Turbine equipped with an embedded electric machine having a segmented and movable stator

Abstract

A turbine equipped with an embedded motor having a segmented and movable stator is provided. In one aspect, a turbine defines a radial direction and includes a rotating component, an actuator, and a motor. The motor includes a rotor assembly that can rotate with the rotating component and is operatively connected to the rotating component. The motor also includes a stator assembly that has a stator divided into stator segments. Each of the stator segments can be moved between a first position and a second position in a radial direction by one of the actuators, and each of the stator segments is closer to the rotor assembly in the radial direction when in the first position than when in the second position.

Description

[0001] CROSS-REFERENCE TO RELATED APPLICATIONS

[0002] This application claims the benefit of U.S. Provisional Patent Application Serial No. 63 / 072,471, filed on August 31, 2020, which is incorporated herein by reference in its entirety. Technical Field

[0003] The present subject matter generally relates to turbines equipped with embedded electric machines. Background Art

[0004] A typical aircraft propulsion system includes one or more gas turbine engines. For some propulsion systems, the gas turbine engine generally includes a fan and a core arranged to flow in communication with each other. In addition, the core of the gas turbine engine generally includes a compressor section, a combustion section, a turbine section, and an exhaust section downstream of the fan in a series flow order. In operation, air is provided from the fan to the inlet of the compressor section, where one or more axial flow compressors gradually compress the air until the air reaches the combustion section. Fuel is mixed with the compressed air and burned in the combustion section to provide combustion gases. The combustion gases are directed from the combustion section to the turbine section. The combustion gas flow through the turbine section drives the turbine section and is then directed to, for example, the atmospheric environment through the exhaust section.

[0005] For certain aircraft propulsion systems, and aircraft incorporating such aircraft propulsion systems, it may be beneficial for the propulsion system to include an electric machine to generate electrical power, for example, for the gas turbine engine and / or various accessory systems of the aircraft, for electric or hybrid electric propulsion devices, etc. One problem with permanent magnet electric machines is that in the event of a fault condition, such as a short circuit within a stator coil, continued rotation of the rotor continues to generate magnetic flux / current across such a fault, potentially generating high temperatures. When the electric machine is connected to an integral part of the aircraft propulsion system, such as a main gas turbine engine, it may be impractical to shut down the gas turbine engine to prevent rotation of the rotor of the electric machine.

[0006] Therefore, it would be useful to have a propulsion system for an aircraft having an electric machine that could address one or more of these issues. Summary of the invention

[0007] Technical Solution 1. A motor, which defines an axial direction, a radial direction and a center line extending along the axial direction, the motor comprising:

[0008] a rotor assembly rotatable about the centerline; and

[0009] A stator assembly having a stator divided into stator segments, each of the stator segments being movable along the radial direction between a first position and a second position, each of the stator segments being closer to the rotor assembly in the first position than in the second position.

[0010] Technical Solution 2. The motor according to any one of the preceding technical solutions, wherein the first position is an engaged position, and the second position is a disengaged position.

[0011] Technical Solution 3. The electric machine according to any one of the preceding technical solutions, wherein each of the stator segments has an associated set of stator windings, and wherein the stator windings of each set are only wound within their corresponding stator segments.

[0012] Technical Solution 4. An electric machine according to any one of the preceding technical solutions, wherein each stator segment has an associated power converter.

[0013] Technical Solution 5. The electric machine according to any one of the preceding technical solutions, wherein the stator segments are individually movable between their respective first and second positions.

[0014] Technical Solution 6. The electric machine according to any one of the preceding technical solutions, wherein the stator segment comprises at least four stator segments.

[0015] Technical Solution 7. According to any one of the preceding technical solutions, the electric machine, each of the stator segments is capable of moving a distance greater than 0.5 inches and less than 10 inches along the radial direction between their respective first position and second position.

[0016] Technical Solution 8. An electric machine according to any one of the preceding technical solutions, wherein each stator segment has an actuator associated therewith, each of the actuators being operable to move a corresponding one of the stator segments between a corresponding first position and a second position of the stator segment.

[0017] Technical Solution 9. An electric motor according to any one of the preceding technical solutions, wherein a controller associated with the motor and operably connected to the actuator is configured to: in response to receiving data indicating a fault in the motor, cause the actuator to move their respective stator segments from their respective first positions away from the rotor assembly to their respective second positions.

[0018] Technical Solution 10. An electric motor according to any one of the preceding technical solutions, wherein a controller associated with the electric motor and operably connected to the actuator is configured to cause the actuator to move their respective stator segments away from the rotor assembly to respective partial power positions located between their respective first positions and second positions.

[0019] Technical Solution 11. An electric motor according to any one of the preceding technical solutions, wherein, when the stator segments are in their respective first positions, each stator segment engages with an adjacent one of the stator segments, and when the stator segments are in their respective second positions, the stator segments disengage from each other.

[0020] Technical Solution 12. An electric motor according to any one of the preceding technical solutions, wherein the rotor assembly comprises a plurality of permanent magnets.

[0021] Technical Solution 13. The electric machine according to any one of the preceding technical solutions, wherein the stator segments are capable of moving simultaneously between their respective first and second positions.

[0022] Technical Solution 14. A turbine, which defines a radial direction, comprising:

[0023] Rotating parts;

[0024] Actuator;

[0025] An electric motor comprising:

[0026] a rotor assembly rotatable with and operatively coupled to the rotating component; and

[0027] A stator assembly having a stator divided into stator segments, each of the stator segments being movable by one of the actuators along the radial direction between a first position and a second position, each of the stator segments being closer to the rotor assembly along the radial direction when in the first position than when in the second position.

[0028] Technical Solution 15. The turbine according to any one of the above technical solutions, further comprising:

[0029] one or more sensors associated with the motor; and

[0030] a controller associated with the motor and communicatively coupled to the actuator and the one or more sensors, the controller being configured to:

[0031] receiving data from the one or more sensors indicative of a fault associated with the electric machine; and

[0032] In response to receiving the data indicative of the fault associated with the electric machine, the actuators are caused to move their respective stator segments in the radial direction away from the rotor assembly.

[0033] Technical Solution 16. The turbine according to any one of the above technical solutions, further comprising:

[0034] a controller associated with the motor and communicatively coupled to the actuator, the controller being configured to:

[0035] receiving an electrical power demand indicative of electrical power required by one or more electrical loads electrically coupled to the electric machine; and

[0036] The actuators are caused to move their respective stator segments relative to the rotor assembly along the radial direction in response to receiving the electrical power demand.

[0037] Technical Solution 17. The turbine according to any one of the preceding technical solutions, wherein the turbine is an aircraft gas turbine engine, and wherein the rotating component is one of a low-pressure shaft and a high-pressure shaft of the aircraft gas turbine engine.

[0038] Technical Solution 18. A method comprising:

[0039] an electric machine operating to convert electrical power to rotational power or vice versa, the electric machine having a stator assembly and a rotor assembly rotatable with a rotating component of the turbine, the stator assembly having a stator segmented into stator segments;

[0040] receiving data indicative of a fault condition within the electric machine; and

[0041] In response to receiving the data indicative of the fault condition within the electric machine, each of the stator segments is moved away from the rotor assembly along a radial direction defined by the turbine.

