Patent ID: 9664062
Date: 2017-05-30
CPC Classifications: F01D

Claim:
1. A gas turbine engine comprising: at least one exhaust diffuser positioned downstream from a turbine assembly, extending circumferentially around a central longitudinal axis of the gas turbine engine and having an increasing cross-sectional area from an upstream edge to a downstream edge; wherein the downstream edge of the at least one exhaust diffuser includes at least one downstream attachment flange having at least one downstream attachment orifice extending therethrough; an outer case comprising the turbine exhaust case and a spool structure, wherein the turbine exhaust case extends circumferentially around the at least one exhaust diffuser, and an outer case surface extending circumferentially around the central longitudinal axis, wherein the exhaust case includes an exhaust case flange, and wherein the spool structure has a spool structure flange forming a joint with the exhaust case flange; a thermal barrier/cooling system for controlling a temperature of the outer case, the thermal barrier/cooling system including: