Exhaust case 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 secured to a turbine case enclosing the turbine section, the turbine case having a flange protruding radially away from the central axis;
• and
• a turbine exhaust duct (TED) having an annular inlet conduit extending around the central axis for directing combustion gases generally in an axial direction and outlet conduits communicating with the annular inlet conduit and extending generally radially outward relative to the annular inlet conduit, the outlet conduits communicating with the opening of the exhaust case,
• wherein the exhaust case has:
• a frustoconical section extending from a fore end at an intersection with a remainder of the exhaust case to an aft end securable to a turbine case, the frustoconical section converging towards the central axis from the fore end to the aft end;
• and
• a connecting flange protruding inwardly towards the central axis from the frustoconical section,
• wherein the flange of the turbine case abuts an annular face of the frustoconical section, the annular face oriented towards the central axis, the flange of the turbine case axially facing an axial face of the connecting flange.