[0042] Technical Solution 19. A method according to any one of the aforementioned technical solutions, wherein the stator segments include a first stator segment and a second stator segment, and wherein moving each of the stator segments away from the rotor assembly along the radial direction includes moving the first stator segment and the second stator segment relative to each other along the radial direction.

[0043] Technical Solution 20. The method according to any one of the preceding technical solutions, wherein the stator segment moves away from the rotor assembly along the radial direction by a distance greater than 0.5 inches and less than 10 inches. BRIEF DESCRIPTION OF THE DRAWINGS

[0044] A complete and enabling disclosure of the present invention, including the best mode thereof, to one of ordinary skill in the art is set forth in the specification with reference to the accompanying drawings, in which:

[0045] Figure 1 is a schematic cross-sectional view of a gas turbine engine according to an exemplary aspect of the present disclosure;

[0046] Figure 2 is a schematic cross-sectional view of an electric machine embedded in a gas turbine engine according to an exemplary embodiment of the present disclosure and depicts a stator segment of the electric machine in a first position;

[0047] Figure 3 yes Figure 2 A schematic cross-sectional view of an exemplary electric machine of FIG. 1 and depicting a stator segment of the electric machine in a second position;

[0048] Figure 4 yes Figure 2 Schematic axial view of an electric machine of , depicting stator segments of the electric machine in their respective first positions;

[0049] Figure 5 yes Figure 2 , depicting a stator segment of the electric machine in its respective second position;

[0050] Figure 6 is a flow chart of a method of operating an electric machine according to an exemplary aspect of the present disclosure; and

[0051] Figure 7 is a block diagram of an example computing system that can be used to implement aspects of the present disclosure. DETAILED DESCRIPTION

[0052] Reference will now be made in detail to the present embodiments of the present invention, one or more examples of which are shown in the accompanying drawings. The detailed description uses numerical and letter designations to refer to features in the drawings. The same or similar designations in the drawings and description are used to refer to the same or similar parts of the present invention.

[0053] As used herein, the terms “first,” “second,” and “third” may be used interchangeably to distinguish one component from another, and are not intended to indicate the position or importance of each component.

[0054] The terms "front" and "rear" refer to relative positions within a gas turbine engine or vehicle and refer to the normal operating attitude of the gas turbine engine or vehicle. For example, for a gas turbine engine, front refers to a position closer to the engine inlet and rear refers to a position closer to the engine nozzle or exhaust.

[0055] The terms "upstream" and "downstream" refer to relative directions with respect to the flow of a fluid in a fluid path. For example, "upstream" refers to the direction from which the fluid is flowing, and "downstream" refers to the direction to which the fluid is flowing.

[0056] The terms "coupled," "fixed," "attached to," and the like refer to both direct coupling, fixing, or attachment as well as indirect coupling, fixing, or attachment through one or more intermediate components or features, unless otherwise indicated herein.

[0057] The singular forms "a," "an," and "the" include plural references unless the context clearly dictates otherwise.

[0058] As used throughout the specification and claims, approximate language is used to modify any quantitative representation, and variations of the quantitative representation may be permitted without causing changes to the basic functions associated therewith. Therefore, the values ​​modified by one or more terms such as "about", "approximately" and "substantially" are not limited to the exact values ​​specified. In at least some cases, approximate language may correspond to the accuracy of an instrument for measuring a value, or the accuracy of a method or machine for constructing or manufacturing a component and / or system. For example, approximate language may refer to within a margin of 1%, 2%, 4%, 5%, 10%, 15% or 20% of any individual value, range of value and / or endpoint of a range of defined values.

[0059] Here and throughout the specification and claims, range limitations are combined and interchanged, such that ranges are identified and include all sub-ranges contained therein unless context or language indicates otherwise. For example, all ranges disclosed herein include the endpoints, and the endpoints are independently combinable with each other.

[0060] Aspects of the present disclosure are directed to an electric machine having a segmented and movable stator, a turbine in which such an electric machine is embedded, and a method of operating such an electric machine. In one aspect, a turbine defines a radial direction and includes a rotating component, an actuator, and an electric machine. The turbine may be, for example, an aircraft gas turbine engine. For example, the rotating component may be one of a low-pressure and a high-pressure shaft or a rotating shaft. The electric machine includes a rotor assembly that is capable of rotating with the rotating component and is operatively coupled to the rotating component. The electric machine also includes a stator assembly having a stator that is segmented or segmented into stator segments. Each of the stator segments can be moved between a first position and a second position in a radial direction by one of the actuators. The stator segment is closer to the rotor assembly in the first position than in the second position in the radial direction. Moving the stator segment relative to the rotor assembly can prevent or mitigate damage when a fault or failure associated with the electric machine is detected, and can be used to control the amount of power extracted by the electric machine and other benefits.

[0061] Referring now to the drawings, in which like numerals refer to like elements throughout the several views, Figure 1 1 is a schematic cross-sectional view of a propulsion engine according to an exemplary embodiment of the present disclosure. In certain exemplary embodiments, the propulsion engine may be configured as a turbofan jet engine, referred to herein as a "turbofan engine 100". Turbofan engine 100 may be incorporated into an aircraft propulsion system, such as as an underwing mounted turbofan engine. However, alternatively, in other embodiments, turbofan engine 100 may be incorporated into any other suitable aircraft or propulsion system. Figure 1 As shown, the turbofan engine 100 defines an axial direction A (extending parallel to a longitudinal centerline 102 provided for reference) and a radial direction R. The turbofan engine 100 also defines a circumferential direction C ( Figure 2 ).

[0062] The turbofan engine 100 includes a fan section 104 and a core engine 106 disposed downstream of the fan section 104. The depicted core turbine engine 106 includes a substantially tubular outer casing 108 defining an annular core inlet 120. The outer casing 108 encloses in series flow relationship: a compressor section including a boost or low pressure (LP) compressor 122 and a high pressure (HP) compressor 124; a combustion section 126; a turbine section including an HP turbine 128 and an LP turbine 130; and an injection nozzle exhaust nozzle section 132. The compressor section, combustion section 126, and turbine section together define a core air flow path 164 extending from the annular core inlet 120 through the LP compressor 122, the HP compressor 124, the combustion section 126, the HP turbine section 128, the LP turbine section 130, and the injection nozzle exhaust section 132. The HP shaft or spool 134 drivingly connects the HP turbine 128 to the HP compressor 124. An LP shaft or spool 136 drivingly connects the LP turbine 130 to the LP compressor 122 .

[0063] The fan section 104 includes a variable pitch fan 138 having a plurality of fan blades 140 coupled to a disk 142 in a spaced apart manner. As depicted, the fan blades 140 extend outwardly from the disk 142 generally along a radial direction R. The fan blades 140 and the disk 142 are capable of rotating together about the longitudinal centerline 112 across a power gearbox 144 via an LP shaft 144. The power gearbox 144 includes a plurality of gears for adjusting the rotational speed of the LP shaft 136. In addition, for the depicted embodiment, the disk 142 of the variable pitch fan 138 is covered by a rotatable spinner or front hub 146, which is aerodynamically contoured to facilitate airflow through the plurality of fan blades 140.

