Gas turbine engine equipped with a control system using motor managed rotor mode

Abstract

A turbomachine is provided. In one aspect, the turbomachine includes a rotating component and an electric machine including a stator assembly and a rotor assembly that rotates with the rotating component relative to the stator assembly. Further, the turbomachine includes an actuator coupled with the rotor assembly, the stator assembly, or both, for moving the rotor assembly, moving the stator assembly, or both relative to one another. Further, the turbomachine includes a controller configured to receive data indicative of an operating condition of the rotating component and cause the actuator to adjust a position of at least one of the stator assembly and the rotor assembly based at least in part on the operating condition of the rotating component.

Description

[0001] Priority information

[0002] This application claims priority to Indian Patent Application No. 202111013074, filed on March 25, 2021. Technical Field

[0003] This topic generally relates to a gas turbine engine equipped with a control system that uses an electric motor to manage rotor modes. Background Technology

[0004] A typical aircraft propulsion system includes one or more gas turbine engines. For some propulsion systems, a gas turbine engine generally includes a fan and a core, arranged in flow communication with each other. Additionally, the engine core of a gas turbine engine generally comprises, in a serial flow sequence, a compressor section, a combustion section, a turbine section, and an exhaust section downstream of the fan. The compressor section may include a low-pressure compressor and a high-pressure compressor. The high-pressure compressor is downstream of the low-pressure compressor. The turbine section may include a high-pressure turbine and a low-pressure turbine downstream of the high-pressure compressor. A high-pressure rotor or spool can drive the high-pressure turbine to the high-pressure compressor, and a low-pressure rotor or spool can drive the low-pressure turbine to the low-pressure compressor and the fan.

[0005] For certain aircraft propulsion systems, and aircraft incorporating such propulsion systems, the propulsion system may advantageously include one or more motors operatively coupled to a high-pressure rotor or a low-pressure rotor. For example, such motors can be used to generate electricity for gas turbine engines and / or various accessory systems of the aircraft.

[0006] In some cases, engines cannot be designed to vibrate in rotor modes outside their operating range. Therefore, it is necessary to mitigate resonance by using damping devices such as squeeze film dampers (SFD). While such damping devices are generally effective in controlling rotor vibration, they increase engine weight and complexity, and in some cases, can lead to a loss of engine efficiency.

[0007] Therefore, a propulsion system for an aircraft with an electric motor capable of solving one or more of these problems would be useful. Summary of the Invention

[0008] Aspects and advantages of the invention will be set forth in part in the description which follows, or may be apparent from the description, or may be learned by practice of the invention disclosed herein.

[0009] In one aspect, a turbine is provided. The turbine includes a rotating component rotatable about a rotational axis. The turbine also includes an electric motor. The electric motor includes a stator assembly and a rotor assembly, the rotor assembly being rotatable relative to the stator assembly along with the rotating component. Further, the turbine includes an actuator operatively coupled to at least one of the rotor assembly and the stator assembly for moving the rotor assembly, moving the stator assembly, or moving both relative to each other. Additionally, the turbine includes a controller communicatively coupled to the actuator. The controller is configured to: receive data indicating the operating state of the rotating component; and cause the actuator to adjust the position of at least one of the stator assembly and the rotor assembly at least in part based on the operating state of the rotating component.

[0010] In another aspect, a method of operating a turbine is provided. The method includes receiving data indicating the operating state of rotating components of the turbine. The turbine includes an electric motor having a stator assembly and a rotor assembly. The rotor assembly is rotatable and operatively coupled to the rotating components. The method further includes moving the position of at least one of the stator assembly and the rotor assembly, at least in part based on the operating state of the rotating components, to change the air gap defined between the rotor assembly and the stator assembly.

[0011] In another aspect, a non-transient computer-readable medium is provided. The non-transient computer-readable medium includes computer-executable instructions, wherein, when executed by one or more processors of a controller, the computer-executable instructions cause the one or more processors to: receive data indicating the operating state of a rotating component of a turbine, the turbine including a motor having a stator assembly and a rotor assembly, the rotor assembly being rotatable and operatively coupled to the rotating component; generate a control command at least partially based on the operating state of the rotating component, the control command being used to cause an actuator to adjust the position of at least one of the stator assembly and the rotor assembly; and cause the actuator to adjust the position of at least one of the stator assembly and the rotor assembly at least partially based on the control command.

[0012] These and other features, aspects, and advantages of this disclosure will become better understood with reference to the following description and the appended claims. The accompanying drawings, which are incorporated in and constitute a part of this specification, illustrate various aspects of this disclosure and, together with the description, serve to explain the principles of the invention. Attached Figure Description

[0013] The specification sets forth a complete and enabling disclosure for those skilled in the art, including its best mode, which relates to the accompanying drawings, in which:

[0014] Figure 1 An exemplary cross-sectional view of a gas turbine engine according to an exemplary aspect of this disclosure is provided;

[0015] Figure 2 Provides embedding Figure 1 An exemplary cross-sectional view of the electric motor in a gas turbine engine, depicting the rotor assembly of the motor in a first position;

[0016] Figure 3 Provided Figure 2 An exemplary cross-sectional view of the motor is shown, depicting the rotor assembly in a second position;

[0017] Figure 4 A block diagram of an exemplary control system for controlling the position of at least one of a rotor assembly and a stator assembly of an electric motor, according to an exemplary aspect of this disclosure, is provided.

[0018] Figure 5 A graph is provided depicting the vibration response of a rotating component of a gas turbine engine according to an exemplary aspect of this disclosure under various stiffnesses applied by an electric motor as a function of the velocity of the rotating component;

[0019] Figure 6 An exemplary cross-sectional view of a gas turbine engine according to another exemplary embodiment of the present disclosure is provided;

[0020] Figure 7 An exemplary cross-sectional view of an embedded gas turbine engine in a first position, according to another exemplary embodiment of the present disclosure, is provided;

[0021] Figure 8 Provided embedded in gas turbine engine Figure 7 An exemplary cross-sectional view of an exemplary motor in a second position;

[0022] Figure 9 A flowchart is provided for a method of operating a gas turbine engine having an embedded electric motor according to an exemplary aspect of this disclosure; and

[0023] Figure 10 This is a block diagram of an exemplary computing system that can be used to implement aspects of this disclosure. Detailed Implementation

[0024] Reference will now be made in detail to the present embodiments of the invention, one or more examples of which are illustrated in the accompanying drawings. Detailed description uses numerals and letter names to refer to features in the drawings. Similar or analogous reference numerals in the drawings and description are used to refer to similar or analogous portions of the invention.

[0025] As used in this application, the terms “first,” “second,” and “third” are used interchangeably to distinguish one component from another and are not intended to indicate the location or importance of a single component.

[0026] The terms "front" and "rear" refer to relative positions within a gas turbine engine or vehicle, and to the normal operating posture of the gas turbine engine or vehicle. For example, in the context of a gas turbine engine, "front" refers to the position closer to the engine inlet, and "rear" refers to the position closer to the engine nozzle or exhaust.

[0027] Furthermore, the terms "upstream" and "downstream" refer to the relative directions of fluid flow within a fluid path. For example, "upstream" refers to the direction from which the fluid flows, while "downstream" refers to the direction from which the fluid flows.

[0028] The terms “connection,” “fixation,” “attachment,” etc., refer to direct connection, fixation, or attachment, as well as indirect connection, fixation, or attachment via one or more intermediate components or features, unless otherwise specified herein.

[0029] Unless the context clearly specifies otherwise, the singular forms “a,” “an,” and “the” include plural references.

[0030] The approximate language used in this specification and claims is intended to modify any quantitative expression that may be varied without altering the underlying function. Therefore, values ​​modified by one or more terms, such as “approximately,” “approximately,” and “basically,” are not limited to specified precise values. In at least some cases, approximate language may correspond to the precision of the instrument used to measure the value, or the precision of the method or machine used to construct or manufacture the component and / or system. For example, approximate language may refer to a margin of 1, 2, 4, 10, 15, or 20%.

