Thermally compliant forward outer-diameter ring for a gas turbine engine

A cooled turbine exhaust case assembly for a gas turbine engine, the assembly comprising:

• a forward outer diameter ring, the forward outer diameter ring comprising:
• a flowpath ring extending circumferentially about a central axis and extending axially from a first end to a second end relative to the central axis, wherein the second end is axially aft of the first end;
• a hoop stiffener connected to the second end of the flowpath ring and extending circumferentially around the second end of the flowpath ring, and wherein the hoop stiffener comprises:
• a first stiffener end connected to the second end of the flowpath ring;
• a second stiffener end axially aft of the first stiffener end;
• and
• tabs formed in the second stiffener end, and wherein the tabs are circumferentially spaced apart from one another;
• case segments connected to the second stiffener end by the tabs, and wherein the case segments are circumferentially spaced about the central axis from one another;
• a slot between each pair of the case segments;
• and
• a seal extending axially along the slot, wherein the seal is connected to two of the case segments;
• a turbine case located radially outward of the forward outer diameter ring;
• a turbine exhaust case axially aft the turbine case and connected to the turbine case via a forward outer turbine exhaust case;
• a plenum defined by the forward outer diameter ring, the turbine case, the turbine exhaust case, and the forward outer turbine exhaust case;
• an inlet opening in the turbine case for introducing cooling air to the plenum;
• and
• one or more film cooling openings in a fore region of the forward outer diameter ring configured to allow cooling air to exit the plenum to a hot gas path of the gas turbine engine to provide film cooling to the forward outer diameter ring.