[0064] The turbofan engine 100 also includes a plurality of circumferentially spaced outlet guide vanes 150. The plurality of outlet guide vanes 150 are positioned downstream of the fan 138 along the axial direction A and extend outwardly from the outer casing 108 of the core engine 106 generally along the radial direction R. Figure 1 In the depicted embodiment, turbofan engine 100 does not include any external fan case enclosing fan section 104 and / or outlet guide vanes 150. In addition, fan section 104 includes only a single fan. Figure 1 The turbofan engine 100 depicted in FIG. 1 may be referred to as an unducted single fan (USF) turbofan engine.

[0065] For the exemplary turbofan engine 100 depicted, the fan section 104 (or more specifically, the rotation of the fan blades 140 of the fan 138) provides the majority of the propulsive thrust of the turbofan engine 100. Additionally, a plurality of exit guide vanes 150 are provided to increase the efficiency of the fan section 104 and to provide other benefits, such as reducing the amount of noise generated by the turbofan engine 100 by directing the air flow from the plurality of fan blades 140 of the fan section 104.

[0066] During operation of the turbofan engine 100, a volume of air 156 passes through the plurality of blades 140 of the fan section 104. A first portion of the volume of air 156 (i.e., first portion of air 160) is directed or channeled into a core air flow path 164 extending through the compressor section, the combustion section 126, the turbine section, and the exhaust section 132. Additionally, a second portion of the volume of air 156 (i.e., second portion of air 162) flows around the core engine 106, thereby bypassing the core engine 106 (i.e., in a bypass air flow path). The ratio between the second portion of air 162 and the first portion of air 160 is generally referred to as a bypass ratio.

[0067] The pressure of first portion of air 160 increases as it is directed through LP compressor 122 and subsequently through HP compressor 124. Compressed first portion of air 160 is then provided to combustion section 126 where it is mixed with fuel and combusted to provide combustion gases 174. Combustion gases 174 are directed through HP turbine 128 where a portion of the thermal and / or kinetic energy from combustion gases 174 is extracted via sequential stages of HP turbine stator vanes 176 coupled to outer casing 108 and HP turbine rotor blades 178 coupled to HP shaft 134. The extraction of thermal and / or kinetic energy from combustion gases 174 causes HP shaft 134 to rotate, thereby supporting operation of HP compressor 124. The combustion gases 174 are then directed through the LP turbine 130 where a second portion of the thermal and kinetic energy is extracted from the combustion gases 174 via sequential stages of LP turbine stator vanes 180 coupled to the outer casing 108 and LP turbine rotor blades 182 coupled to the LP shaft 136, thereby rotating the LP shaft or spool 136 to support operation of the LP compressor 122 and / or rotation of the fan 138. The combustion gases 174 are then directed through the ejection exhaust nozzle section 132 of the core engine 106 to provide propulsive thrust to supplement the propulsive thrust provided by the fan 138.

[0068] like Figure 1 As further shown, the exemplary turbofan engine 100 includes an electric motor 200 embedded therein. For this embodiment, the electric motor 200 is operatively coupled to the low pressure system (and more particularly the LP shaft 136) of the turbofan engine 100. The electric motor 200 includes a rotor assembly 210 and a stator assembly 230. The rotor assembly 210 is capable of rotating together with one or more rotatable components of the turbofan engine 100. Specifically, for this embodiment, the rotor assembly 210 is mounted to the LP shaft 136 and is capable of rotating together with the LP shaft 136. In addition, the electric motor 200 is arranged coaxially with the LP shaft 136. As used herein, "coaxially" refers to axis alignment. However, it should be understood that in other embodiments, the axis of the electric motor 200 may be radially offset from the axis of the LP shaft 136. The rotor assembly 210 and the stator assembly 230 define an air gap 270 ( Figure 2 As will be further explained below, the stator assembly 230 includes a stator segmented into stator segments, each of which is movable in a radial direction R relative to the rotor assembly 210 during certain operations.

[0069] It will be understood that Figure 1The turbofan engine 100 depicted in the drawings is provided by way of example only, and in other exemplary embodiments, the turbofan engine 100 may have any other suitable configuration. For example, in other exemplary embodiments, the turbofan engine 100 may be configured as a turboprop engine, a turbojet engine, a turbofan engine of a different configuration, or any other suitable gas turbine engine. Additionally or alternatively, the exemplary aspects of the present disclosure (such as the motor 200) may be incorporated into or otherwise used with any other suitable type of turbine, such as an aeroderivative gas turbine engine, a marine gas turbine engine, a power generation gas turbine engine, an internal combustion engine, etc., or further used with any other machine having a rotating component.

[0070] Reference now Figure 2 , a schematic cross-sectional view of the motor 200 is provided. For this embodiment, the motor 200 is embedded in the turbofan engine 100 along the axial direction A behind the fan 138 and in front of the inlet guide vanes 184 located at the annular core inlet 120. However, it will be understood that in other exemplary embodiments, the motor 200 may be located at other suitable locations within the turbofan engine 100. In addition, as shown, the motor 200 defines a centerline 202. For this embodiment, the centerline 202 is aligned with the longitudinal axis 102 of the turbofan engine 100.

[0071] As noted above, the motor 200 includes a rotor assembly 210 and a stator assembly 230. The rotor assembly 210 generally includes a rotor 212 and a rotor connection member 214. The stator assembly 230 includes a stator 232 and a stator connection member 234. The stator 232 is connected to and supported by the stator connection member 234. The rotor 212 of the rotor assembly 210 and the stator 232 of the stator assembly 230 together define an air gap 270 therebetween. In addition, for this embodiment, the rotor 212 includes a plurality of magnets 216, such as a plurality of permanent magnets, and the stator 232 includes a plurality of coils or windings 236. As such, it will be understood that the motor 200 may be referred to as a permanent magnet motor. However, in other exemplary embodiments, the motor 200 may be configured in any other suitable manner. For example, the motor 200 may be configured as an electromagnetic motor including a plurality of electromagnets and active circuits, an induction motor, a switched reluctance motor, a synchronous AC motor, an asynchronous motor, or having any other suitable configuration.

[0072] For the illustrated embodiment, the rotor assembly 210 is operatively coupled with the LP shaft 136, and thus, the rotor assembly 210 is rotatable with the LP shaft 136. More specifically, as depicted, the rotor connection member 214 extends between the LP shaft 136 and the rotor 212 for connecting the rotor 212 to the LP shaft 136. For this embodiment, the rotor connection member 214 is connected to the LP shaft 136 via a spline connection. In particular, the rotor connection member 214 includes a connection portion 218 having a plurality of teeth 220 arranged generally along the axial direction A, and similarly, the LP shaft 136 includes a connection portion 186 having a plurality of teeth 188 arranged generally along the axial direction A. The plurality of teeth 220 of the connection portion 218 of the rotor connection member 214 is configured to engage with the plurality of teeth 188 of the connection portion 186 of the LP shaft 136, thereby securing the two components to each other along the circumferential direction C. Notably, however, this configuration allows for relative movement of the rotor assembly 210 along the axial direction A relative to the LP shaft 136 .

[0073] It will be appreciated that in other embodiments, the rotor connection member 214 may be coupled to the LP shaft 136 in any other suitable manner to allow relative movement along the axial direction A while securing the components along the circumferential direction C. For example, in other example embodiments, the rotor connection member 214 may be coupled to the LP shaft 136 using a plurality of linear bearings, linear slides, etc.