[0031] Throughout this specification and claims, scope limitations are combined and interchanged, and these scopes are identified and include all subscopes contained herein, unless otherwise indicated by context or language. For example, all scopes disclosed herein include endpoints, and endpoints may be combined independently of each other.

[0032] This disclosure relates to a turbine having an embedded motor for controlling or mitigating the vibration response of a rotating component to which the motor is coupled. In one exemplary aspect, the turbine includes a rotating component, such as a rotor. The turbine also includes a motor comprising a stator assembly and a rotor assembly. The rotor assembly is rotatable relative to the stator assembly along with the rotating component. Further, the turbine includes an actuator coupled to at least one of the rotor assembly and the stator assembly. The actuator can be commanded to move the rotor assembly, move the stator assembly, or move both relative to each other. As an example, the actuator can move the rotor assembly relative to the stator assembly. As another example, the actuator can move the stator assembly relative to the rotor assembly. Furthermore, the turbine includes a controller. The controller is configured to receive data indicating the operating state of the rotating component. For example, the controller can receive data indicating the rotational speed of the rotating component. The controller is also configured to cause the actuator to adjust the position of at least one of the stator assembly and the rotor assembly at least partially based on the operating state of the rotating component. By adjusting the position of at least one of the stator assembly and the rotor assembly relative to each other, the air gap defined between the stator assembly and the rotor assembly is changed. Therefore, the stiffness of the motor is altered. Advantageously, this change in motor stiffness can be used to mitigate the high vibration response of rotating components.

[0033] Referring now to the accompanying drawings, in which the same numbers throughout the drawings denote the same elements. Figure 1 An exemplary cross-sectional view of a propulsion engine according to an exemplary embodiment of the present disclosure is provided. In this embodiment, the propulsion engine is configured as a high-bypass turbofan jet engine 100, referred to herein as "turbofan 100". Turbofan 100 can be incorporated into an aircraft propulsion system, for example, as an underwing turbofan engine. Alternatively, in other embodiments, turbofan 100 can be incorporated into any other suitable aircraft or propulsion system. For reference, turbofan 100 defines an axial direction A, a radial direction R, and a circumferential direction C extending parallel to the longitudinal centerline 101. Figure 2 ).

[0034] The turbofan 100 includes a fan section 102 and a core engine 104 disposed downstream of the fan section 102. The core engine 104 includes a generally tubular housing 106 defining an annular core inlet 108. The housing 106 surrounds, in a series relationship: a compressor section including a boost or low-pressure (LP) compressor 110 and a high-pressure (HP) compressor 112; a combustion section 114; a turbine section including an HP turbine 116 and an LP turbine 118; and an exhaust nozzle section 120. The compressor section, combustion section 114, and turbine section together define a core gas flow path 121 extending from the annular core inlet 108 through the LP compressor 110, HP compressor 112, combustion section 114, HP turbine section 116, LP turbine section 118, and exhaust nozzle section 120. HP rotor 122 or spool drives HP turbine 116 to HP compressor 112. LP rotor 124 or spool drives LP turbine 118 to LP compressor 110.

[0035] for Figure 1 In the illustrated embodiment, fan section 102 includes a variable pitch fan 126 having a plurality of fan blades 128 spaced apart and coupled to disk 130. The fan blades 128 generally extend outward from disk 130 in a radial direction R. Each fan blade 128 is operatively coupled to a suitable actuating member 132, which is configured to simultaneously change the pitch of the fan blades 128 about a pitch axis P relative to disk 130. The fan blades 128, disk 130, and actuating member 132 can rotate together via LP rotor 124 through a power gearbox 134 about a longitudinal axis 101. The power gearbox 134 includes a plurality of gears for reducing the rotational speed of LP rotor 124 to a more efficient fan speed.

[0036] The disc 130 is covered by a rotatable swivel or front hub 136, which is aerodynamically shaped to facilitate airflow through multiple fan blades 128. Additionally, the fan section 102 includes an annular fan housing or outer nacelle 138 circumferentially surrounding at least a portion of the fan 126 and / or the core engine 104. The nacelle 138 is supported relative to the core engine 104 by a plurality of circumferentially spaced outlet guide vanes 140. A downstream section 142 of the nacelle 138 extends externally over the core engine 104 to define a bypass airflow passage 144 therebetween.

[0037] Additionally, the turbofan 100 includes a motor 146, which is rotatable with one or more rotatable components of the turbofan 100. Specifically, in this embodiment, the motor 146 rotates with the LP system of the turbofan 100. Specifically, in the depicted embodiment, the motor 146 is arranged coaxially with and mounted to the LP rotor 124. As used herein, "coaxial" means axial alignment. However, it should be understood that in other embodiments, the axis of the motor 146 may be radially offset from the axis of the LP rotor 124, and may also be tilted relative to the axis of the LP rotor 124, such that the motor 146 can be positioned at any suitable location at least partially inward of the core gas flow path 121.

[0038] Motor 146 includes a rotor assembly 148 and a stator assembly 150. In the depicted embodiment, the rotor assembly 148 and the stator assembly 150 define a tapered air gap. Figure 2 Furthermore, the rotor assembly 148 is configured to move relative to the stator assembly 150 during certain operations, as will be explained in more detail below.

[0039] It should be understood that, Figure 1 The turbofan engine 100 shown is provided by way of example only and is not intended to be limiting. For example, in other exemplary embodiments, the turbofan engine 100 may have any other suitable configuration. For example, in other embodiments, the turbofan engine 100 may be configured as a turboprop engine, a turbojet engine, a turboshaft engine, a turbofan engine of different configurations, or any other suitable gas turbine engine. Additionally or optionally, exemplary aspects of this disclosure (such as motor 146) may be incorporated into or otherwise used with any other suitable type of engine, such as an aerospace-derived gas turbine engine, a marine gas turbine engine, a power generation gas turbine engine, an internal combustion engine, etc., or further combined with any other turbine or machine having rotating parts.

[0040] For reference Figure 2 A close-up schematic diagram of a motor 146 embedded within a turbine fan 100 is provided. As shown, the motor 146 is embedded within the turbine section of the turbine fan 100, and more specifically, the motor 146 is operatively coupled to the LP rotor 124. Furthermore, the motor 146 is at least partially located within or at the rear of the LP turbine 118 of the turbine section along the axial direction A. It should be understood that in other exemplary embodiments, the motor 146 may be located at other suitable locations within the turbine fan 100.

[0041] Motor 146 includes a rotor assembly 148 and a stator assembly 150. Motor 146 also defines a centerline 155, which in this exemplary embodiment is aligned with or coaxial with the longitudinal axis 101 of the turbine fan 100. Rotor assembly 148 includes rotor connecting members 152 and a rotor 154. Stator assembly 150 similarly includes stator connecting members 156 and a stator 158. The rotor 154 of rotor assembly 148 and the stator 158 of stator assembly 150 together define an air gap 160 therebetween. Furthermore, in this embodiment, rotor 154 includes a plurality of magnets 162, such as a plurality of permanent magnets, and stator 158 includes a plurality of windings or coils 164. Therefore, motor 146 can be referred to as a permanent magnet motor. However, in other exemplary embodiments, motor 146 can be configured in any suitable manner. For example, motor 146 can be configured as an electromagnetic motor, including multiple electromagnets and active circuitry, as an induction motor, a switched reluctance motor, a synchronous AC motor, an asynchronous motor, or as any other suitable generator or motor.

[0042] As described above, in this embodiment, rotor assembly 148 is coupled to or attached to LP rotor 124. In this way, rotor assembly 148 can rotate together with LP rotor 124. The attachment of rotor assembly 148 to LP rotor 124 will be described in more detail below. Stator assembly 150 is coupled to or attached to structural support assembly 166 of turbine section. More specifically, stator connecting member 156 extends from structural support assembly 166 to stator 158 to support stator 158. Notably, structural support assembly 166 is configured as part of rear frame assembly 168. Rear frame assembly 168 also includes rear frame strut 170, which extends through core gas flow path 121 of core engine 104. Figure 1 The rear frame strut 170 provides structural support for the turbine fan 100. The structural support assembly 166 extends radially R from the inner end of the rear frame strut 170.

