Propulsion system for an aircraft

Abstract

A propulsion system for an aircraft includes a combustion engine, a propulsor, and an electric machine configured to be driven by the combustion engine or to drive the propulsor. The electric machine defines an axis. The electric machine includes a rotor extending along the axis and rotatable about the axis, and a stator including a plurality of winding assemblies spaced apart along the axis of the electric machine, each winding assembly being operable with the rotor independently of adjacent winding assemblies during operation of the electric machine.

Description

Technical Field

[0001] This disclosure relates generally to aircraft propulsion systems, and more specifically to electric motors used in aircraft propulsion systems. Background Technology

[0002] Traditional commercial aircraft generally consist of a fuselage, a pair of wings, and a propulsion system that provides thrust. The propulsion system typically includes at least two aircraft engines, such as turbofan jet engines. Each turbofan jet engine is mounted to a corresponding wing of the aircraft, for example, in a suspended position below the wing, separate from the fuselage.

[0003] Recently, propulsion systems with hybrid-electric designs have been proposed. In these systems, a power source can provide electrical power to a fan assembly to power the fan assembly. The fan assembly generally consists of an electric motor and a propeller, such as a fan or propeller. The electric motor receives electrical power and converts this electrical power into mechanical power to drive the propeller.

[0004] To ensure the propulsion system achieves the desired level of reliability, redundant motors are required, allowing the aircraft to continue operating in the event of a main motor failure. However, redundant motors can increase the weight and cost of the propulsion system. Therefore, it would be useful for the propulsion system's motors to have redundancy, eliminating the need for a second motor. Summary of the Invention

[0005] Various aspects and advantages of the invention will be set forth in part in the description which follows, or will be apparent from the description, or may be learned by practice of the invention.

[0006] In one exemplary embodiment of the present invention, a propulsion system for an aircraft is provided. The propulsion system includes a combustion engine, a thruster, and an electric machine configured to be driven by the combustion engine or configured to drive the thruster. The electric machine defines an axis. The electric machine includes a rotor extending along and rotatable about the axis; and a stator including a plurality of winding assemblies spaced apart along the axis of the electric machine, each winding assembly being capable of operating independently of adjacent winding assemblies with the rotor during operation of the electric machine.

[0007] In some exemplary embodiments, the plurality of winding assemblies includes a first winding assembly and a second winding assembly spaced apart along the axis of the motor, wherein the rotor extends continuously between the first winding assembly and the second winding assembly. For example, in some exemplary embodiments, the rotor includes a plurality of permanent magnets, wherein the plurality of permanent magnets extend continuously along the axis between the first winding assembly and the second assembly.

[0008] In some exemplary embodiments, the stator includes at least three winding assemblies and up to thirty winding assemblies.

[0009] In some exemplary embodiments, the rotor includes a plurality of permanent magnets.

[0010] In some exemplary embodiments, the rotor is positioned inside the stator.

[0011] In some exemplary embodiments, each winding assembly includes a set of windings dedicated to the winding assembly.

[0012] In some exemplary embodiments, the motor is an electric motor configured to drive the propulsion system, wherein the propulsion system further includes an electric generator configured to be driven by the aircraft combustion engine, and wherein the generator is electrically connected to the electric motor.

[0013] In some exemplary embodiments, the propulsion system further includes an electric power bus, wherein the plurality of winding assemblies are electrically connected to the electric power bus separately. For example, in some exemplary embodiments, the plurality of winding assemblies are electrically connected to the electric power bus separately in parallel electrical communication. For example, in some exemplary embodiments, one or more of the plurality of winding assemblies are selectively electrically connected to the electric power bus.

[0014] In some exemplary embodiments, the motor includes a housing, wherein both the rotor and the stator are positioned within the housing.

[0015] In another exemplary embodiment of the invention, a propulsion system for an aircraft is provided. The propulsion system includes a power source comprising a combustion engine and a generator powered by the combustion engine. The propulsion system also includes an electric thruster assembly comprising a thruster and an electric motor configured to drive the thruster. The electric motor defines an axis and includes: a rotor extending along and rotatable about the axis; and a stator including a plurality of winding assemblies. The plurality of winding assemblies are spaced apart along the axis of the electric motor, and each winding assembly is capable of operating independently of adjacent winding assemblies with the rotor during operation of the electric motor.