[0074] During certain operations of the turbofan engine 100, the LP shaft 136 may rotate the rotor assembly 210 of the motor 200 relative to the stator assembly 230, thereby allowing the motor 200 to operate in a generator mode. Therefore, during such operations, the motor 200 may generate electrical power. For this embodiment, the motor 200 is electrically coupled to the power bus 190. The power bus 190 may electrically couple or connect the motor 200 to various electrical absorbers (accessory systems, electrical / hybrid electrical propulsion equipment, etc.), power sources (other motors, electrical energy storage units, etc.), or both. In this way, the electrical power generated by the motor 200 may be provided to such electrical absorbers and / or power sources. During some operations, the motor 200 may operate in a drive mode. Therefore, during such operations, the motor 200 may drive the LP shaft 136 around the longitudinal centerline 102.

[0075] In addition, in some embodiments, the turbofan engine 100 may further include a cavity wall surrounding at least a portion of the motor 200. In some embodiments, the cavity wall may substantially completely surround the motor 200, extending from a position near the front end of the motor 200 to a position behind the motor 200. The cavity wall may be used as, for example, a cooling air cavity wall, a sump for cooling fluid, a protective cover for the motor 200, etc. For example, in some embodiments, the engine may further include a second cavity wall (not shown) to form a buffer cavity around the motor 200 and thermally protect the motor 200.

[0076] Reference now Figure 2 , Figure 3 , Figure 4 and Figure 5 The stator assembly 230 will now be described further. Figure 4 and Figure 5 As best shown in , the stator 232 is split or segmented into stator segments. The stator 232 is split into at least two stator segments. The stator 232 may be split into any suitable number of stator segments. In some embodiments, for example, the stator 232 may be split into a first segment and a second segment. In other embodiments, the stator 232 may be split into at least four stator segments. For example, for this embodiment, the stator 232 is split into four stator segments, including a first stator segment 232A, a second stator segment 232B, a third stator segment 232C, and a fourth stator segment 232D. Figure 2 and Figure 3 Only the first stator segment 232A is depicted in FIG. The four stator segments 232A, 232B, 232C, 232D may be segments of uniform or equal size, such as Figure 4 and Figure 5 Best shown in .

[0077] Each of the stator segments 232A, 232B, 232C, 232D has an associated set of stator windings or coils. Figure 4 and Figure 5As best shown in FIG. 1 , the first stator segment 232A has a first set of stator windings 236A associated therewith, the second stator segment 232B has a second set of stator windings 236B associated therewith, the third stator segment 232C has a third set of stator windings 236C associated therewith, and the fourth stator segment 232D has a fourth set of stator windings 236D associated therewith. Notably, the stator windings 236A, 236B, 236C, 236D of each set are wound only within their respective stator segments 232A, 232B, 232C, 232D. This allows the stator segments 232A, 232B, 232C, 232D to be individually movable along the radial direction R, as will be explained below. The stator windings 236A, 236B, 236C, 236D may be wound within their respective stator segments 232A, 232B, 232C, 232D simply through the slots defined between adjacent teeth of the stator segments 232A, 232B, 232C, 232D, as shown in FIG. Figure 4 and Figure 5 shown.

[0078] In addition, for this embodiment, the first set of stator windings 236A wound only in the first stator segment 232A includes one or more windings associated with the first phase, one or more second windings associated with the second phase, and one or more third windings associated with the third phase. Therefore, the first set of stator windings 236A is a three-phase set of windings. The second set of stator windings 236B, the third set of stator windings 236C, and the fourth set of stator windings 236D wound only in their respective stator segments 232B, 232C, 232D can each be wound similarly to the first set of stator windings 236A. Therefore, in this example, each stator segment 232A, 232B, 232C, 232D includes a set of three-phase windings 236A, 236B, 236C, 236D wound only in their respective stator segments 232A, 232B, 232C, 232D. It will be appreciated that the inventive aspects of the present disclosure may be applied to any multi-phase winding arrangement having any suitable number of phases, such as six phases. For example, each stator segment may have an associated set of six-phase windings rather than an associated set of three-phase windings.

[0079] In some embodiments, the stator windings of a group associated with one of the stator segments may be arranged in a toothed or concentrated configuration. In such a configuration, the entry side of a given winding is wound through a slot, and the return side of a given winding is wound through an adjacent slot. Thus, in a toothed or concentrated winding configuration, the stator windings are within the same stator segment and travel back and forth between slots that are separated from each other by only a single slot (i.e., they are adjacent slots). Figure 4 and Figure 5, the stator windings 236A, 236B, 236C, 236D are shown as being wound in their respective stator segments 232A, 232B, 232C, 232D in a tooth or concentrated winding configuration. In other embodiments, the stator windings may be arranged in a distributed configuration. In a distributed configuration, the stator windings travel back and forth within the same stator segment and in slots that are separated from each other by more than one slot. It will be understood that the winding configurations disclosed herein are non-limiting examples and that the groups of stator windings associated with their respective stator segments may be wound in other suitable configurations.

[0080] like Figure 4 As best shown in FIG. 1 , each of the stator segments 232A, 232B, 232C, 232D has at least one associated power converter 260A, 260B, 260C, 260D. Each of the power converters 260A, 260B, 260C, 260D is electrically coupled to the stator windings 236A, 236B, 236C, 236D of their respective stator segments 232A, 232B, 232C, 232D. As an example, the power converters 260A, 260B, 260C, 260D may each be operable to convert the electrical power generated by the motor 200 from alternating current (AC) to direct current (DC) and / or to convert the input electrical power provided to the motor 200 from DC to AC.

[0081] By Figure 4 The positions of the middle stator segments 232A, 232B, 232C, 232D are Figure 5 By comparing their corresponding positions in FIG. 1 , it will be appreciated that each of the stator segments 232A, 232B, 232C, 232D can be in a first position ( Figure 4 shown) and the second position ( Figure 5 shown). Figure 2 and Figure 3 It is shown that it is possible to Figure 2 ) and the second position ( Figure 3 ). Notably, each of the stator segments 232A, 232B, 232C, 232D is movable between their respective first and second positions along a radial direction R. Each of the stator segments 232A, 232B, 232C, 232D is closer to the rotor assembly 210 when in their respective first positions than when in their respective second positions. In some cases, each of the stator segments 232A, 232B, 232C, 232D can be moved to an intermediate position between their respective first and second positions.

[0082] Each of the stator segments 232A, 232B, 232C, 232D can be moved relative to the rotor assembly 210 in a radial direction R by an actuator. Figure 4 and Figure 5 As best shown in , each stator segment has an actuator associated therewith. In particular, the first stator segment 232A has a first actuator 250A associated therewith, the second stator segment 232B has a second actuator 250B associated therewith, the third stator segment 232C has a third actuator 250C associated therewith, and the fourth stator segment 232D has a fourth actuator 250D associated therewith. Each of the actuators 250A, 250B, 250C, 250D is operable to move their respective stator segment 232A, 232B, 232C, 232D along the radial direction R between their respective first and second positions or to an intermediate position between the first and second positions.