[0043] The turbofan 100 further includes a cavity wall 172 surrounding at least a portion of the motor 146. More specifically, the cavity wall 172 substantially completely surrounds the motor 146, extending from a position near the front end of the motor 146 to a position near the rear end of the motor 146. The cavity wall 172 can serve as, for example, a cooling gas cavity wall, a reservoir for cooling fluid, a protective cover for the motor 146, etc. For example, in some embodiments, the engine may further include a second cavity wall (not shown) to form a buffer cavity surrounding the motor 146 and to provide thermal protection for the motor 146.

[0044] During certain operations of the turbofan 100, the LP rotor 124 rotates the rotor assembly 148 of the motor 146, thereby allowing the motor 146 to generate electricity. Therefore, the motor 146 can operate in generator mode. In some embodiments, in addition to or instead of operating in generator mode, the motor 146 can operate in drive mode during certain operations of the turbofan 100. In drive mode, the rotor assembly 148 of the motor 146 drives the LP rotor 124. The motor 146 is electrically connected to a power bus 174. The power bus 174 is electrically connected to the motor 146 at a location in the radial direction R inwards from the core airflow path 121. The power bus 174 may extend through the core gas flow path 121 (e.g., through the rear frame strut 170) and electrically connect the motor 146 to various other electrical sinks (accessory systems, electric / hybrid electric propulsion devices, etc.), power sources (other motors, energy storage units, etc.), or both. Electricity can be supplied to motor 146 via power bus 174, for example, when motor 146 is operating in drive mode, and the electricity generated by motor 146 can be transmitted or transferred to electrical system via power bus 174, for example, when motor 146 is operating in generator mode.

[0045] Now for reference Figure 2 and Figure 3 , Figure 3 Another near-view schematic diagram of motor 146 is provided. For this embodiment, by comparison... Figure 2 The position of the middle rotor assembly 148 and Figure 3 The position of the rotor assembly 148 can be understood to mean that the rotor assembly 148 is movable relative to the stator assembly 150. Specifically, the motor 146 can... Figure 2 The first position shown and Figure 3 Move between the second positions shown.

[0046] As shown, the turbofan 100 includes an actuator 176. The actuator 176 is operatively coupled to a rotor assembly 148, a stator assembly 150, or both, to move at least one of the rotor assembly 148 and the stator assembly 150. The actuator 176 can move at least one of the rotor assembly 148 and the stator assembly 150 along a centerline 155 of the motor 146 between a first position and a second position, or to a position between them. In this embodiment, the actuator 176 is operatively coupled to the rotor assembly 148 to move the rotor assembly 148 along the centerline 155 of the motor 146 relative to the stator assembly 150 between a first position and a second position. The rotor assembly 148 is positioned closer to the stator assembly 150 in the first position than in the second position.

[0047] As described above, in this embodiment, rotor assembly 148 is coupled to LP rotor 124. Rotor assembly 148 includes rotor 154 and rotor connecting member 152. Rotor connecting member 152 extends between LP rotor 124 and rotor 154 for connecting rotor 154 to LP rotor 124. In the illustrated embodiment, rotor connecting member 152 is connected to LP rotor 124 via a spline connection. More specifically, rotor connecting member 152 includes a connecting portion 178 having a plurality of teeth 180 extending substantially along the axial direction A, and similarly, LP rotor 124 includes a connecting portion 182 having a plurality of teeth 184 extending substantially along the axial direction A. The plurality of teeth 180 of connecting portion 178 of rotor connecting member 152 are configured to engage with the plurality of teeth 184 of connecting portion 182 of LP rotor 124, thereby securing the two components to each other in the circumferential direction C. It can be noted that this configuration allows relative movement of rotor assembly 148 relative to LP rotor 124 in the axial direction A.

[0048] In an alternative embodiment, the rotor connecting member 152 may be coupled to the LP rotor 124 in any other suitable manner that allows relative movement in the axial direction A while fixing the component in the circumferential direction C. For example, the rotor connecting member 152 may be coupled to the LP rotor 124 using multiple linear bearings, linear slides, etc.

[0049] Furthermore, in this embodiment, the actuator 176 is coupled to the rotor connecting member 152 of the rotor assembly 148 such that the rotor connecting member 152 is movable relative to the LP rotor 124 along the centerline 155 of the motor 146. In this way, the actuator 176 can move the rotor assembly 148 relative to the LP rotor 124 in the axial direction A and along the centerline 155 of the motor 146.

[0050] In this embodiment, actuator 176 is a linear actuator. Actuator 176 includes a base 186 and an extension 188, which is movable relative to the base 186 in the axial direction A. The extension 188 is rotatably coupled to rotor connecting member 152 and supported by a plurality of bearings 190, wherein the plurality of bearings 190 are axial load bearings. In this way, rotor connecting member 152 can rotate relative to extension 188 in the circumferential direction C, but is fixed to extension 188 in the axial direction A.

[0051] Actuator 176 may be a hydraulically driven actuator, a pneumatically driven actuator, an electric actuator, a thermally driven actuator, a magnetic actuator, etc. Furthermore, in alternative embodiments, actuator 176 may not be a linear actuator, but rather a scissor actuator, a circular-to-linear actuator (such as a screw actuator), or any other actuator capable of producing or facilitating linear movement.

[0052] Actuator 176 is further coupled to structural support assembly 166 of the turbine section, which, as described above, is part of rear frame assembly 168 having rear frame strut 170. In this respect, actuator 176 is coupled to the same frame as stator assembly 150. It is noteworthy that this configuration ensures that the air gap 160 defined between rotor 154 of rotor assembly 148 and stator 158 of stator assembly 150 remains at a desired value or distance during operation of turbine fan 100. More specifically, it should be noted that as turbine fan 100 changes operating conditions, the temperature of various components may rise or fall. For example, the temperature of LP rotor 124 may increase, which could cause the length of LP rotor 124 to increase in the axial direction A. The connection of actuator 176 to the same frame of stator assembly 150 and the spline connection between rotor connecting member 152 and LP rotor 124 ensure that any increase or decrease in the length of LP rotor 124 does not significantly affect the size of the air gap 160 defined between rotor 154 and stator 158.

[0053] Still refer to Figure 2 and 3 The first position is a closed or engaged position, and the second position is an open or disengaged position. As used herein, the term "engaged position" refers to the relative positioning of rotor 154 and stator 158, where motor 146 can operate within a reasonable margin of its design efficiency. For example, in the engaged position, the air gap 160 defined between rotor 154 of rotor assembly 148 and stator 158 of stator assembly 150 is within a reasonable margin of its optimal design value, allowing a desired portion of the magnetic flux from magnet 162 of rotor 154 to reach stator 164. Conversely, as used herein, the term "disengaged position" refers to the relative positioning of rotor 154 of rotor assembly 148 and stator 158 of stator assembly 150, where motor 146 cannot operate at a reasonable efficiency (e.g., less than 10% of maximum efficiency). It should be understood that rotor assembly 148 can move relative to stator assembly 150 between the first and second positions, and therefore, the efficiency of motor 146 generally corresponds to the position of rotor assembly 148 relative to stator assembly 150.

[0054] In this embodiment, the motor 146 is integrated within the internal location of the turbofan 100 (within the core gas flow path 121), where there may not be excessive space. Therefore, to facilitate movement of the rotor assembly 148 relative to the stator assembly 150 between an engaged position and a disengaged position, or to a position in between, the air gap 160 defines an angle 192 greater than 0° and less than 90° relative to the centerline 155 of the motor 146. More specifically, in the illustrated embodiment, the angle 192 defined by the air gap 160 relative to the centerline 155 of the motor 146 is greater than 10° and less than 45°, such as less than 30°. This configuration facilitates movement between the engaged and disengaged positions without requiring excessive movement of the rotor assembly 148 along the centerline 155 of the motor 146 relative to the stator assembly 150.

