Electromagnetic inducer for gas turbine rotating turbomachinery
Gas turbine engines include fan, compressor, combustor, and turbine sections. An electric machine assembly includes a rotating component comprising a plurality of airfoils and a plurality of first electric machine elements, with each airfoil including a respective first magnetic material electric machine element. A housing is arranged radially outward from the airfoils and includes a circumferential slot. A second electric machine element is arranged within the circumferential slot in the form of a circumferential winding arranged radially outward from the rotating component. A control system is electrically connected to the second electric machine element. Rotation of the rotating component causes the first electric machine elements to generate a magnetic flux and induce a current within the second electric machine element and the control system is configured to distribute the induced current to at least one of a storage device or electrical components of the gas turbine engine.
1. A gas turbine engine comprising:
a fan section, a compressor section, a combustor section, and a turbine section, wherein at least a portion of the fan section, the compressor section, and the turbine section are operably connected by a shaft; and
an electric machine assembly comprising:
a rotating component connected to the shaft and comprising a plurality of airfoils;
a plurality of first electric machine elements, wherein each airfoil of the plurality of airfoils comprises a respective first electric machine element, wherein each first electric machine element comprises a magnetic material;
a housing arranged radially outward from the plurality of airfoils, the housing comprising a circumferential slot;
a second electric machine element arranged within the circumferential slot, wherein the second electric machine element comprises a coil configured as a circumferential winding arranged radially outward from the rotating component and within the circumferential slot, wherein the coil has a coil diameter (D) that is sized relative to a chord length (L) of the plurality of airfoils such that: 0.25 L≤D≤1.50 L; and
a control system electrically connected to the second electric machine element and completely encapsulated within the circumferential slot, wherein the coil of the second electric machine element connects to a first side of the control system, extends continuously about the circumferential slot, and connects to a second side of the control system,
wherein rotation of the rotating component causes the plurality of first electric machine elements to generate a dynamic magnetic flux to induce a current within the second electric machine element, and
wherein the control system is configured to distribute the current induced within the second electric machine element to at least one of a storage device or electrical components of the gas turbine engine.
2. The gas turbine engine of claim 1 , wherein each first electric machine element comprises a magnetic cap arranged at a tip of a respective airfoil.
3. The gas turbine engine of claim 1 , wherein each first electric machine element comprises a magnetic coating applied to a tip of a respective airfoil.
4. The gas turbine engine of claim 1 , wherein each airfoil of the plurality of airfoils comprises a magnetic material that extends from a root to a tip of the respective airfoil, wherein the plurality of first electric machine elements is defined by the magnetic material airfoils.
5. The gas turbine engine of claim 1 , further comprising a cover arranged between tips of the respective airfoils and the second electric machine element, the cover sealing the second electric machine element and the control system within the slot.
6. The gas turbine engine of claim 1 , further comprising a filler material arranged within the slot to secure the second electric element within the slot.
7. The gas turbine engine of claim 1 , wherein the control system comprises at least one electronic control element and an electrical storage element.
8. The gas turbine engine of claim 1 , wherein the control system is configured to direct a current through the second electric machine element in a reverse direction counter to a direction of rotation of the rotating component.
9. The gas turbine engine of claim 8 , further comprising at least one sensor arranged to monitor an air gap between blade tips of the plurality of airfoils and the housing, wherein the control system is configured to control a current through the second electric machine element to correct for deviations in the air gap and balance or align the rotating component relative to the housing.
10. The gas turbine engine of claim 8 , wherein the control system is configured to direct a counter current through the second electric machine element to induce a reverse magnetic field and slow a rotation of the rotating component.
11. The gas turbine engine of claim 8 , wherein the control system is configured to maintain an alignment of the rotating component relative to the housing by selectively directing the current through the second electric machine component.
12. The gas turbine engine of claim 1 , wherein the rotating component is part of at least one of the fan section, the compressor section, or the turbine section.
13. The gas turbine engine of claim 1 , wherein the second electric machine element is formed of a coil made from at least one of copper, gold, aluminum, silver.
14. The gas turbine engine of claim 1 , wherein the first electric machine element is formed from neodymium.
15. The gas turbine engine of claim 1 , wherein the fan section, a low pressure compressor of the compressor section, and a low pressure turbine of the turbine section comprise a low-pressure system having a rotational speed of N1 and a high pressure compressor of the compressor section and a high pressure turbine of the turbine section comprise a high-pressure system having a rotational speed of N2, wherein the control system is configured to distribute the current to at least one of the low-pressure system and the high-pressure system to couple the rotational speeds N1, N2.
16. A method of operating a gas turbine engine, wherein the gas turbine engine comprises a fan section, a compressor section, a combustor section, and a turbine section, wherein at least a portion of the fan section, the compressor section, and the turbine section are operably connected by a shaft, the method comprising:
rotating a plurality of first electric machine elements on a rotating component, wherein the plurality of first electric machine elements are arranged at tips of respective airfoils of the rotating component, wherein each first electric machine element comprises a magnetic material;
inducing a current within a second electric machine element, the second electric machine element configured as a coil arranged within a circumferential slot in a housing that is arranged radially outward from the airfoils of the rotating component; wherein the coil is arranged as a circumferential winding arranged radially outward from the rotating component within the circumferential slot, and wherein the coil has a coil diameter (D) that is sized relative to a chord length (L) of the plurality of airfoils such that: 0.25 L≤D≤1.50 L; and
distributing the current induced within the second electric machine element using a control system that is electrically connected to the second electric machine element, wherein the control system is completely encapsulated within the circumferential slot, and wherein the coil of the second electric machine element connects to a first side of the control system, extends continuously about the circumferential slot, and connects to a second side of the control system;
wherein rotation of the rotating component causes the plurality of first electric machine elements to generate a dynamic magnetic flux to induce the current within the second electric machine element, and
wherein the current is distributed to at least one of a storage device or electrical components of the gas turbine engine.
17. The method of claim 16 , further comprising reversing a current through the second electric machine element to cause a balancing operation to maintain an air gap between tips of the plurality of airfoils and the housing.
18. The method of claim 16 , further comprising reversing a current through the second electric machine element to generate a braking force to slow a rotation of the rotating component.
19. The method of claim 16 , wherein the fan section, a low pressure compressor of the compressor section, and a low pressure turbine of the turbine section comprise a low-pressure system having a rotational speed of N1 and a high pressure compressor of the compressor section and a high pressure turbine of the turbine section comprise a high-pressure system having a rotational speed of N2, the method further comprising:
distributing the current to at least one of the low-pressure system and the high-pressure system to couple the rotational speeds N1, N2.