TURBINE EXHAUSE CASE MIXER

The turbine exhaust case (TEC) mixer assembly for an aircraft engine includes a center body (30) including a hub (31) that encloses a center body cavity (32) and has a first wall portion (31A) and a second wall portion (31B) that are axially spaced apart. The first and second wall portions (31A, 31B) have axial end segments which are removably coupled to each other radially inwardly from an outer periphery (34) of the center body (30) via a fixing arrangement including a fastener that is enclosed within the center body cavity (32). An axial spring (50) includes a gap axially defined between portions of the axial end segments and located at the outer periphery (34) of the center body (30). A mixer (29) extends peripherally about the center body (30) and is spaced radially outward from the hub (31) by a plurality of struts (40) extending between the hub (31) and the mixer (29), the plurality of struts (40) being axially offset from the gap at a strut-hub interface (41).