[0055] For example, when the rotor assembly 148 is in the engaged position relative to the stator assembly 150, the size of the air gap 160 ( Figure 3 The distance 194 shown may be a first value, and the size of the air gap 160 may be equal to a second value when the rotor assembly 148 is in the disengaged position relative to the stator assembly 150. In at least some exemplary embodiments, the second value is at least twice the size of the first value, such as at least four times the size of the first value, such as at least five times the size of the first value, such as up to 200 times the size of the first value, such as up to 100 times the size of the first value, such as up to 20 times the size of the first value.

[0056] Furthermore, given an angle 192 of the air gap 160 relative to the centerline 155, only a relatively small movement of the rotor assembly 148 along the centerline 155 is required to increase or decrease the size of the air gap 160. For example, in an embodiment, the actuator 176 may be configured to move the rotor 154 along the centerline 155 relative to the stator assembly 150 between an engaged position and a disengaged position by a distance greater than 0.5 inches and less than 10 inches, such as greater than 1 inch and less than 5 inches.

[0057] Exemplary methods by which the motor 146 can be used to control or mitigate unwanted vibrations of rotating components, such as the LP rotor 124, will now be provided. Generally, actuation or movement of the stator assembly 150, rotor assembly 148, or both relative to each other introduces an equivalence of a negative stiffness relationship between the stator 158 of the stator assembly 150 and the rotor 154 of the rotor assembly 148. Therefore, actuation or movement of the stator assembly 150, rotor assembly 148, or both provides a means to influence the level of negative stiffness applied to the LP rotor 124, and thus provides the ability to generally manipulate the dynamic behavior of the LP rotor 124 and / or the turbofan 100. For example, actuation or movement of the stator assembly 150, rotor assembly 148, or both can provide a means to control the modal response of the LP rotor 124.

[0058] Now for reference Figure 2 , Figure 3 as well as Figure 4 , Figure 4 A block diagram of an exemplary control system 220 is provided for controlling the position of at least one of the stator assembly 150 and rotor assembly 148 to ultimately control or mitigate unwanted vibrations of the LP rotor 124 and / or turbine fan 100. As shown, the control system 220 includes a controller 198, one or more sensors 195, and one or more controllable devices, in this embodiment, said controllable device being an actuator 176. The controller 198 is communicatively coupled to the one or more sensors 195 and actuator 176, for example, via suitable wired and / or wireless communication links.

[0059] Controller 198 includes one or more memory devices and one or more processors. The one or more memory devices may store information accessible by the one or more processors, including computer-executable instructions that are executed by the one or more processors. 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 198 may be configured to... Figure 10 The computing system 400 is configured. Although the controller 198 is... Figure 2 and 3 As shown in the diagram near the motor 146, it should be understood that the controller 198 can be located at any suitable location within the turbofan 100, such as under the shroud. The controller 198 can also be located at a remote location relative to the turbofan 100, for example, within the fuselage of the aircraft in which the turbofan 100 is mounted. In some embodiments, the controller 198 may be a dedicated controller for controlling the actuation of at least one of the stator assembly 150 and the rotor assembly 148. In other embodiments, the controller 198 may be an electronic engine controller (EEC) of a full authority digital engine control (FADEC) system.

[0060] For this embodiment, one or more sensors 195 (in) Figure 2 and 3The LP rotor 124 (represented by a single sensor) includes at least one sensor operable to sense or measure parameter values ​​indicating the operating state of the LP rotor 124. As an example, sensor 195 may be a speed sensor operable to sense the rotational speed of the LP rotor 124. Therefore, in these embodiments, the operating state of the LP rotor 124 is indicated by the speed of the LP rotor 124. As another example, sensor 195 may be a temperature sensor operable to sense the temperature of the LP rotor 124. Therefore, in these embodiments, the operating state of the LP rotor 124 is indicated by the temperature of the LP rotor 124. As yet another example, sensor 195 may be a vibration sensor (e.g., an accelerometer) operable to sense the vibration of the LP rotor 124. Therefore, in these embodiments, the operating state of the LP rotor 124 is indicated by the vibration of the LP rotor 124. It should be understood that the operating state of the LP rotor 124 may also be indicated by other suitable parameters, including combinations of parameters. Furthermore, the recorded parameter values ​​do not need to be directly related to the LP rotor 124. For example, HP rotor 122 ( Figure 1 The rotational speed of the sensor 195 can be used to indicate the operating state of the LP rotor 124, for example, via a known correlation. The sensor 195 can be located in any suitable position. As an example, such as... Figure 2 and 3 As shown, sensor 195 can be located near LP rotor 124.

[0061] like Figure 4 As best shown, controller 198 is configured to receive data 224 indicating the operating state of LP rotor 124. For example, controller 198 may receive data 224 from sensor 195 or multiple sensors. As described above, the operating state of LP rotor 124 can be indicated by any number of suitable parameters, such as the rotational speed of LP rotor 124. Furthermore, in some embodiments, controller 198 is configured to receive feedback data 226 indicating the current position (e.g., current axial position) of actuator 176. In this way, the current position of actuator 176 can be associated with rotor assembly 148 relative to stator assembly 150. Feedback data 226 can be received from actuator 176 or one or more sensors associated with actuator 176. Furthermore, in some embodiments, controller 198 is configured to receive power demand 228. Power demand 228 may indicate the power required by one or more electrical loads electrically connected to motor 146.

[0062] The controller 198 is also configured to generate control commands 230 based at least in part on the operating state of the LP rotor 124. Control commands 230 can represent instructions regarding how the actuator 176 adjusts its position, and thus how the position (if any) of at least one of the stator assembly 150 and rotor assembly 148 is adjusted. In some cases, for example, control commands 230 can represent instructions instructing the actuator 176 to maintain its current position, which maintains the current position of the stator assembly 150 and / or rotor assembly 148. In other cases, control commands 230 can represent instructions instructing the actuator 176 to move or actuate. In this way, the current position of the stator assembly 150 and / or rotor assembly 148 can be moved. As will be explained further below, the controller 198 enables the actuator 176 to adjust the position of at least one of the stator assembly 150 and rotor assembly 148 based at least in part on the determined control commands 230.

[0063] In some embodiments, controller 198 generates control command 230 based on associating received values ​​from data 124 with pre-selected actuator positions using a schedule or lookup table. For example, values ​​received as part of data 224 indicating the operating state of LP rotor 124 may be associated with pre-selected positions of actuator 176. Controller 198 is capable of storing and accessing schedules or lookup tables that associate parameter values ​​with pre-selected positions of actuator 176. The correlation can be determined by engineering analysis, such as during engine testing. The correlation can be established specific to the engine's vibration characteristics, or a general correlation of a specific engine model can be used. For example, it can be based on the LP shaft or intermediate shaft (e.g., Figure 3 The known fundamental frequency (primary modal resonance frequency) of the shaft portion (located on the left side of shaft 124, extending between the LP shaft bearings) is used to establish this. The controller 198 can generate control commands representing instructions for controlling the actuator 176 to a pre-selected position associated with the received value. In some embodiments, the controller 198 generates the control command 230 based at least in part on the operating state of the LP rotor 124 and the current position of the actuator 176 provided in the received feedback data 226. For example, the current position of the actuator 176 may also be considered after associating the received value with the pre-selected position to ensure that the actuator 176 is commanded to move from its current position to the pre-selected position.

[0064] In other embodiments, the controller 198 generates the control command 230 based at least in part on the operating state of the LP rotor 124, the current position of the actuator 176 provided in the received feedback data 226, and the power demand 228. For example, in some embodiments, the power demand 228 may be a primary factor or consideration in generating the control command 230. As an example, if one or more motors driving the respective thrusters of an aircraft are electrically connected to the motor 146, and it requires or demands full power, then even without utilizing the motor 146 to mitigate undesirable responses, it may lead to undesirable modal vibration responses in the LP rotor 124, but for safety purposes, movement of the rotor assembly 148 relative to the stator assembly 150 is not feasible, and vice versa.

[0065] Therefore, in these embodiments, the controller 198 generates the control command 230 solely based on the power demand 228. For example, if the power demand 228 exceeds a demand threshold (e.g., surpasses the demand threshold), the controller 198 can generate the control command 230 for the actuator 176, which can cause the actuator 176 to shut down or stop actuation, and in some cases, can immediately cause the actuator 176 to move the rotor assembly 148 to a first position so that the motor 146 can generate power most efficiently. When the power demand 228 decreases to the point that it again exceeds the demand threshold (e.g., falls below the demand threshold), the actuation function can be restored.

