Bearing current mitigation for an electric machine embedded in a gas turbine engine
A propulsor is provided including a gas turbine engine having a shaft and one or more bearings supporting the shaft, a rotor hub operatively coupled to the shaft and comprising a hub flange, an electric machine comprising a stator assembly and a rotor assembly, a rotor connection member operatively coupled to the rotor assembly of the electric machine and comprising a connection flange, and an insulated joint for operatively coupling the rotor assembly with the shaft. The insulated joint includes a plurality of insulative layers, at least one of the plurality of insulative layers extending between the hub flange and the connection flange to interrupt common mode electric current from flowing between the rotor assembly and the shaft.
1. A propulsor, comprising:
a gas turbine engine having a shaft and one or more bearings supporting the shaft;
a rotor hub operatively coupled to the shaft and comprising a hub flange;
an electric machine comprising a stator assembly and a rotor assembly;
a rotor connection member operatively coupled to the rotor assembly of the electric machine and comprising a connection flange; and
an insulated joint for operatively coupling the rotor assembly with the shaft, the insulating joint comprising:
a plurality of insulative layers, at least one of the plurality of insulative layers extending between the hub flange and the connection flange to interrupt common mode electric current from flowing between the rotor assembly and the shaft, wherein the plurality of insulative layers comprise hub-side insulative layers, wherein the hub-side insulative layers comprise an outer layer and an inner layer spaced apart along an axial direction.
2. The propulsor of claim 1 , wherein the outer layer forms an outer surface of the hub flange.
3. The propulsor of claim 1 , wherein the plurality of insulative layers comprise interface-side insulative layers, wherein the interface-side insulative layers comprise an outer layer and an inner layer spaced apart along an axial direction.
4. The propulsor of claim 3 , wherein the outer layer forms an interface between the hub flange and the connection flange.
5. The propulsor of claim 3 , wherein the outer layer and the inner layer extend at least partially along the axial direction between an outer member of the hub flange and the connection flange.
6. The propulsor of claim 3 , wherein the interface-side insulative layers form part of the hub flange or the connection flange.
7. The propulsor of claim 1 , wherein the plurality of insulative layers comprise aperture-side insulative layers, wherein the aperture-side insulative layers comprise an outer layer and an inner layer spaced apart along a radial direction.
8. The propulsor of claim 7 , wherein the outer layer extends circumferentially around an aperture defined by at least one of the hub flange or the connection flange.
9. The propulsor of claim 1 , a bolt extending through the hub flange and the connection flange, wherein at least one of the plurality of insulative layers extends between the bolt and the hub flange and at least one of the plurality of insulative layers extends between the bolt and the connection flange.
10. The propulsor of claim 9 , wherein at least a portion of the bolt is coated with an insulative coating, the portion being in physical contact with at least one of the hub flange or the connection flange.
11. The propulsor of claim 9 , wherein the insulated joint further comprises:
a hub shim positioned between the hub flange and one of a head of the bolt and a nut secured to the bolt opposite the head, an interface shim positioned between the hub flange and the connection flange so that the hub flange and the connection flange are not in physical contact with one another, and a connection shim positioned between the hub flange and one of the head of the bolt and the nut secured to the bolt opposite the head.
12. The propulsor of claim 1 , wherein at least one of the plurality of insulative layers comprises at least two layers and wherein a metallic layer is positioned at least partially between the at least two layers.
13. The propulsor of claim 1 , wherein the plurality of insulative layers are formed from ceramic.
14. The propulsor of claim 1 , wherein the electric machine is electrically coupled with a power converter.
15. The propulsor of claim 1 , wherein the gas turbine engine further comprises a grounding device having a stationary component, a rotating component connected to the shaft, and one or more electrical contacts providing an electrical grounding pathway between the rotating component and the stationary component, the stationary component being electrically coupled with a grounding system.
16. The propulsor of claim 15 , wherein the grounding device is integrated into a brush seal, the brush seal comprising a plurality of brushes separated by walls that extend along a radial direction.
17. The propulsor of claim 16 , wherein the shaft comprises a wear resistant coating and a distal end of each of the plurality of brushes contact the wear resistant coating.
18. The propulsor of claim 1 , wherein the gas turbine engine includes a low speed shaft and a high speed shaft, and wherein the shaft is the low speed shaft.
19. A method, comprising:
operating a propulsor having a gas turbine engine equipped with an electric machine operatively coupled with a shaft of the gas turbine engine, the electric machine being electrically coupled with a power converter, and a rotor hub comprising a hub flange and being operatively coupled to the shaft; and
wherein operating the propulsor comprises:
i) interrupting, via an insulated joint that operatively couples a rotor assembly of the electric machine with the shaft, a common mode electric current driven by the power converter to the electric machine from flowing between the rotor assembly and the shaft, the insulated joint comprising a plurality of insulative layers, at least one of the plurality of insulative layers extending between the hub flange and a connection flange of the rotor assembly, wherein the plurality of insulative layers comprise hub-side insulative layers, wherein the hub-side insulative layers comprise an outer layer and an inner layer spaced apart along an axial direction; and
ii) electrically grounding, by a grounding device, the shaft.
20. A propulsor, comprising:
a gas turbine engine having a shaft and one or more bearings supporting the shaft;
a rotor hub operatively coupled to the shaft and comprising a hub flange;
an electric machine comprising a stator assembly and a rotor assembly;
a rotor connection member operatively coupled to the rotor assembly of the electric machine and comprising a connection flange; and
an insulated joint for operatively coupling the rotor assembly with the shaft, the insulating joint comprising:
a plurality of insulative layers, at least one of the plurality of insulative layers extending between the hub flange and the connection flange to interrupt common mode electric current from flowing between the rotor assembly and the shaft, wherein the plurality of insulative layers comprise interface-side insulative layers, wherein the interface-side insulative layers comprise an outer layer and an inner layer spaced apart along an axial direction.