Abstract: An exhaust casing for a gas turbine engine comprises a shroud configured to surround an exhaust cone, and a heat shield attached to the shroud. The heat shield has a first end and a second end axially spaced apart from each other. A gap is defined radially between the shroud and the heat shield. The gap is configured to enclose at least a portion of an interface defined between at least one strut and the shroud. The exhaust casing is configured to surround the exhaust cone and configured to be connected to the exhaust cone via the at least one strut.

Abstract: A gas turbine engine comprises a main gas path having an inner flow boundary wall and an outer flow boundary wall. A turbine exhaust case inner body defines a portion of the inner flow boundary wall of the main gas path. A lobed exhaust mixer defines a portion of the outer flow boundary wall of the main gas path. A stiffener ring is interconnected to at least a number lobes of the lobed exhaust mixer by a plurality of circumferentially spaced-apart struts extending through the main gas path. The stiffener ring is attached to the turbine exhaust case inner body by flexible features, such as circumferentially spaced-apart spring blades.

Abstract: An integrated mixer/TEC having structural features that may be individually used or combined to achieve a robust and durable design.