Turbine exhaust case mixer

A turbine exhaust case (TEC) mixer for an aircraft engine, the aircraft engine having an inner shroud, a nacelle, a fan assembly, a compressor assembly and a turbine assembly, the TEC mixer comprising struts extending from the TEC mixer and being adapted to connect to the inner shroud at a shroud-strut interface, at least one of the struts including a stepped configuration for reducing at least one stress in the at least one of the struts, the stepped structure including a first step adapted to be connected to the inner shroud, the first step defined by multiple planar surfaces, each planar surface of the multiple planar surfaces extending radially outwardly from the shroud-strut interface, each planar surface of the multiple planar surfaces joined along a joining edge thereof to another planar surface of the multiple planar surfaces, the joining edges extending radially outwardly from the shroud-strut interface.

A turbine exhaust case (TEC) mixer for an aircraft engine configured for mixing concentric core and bypass gas flows via a lobed mixer, the TEC mixer comprising struts extending in a span-wise direction from mixer lobes to an inner shroud across the core gas flow, the struts having a leading edge and a trailing edge separated by an axial chord, the struts axially narrower in the axial chord at a mid-span portion of the strut than at an interface of the strut and the inner shroud, the struts including a stepped structure at the interface, the stepped structure including a first step adapted to be connected to the inner shroud, the first step defined by multiple planar surfaces, each planar surface of the multiple planar surfaces configured to extend radially outwardly from the interface, each planar surface of the multiple planar surfaces joined along a joining edge thereof to another planar surface of the multiple planar surfaces, the joining edges configured to extend radially outwardly from the interface.