[0066] The controller 198 is further configured to cause the actuator 176 to adjust the position of at least one of the stator assembly 150 and the rotor assembly 148. Specifically, as described above, the controller 198 can generate and output a control command 230. The control command 230 can be output by the controller 198 (e.g., as one or more electronic signals) and can be transmitted to the actuator 176. The actuator 176 can be controlled according to the received control command 230. The controller 198 enables the actuator 176 to adjust the position of at least one of the stator assembly 150 and the rotor assembly 148 at least partially based on the generated control command 230. When the control command 230 is generated at least partially based on the operating state of the LP rotor 124, the controller 198 then causes the actuator 176 to adjust the position of at least one of the stator assembly 150 and the rotor assembly 148 at least partially based on the operating state of the LP rotor 124.

[0067] for Figure 2 and 3In the illustrated embodiment, controller 198 causes actuator 176 to adjust the position of rotor assembly 148 relative to stator assembly 150. However, in an alternative embodiment, controller 198 is capable of causing actuator 176 to adjust the position of stator assembly 150 relative to rotor assembly 148. Notably, when actuator 176 adjusts the position of at least one of stator assembly 150 and rotor assembly 148, the position of at least one of stator assembly 150 and rotor assembly 148 is adjusted such that the air gap 160 defining the space between rotor assembly 148 and stator assembly 150 is altered. The change in air gap 160 or distance 194 between rotor 154 and stator 158 effectively alters the stiffness of motor 196. As described above, altering the stiffness of motor 196 can be used to manipulate the modal response or dynamic behavior of LP rotor 124.

[0068] In some exemplary embodiments, the controller 198 may iteratively receive data, including data 224 indicating the operating state of the LP rotor 124, feedback data 226 indicating the current position of the actuator 176, and / or power demand 228, and based on the received data, the controller 198 may iteratively generate control commands 230. The control commands 230 may be output to the actuator 176, causing the actuator 176 to either maintain its current position, and thus maintain the current position of the rotor assembly 148 relative to the stator assembly 150, or move at least one of the rotor assembly 148 and the stator assembly 150, thereby changing the air gap 160 therebetween. In some embodiments, the controller 198 may continuously monitor and control the position of at least one of the rotor assembly 148 and the stator assembly 150 relative to the other during operation.

[0069] In other embodiments, particularly where the motor 146 is operatively coupled to the rotating components of an aero gas turbine engine mounted on the aircraft, the controller 198 is capable of monitoring and controlling the position of at least one of the rotor assembly 148 and the stator assembly 150 relative to the other during certain flight segments, such as those where high-speed vibrations may occur. In such embodiments, the controller 198 is capable of shutting off or stopping the operation of the actuation function during certain flight segments. The controller 198 is capable of automatically determining the flight segment in which the gas turbine engine is operating, for example, at least in part based on received data indicating the aircraft's altitude.

[0070] Specific examples of an exemplary manner in which the motor 146 can be used to mitigate the vibration response of the LP rotor 124 will now be provided in detail. Reference is now made to... Figure 2 , Figure 3 , Figure 4 as well as Figure 5 , Figure 5A graph depicting the vibration response of the LP rotor 124 as a function of its speed under various applied stiffnesses is provided. Specifically, the graphs provide the vibration response of the LP rotor 124 as a function of its speed at 0% stiffness amplitude, at 25% stiffness amplitude, at 50% stiffness amplitude, at 75% stiffness amplitude, and at 100% stiffness amplitude. The vibration response of the LP rotor 124 as a function of its speed under the applied stiffness can be obtained in any suitable manner, for example, by testing the engine before introduction to the site or during service visits.

[0071] As depicted, the modal or vibration response of the LP rotor 124 is generally such that applying 0% stiffness amplitude from idle to approximately 2600 rpm provides the lowest vibration response. However, for speeds above 2600 RPM, applying 100% stiffness amplitude provides the lowest vibration response. Therefore, the controller 198 is able to control the actuator 176 to position the rotor assembly 148 relative to the stator assembly 150 in the following example manner.

[0072] When the engine is started and from idle to approximately 2600 RPM, the controller 198 is able to move the actuator 176 and / or hold the rotor assembly 148 in a disengaged or second position, for example, as Figure 3 As shown, the controller 198 is capable of iteratively receiving data 224 indicating the operating state of the LP rotor 124. Each group of received data 224 can include parameter values ​​for parameters indicating the operating state of the LP rotor 124. The controller 198 is capable of determining whether the parameter value indicating the operating state of the LP rotor 124 has exceeded a threshold. For example, if the parameter value is the rotational speed of the LP rotor 124, the controller 198 can determine whether the speed of the LP rotor 124 has exceeded a threshold. In this embodiment, the threshold T1 is set to approximately 2600 RPM, such as... Figure 5 As shown, as used in this paper, passing the threshold means that the parameter value exceeds or is greater than the threshold, where the parameter value generally increases before reaching the threshold, or the parameter value is less than the threshold, where the parameter value generally decreases before reaching the threshold.

[0073] On one hand, when the speed of the LP rotor 124 has not exceeded the threshold T1, the controller 198 can control the actuator 176 to maintain its current position, thereby keeping the rotor assembly 148 in the disengaged or second position. In this way, the motor 146 applies 0% stiffness amplitude to the LP rotor 124, thus the LP rotor 124 experiences the lowest possible vibration in this example. On the other hand, when the speed of the LP rotor 124 exceeds the threshold T1, the controller 198 can control the actuator 176 to adjust the position of the rotor assembly 148 relative to the stator assembly 150. That is, the controller 198 can generate and output a control command 230 that instructs the actuator 176 to disengage the rotor assembly 148 from the stator assembly 150. Figure 3 The indicated disengagement position or second position is adjusted to face the direction. Figure 2 The engagement position or first position is shown. Therefore, the distance 194 of the air gap 160 is reduced, thereby generating more power by the motor 146. As a result, the amplitude of the stiffness applied by the motor 146 to the LP rotor 124 is increased. This change in applied stiffness can advantageously alter the modal response of the LP rotor 124, such as the modal frequency and modal shape of the LP rotor 124.

[0074] In some embodiments, when the speed of the LP rotor 124 exceeds a threshold T1, the controller 198 can control the actuator 176 to move the position of the rotor assembly 148 from... Figure 3 The second position shown is directly adjusted to Figure 2 The first position is shown. In this way, the stiffness applied to the LP rotor 124 by the motor 146 can change from 0% stiffness amplitude to 100% stiffness amplitude. Therefore, for this embodiment, the lowest possible vibration response of the LP rotor 124 can be achieved for the depicted engine speed range.

[0075] In other embodiments, when the speed of the LP rotor 124 exceeds a threshold T1, the controller 198 may control the actuator 176 to move the position of the rotor assembly 148 from... Figure 3 The second position shown is adjusted to a first intermediate position between the first and second positions. This first intermediate position can be maintained until the engine speed passes a second threshold. When the speed of the LP rotor 124 passes the second threshold, the controller 198 can control the actuator 176 to adjust the position of the rotor assembly 148 from the first intermediate position to a second intermediate position, which is between the first and second positions and closer to the first position than the first intermediate position. Alternatively, the position of the rotor assembly 148 can be adjusted from the first intermediate position back to the first position. Based on known vibration characteristics, any number of iterations can be performed to control the vibration response of the LP rotor 124.

[0076] In other embodiments, when the speed of the LP rotor 124 exceeds the threshold T1, the controller 198 can control the actuator 176 to adjust the position of the rotor assembly 148 relative to the stator assembly 150 in a stepwise manner from one position to another, such as from the second position to the first position, from the first position to the second position, from the intermediate position to one of the first and second positions, from one of the first and second positions to the intermediate position, etc.