[0083] The first actuator 250A is coupled to the first stator segment 232A for moving the first stator segment 232A relative to the rotor assembly 210 along a radial direction R, for example between a first position and a second position. For this embodiment, the first actuator 250A is a linear actuator. The first actuator 250A includes a base 252A and an extension 254A that is movable relative to the base 252A along the radial direction R. The base 252A is coupled or attached to the stator connection member 234, such as Figure 2 and Figure 3 As shown. The extension portion 254A is coupled or attached to the first stator segment 232A. In a similar manner, the second actuator 250B is coupled to the second stator segment 232B to move the second stator segment 232B along the radial direction R relative to the rotor assembly 210, for example between a first position and a second position. The second actuator 250B is also a linear actuator and includes a base 252B and an extension portion 254B that is movable along the radial direction R relative to the base 252B. Although not shown, the base 252B is coupled or attached to the stator connection member 234 at a position (such as Figure 2 and Figure 3 The extension portion 254B is coupled or attached to the stator connection member at circumferentially spaced locations (as shown). The extension portion 254B is coupled or attached to the second stator segment 232B.

[0084] In addition, the third actuator 250C is coupled to the third stator segment 232C to move the third stator segment 232C relative to the rotor assembly 210 along the radial direction R, for example, between the first position and the second position. The third actuator 250C is a linear actuator and includes a base 252C and an extension portion 254C that is movable relative to the base 252C along the radial direction R. The base 252C may be coupled to the base 252A of the first actuator 250A or attached to the stator connection member 234 at a position (e.g., Figure 2 and Figure 3 ) and the base 252B of the second actuator 250B is coupled or attached to the stator connection member at a position circumferentially spaced apart from the position where the base 252B of the first actuator 250A is coupled to its corresponding stator connection member. The extension 254C is coupled or attached to the third stator segment 232C. Similarly, like the other actuators, the fourth actuator 250D is coupled to the fourth stator segment 232D to move the fourth stator segment 232D along the radial direction R relative to the rotor assembly 210, for example between a first position and a second position. For this embodiment, the fourth actuator 250D is a linear actuator and includes a base 252D and an extension 254D that is movable along the radial direction R relative to the base 252D. The base 252D is coupled or attached to the stator connection member 234 at a position (as shown) where the base 252A of the first actuator 250A is coupled or attached to the ... Figure 2 and Figure 3 The extension portion 254D is coupled or attached to the stator connection member at positions circumferentially spaced apart from the positions where the base 252B of the second actuator 250B is coupled to its corresponding stator connection member and the positions where the base 252C of the third actuator 250C is coupled to its corresponding stator connection member. The extension portion 254D is coupled or attached to the fourth stator segment 232D.

[0085] The actuators 250A, 250B, 250C, 250D may be powered in any suitable manner. For example, the actuators 250A, 250B, 250C, 250D may be hydraulically driven, pneumatically driven, electrically driven, thermally activated, magnetically activated, etc. Further, in other embodiments, the actuators 250A, 250B, 250C, 250D may not be linear actuators, and instead may be scissor actuators, circular to linear actuators (such as screw actuators), or any other actuator capable of producing linear movement.

[0086] Still reference Figure 2 , Figure 3 , Figure 4 and Figure 5 For the illustrated embodiment, when the stator segments 232A, 232B, 232C, 232D are positioned as shown Figure 2 and Figure 4When the stator segments 232A, 232B, 232C, 232D are positioned as shown in their respective first positions, they are each in an engaged position. Figure 3 and Figure 5 2, they are each in a disengaged position when the rotor 212 of the rotor assembly 210 is in their respective second positions shown. As used herein, the term "engaged position" refers to the relative positioning of the rotor 212 of the rotor assembly 210 relative to the stator 232 of the stator assembly 230 in which the motor 200 can operate within a reasonable error margin of the design efficiency of the motor 200. For example, in the engaged position, the air gap 270 defined between the rotor 212 of the rotor assembly 210 and the stator 232 of the stator assembly 230 can be within a reasonable margin of the optimal design value so that a desired portion of the magnetic flux from the magnets 216 of the rotor 212 can reach the stator windings 236A, 236B, 236C, 236D of the stator segments 232A, 232B, 232C, 232D. In contrast, as used herein, the term “disengaged position” refers to the relative positioning of the rotor 212 of the rotor assembly 210 relative to the stator 232 of the stator assembly 230, in which the motor 200 cannot operate at reasonable efficiency (e.g., where the efficiency is less than 10% of maximum efficiency).

[0087] When the stator segments 232A, 232B, 232C, 232D are positioned in their respective first or engaged positions, as shown in FIG. Figure 2 and Figure 4 As shown, the size of the air gap 270 (i.e., the distance 272 between the given stator segment and the rotor 212, which is Figure 3 and Figure 5 When the stator segments 232A, 232B, 232C, 232D are positioned in their respective second or disengaged positions, as shown in Figure 3 and Figure 5 As shown, the size of the air gap 270 can be a second value. In some embodiments, the second value is at least twice the first value, such as at least four times the first value, such as at least five times the first value, such as up to 200 times the first value, such as up to 100 times the first value, such as up to 20 times the first value. In some embodiments, the actuators 250A, 250B, 250C, 250D can move their respective stator segments 232A, 232B, 232C, 232D along the radial direction R between the engaged position and the disengaged position or between the disengaged position and the engaged position, wherein the movement distance is greater than 0.5 inches and less than 10 inches, such as greater than 1 inch and less than 5 inches.

[0088] The motor 200 configured as provided herein may provide an additional level of safety in the event of a failure or malfunction of the motor 200. More specifically, in the event of a short circuit or other malfunction within the stator 232 of the stator assembly 230 (e.g., within one or more of the windings 236A, 236B, 236C, 236D), when the rotor assembly 210 is in an engaged position relative to the stator 232, continued rotation of the rotor 212 of the rotor assembly 210 relative to the stator 232 may generate excessive heat, potentially damaging other components within the turbofan engine 100. By utilizing the actuators 250A, 250B, 250C, 250D to move their respective stator segments 232A, 232B, 232C, 232D from their respective engaged positions to their respective disengaged positions, the turbofan engine 100 may continue to operate without risk of additional damage thereto. This functionality may be particularly useful when the turbofan engine 100 is, for example, an aviation gas turbine engine that generates thrust for an aircraft.

[0089] In this manner, turbofan engine 100 may include a control system for controlling the position of stator segments 232A, 232B, 232C, 232D relative to rotor assembly 210. Figure 2 and Figure 3 As best shown in FIG. 1 , the turbofan engine 100 and / or the motor 200 may include a controller 280, one or more sensors 282 ( Figure 2 and Figure 3 Controller 280 is communicatively coupled to one or more sensors 282 and each of actuators 250A, 250B, 250C, 250D, for example, via one or more suitable wired and / or wireless communication links.

[0090] Controller 280 includes one or more memory devices and one or more processors. The one or more memory devices may store information that can be accessed by the one or more processors, including computer executable instructions that can be executed by the one or more processors. The instructions may be any set of instructions that, when executed by the one or more processors, cause the one or more processors to perform operations, such as those provided herein. Controller 280 may be based on Figure 7 Although the controller 280 is configured in Figure 2 and Figure 3200, but it will be appreciated that controller 280 may be located at any suitable location within turbofan engine 100, such as under a cowling. Controller 280 may also be located at a remote location relative to turbofan engine 100, such as within the fuselage of an aircraft on which turbofan engine 100 is installed. In some embodiments, controller 280 may be a dedicated controller for controlling actuation of stator segments 232A, 232B, 232C, 232D. In other embodiments, controller 280 may be an electronic engine controller (EEC) of a full authority digital engine control (FADEC) system.

