Aircraft engine with exhaust having removable deflector

An aircraft engine, comprising:

• a thermal engine having an engine inlet and an engine outlet;
• an axial turbine having a turbine inlet;
• and
• an exhaust assembly fluidly connecting the engine outlet of the thermal engine to the turbine inlet of the axial turbine, the exhaust assembly having a exhaust inlet fluidly connected to the engine outlet and an exhaust outlet fluidly connected to the turbine inlet, the exhaust assembly including:
• a housing extending circumferentially about a central axis, the housing having an outer wall and an inner wall disposed radially inwardly of the outer wall relative to the central axis, the inner wall and the outer wall curving from a radial orientation at the exhaust inlet to an axial orientation at the exhaust outlet, the exhaust outlet being annular and defined radially between the inner wall and the outer wall;
• and
• a deflector removably mounted within the housing, the deflector having vanes circumferentially distributed about the central axis, flow passages interspaced between the vanes, the flow passages curving from passages inlets to passage outlets, axial components of passage axes of the flow passages increasing from the passage inlets to the passage outlets,
• wherein the deflector is a first deflector having a first set of geometric characteristics, the deflector removable from the housing and replaceable by a second deflector having a second set of geometric characteristics different from the first set of geometric characteristics, wherein the first deflector is one of a first class of deflectors and the second deflector is one of a second class of deflectors, the first and second class of deflectors respectively defining first and second exhaust flow profiles that differ from each other.