[0077] although Figure 5 A single threshold is shown, but it should be understood that multiple thresholds or triggers can be set at different speeds according to a threshold schedule, such that when a given threshold is passed, controller 198 can control actuator 176 to adjust the position of rotor assembly 148 relative to stator assembly 150. In some cases, when the speed of LP rotor 124 passes a given threshold, controller 198 can cause actuator 176 to adjust the position of rotor assembly 148 relative to stator assembly 150 so that stator assembly 150 and rotor assembly 148 are positioned closer to each other, or in other words, so that rotor assembly 148 moves closer to a first position. In other examples, when the speed of LP rotor 124 passes a given threshold, controller 198 can cause actuator 176 to adjust the position of rotor assembly 148 relative to stator assembly 150 so that stator assembly 150 and rotor assembly 148 are positioned further away from each other, or in other words, so that rotor assembly 148 moves closer to a second position.

[0078] It should be further understood that the exemplary turbo fan 100 has Figure 1 , 2 The embedded motor 146 shown in Figure 3 is provided by way of example only. In other exemplary embodiments, the motor 146 and the gas turbine engine can have any other suitable configuration. For example, in other exemplary embodiments, the motor can be positioned in any other suitable location within the gas turbine engine. Figure 4 The control system 220 provided and described in conjunction with the text is capable of controlling the modal response of a rotating component having an electric motor operably coupled thereto (for other suitable electric motor and gas turbine engine configurations).

[0079] For example, Figure 6 Provided in a similar way Figure 1 An exemplary cross-sectional view of a gas turbine engine configured in an exemplary turbofan manner. As shown by the dashed lines, Figure 6The exemplary gas turbine engine 100 can include the motor 146 in a variety of other suitable locations. For example, the gas turbine engine 100 can include a first motor 146A coupled to the LP rotor 124 at a position in front of the LP compressor 110. Additionally or alternatively, the gas turbine engine 100 can include a second motor 146B coupled to the LP rotor 124, HP rotor 122, or both at a position in front of the HP compressor 112 within the compressor section. Additionally or alternatively, the gas turbine engine 100 can include a third motor 146C coupled to the LP rotor 124, HP rotor 122, or both together at a position inside the HP compressor 212 within the compressor section. Additionally or alternatively, the gas turbine engine 100 can include a fourth motor 146D coupled to the LP rotor 124 at a position in front of the LP turbine 218 within the turbine section. In other embodiments, according to one or more exemplary embodiments of this disclosure, the motor 146 can be embedded in other suitable locations.

[0080] For example, now refer to Figure 7 and 8 A close-up cross-sectional schematic diagram of an LP compressor 110 or a booster compressor with an embedded motor 146 of a gas turbine engine is provided. Figure 7 A view of an exemplary motor 146 in a first position is provided, while Figure 8 A view of an exemplary motor 146 in a second position is provided.

[0081] The depicted LP compressor 110 of the gas turbine engine generally includes a plurality of LP compressor rotor blades 200 and a plurality of LP compressor stator blades 202. The plurality of LP compressor rotor blades 200 include a plurality of stages 204 of LP compressor rotor blades 200 spaced apart along the axial direction A of the gas turbine engine. The gas turbine engine also includes a frame assembly 206, which may be a compressor front frame. In this embodiment, the LP compressor stator blades 202 are coupled to the frame assembly 206.

[0082] Furthermore, the exemplary gas turbine engine includes an electric motor 146 configured according to an exemplary embodiment of the present disclosure. Therefore, the electric motor 146 generally includes a stator assembly 150 and a rotor assembly 148 rotatable relative to the stator assembly 150 about a centerline 155. Figure 7 and 8(Not shown; centerline 155 is aligned with the engine centerline). Rotor assembly 148 includes rotor 154, stator assembly 150 includes stator 158, and rotor 154 and stator 158 define an air gap 160 therebetween. Furthermore, actuator 176 is operatively coupled to rotor assembly 148, stator assembly 150, or both, to move rotor assembly 148 or stator assembly 150 along centerline 155 relative to another of rotor assembly 148 or stator assembly 150 between a first position and a second position.

[0083] Specifically, for Figure 7 and 8 In an exemplary embodiment, actuator 176 is operatively coupled to stator assembly 150 to move stator assembly 150 relative to rotor assembly 148 along centerline 155 between a first position and a second position. As in the embodiments described above, the first position is an engaged position, such as... Figure 7 As shown, the second position is the disengagement position, as... Figure 8 As shown. It should be understood that when the rotor assembly 148 is in the engaged position, it is positioned closer to the stator assembly 150 compared to when it is in the disengaged position.

[0084] Further for Figure 7 and 8 An exemplary embodiment is provided. The rotor assembly 148 is not coupled to the LP rotor 124 of the engine, but is instead coupled to a plurality of rotor blades of the gas turbine engine at a location outside the plurality of rotor blades of the gas turbine engine along the radial direction R of the gas turbine engine. More specifically, for the depicted embodiment, the plurality of rotor blades are a plurality of LP compressor rotor blades 200 in stage 204 of LP compressor blades 200.

[0085] It should be understood that in other exemplary embodiments, the gas turbine engine, the electric motor 146, or both may have other suitable configurations. Furthermore, although the exemplary electric motor 146 described herein is depicted within a gas turbine engine and is described herein as being embedded within a gas turbine engine, in other exemplary embodiments, the exemplary electric motor 146 can be used with any other suitable electric motor having at least one rotating component.

[0086] For reference Figure 9 A flowchart of a method (300) for operating a turbine according to an exemplary aspect of this disclosure is depicted. In some exemplary aspects, the method (300) may utilize the above references Figure 1-3 One or more of the exemplary motors described in 6-8. Therefore, in some exemplary aspects, the motor may include a stator assembly and a rotor assembly, and may define a centerline. Furthermore, it may use... Figure 4The control system 220 implements certain aspects of the method (300). The turbine can be any suitable turbine, such as any turbine described herein.

[0087] At (302), method (300) includes receiving data indicating the operating state of a rotating component of a turbine, the turbine including an electric motor having a stator assembly and a rotor assembly, the rotor assembly being rotatable and operatively coupled to the rotating component. For example, the turbine can be operated such that the rotating component rotates about an axis of rotation, thereby causing the rotor assembly of the electric motor to rotate together with the rotating component about its axis of rotation or centerline. The rotating component may, for example, be the rotor of the turbine. The electric motor can be configured according to the exemplary embodiments provided herein.

[0088] This data can be received by the controller from a sensor operable to sense or measure the value of a parameter indicating the operating state of the rotating component. As an example, the sensor could be a speed sensor operable to sense the rotational speed of the rotating component. Therefore, in this embodiment, the operating state of the rotating component is indicated by the speed of the rotating component. As another example, the sensor could be a temperature sensor operable to sense the temperature of the rotating component. Therefore, in this embodiment, the operating state of the rotating component is indicated by the temperature of the rotating component. As yet another example, the sensor could be a vibration sensor operable to sense the vibration of the rotating component. Therefore, in this embodiment, the operating state of the rotating component is indicated by the vibration of the rotating component. It should be understood that the operating state of the rotating component can also be indicated by other suitable parameters, including combinations of parameters.

[0089] Furthermore, in some embodiments, in addition to data indicating the operating state of the rotating component, the controller may receive feedback data indicating the current position of the actuator and / or the power required by one or more electrical loads electrically connected to the motor. As will be explained below, this data can be used to generate control commands.

[0090] At (304), method (300) includes moving the position of at least one of the stator assembly and rotor assembly based at least partially on the operating state of the rotating component to change the air gap defined between the rotor assembly and the stator assembly. For example, the controller may receive data indicating the operating state of the rotating component of the turbine and may generate a control command that instructs the actuator to adjust the position of at least one of the stator assembly and rotor assembly. The control command may be generated based at least partially on the operating state of the rotating component. As an example, the operating state may be indicated by the rotational speed of the rotating component, and therefore the generated control command may be based on a sensed or calculated rotational speed. The position of at least one of the stator assembly and rotor assembly is moved based at least partially on the control command.