[0091] In some embodiments, the controller 280 is configured to receive data from one or more sensors 282. The data may indicate a fault within or associated with the motor 200. For example, the one or more sensors 282 may be one or more temperature sensors, for example, configured to sense the temperature of their respective stator segments 232A, 232B, 232C, 232D. If the data sensed by the one or more sensors 282 indicates that the temperature associated with one or more of the stator segments 232A, 232B, 232C, 232D exceeds a certain threshold, this may indicate a fault within the motor 200. Therefore, the controller 280 may determine that the fault is associated with the motor 200 and may cause the actuators 250A, 250B, 250C, 250D to move their respective stator segments 232A, 232B, 232C, 232D from their respective first or engaged positions along the radial direction R outwardly away from the rotor assembly 210 to their respective second or disengaged positions. In other words, in response to receiving data indicative of a fault within the electric machine 200 , the controller 280 may cause the actuators 250A, 250B, 250C, 250D to move their respective stator segments 232A, 232B, 232C, 232D from their respective first or engaged positions to their respective second or disengaged positions along the radial direction R. In this manner, in the event of a fault within or associated with the electric machine 200 , damage to the electric machine 200 and / or other components of the turbofan engine 100 may be prevented or mitigated.

[0092] Additionally, in some embodiments, the controller 280 is configured to receive subsequent data indicating that the fault within or associated with the motor 200 has been remedied or no longer exists and / or a command indicating that the motor 200 is to operate despite the fault condition. Thus, in such embodiments, the controller 280 may cause the actuators 250A, 250B, 250C, 250D to move their respective stator segments 232A, 232B, 232C, 232D from their respective second or disengaged positions inwardly toward the rotor assembly 210 along the radial direction R to their respective first or engaged positions. The subsequent data may be received from one or more sensors 282, an aircraft flight management system, a pilot, etc.

[0093] In addition to the functions noted above, it should be appreciated that the controller 280 may cause the actuators 250A, 250B, 250C, 250D to move their respective stator segments 232A, 232B, 232C, 232D to one or more intermediate or partial power positions between their respective first and second positions (or more specifically, between their respective engaged and disengaged positions) along the radial direction R. In this manner, the actuators 250A, 250B, 250C, 250D may be configured to move their respective stator segments 232A, 232B, 232C, 232D relative to the rotor assembly 210 in order to affect the efficiency of the electric machine 200, thereby effectively controlling the amount of power extracted by the electric machine 200.

[0094] Therefore, in such an embodiment, the controller 280 is configured to receive data indicating an electrical power demand. The electrical power demand may indicate the electrical power required by one or more electrical loads electrically coupled to the motor 200. The electrical power demand may be a request to increase electrical power, decrease electrical power, or in some cases, a request to request the same electrical power as previously requested. In response to the electrical power demand, the controller 280 may cause the actuators 250A, 250B, 250C, 250D to move their respective stator segments 232A, 232B, 232C, 232D away from or toward the rotor assembly 210 in the radial direction R.

[0095] For example, in one aspect, if the electrical power demand is a demand requesting an increase in electrical power, the controller 280 may cause the actuators 250A, 250B, 250C, 250D to move their respective stator segments 232A, 232B, 232C, 232D along the radial direction R toward the rotor assembly 210. The radial distance that the stator segments 232A, 232B, 232C, 232D are moved along the radial direction R toward the rotor assembly 210 may be based on, for example, a plan that associates the required electrical power with the respective positions of the stator segments 232A, 232B, 232C, 232D and / or their associated actuators 250A, 250B, 250C, 250D.

[0096] On the other hand, if the electrical power demand is a demand requesting a reduction in electrical power, the controller 280 may cause the actuators 250A, 250B, 250C, 250D to move their respective stator segments 232A, 232B, 232C, 232D in the radial direction R away from the rotor assembly 210. The radial distance that the stator segments 232A, 232B, 232C, 232D are moved in the radial direction R away from the rotor assembly 210 may be based on a plan that associates the required electrical power with the respective positions of the stator segments 232A, 232B, 232C, 232D and / or their associated actuators 250A, 250B, 250C, 250D, for example. The controller 280 may cause the actuators 250A, 250B, 250C, 250D to maintain the positions of their respective stator segments 232A, 232B, 232C, 232D along the radial direction R if the electrical power demand is a demand that neither requires a decrease nor an increase in electrical power.

[0097] Thus, advantageously, the controller 280 may control the radial position of each of the stator segments 232A, 232B, 232C, 232D relative to the rotor assembly 210 to control the amount of power extracted from the electric machine 200. Furthermore, the electrical power output by the electric machine 200 may be decoupled from the rotational speed of the rotating component to which the rotor assembly 210 is coupled, which in this example is the LP shaft 136.

[0098] It will also be understood that Figures 1 to 5The depicted exemplary motor 200 and turbofan engine 100 are provided by way of example only. In other exemplary embodiments, the motor 200 and turbofan engine 100 may have any other suitable configuration. For example, in other exemplary embodiments, the motor 200 may be positioned at any other suitable position within the gas turbine engine. For example, the gas turbine engine may include a motor coupled to the LP shaft, the HP shaft, or both within the compressor section at a position in front of the HP compressor. Additionally or alternatively, the gas turbine engine may include a motor coupled to the LP shaft, the HP shaft, or both within the compressor section at a position inside the HP compressor. Additionally or alternatively, the gas turbine engine may include a motor coupled to the LP shaft within the turbine section (e.g., at a position in front of the LP turbine). Other suitable positions are also possible.

[0099] Reference now Figure 6 , depicts a flow chart of a method (300) for operating a turbomachine according to exemplary aspects of the present disclosure. In certain exemplary aspects, the method (300) may utilize the motor 200 provided herein. Thus, in certain exemplary aspects, the motor may include a stator assembly and a rotor assembly, and may define a centerline. In addition, the control system described herein may be used to implement all or certain aspects of the method (300). The turbomachine may be any suitable turbomachine, such as an aviation gas turbine engine.

[0100] At (302), the method (300) includes operating an electric motor to convert electrical power into rotational power or converting rotational power into electrical power. The electric motor has a stator assembly and a rotor assembly, which is capable of rotating with a rotating component of the turbine. It is noteworthy that the stator assembly has a stator divided into stator segments. In some embodiments, for example, the stator assembly can be divided or segmented into at least two segments. In some embodiments, the stator assembly can be divided or segmented into at least four segments. In addition, in some embodiments, the turbine is an aviation gas turbine engine. In such an embodiment, the rotating component can be one of a low-pressure shaft and a high-pressure shaft of an aviation gas turbine engine. In addition, in such an embodiment, operating the electric motor to convert rotational power into electrical power can occur during flight operations such as take-off operations, climb operations, cruise operations, and / or descent operations, or alternatively during ground operations.

[0101] At (304), the method (300) includes receiving data indicating a fault condition within the electric machine. Receiving data indicating a fault condition within the electric machine at (304) may include receiving sensor data indicating a short circuit within one or more stator windings or coils associated with one of the stator segments. For example, receiving data indicating a fault condition within the electric machine at (304) may include receiving data indicating a temperature of one or more aspects of a stator assembly.

