Method and apparatus for cooling an rotor assembly

1. A rotor assembly for an inside-out electric machine comprising:

an annular rotor core defining a set of rotor posts, the annular rotor core rotatable about an axis of rotation;

a set of rotor windings wound around the respective set of rotor posts; and

a thermally conductive wedge disposed between adjacent rotor windings of the set of rotor windings, the thermally conductive wedge defining a first distal end and a second distal end, spaced from the first distal end and having an inner surface defining a hollow cavity extending through the thermally conductive wedge in an axial direction between the first distal end and the second distal end;

a cap disposed entirely within the rotor core and fully enclosed thereby, the cap positioned radially outward from the thermally conductive wedge and configured to prevent a radial movement of the thermally conductive wedge during a rotational movement of the rotor assembly; and

wherein the thermally conductive wedge receives an airflow at the first distal end, through the entire hollow cavity to the second distal end and heat from the set of rotor windings is thermally transferred to the inner surface of the thermally conductive wedge and the airflow therein.

2. The rotor assembly of claim 1 wherein the rotor assembly is further disposed within a booster cavity of a gas turbine engine.

3. The rotor assembly of claim 2 wherein the rotor assembly is rotationally connected with a turbine engine rotating assembly.

4. The rotor assembly of claim 1 wherein the airflow is ambient air.

5. The rotor assembly of claim 1 wherein the thermally conductive wedge has a geometric cross section in an axial direction.

6. The rotor assembly of claim 5 wherein the thermally conductive wedge has a triangular cross section in the axial direction.

7. The rotor assembly of claim 1 wherein the inner surface includes additional heat-dissipating surfaces.

8. The rotor assembly of claim 7 wherein the additional heat-dissipating surfaces are heat fins.

9. The rotor assembly of claim 8 wherein the heat fins are oriented in parallel with the axis of rotation.

10. The rotor assembly of claim 1 wherein the thermally conductive wedge circumferentially spaces a first set of windings from an adjacent second set of windings.

11. The rotor assembly of claim 10 wherein the thermally conductive wedge comprises a first face in a thermally conductive relationship with the first set of windings and a second face in a thermally conductive relationship with the second set of windings.

12. A gas turbine engine, comprising:

a rotatable assembly having a fan section and a booster section, the rotatable assembly rotatable about an axis of rotation;

at least one non-rotatable axial shaft;

a booster cavity defined in a space between the booster section and the at least one non-rotatable axial shaft; and

an inside-out electric machine disposed within the booster cavity, and further comprising:

an annular rotor core rotationally connected with the rotatable assembly and defining a set of rotor posts;

a set of rotor windings wound around the respective set of rotor posts;

a thermally conductive wedge disposed between adjacent rotor windings of the set of rotor windings, the thermally conductive wedge defining a first distal end and a second distal end spaced from the first distal end, and having an inner surface defining a hollow cavity extending through the thermally conductive wedge in an axial direction between the first distal end and the second distal end;

a cap disposed entirely within the rotor core and fully enclosed thereby, the cap positioned radially outward from the thermally conductive wedge and configured to prevent a radial movement of the thermally conductive wedge during a rotational movement of the rotatable assembly; and

an annular stator assembly arranged concentrically within the rotor core; and

wherein the booster cavity receives an airflow traversing the first distal end, through the entire hollow cavity to the second distal end of the thermally conductive wedge, and wherein heat from the set of rotor windings is thermally conducted to the airflow traversing the entire hollow cavity and the airflow therein.

13. The gas turbine engine of claim 12 wherein the airflow is ambient air.

14. The gas turbine engine of claim 12 wherein the thermally conductive wedge has a geometric cross section in an axial direction.

15. The gas turbine engine of claim 14 wherein the thermally conductive wedge has a triangular cross section in the axial direction.

16. The gas turbine engine of claim 12 wherein the inner surface includes additional heat-dissipating surfaces.

17. The gas turbine engine of claim 16 wherein the additional heat-dissipating surfaces are heat fins oriented in parallel with the axis of rotation.

18. The gas turbine engine of claim 12 wherein the thermally conductive wedge comprises a first face in a thermally conductive relationship with a first set of windings and a second face in a thermally conductive relationship with a second set of windings.

19. A method of cooling a rotor assembly for an inside-out electric machine, the method comprising:

receiving an airflow within a booster section of a gas turbine engine along and through an axially-oriented hollow cavity of a thermally conductive wedge circumferentially spacing at least two sets of rotor windings of an annular rotor assembly rotatably arranged concentric to non-rotating stator assembly received within the rotor assembly, the entire airflow through the hollow cavity flowing from a first distal end of the thermally conductive wedge to a second distal end of the thermally conductive wedge; and

wherein the at least a first face of the thermally conductive wedge is in a thermally conductive relationship with a first set of adjacent rotor windings and a second face of the thermally conductive wedge is in a thermally conductive relationship with a second set of adjacent rotor windings, wherein a cap is disposed entirely within the rotor assembly and fully enclosed thereby, the cap positioned radially outward from the thermally conductive wedge and configured to prevent a radial movement of the thermally conductive wedge during a rotational movement of the rotor assembly, and wherein the airflow removes heat from the first and second sets of rotor windings.