Modular exhaust case for reverse flow gas turbine engine

An exhaust system for an aircraft engine, comprising:

• a turbine exhaust duct (TED) having an inner wall and an outer wall conjointly defining an annular inlet conduit for directing combustion gases in an axial direction and extending around a central axis and outlet conduits fluidly communicating with the annular inlet conduit and extending generally radially outwardly relative to the inlet conduit;
• and
• an exhaust case enclosing the TED and extending around the central axis, the exhaust case defining exit ports fluidly communicating with the outlet conduits of the TED, the outlet conduits of the TED being devoid of connection to the exhaust case, annular gaps extending around outlet ends of the outlet conduits to allow movement of the TED relative to the exhaust case, the exhaust case extending from a forward end to a rearward end and having:
• a first section extending between the forward end and the rearward end, the first section extending around the central axis from a first edge to a second edge, the first section having a first flange at the first edge and a second flange at the second edge;
• and
• a second section extending between the forward end and the rearward end, the second section extending around the central axis from a third edge to a fourth edge, the second section having a third flange at the third edge and a fourth flange at the fourth edge,
• wherein the first section is detachably secured to the second section via the first flange being detachably secured to the third flange and the second flange being detachably secured to the fourth flange.