[0091] In some implementations, control commands may be additionally generated based on feedback data provided by the actuator. The feedback data may indicate the current position of the actuator. In some further implementations, control commands may be generated at least in part based on the power required by one or more electrical loads electrically connected to the motor. For example, if the motor driving the propulsion system of an aircraft is electrically connected to the motor and requires full power, it is not feasible to move the rotor assembly 148 relative to the stator assembly 150 for safety purposes, even without mitigating the modal vibration response by driving at least one of the rotor assembly and stator assembly relative to the other, resulting in an undesirable modal vibration response.

[0092] Furthermore, in some implementations, for example, such as Figure 2 and 3 In the embodiments provided, the position of moving at least one of the stator assembly and rotor assembly includes moving the position of the rotor assembly relative to the stator assembly. In other embodiments, for example, as in... Figure 7 and 8 In the embodiments provided, the position of at least one of the moving stator assembly and the rotor assembly includes the position of moving the stator assembly relative to the rotor assembly.

[0093] It is worth noting that, as described above, by moving the position of at least one of the stator assembly and the rotor assembly, the position of at least one of the stator assembly and the rotor assembly is adjusted, thereby changing the air gap defined between the rotor assembly and the stator assembly. The change in the air gap or distance between the rotor of the rotor assembly and the stator of the stator assembly effectively alters the stiffness of the motor. Changing the stiffness of the motor can be used to manipulate the modal response or dynamic behavior of the rotating components.

[0094] In some implementations, for example, such as Figure 2 and 3 As shown, the air gap defines an angle greater than zero degrees and less than 90 degrees relative to the centerline. Therefore, in this embodiment, moving the rotor assembly (or vice versa) at (304) relative to the stator assembly along the motor's centerline includes moving the rotor assembly (or vice versa) at least 0.5 inches and less than 10 inches relative to the stator assembly along the motor's centerline. The tilt of the air gap allows for relatively short movements of either the rotor or stator assembly while still achieving the desired separation between the rotor and stator assemblies.

[0095] Figure 10 A block diagram of a computing system 400 according to an exemplary aspect of this disclosure is provided. The computing system 400 is an example of a suitable computing system for implementing certain aspects of this disclosure.

[0096] like Figure 10As shown, computing system 400 includes one or more processors 404 and one or more memory devices 406. The one or more processors 404 and one or more memory devices 406 may be implemented in one or more computing devices 402, such as the controller 198 provided herein. The one or more processors 404 may include any suitable processing device, such as a microprocessor, microcontroller, integrated circuit, logic device, or other suitable processing device. The one or more memory devices 406 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.

[0097] One or more memory devices 406 may store information accessible by one or more processors 404, including computer-readable instructions 408 executable by one or more processors 404. Instructions 408 may be any set of instructions that, when executed by one or more processors 404, cause one or more processors 404 to perform an operation. Instructions 408 may be software written in any suitable programming language or may be implemented in hardware. Instructions 408 may be any computer-readable instruction described herein.

[0098] The memory device 406 may further store data 410 accessible by the processor 404. For example, data 410 may include received data 224, feedback data 226, and other data. Figure 4 Furthermore, according to exemplary embodiments of this disclosure, data 410 may include one or more tables, functions, algorithms, models, equations, etc.

[0099] One or more computing devices 402 may also include components for, for example, use with control system 220 ( Figure 4 The communication interface 412 is a communication interface for communicating with other components or other systems or devices. The communication interface 412 may include any suitable components for communicating with one or more network interfaces, including, for example, a transmitter, receiver, port, controller, antenna or other suitable components.

[0100] The technologies discussed herein refer to computer-based systems and the actions taken by and from these systems, as well as the information sent to and from them. It should be understood that the inherent flexibility of computer-based systems allows for a wide variety of possible configurations, combinations, and divisions of tasks and functions between and within components. For example, the processes discussed herein can be implemented using a single computing device or multiple computing devices working in combination. Databases, memory, instructions, and applications can be implemented on a single system or distributed across multiple systems. Distributed components can operate sequentially or in parallel.

[0101] This written description uses examples to disclose aspects of this disclosure, including best practices, and also enables those skilled in the art to practice aspects of this disclosure, including making and using any device or system and performing any combined methods. The patentable scope of this invention is defined by the claims and can include other examples that would occur to those skilled in the art. Such other examples are intended to be within the scope of the claims if they have structural elements that do not differ from the wording of the claims, or if they include equivalent structural elements that do not differ significantly from the wording of the claims.

[0102] Other exemplary aspects will be described below with reference to the following clauses:

[0103] 1. A turbine comprising: a rotating component rotatable about a rotation axis; an electric motor including: a stator assembly; a rotor assembly rotatable together with the rotating component relative to the stator assembly; an actuator operably coupled to at least one of the rotor assembly and the stator assembly for moving the rotor assembly, moving the stator assembly, or moving both the rotor assembly and the stator assembly relative to each other; and a controller communicatively coupled to the actuator, the controller being configured to: receive data indicating an operating state of the rotating component; and cause the actuator to adjust the position of at least one of the stator assembly and the rotor assembly at least in part based on the operating state of the rotating component.

[0104] 2. A turbine according to any of the foregoing provisions, wherein, when the actuator adjusts the position of at least one of the stator assembly and the rotor assembly, the position of at least one of the stator assembly and the rotor assembly is moved to change the air gap defined between the rotor assembly and the stator assembly.

[0105] 3. A turbine according to any of the foregoing provisions, wherein the operating state of the rotating component is indicated by the speed of the rotating component.

[0106] 4. A turbine according to any of the foregoing provisions, wherein the controller is further configured to: determine whether a parameter value received as part of data has passed a threshold, and wherein, when the parameter value has passed the threshold, the controller is configured to cause the actuator to adjust the position of at least one of the stator assembly and the rotor assembly.

[0107] 5. A turbine according to any of the foregoing provisions, wherein when the parameter value has passed the threshold, the controller is configured to cause the actuator to adjust the position of at least one of the stator assembly and the rotor assembly so that the stator assembly and the rotor assembly are positioned closer to each other.

[0108] 6. A turbine according to any of the foregoing provisions, wherein when the parameter value has passed the threshold, the controller is configured to cause the actuator to adjust the position of at least one of the stator assembly and the rotor assembly such that the stator assembly and the rotor assembly are positioned further away from each other.

[0109] 7. A turbine according to any of the foregoing provisions, wherein the rotor assembly and the stator assembly together define an air gap, and wherein the air gap defines an angle relative to a centerline defined by the motor, the angle being greater than zero degrees and less than 90 degrees.

[0110] 8. A turbine according to any of the foregoing clauses, wherein the angle defined by the air gap relative to the centerline is greater than 10 degrees and less than 45 degrees.

[0111] 9. A turbine according to any of the foregoing provisions, wherein the controller causes the actuator to adjust the position of the rotor assembly relative to the stator assembly.

[0112] 10. A turbine according to any of the foregoing provisions, wherein the controller causes the actuator to adjust the position of the stator assembly relative to the rotor assembly.

[0113] 11. The turbine in any of the foregoing clauses, wherein the turbine is the core engine of an aviation gas turbine engine, and the rotating component is one of the high-pressure rotor and the low-pressure rotor of the core engine.

[0114] 12. A turbine according to any of the foregoing provisions, wherein the controller is further configured to: generate a control command at least in part based on the operating state of the rotating component, the control command indicating instructions for adjusting the position of at least one of the stator assembly and the rotor assembly by an actuator, and wherein the position of at least one of the stator assembly and the rotor assembly is adjusted at least in part based on the control command.

[0115] 13. A turbine according to any of the foregoing provisions, wherein the controller is further configured to: receive feedback data indicating the current position of the actuator, and wherein the control command is generated based at least in part on the feedback data.

[0116] 14. A turbine according to any of the foregoing provisions, wherein the controller is further configured to: receive a power demand indicating the power required by one or more electrical loads electrically connected to the motor, and wherein the control command is generated based at least in part on the power demand.

[0117] 15. A turbine according to any of the foregoing provisions, wherein the controller is further configured to: determine whether the power demand has exceeded a demand threshold, and wherein when the power demand has exceeded the demand threshold, the controller causes the actuator to adjust the position of at least one of the stator assembly and the rotor assembly to reduce the air gap between the rotor assembly and the stator assembly.

