Turbine case structure for an aircraft propulsion system engine

A gas turbine engine for an aircraft, the gas turbine engine comprising:

• a turbine section extending along a rotational axis of the gas turbine engine, the turbine section including a bladed turbine rotor interconnected with a shaft;
• a turbine case including an inner wall disposed downstream of the bladed turbine rotor, the inner wall extending circumferentially about the rotational axis, the inner wall extending between and to an upstream axial end and a downstream axial end, the upstream axial end disposed at and downstream of the bladed turbine rotor, the inner wall forming a first sealing surface and a second sealing surface axially spaced from the first sealing surface;
• an inner case extending circumferentially about the rotational axis, the inner case disposed radially inward of the upstream axial end, the inner case extending between and to a first axial case end and a second axial case end, the inner case mounted to the turbine case at the first axial case end, the inner case forming a bearing compartment housing at the shaft;
• and
• a damping seal baffle extending circumferentially about the rotational axis, the damping seal baffle mounted to the inner case at the second axial case end, the damping seal baffle disposed in contact with one or both of the first sealing surface or the second sealing surface and configured to move relative to the first sealing surface and the second sealing surface.

A gas turbine engine for an aircraft, the gas turbine engine comprising:

• a turbine section extending along a rotational axis of the gas turbine engine;
• a turbine case forming an engine exhaust of the gas turbine engine downstream of the turbine section, the engine exhaust including an exhaust duct, the turbine case including an outer wall and an inner wall cantilevered from the outer wall, the inner wall forming an inner radial portion of the exhaust duct through the engine exhaust, the inner wall extending circumferentially about the rotational axis, the inner wall extending between and to an upstream axial end and a downstream axial end, the upstream axial end disposed at and downstream of the turbine section, the downstream axial end disposed at the outer wall, the inner wall forming a first sealing surface and a second sealing surface axially spaced from the first sealing surface;
• an inner case extending circumferentially about the rotational axis, the inner case disposed radially inward of the inner wall;
• and
• a damping seal baffle including a compliant sheet metal body extending circumferentially about the rotational axis, the compliant sheet metal body mounted to the inner case, the compliant sheet metal body disposed in contact with one or both of the first sealing surface or the second sealing surface and configured to move relative to the first sealing surface and the second sealing surface.