[0102] At (306), the method (300) includes: in response to receiving data indicating a fault condition within the electric machine, moving each of the stator segments away from the rotor assembly along a radial direction defined by the turbine. For example, the stator segments may be moved outwardly along the radial direction from their respective first or engaged positions to respective second or disengaged positions, wherein the stator segments are each positioned closer to the rotor assembly when in their respective first positions than when in their respective second positions. This may increase an air gap or distance between the stator segments and the rotor assembly.

[0103] In some embodiments, the stator segments are simultaneously movable between their respective first and second positions. In some embodiments, the stator segments are each individually movable between their respective first and second positions, such as by an associated actuator. In some embodiments, the stator segments are each movable in a radial direction away from the rotor assembly a distance greater than 0.5 inches and less than 10 inches.

[0104] Furthermore, in some embodiments, the stator is split or segmented into a first stator segment and a second stator segment. In such embodiments, moving each of the stator segments away from the rotor assembly in a radial direction includes moving the first stator segment and the second stator segment relative to each other in a radial direction. In other embodiments, the stator is split or segmented into a first stator segment, a second stator segment, a third stator segment, and a fourth stator segment, for example, Figure 4 and Figure 5 In such an embodiment, moving each of the stator segments away from the rotor assembly in a radial direction includes moving the first stator segment and the third stator segment relative to each other in a radial direction, and moving the second stator segment and the fourth stator segment relative to each other in a radial direction. In this way, each of the stator segments moves away from the rotor assembly in a radial direction opposite to the opposite segment.

[0105] Additionally or alternatively, it should be appreciated that the method (300) may be configured to additionally move the stator segments to respective intermediate positions between their respective first and second positions (or more precisely, between their respective engaged and disengaged positions) in a radial direction relative to the rotor assembly. In this manner, the method (300) may also be implemented to affect the efficiency of the electric machine, thereby effectively controlling the amount of power extracted by the electric machine (or provided to an engine including the electric machine).

[0106] In this manner, a controller associated with the electric machine may also be configured to move the stator segments in a radial direction relative to the rotor assembly to control the amount of power extracted from the electric machine or provided to an engine including the electric machine. For example, a controller associated with the electric machine may determine that additional power extraction is needed or desired, and in response, the stator segments may be moved to reduce the air gap and increase the power extraction. Additionally or alternatively, a controller associated with the electric machine may determine that a lesser amount of power extraction is needed or desired, and in response, the stator segments may be moved to increase the air gap and reduce the power extraction. Additionally or alternatively, a controller associated with the electric machine may determine that additional power is needed or desired to be provided to an engine including the electric machine, and in response, the stator segments may be moved to reduce the air gap and increase the power provided to the engine. Additionally or further alternatively, a controller associated with the electric machine may determine that a lesser amount of power is needed or desired to be provided to an engine including the electric machine, and in response, the stator segments may be moved to increase the air gap and reduce the power provided to the engine.

[0107] Figure 7 A block diagram of a computing system 400 is provided in accordance with exemplary aspects of the present disclosure. Computing system 400 is one example of a suitable computing system for implementing certain aspects of the present disclosure.

[0108] like Figure 7 As shown, computing system 400 may include one or more processors 404 and one or more memory devices 406. One or more processors 404 and one or more memory devices 406 may be included in one or more computing devices 402, such as controller 280 provided herein. One or more processors 404 may include any suitable processing device, such as a microprocessor, a microcontroller, an integrated circuit, a logic device, or other suitable processing device. One or more memory devices 406 may include one or more computer-readable media, including but not limited to non-transitory computer-readable media or media, RAM, ROM, hard disk drives, flash drives, and other memory devices, such as one or more buffer devices.

[0109] The one or more memory devices 406 may store information accessible by the one or more processors 404, including computer readable instructions 408 executable by the one or more processors 404. The instructions 408 may be any set of instructions that, when executed by the one or more processors 404, causes the one or more processors 404 to perform operations. The instructions 408 may be software written in any suitable programming language, or may be implemented in hardware. The instructions 408 may be any computer readable instructions noted herein.

[0110] The memory device(s) 406 may further store data 410 that may be accessed by the processor(s) 404. For example, the data 410 may include data from one or more sensors 282 ( Figure 2 and Figure 3 ) received. In addition, according to an exemplary embodiment of the present disclosure, the data 410 may include one or more tables, functions, algorithms, models, equations, etc.

[0111] The one or more computing devices 402 may also include a communication interface 412 for communicating with other systems or devices (e.g., actuators 250A, 250B, 250C, 250D), for example. The communication interface 412 may include any suitable components for interfacing with one or more networks, including, for example, a transmitter, a receiver, a port, a controller, an antenna, or other suitable components.

[0112] The techniques discussed herein refer to computer-based systems and actions taken by computer-based systems and information sent to and from computer-based systems. It will be appreciated that the inherent flexibility of computer-based systems allows for various possible configurations, combinations, and divisions of tasks and functions between and among components. For example, the processes discussed herein can be implemented using a single computing device or multiple computing devices working in combination. Databases, memories, instructions, and applications can be implemented on a single system or distributed across multiple systems. Distributed components can operate sequentially or in parallel.

[0113] This written description uses examples to disclose the invention, including the best mode, and also to enable any person skilled in the art to practice the invention, including making and using any devices or systems and performing any incorporated methods. The patentable scope of the invention is defined by the claims and may include other examples that occur to one skilled in the art. These other examples are intended to be within the scope of the claims if they include structural elements that are not different from the literal language of the claims, or if they include equivalent structural elements that have insubstantial differences from the literal language of the claims.

[0114] Further exemplary aspects will be described below with reference to the following clauses:

[0115] 1. An electric machine, which defines an axial direction, a radial direction and a centerline extending along the axial direction, the electric machine comprising: a rotor assembly, which is rotatable about the centerline; and a stator assembly, which has a stator divided into stator segments, each of the stator segments being movable between a first position and a second position along the radial direction, each of the stator segments being closer to the rotor assembly when in the first position than when in the second position.

[0116] 2. An electric machine according to any of the preceding clauses, wherein the first position is an engaged position and the second position is a disengaged position.

[0117] 3. An electrical machine according to any of the preceding clauses, wherein each of the stator segments has an associated set of stator windings, and wherein the stator windings of each set are wound only within their respective stator segment.

[0118] 4. An electrical machine according to any of the preceding clauses, wherein each stator segment has an associated power converter.

[0119] 5. An electrical machine according to any of the preceding clauses, wherein the stator segments are individually movable between their respective first and second positions.

[0120] 6. An electrical machine according to any of the preceding clauses, wherein the stator segment comprises at least four stator segments.

[0121] 7. An electrical machine as claimed in any preceding clause, the stator segments being each movable in a radial direction between their respective first and second positions a distance greater than 0.5 inches and less than 10 inches.

[0122] 8. An electrical machine according to any of the preceding clauses, wherein each stator segment has an actuator associated therewith, each of the actuators being operable to move their respective one of the stator segments between respective first and second positions of the stator segments.

[0123] 9. An electric machine according to any of the preceding clauses, wherein a controller associated with the electric machine and operatively connected to the actuator is configured to: in response to receiving data indicating a fault in the electric machine, cause the actuator to move their respective stator segments from their respective first positions away from the rotor assembly to their respective second positions.

