Abstract: The turbine exhaust case can have an outer shroud, an inner shroud internal to the outer shroud, an annular exhaust path between the outer shroud and the inner shroud, and a plurality of struts each having a length extending across the annular exhaust path from a radially inner end to a radially outer end, the struts circumferentially interspaced from one another, the struts each having a leading edge and a trailing edge, a stiff connection between the radially inner end and the inner shroud, and a point connection between the radially outer end and the outer shroud.

Abstract: An exhaust duct of a gas turbine engine comprises a hub defining a radially-inner surface of a substantially annular exhaust gas path, and a strut extending into the exhaust gas path. The strut is attached to the hub via a first fastener at a forward fastening location closer to a leading edge of the strut than to a trailing edge of the strut, and via a second fastener at an aft fastening location closer to the trailing edge than to the leading edge. The second fastener is engaged with an appendage of the strut. The appendage is received into a receptacle formed in the hub open to the radially-inner surface.

Abstract: An exhaust duct of a gas turbine engine comprises a hub defining a radially-inner surface of a substantially annular exhaust gas path, and a strut extending into the exhaust gas path. The strut is attached to the hub via a first fastener at a forward fastening location closer to a leading edge of the strut than to a trailing edge of the strut, and via a second fastener at an aft fastening location closer to the trailing edge than to the leading edge. The second fastener is engaged with an appendage of the strut. The appendage is received into a receptacle formed in the hub open to the radially-inner surface.

Abstract: The turbine exhaust case can have an outer shroud, an inner shroud internal to the outer shroud, an annular exhaust path between the outer shroud and the inner shroud, and a plurality of struts each having a length extending across the annular exhaust path from a radially inner end to a radially outer end, the struts circumferentially interspaced from one another, the struts each having a leading edge and a trailing edge, a stiff connection between the radially inner end and the inner shroud, and a point connection between the radially outer end and the outer shroud.

Abstract: A turbine exhaust case (TEC) mixer for an aircraft engine is disclosed. The aircraft engine has an inner shroud, a nacelle, a fan assembly, a compressor assembly and a turbine assembly. The TEC mixer includes struts extending from the mixer and is adapted to connect to the inner shroud at a shroud-strut interface. A plurality of the struts are narrower in a middle portion thereof than at the shroud-strut interface.