Embedded electric machine

1. A method for maintaining a gas turbine engine installed on an aircraft, the gas turbine engine including an electric machine mounted at least partially inward of a core air flowpath of the gas turbine engine, the method comprising:

removing a rotor mount connecting a rotor of the electric machine to a rotary component of the gas turbine engine;

removing a stator mount connecting a stator of the electric machine to a stationary component of the gas turbine engine; and

removing in situ the electric machine, wherein the gas turbine engine extends between a forward end and an aft end, and wherein the electric machine is positioned at the aft end of the gas turbine engine, wherein removing in situ the electric machine comprises moving the electric machine to electrically disconnect the electric machine from the electric communication bus at a quick release electric connection, wherein the quick release electric connection includes a first member and a second member, wherein the first member and second member are automatically decoupled by removing in situ the electric machine.

2. The method of claim 1 , further comprising:

removing a cover assembly to expose the rotor mount, the stator mount, or both.

3. The method of claim 2 , wherein the cover assembly includes an aft cone and a cavity wall.

4. The method of claim 1 , wherein removing the rotor mount comprises removing a mechanical connector connecting a shaft extension member to the rotor of the electric machine.

5. The method of claim 4 , wherein removing the rotor mount further comprises moving the shaft extension member at least partially along an axial direction of the gas turbine engine to decouple the shaft extension member from the rotary component of the gas turbine engine at a splined connection.

6. The method of claim 1 , wherein the electric machine defines an aft end, and wherein the rotor mount, the stator mount, or both are positioned proximate the aft end of the electric machine.

7. The method of claim 1 , wherein the electric machine is a first electric machine, and wherein the method further comprises:

installing in situ a second electric machine in place of the first electric machine.

8. The method of claim 1 , wherein the electric machine comprises at least one bearing configured to rotatably support the rotor of the electric machine relative to the stator of the electric machine, and wherein removing in situ the electric machine comprises removing in situ the electric machine as a complete unit.

9. A gas turbine engine defining a radial direction and an axial direction, the gas turbine engine comprising:

a turbomachine comprising a compressor, a turbine, a rotary component rotatable with the compressor and the turbine, and a stationary component, the compressor and turbine together defining at least in part a core air flowpath;

an electric machine positioned at least partially inward of the core air flowpath along the radial direction, the electric machine comprising a rotor and a stator;

a rotor mount removably coupling the rotor of the electric machine to the rotary component;

a stator mount removably coupling the stator of the electric machine to the stationary component; and

a cover assembly removably positioned over the electric machine, the electric machine and cover assembly positioned such that the electric machine is removable from the gas turbine engine in situ when the cover assembly is removed;

wherein the electric machine comprises a quick release electric connection for selectively electrically connecting the electric machine to an electric communication bus, wherein the quick release electrical connection includes a first member and a second member, and wherein the first and second members are automatically decoupled by removing in situ the electric machine.

10. The gas turbine engine of claim 9 , wherein the cover assembly comprises an aft cone and a cavity wall.

11. The gas turbine engine of claim 9 , wherein the cover assembly consists essentially of an aft cone and a cavity wall.

12. The gas turbine engine of claim 9 , further comprising:

an electric communication bus; and

the electric machine electrically connected to the electric communication bus through the quick release electric connection.

13. The gas turbine engine of claim 9 , wherein the gas turbine engine defines an aft end, and wherein the electric machine is positioned proximate the aft end.

14. The gas turbine engine of claim 9 , wherein at least a portion of the cover assembly is visible from an outside of the gas turbine engine.

15. The gas turbine engine of claim 9 , further comprising:

an electric machine mount coupled to, or formed integrally with, the stationary component of the turbomachine, and wherein the electric machine is slidably received on the electric machine mount.

16. The gas turbine engine of claim 9 , wherein the stator mount fixedly couples the electric machine to an electric machine mount.

17. A method for maintaining a gas turbine engine installed on an aircraft, the gas turbine engine including an electric machine mounted at least partially inward of a core air flowpath of the gas turbine engine, the method comprising:

removing a rotor mount connecting a rotor of the electric machine to a rotary component of the gas turbine engine;

removing a stator mount connecting a stator of the electric machine to a stationary component of the gas turbine engine; and

removing in situ the electric machine, wherein removing in situ the electric machine comprises moving the electric machine to electrically disconnect the electric machine from the electric communication bus at a quick release electric connection, wherein the quick release electric connection includes a first member and a second member, wherein the first member and second member are automatically decoupled by removing in situ the electric machine.

18. The method of claim 17 , wherein moving the electric machine to electrically disconnect the electric machine from the electric communication bus comprises moving the electric machine at least partially along an axial direction of the engine to electrically disconnect the electric machine from the electric communication bus.