiated energy from structure located radially inwardly from the outer case; and a convective cooling channel defined by a panel structure located in radially spaced relation to the outer case surface and extending continuously around the circumference of the outer case surface and located within a space defined between the upstream and downstream exhaust case flanges, the convective cooling channel is axially aligned with the internal insulating layer and forms a flow path for an ambient air flow cooling the outer case surface.