[0118] 16. A method of operating a turbine, the method comprising: receiving data indicating an operating state of a rotating component of the turbine, the turbine including an electric motor having a stator assembly and a rotor assembly, the rotor assembly being rotatable and operatively coupled to the rotating component; and moving at least one of the stator assembly and the rotor assembly at least in part based on the operating state of the rotating component to change the air gap defined between the rotor assembly and the stator assembly.

[0119] 17. The method according to any of the foregoing clauses further includes: receiving feedback data indicating the current position of an actuator operatively coupled to at least one of the stator assembly and the rotor assembly; receiving a power demand indicating the power required by one or more electrical loads electrically coupled to the motor; and generating a control command based at least in part on the operating state of the rotating component, the current position of the actuator, and the power demand, the control command indicating instructions for moving the actuator to a position of at least one of the stator assembly and the rotor assembly, and wherein the position of at least one of the stator assembly and the rotor assembly is moved based at least in part on the control command.

[0120] 18. The method according to any of the foregoing clauses, wherein the movement includes moving the position of the rotor assembly relative to the stator assembly.

[0121] 19. The method according to any of the foregoing clauses, wherein the movement includes moving the position of the stator assembly relative to the rotor assembly.

[0122] 20. A non-transient computer-readable medium comprising computer-executable instructions, which, when executed by one or more processors of a controller, cause the one or more processors to: receive data indicating an operating state of a rotating component of a turbine, the turbine including a motor having a stator assembly and a rotor assembly, the rotor assembly being rotatable and operatively coupled to the rotating component; generate a control command at least partially based on the operating state of the rotating component, the control command being used to cause an actuator to adjust the position of at least one of the stator assembly and the rotor assembly; and cause the actuator to adjust the position of at least one of the stator assembly and the rotor assembly at least partially based on the control command.

Claims

1. A turbine, characterized in that, include: A rotating component, the rotating component being capable of rotating about a rotation axis; The motor includes: Stator assembly; A rotor assembly capable of rotating together with the rotating component relative to the stator assembly; An actuator operatively coupled to at least one of the rotor assembly and the stator assembly for moving the rotor assembly, moving the stator assembly, or moving both the rotor assembly and the stator assembly relative to each other; and A controller, communicatively connected to the actuator, is configured to: Receive data indicating the operating status of the rotating component; This causes the actuator to adjust the position of at least one of the stator assembly and the rotor assembly based at least in part on the operating state of the rotating component; and Determine whether the parameter value received as part of the data has exceeded the threshold, and Wherein, when the parameter value has exceeded the threshold, the controller is configured such that the actuator adjusts the position of at least one of the stator assembly and the rotor assembly, and the rotor assembly controls the vibration response of the rotating component to which the motor is connected and changes the stiffness of the motor, and When the actuator adjusts the position of at least one of the stator assembly and the rotor assembly, the position of at least one of the stator assembly and the rotor assembly is changed so as to change the air gap defined between the rotor assembly and the stator assembly and the stiffness of the motor.

2. The turbine according to claim 1, characterized in that, When the actuator adjusts the position of at least one of the stator assembly and the rotor assembly, the position of at least one of the stator assembly and the rotor assembly is moved to change the air gap defined between the rotor assembly and the stator assembly.

3. The turbine according to claim 1, characterized in that, The operating state of the rotating component is indicated by the speed of the rotating component.

4. The turbine according to claim 1, characterized in that, When the parameter value has passed the threshold, the controller is configured to cause the actuator to adjust the position of at least one of the stator assembly and the rotor assembly so that the stator assembly and the rotor assembly are positioned closer to each other.

5. The turbine according to claim 1, characterized in that, When the parameter value has passed the threshold, the controller is configured to cause the actuator to adjust the position of at least one of the stator assembly and the rotor assembly, such that the stator assembly and the rotor assembly are positioned further away from each other.

6. The turbine according to claim 1, characterized in that, The rotor assembly and the stator assembly together define an air gap, and the air gap is defined at an angle relative to the centerline defined by the motor, the angle being greater than zero degrees and less than 90 degrees.

7. The turbine according to claim 6, characterized in that, The angle defined by the air gap relative to the centerline is greater than 10 degrees and less than 45 degrees.

8. The turbine according to claim 1, characterized in that, The controller causes the actuator to adjust the position of the rotor assembly relative to the stator assembly.

9. The turbine according to claim 1, characterized in that, The controller causes the actuator to adjust the position of the stator assembly relative to the rotor assembly.

10. The turbine according to claim 1, characterized in that, The turbine is the core engine of an aviation gas turbine engine, and the rotating component is one of the high-pressure rotor and the low-pressure rotor of the core engine.

11. The turbine according to claim 1, characterized in that, The controller is further configured to: Control commands are generated at least in part based on the operating state of the rotating component, the control commands indicating instructions for causing the actuator to adjust the position of at least one of the stator assembly and the rotor assembly, and The position of at least one of the stator assembly and the rotor assembly is adjusted based at least in part on the control commands.

12. The turbine according to claim 11, characterized in that, The controller is further configured to: Receive feedback data indicating the current position of the actuator, and The control commands are generated based at least in part on the feedback data.

13. The turbine according to claim 11, characterized in that, The controller is further configured to: Receive power demand, which indicates the power required by one or more electrical loads electrically connected to the motor, and The control commands are generated based at least in part on the power demand.

14. The turbine according to claim 13, characterized in that, The controller is further configured to: Determine whether the electricity demand has exceeded the demand threshold, and When the power demand exceeds the demand threshold, the controller causes the actuator to adjust the position of at least one of the stator assembly and the rotor assembly, thereby reducing the air gap between the rotor assembly and the stator assembly.

15. A method of operating a turbine, characterized in that, The method includes: Receive data indicating the operating state of the rotating components of the turbine, the turbine including a motor having a stator assembly and a rotor assembly, the rotor assembly being rotatable and operably coupled to the rotating components; and The position of at least one of the stator assembly and the rotor assembly is moved, at least in part, based on the operating state of the rotating component, in order to change the air gap defined between the rotor assembly and the stator assembly; and Determine whether the parameter value received as part of the data has exceeded the threshold, and When the parameter value has exceeded the threshold, the position of at least one of the stator assembly and the rotor assembly is adjusted, and the rotor assembly controls the vibration response of the rotating component to which the motor is connected and changes the stiffness of the motor.

16. The method according to claim 15, characterized in that, Further includes: Receive feedback data indicating the current position of an actuator operatively coupled to at least one of the stator assembly and the rotor assembly; Receive power demand, which indicates the power required by one or more electrical loads electrically connected to the motor; and Control commands are generated, at least in part, based on the operating state of the rotating component, the current position of the actuator, and the power demand, instructing the actuator to move at least one of the stator assembly and the rotor assembly to a position. The position of at least one of the stator assembly and the rotor assembly is moved, at least in part, based on the control commands.

17. The method according to claim 15, characterized in that, The movement includes moving the position of the rotor assembly relative to the stator assembly.

18. The method according to claim 15, characterized in that, The movement includes moving the position of the stator assembly relative to the rotor assembly.

19. A non-transient computer-readable medium, characterized in that, The medium includes computer-executable instructions that, when executed by one or more processors of the controller, cause the one or more processors to: Receive data indicating the operating state of a rotating component of a turbine, the turbine including a motor having a stator assembly and a rotor assembly, the rotor assembly being rotatable and operably coupled to the rotating component; Control commands are generated at least in part based on the operating state of the rotating component, the control commands being used to cause the actuator to adjust the position of at least one of the stator assembly and the rotor assembly; This causes the actuator to adjust the position of at least one of the stator assembly and the rotor assembly based at least in part on the control command; as well as Determine whether a parameter value received as part of the data has passed a threshold, and wherein, when the parameter value has passed the threshold, the actuator adjusts the position of at least one of the stator assembly and the rotor assembly, and the rotor assembly controls the vibration response of the rotating component to which the motor is connected and changes the stiffness of the motor.

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