[0016] In some exemplary embodiments, the propulsion system further includes a power bus, wherein the plurality of winding assemblies are electrically connected separately to the power bus.

[0017] In some exemplary embodiments, the plurality of winding assemblies are electrically connected separately in parallel with the power bus.

[0018] In some exemplary embodiments, one or more of the plurality of winding assemblies are selectively electrically connected to the power bus.

[0019] In some exemplary embodiments, the electric motor includes a housing, wherein both the rotor and the stator are positioned within the housing.

[0020] In some exemplary embodiments, the stator includes at least three winding assemblies and up to thirty winding assemblies.

[0021] In yet another exemplary embodiment of the present invention, an electric motor is provided. The electric motor includes: a rotor extending along an axis of the motor and rotatable about the axis of the motor; and a stator including a plurality of winding assemblies. The plurality of winding assemblies are spaced apart along the axis of the motor, and during operation of the motor, each winding assembly is capable of operating independently of adjacent winding assemblies with the rotor.

[0022] In some exemplary embodiments, the stator includes at least three winding assemblies and up to thirty winding assemblies.

[0023] These and other features, aspects, and advantages of the invention will become more readily 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 embodiments of the invention and, together with the description, serve to explain the principles of the invention.

[0024] The present invention provides a propulsion system for an aircraft, the propulsion system comprising: a combustion engine; a thruster; and a motor, the motor being configured to be driven by the combustion engine or configured to drive the thruster, the motor defining an axis and including: a rotor extending along the axis and rotatable about the axis; and a stator including a plurality of winding assemblies spaced apart along the axis of the motor, wherein during operation of the motor, each winding assembly is capable of working independently of adjacent winding assemblies with the rotor.

[0025] Technical Solution 2: The propulsion system according to Technical Solution 1, wherein the plurality of winding assemblies includes a first winding assembly and a second winding assembly spaced apart along the axis of the motor, and wherein the rotor extends continuously between the first winding assembly and the second winding assembly.

[0026] Technical Solution 3: The propulsion system according to Technical Solution 2, wherein the rotor includes a plurality of permanent magnets, and wherein the plurality of permanent magnets extend continuously along the axis between the first winding assembly and the second assembly.

[0027] Technical Solution 4: The propulsion system according to Technical Solution 1, wherein the stator includes at least three winding assemblies and up to thirty winding assemblies.

[0028] Technical Solution 5: The propulsion system according to Technical Solution 1, wherein the rotor includes a plurality of permanent magnets.

[0029] Technical Solution 6: The propulsion system according to Technical Solution 1, wherein the rotor is positioned within the stator.

[0030] Technical Solution 7: The propulsion system according to Technical Solution 1, wherein each winding assembly includes a set of windings dedicated to the winding assembly.

[0031] Technical Solution 8: The propulsion system according to Technical Solution 1, wherein the motor is an electric motor configured to drive the thruster, wherein the propulsion system further includes a generator configured to be driven by an aircraft combustion engine, and wherein the generator is electrically connected to the electric motor.

[0032] Technical Solution 9: The propulsion system according to Technical Solution 1 further includes: a power bus, wherein the plurality of winding assemblies are electrically connected separately to the power bus.

[0033] Technical Solution 10: The propulsion system according to Technical Solution 9, wherein the plurality of winding assemblies are separately connected in parallel with the power bus.

[0034] Technical Solution 11: The propulsion system according to Technical Solution 9, wherein one or more of the plurality of winding assemblies are selectively electrically connected to the power bus.

[0035] Technical Solution 12: The propulsion system according to Technical Solution 1, wherein the motor includes a housing, and the rotor and stator are both positioned within the housing.

[0036] Technical Solution 13: A propulsion system for an aircraft, the propulsion system comprising: a power source including a combustion engine and a generator powered by the combustion engine; and an electric propulsion assembly including a thruster and an electric motor configured to drive the thruster, the electric motor defining an axis and including: a rotor extending along and rotatable about the axis; and a stator including a plurality of winding assemblies spaced apart along the axis of the electric motor, each winding assembly being capable of operating independently of adjacent winding assemblies with the rotor during operation of the electric motor.

