Turbine exhaust duct for aircraft engine

A reverse-flow gas turbine engine, comprising:

• an outer case assembly extending around a central axis and enclosing a core, the core including a compressor section, a combustor, and a turbine section, the turbine section located forward of the combustor and of the compressor section relative to a direction of travel of the reverse-flow gas turbine engine, the outer case assembly including an exhaust case defining openings;
• a turbine exhaust duct fluidly communicating with the turbine section, the turbine exhaust duct having:
• an annular inlet conduit extending around the central axis;
• outlet conduits communicating with the annular inlet conduit and extending through the openings of the exhaust case, the outlet conduits extending from inlet ends at intersections with the annular inlet conduit to outlet ends, an outlet conduit of the outlet conduits having a redirecting section that curves from a substantially axial orientation to a substantially radial orientation, the outlet conduit having a conduit axis, the redirecting section configured to be impinged by combustion gases exiting the turbine section and to divert the combustion gases radially outwardly, the redirecting section having a thickness greater than a baseline thickness of the outlet conduit outside the redirecting section, the redirecting section defining part of a flow passage of the outlet conduit, the redirecting section having an inner face facing the flow passage and being exposed to the combustion gases, the Inner face facing the conduit axis.