Abstract: A trailing member for a strut of a gas turbine exhaust diffuser includes an upstream side a downstream end spaced along a downstream direction from the upstream side, and two side walls extending from the upstream side to the downstream end. A distance between the two side walls decreases along a direction from the upstream side to the downstream end. A longitudinal extent of the trailing member extends along the upstream side between a first longitudinal end and a second longitudinal end. A first edge of each side wall is disposed proximate to the first longitudinal end. A stress relief slot is provided in at least one of the first and second side walls of the two side walls and opens at the first edge of the respective side wall.

Abstract: A system may include an insulation mount assembly configured to mount insulation within a component of an exhaust diffuser of a combustion system. The insulation mount assembly includes an insulation cover plate configured to cover the insulation over a wall of the component, and a plurality of mounting clips configured to extend partially over the insulation plate and couple to the wall of the component. Each clip of the plurality of mounting clips is configured to enable movement of the insulation cover plate in a first direction along a surface of the wall and block movement of the insulation cover plate in a second direction crosswise to the surface of the wall.

Abstract: A system includes a diffuser configured to receive exhaust gas from a turbine. The diffuser includes an outer barrel, an inner barrel, a seal interface, an outer aft plate, an inner aft plate, and poles. An upstream end of the outer barrel includes an upstream lip interfacing with a downstream lip of an outer wall of the turbine outlet, forming a lap joint. The outer barrel includes a plurality of axial segments disposed between the upstream end of the outer barrel and the outer aft plate, and the axial segments. The inner barrel includes a plurality of axial segments disposed between an upstream end of the inner barrel and the seal interface. The seal interface includes a groove configured to receive the inner aft plate. The poles are spaced about the turbine axis and couple an end of the outer aft plate to an end of the inner aft plate.