[0037] Technical solution 14: The propulsion system according to technical solution 13 further includes: a power bus, wherein the plurality of winding assemblies are electrically connected separately to the power bus.

[0038] Technical solution 15: The propulsion system according to technical solution 14, wherein the plurality of winding assemblies are separately connected in parallel with the power bus.

[0039] Technical solution 16: The propulsion system according to technical solution 14, wherein one or more of the plurality of winding assemblies are selectively electrically connected to the power bus.

[0040] Technical Solution 17: The propulsion system according to Technical Solution 13, wherein the electric motor includes a housing, wherein the rotor and stator are both positioned within the housing.

[0041] Technical solution 18: The propulsion system according to technical solution 13, wherein the stator includes at least three winding assemblies and up to thirty winding assemblies.

[0042] Technical Solution 19: An electric motor comprising: a rotor extending along an axis of the motor and rotatable about the axis of the motor; and a stator including a plurality of winding assemblies spaced apart along the axis of the motor, wherein during operation of the motor, each winding assembly is capable of working independently of adjacent winding assemblies with the rotor.

[0043] Technical solution 20: The motor according to technical solution 19, wherein the stator includes at least three winding assemblies and up to thirty winding assemblies. Attached Figure Description

[0044] This specification sets forth a complete and illustrative disclosure of the invention, including its best mode, to those skilled in the art. Reference is made to the accompanying drawings, in which: Figure 1 This is a top view of an aircraft according to various exemplary embodiments of the present invention.

[0045] Figure 2 It is installed at Figure 1 A schematic cross-sectional view of the gas turbine engine of an exemplary aircraft.

[0046] Figure 3 This is a schematic cross-sectional view of a fan assembly according to an exemplary embodiment of the present invention.

[0047] Figure 4 This is a side cross-sectional view of an electric motor according to an exemplary embodiment of the present invention.

[0048] Figure 5 yes Figure 4 An axial cross-sectional view of an exemplary motor.

[0049] Figure 6 This is a schematic diagram of a propulsion system according to an exemplary embodiment of the present invention.

[0050] Figure 7 This is a schematic diagram of a propulsion system according to another exemplary embodiment of the present invention. Detailed Implementation

[0051] Reference will now be made in detail to the present embodiments of the invention, one or more of which are illustrated in the accompanying drawings. Numerical and alphanumeric designations are used in the detailed description to refer to features in the drawings. The same or similar reference numerals are used in the drawings and description to refer to the same or similar parts of the invention.

[0052] As used in this specification, 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 any individual component.

[0053] The terms "front" and "rear" refer to relative positions within a gas turbine engine or vehicle, and to the normal operating elevation of the gas turbine engine or vehicle. For example, referring to 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 manifold.

[0054] The terms "upstream" and "downstream" refer to the relative directions of flow within a path. For example, relative to fluid flow, "upstream" refers to the direction in which the fluid flows out, and "downstream" refers to the direction in which the fluid flows in. However, when used in this specification, the terms "upstream" and "downstream" also refer to electric current.

[0055] Unless the context explicitly indicates otherwise, the singular forms “a” and “the” include the plural referent.

[0056] As used throughout the specification and claims, approximate language is used to modify any quantitative representations that are permissible to vary without altering their associated essential function. Therefore, values ​​modified by one or more terms such as “about,” “approximately,” and “substantially” are not limited to the specified exact values. In at least some cases, approximate language may correspond to the accuracy of the instrument used to measure the value, or the accuracy 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 10%.

[0057] Throughout this specification and the claims, scope limitations are combined and interchanged; such scope is definite and includes all subscopes contained herein, unless the context or language otherwise indicates otherwise. For example, all scopes disclosed herein include endpoints, and these endpoints can be independently combined with each other.