[0124] 10. An electric machine according to any of the preceding clauses, wherein a controller associated with the electric machine and operatively coupled to the actuator is configured to cause the actuator to move their respective stator segments away from the rotor assembly to respective partial power positions between their respective first and second positions.

[0125] 11. An electrical machine according to any of the preceding clauses, wherein each stator segment engages an adjacent one of the stator segments when the stator segments are in their respective first positions, and the stator segments disengage from each other when the stator segments are in their respective second positions.

[0126] 12. An electric machine according to any of the preceding clauses, wherein the rotor assembly comprises a plurality of permanent magnets.

[0127] 13. An electrical machine according to any of the preceding clauses, wherein the stator segments are simultaneously movable between their respective first and second positions.

[0128] 14. A turbine defining a radial direction, the turbine comprising: a rotating component; an actuator; an electric machine, the electric machine comprising: a rotor assembly capable of rotating together with the rotating component and operatively coupled to the rotating component; and a stator assembly having a stator divided into stator segments, each of the stator segments being capable of being moved along the radial direction between a first position and a second position by one of the actuators, each of the stator segments being closer to the rotor assembly along the radial direction when in the first position than when in the second position.

[0129] 15. A turbine according to any of the preceding clauses, further comprising: one or more sensors associated with the motor; and a controller associated with the motor and communicatively coupled to the actuator and the one or more sensors, the controller being configured to: receive data indicating a fault associated with the motor from the one or more sensors; and in response to receiving the data indicating a fault associated with the motor, cause the actuators to move their respective stator segments in a radial direction away from the rotor assembly.

[0130] 16. A turbine according to any of the preceding clauses, further comprising: a controller associated with the motor and communicatively coupled to the actuator, the controller being configured to: receive an electrical power demand indicative of electrical power required by one or more electrical loads electrically coupled to the motor; and cause the actuator to move their respective stator segments in a radial direction relative to the rotor assembly in response to receiving the electrical power demand.

[0131] 17. The turbomachine according to any of the preceding clauses, wherein the turbomachine is an aircraft gas turbine engine, and wherein the rotating component is one of a low pressure shaft and a high pressure shaft of the aircraft gas turbine engine.

[0132] 18. A method comprising: operating an electric machine to convert electrical power into rotational power or vice versa, the electric machine having a stator assembly and a rotor assembly capable of rotating with a rotating component of a turbine, the stator assembly having a stator segmented into stator segments; receiving data indicating a fault condition within the electric machine; and in response to receiving the data indicating the fault condition within the electric machine, moving each of the stator segments away from the rotor assembly in a radial direction defined by the turbine.

[0133] 19. The method of any of the preceding clauses, wherein the stator segments comprise a first stator segment and a second stator segment, and wherein moving each of the stator segments away from the rotor assembly in a radial direction comprises moving the first stator segment and the second stator segment relative to each other in a radial direction.

[0134] 20. The method of any of the preceding clauses, wherein the stator segments are moved away from the rotor assembly in a radial direction a distance greater than 0.5 inches and less than 10 inches.

Claims

1. An electric machine, which defines an axial direction, a radial direction and a center line extending along the axial direction, the electric machine comprising: a rotor assembly rotatable about the centerline; a stator assembly having a stator segmented into stator segments, each of the stator segments having an actuator associated therewith, each of the actuators being operable to move their respective ones of the stator segments along the radial direction between a first position and a second position, the stator segments each being closer to the rotor assembly when in the first position than when in the second position; and a controller operatively coupled to the actuator and configured to: receiving data from one or more sensors associated with the motor; identifying a fault with the motor based on the data; and In response to identifying the fault with the electric machine, the actuators are operated to move their respective stator segments from their respective first positions away from the rotor assembly to their respective second positions.

2. The motor according to claim 1, wherein: The first position is an engaged position and the second position is a disengaged position.

3. The motor according to claim 1, wherein: Each of the stator segments has an associated set of stator windings, and wherein the stator windings of each set are wound only within their respective stator segment.

4. The motor according to claim 1, wherein: Each stator segment has an associated power converter.

5. The motor according to claim 1, wherein: The stator segments are individually movable between their respective first and second positions.

6. The motor according to claim 1, wherein: The stator segments include at least four stator segments.

7. The electric machine of claim 1, said stator segments each being movable along said radial direction between their respective first and second positions a distance greater than 0.5 inches and less than 10 inches.

8. The motor according to claim 1, wherein: A controller associated with the electric machine and operatively coupled to the actuator is configured to cause the actuator to move their respective stator segments away from the rotor assembly to respective partial power positions between their respective first and second positions.

9. The motor according to claim 1, wherein: Each stator segment engages an adjacent one of the stator segments when the stator segments are in their respective first positions, and the stator segments disengage from one another when the stator segments are in their respective second positions.

10. The electric machine according to claim 1, wherein: The rotor assembly includes a plurality of permanent magnets.

11. The electric machine according to claim 1, wherein: The stator segments are simultaneously movable between their respective first and second positions.

12. A turbine, defining a radial direction, the turbine comprising: Rotating parts; Actuator; An electric motor comprising: a rotor assembly rotatable with and operatively coupled to the rotating component; and a stator assembly having a stator segmented into stator segments, each of the stator segments having a respective one of the actuators associated therewith, each of the actuators being operable to move their respective one of the stator segments along the radial direction between a first position and a second position, each of the stator segments being closer to the rotor assembly along the radial direction when in the first position than when in the second position; one or more sensors associated with the motor; and a controller associated with the motor and communicatively coupled to the actuator and the one or more sensors, the controller being configured to: receiving data from the one or more sensors associated with the motor; identifying a fault with the motor based on the data; and In response to identifying the fault with the electric machine, the actuators are caused to move their respective stator segments from their respective first positions away from the rotor assembly to their respective second positions.

13. The turbine according to claim 12, wherein: The controller is also configured to: receiving an electrical power demand indicative of electrical power required by one or more electrical loads electrically coupled to the electric machine; and The actuators are caused to move their respective stator segments relative to the rotor assembly along the radial direction in response to receiving the electrical power demand.

14. The turbine according to claim 12, wherein: The turbomachine is an aircraft gas turbine engine, and wherein the rotating component is one of a low-pressure shaft and a high-pressure shaft of the aircraft gas turbine engine.

15. A method for operating an electric motor, comprising: operating the electric machine to convert electrical power into rotational power or vice versa, the electric machine having a stator assembly and a rotor assembly capable of rotating with a rotating component of the turbine, the stator assembly having a stator divided into stator segments; receiving data from one or more sensors associated with the motor; identifying a fault with the motor based on the data; in response to identifying the fault with respect to the electric machine, operating actuators to move their respective stator segments from their respective first positions away from the rotor assembly to their respective second positions; and In response to identifying the fault with the electric machine, each of the stator segments is moved away from the rotor assembly along a radial direction defined by the turbine.

16. The method according to claim 15, wherein: The stator segments include a first stator segment and a second stator segment, and wherein moving each of the stator segments away from the rotor assembly along the radial direction includes moving the first stator segment and the second stator segment relative to each other along the radial direction.

17. The method according to claim 15, wherein: The stator segment moves away from the rotor assembly along the radial direction a distance greater than 0.5 inches and less than 10 inches.

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