Gas turbine engine recuperator with floating connection

1. A method of installing a recuperator within an exhaust duct of a gas turbine engine around a central axis of the gas turbine engine, the gas turbine engine having a turbine section, the recuperator segmented circumferentially into a plurality of segments, at least one segment of the plurality of segments having exhaust passages contained in the exhaust duct and extending between an exhaust inlet and an exhaust outlet, and air passages in heat exchange relationship with the exhaust passages and extending between an air inlet and an air outlet, the method comprising:

positioning the plurality of segments inside the exhaust duct around the central axis and axially spaced apart from the turbine section along said central axis of the gas turbine engine and providing a controlled gap between adjacent segments of the plurality of segments that circumferentially space apart and prevent contact between the adjacent segments;

positioning the at least one segment such that the exhaust inlet is in fluid flow communication with the turbine section of the engine and the exhaust outlet is adapted to deliver an exhaust flow to atmosphere;

connecting the plurality of segments inside the exhaust duct independently from each other to maintain the controlled gap upon connection, such that the plurality of segments are allowed to thermally expand without interfering with thermal expansion of adjacent segments of the plurality of segments, including:

engaging the air inlet to a first plenum in fluid flow communication with a compressor discharge of the gas turbine engine; and

engaging the air outlet to a second plenum containing a combustor of the gas turbine engine;

wherein one of engaging the air inlet and engaging the air outlet includes forming a rigid connection providing sealed fluid flow communication with the corresponding a one of the first and second plenums, and the other of engaging the air inlet and engaging the air outlet includes forming a floating connection providing sealed fluid flow communication with the other one of first and second plenums, the floating connection allowing relative movement of the at least one segment about the floating connection relative to the other one of the first and second plenums, the relative movement of the at least one segment within the exhaust duct allowed by the floating connection being defined along different, non-parallel directions with respect to the central axis of the gas turbine engine.

2. The method as defined in claim 1 , further comprising a preliminary step of detaching and removing an exhaust scroll of the gas turbine engine, the at least one segment being installed through an opening previously covered by the exhaust scroll.

3. The method as defined in claim 1 , wherein engaging the air outlet includes forming the rigid connection and engaging the air inlet includes forming the floating connection.

4. The method as defined in claim 1 , wherein forming the floating connection includes rigidly attaching a flexible duct member of the at least one segment to the other one of the first and second plenums.

5. The method as defined in claim 1 , further comprising positioning a control surface of the at least one segment against a wall of the exhaust duct without impeding relative movement between the control surface and the wall.

6. The method as defined in claim 1 , wherein the plenums are contained in an outer case of the engine.

7. The method as defined in claim 1 , wherein positioning the at least one segment includes positioning the exhaust passages and the air passages within the exhaust duct.

8. The method as defined in claim 1 , wherein the rigid connection is contained in the engine.

9. The method as defined in claim 1 , wherein the floating connection is contained in the engine.

10. The method as defined in claim 1 , wherein the relative movement of the at least one segment within the exhaust duct allowed by the floating connection is defined along axial and radial directions with respect to the central axis of the gas turbine engine.

11. The method as defined in claim 1 , wherein forming the rigid connection includes forming the only rigid connection between the at least one segment and all elements of the gas turbine engine not forming part of the recuperator.