[0058] Referring now to the accompanying drawings, similar numbers throughout the drawings indicate the same elements. Figure 1 A top view of an exemplary aircraft 10, which can be incorporated into various embodiments of the present invention, is provided. For example... Figure 1 As shown, aircraft 10 defines a longitudinal centerline 14 extending therethrough, a lateral direction L, a front end 16, and a rear end 18. Furthermore, aircraft 10 includes a fuselage 12 extending longitudinally from the front end 16 to the rear end 18, and wing assemblies including a port side and a starboard side. More specifically, the port side of the wing assembly is a first port-side wing 20, and the starboard side is a second starboard-side wing 22. Both the first wing 20 and the second wing 22 extend laterally outward relative to the longitudinal centerline 14. The first wing 20 and a portion of the fuselage 12 together define a first side 24 of aircraft 10, and the second wing 22 and another portion of the fuselage 12 together define a second side 26 of aircraft 10. For the illustrated embodiment, the first side 24 of aircraft 10 is configured as the port side of aircraft 10, and the second side 26 of aircraft 10 is configured as the starboard side of aircraft 10.

[0059] Each of the wings 20, 22 in the illustrated exemplary embodiment includes one or more leading edge flaps 28 and one or more trailing edge flaps 30. The aircraft 10 also includes a vertical stabilizer 32 with a rudder flap (not shown) for yaw control and a pair of horizontal stabilizers 34, each horizontal stabilizer 34 having an elevator flap 36 for pitch control. The fuselage 12 also includes an outer surface or skin 38. However, it should be understood that in other exemplary embodiments of the invention, the aircraft 10 may, in addition to or alternatively, include any other suitable configuration. For example, in other embodiments, the aircraft 10 may include stabilizers of any other configuration.

[0060] Still referencing Figure 2 and Figure 3 , Figure 1 The exemplary aircraft 10 also includes a propulsion system 50 having a first thruster assembly 52 and a second thruster assembly 54. Figure 2 A schematic cross-sectional view of the first thruster assembly 52 is provided, and Figure 3 A schematic cross-sectional view of the second propulsion assembly 54 is provided. As shown, each of the first propulsion assembly 52 and the second propulsion assembly 54 is configured as an under-wing mounted propulsor assemblies.

[0061] Special reference Figure 1 and Figure 2 The first thruster assembly 52 is mounted or configured to be mounted to the first side 24 of the aircraft 10, or more specifically, to the first wing 20 of the aircraft 10. The first thruster assembly 52 generally includes a turbine 102 and a primary fan (see reference 102). Figure 2 (Referring to "fan 104" for short). More specifically, for the illustrated embodiment, the first thruster assembly 52 is configured as a turbofan engine 100 (i.e., the turbine 102 and fan 104 are configured as components of the turbofan 100).

[0062] like Figure 2 As shown, the turbofan 100 defines an axial direction A1 (extending parallel to the longitudinal centerline 101 provided for reference) and a radial direction R1. As described above, the turbofan 100 includes a fan 104 and a turbine 102 disposed downstream of the fan 104.

[0063] The illustrated exemplary turbine 102 generally includes a substantially tubular outer casing 106 that defines an annular inlet 108. The outer casing 106 encloses, in a serial flow relationship, the following: a compressor section including a turbocharger or low-pressure (LP) compressor 110 and a high-pressure (HP) compressor 112; a combustion section 114; a turbine section including a first low-pressure (LP) turbine 118 and a second high-pressure (HP) turbine 116; and an exhaust nozzle section 120.

[0064] The exemplary turbine 102 of the turbofan 100 also includes one or more shafts capable of rotating with at least a portion of the turbine section (and, in the illustrated embodiment, at least a portion of the compressor section). More specifically, in the illustrated embodiment, the turbofan 100 includes a high-pressure (HP) shaft or spool 122 that drivesly connects the HP turbine 116 to the HP compressor 112. Furthermore, the exemplary turbofan 100 includes a low-pressure (LP) shaft or spool 124 that drivesly connects the LP turbine 118 to the LP compressor 110.

[0065] Furthermore, the exemplary fan 104 is illustrated as a variable pitch fan having a plurality of fan blades 128 spaced apart and coupled to the disk 130. The fan blades 128 extend generally radially outward from the disk 130 in a radial direction R1. Each fan blade 128 is operatively coupled to a suitable actuating member 132, enabling rotation relative to the disk 130 about a corresponding pitch axis P1, the actuating member being configured to collectively change the pitch of the fan blade 128. The fan 104 is mechanically coupled to the LP shaft 124 such that the fan 104 is mechanically driven by a first LP turbine 118. More specifically, the fan 104 (including the fan blades 128), the disk 130, and the actuating member 132 are mechanically coupled to the LP shaft 124 via a power gearbox 134 and are rotatable about a longitudinal axis 101 via the LP shaft 124 spanning the power gearbox 134. The power gearbox 134 includes multiple gears for progressively reducing the rotational speed of the LP shaft 124 to a more efficient rotating fan speed. Therefore, the fan 104 is powered by the LP system of the turbine 102, which includes the LP turbine 118.

[0066] Still referencing Figure 2In an exemplary embodiment, the disk 130 is covered by a rotatable front hub 136 having an aerodynamic profile to facilitate airflow through a plurality of fan blades 128. Furthermore, the turbofan 100 includes an annular fan housing or external nacelle 138 circumferentially surrounding at least a portion of the fan 104 and / or turbine 102. Therefore, the illustrated exemplary turbofan 100 may be referred to as a “ducted” turbofan engine. Additionally, a plurality of circumferentially spaced outlet guide vanes 140 support the nacelle 138 relative to the turbine 102. A downstream section 142 of the nacelle 138 extends above and outside the turbine 102 to define a bypass airflow passage 144 therebetween.

[0067] Still refer to Figure 2 The propulsion system 50 also includes an electric motor, which, in the illustrated embodiment, is configured as a generator 56. The generator 56 and the turbofan engine 100 may be collectively referred to as the power source for the propulsion system 50 in this specification. Furthermore, in the illustrated embodiment, the generator 56 is located within the turbine 102 of the turbofan engine 100 and is mechanically connected to one of the shafts of the turbofan engine 100. More specifically, in the depicted embodiment, the generator is driven by a first LP turbine 118 via an LP shaft 124. The generator 56 is configured to convert the mechanical power of the LP shaft 124 into electrical power. Therefore, the generator 56 is also powered by the LP system of the turbine 102, which includes the LP turbine 118.

[0068] However, it should be understood that in other exemplary embodiments, generator 56 may alternatively be located at any other suitable location within turbine 102, or other locations, and may be powered, for example, by any other suitable means. For example, in other embodiments, generator 56 may be mounted coaxially with LP shaft 124 within the turbine section, or alternatively may be offset relative to LP shaft 124 and driven by a suitable gear train. Furthermore or alternatively, in other exemplary embodiments, generator 56 may alternatively be powered by the HP system (i.e., by HP turbine 116 via HP shaft 122), or by both the LP system (e.g., LP shaft 124) and the HP system (e.g., HP shaft 122) via a dual-drive system.

[0069] It should be understood that in other exemplary embodiments, Figure 2The exemplary turbofan engine 100 illustrated in the figure can have any other suitable configuration. For example, in other exemplary embodiments, fan 104 may not be a variable pitch fan, and further in other exemplary embodiments, LP shaft 124 may be directly mechanically coupled to fan 104 (i.e., turbofan engine 100 may not include gearbox 134). Furthermore, it should be understood that in other exemplary embodiments, the first propulsion assembly 52 may include any other suitable type of engine. For example, in other exemplary embodiments, turbofan engine 100 may alternatively be configured as a turboprop engine or an unducted turbofan engine. Moreover, however, in other embodiments, turbofan engine 100 may alternatively be configured as any other suitable gas turbine for driving generator 56. For example, in other embodiments, turbofan engine may alternatively be configured as a turboshaft engine or any other suitable gas turbine.

[0070] Still refer to Figure 1 and Figure 2 The illustrated propulsion system 50 also includes an electrical power bus 58 to allow the generator 56 to be electrically connected to the propulsion system 50 and / or one or more other components of the aircraft 10. For the illustrated embodiment, the power bus 58 includes one or more cables or wires 60 connected to the generator 56, and for the illustrated embodiment, extends through one or more of the exit guide vanes 140.

[0071] Furthermore, the illustrated propulsion system 50 also includes one or more energy storage devices 55 (e.g., one or more batteries or other electrical energy storage devices) electrically connected to the power bus 58 for, for example, providing electrical power to the second thruster assembly 54 and / or receiving electrical power from the generator 56. Including one or more energy storage devices 55 can provide performance gains and can, for example, enhance the propulsion capability of the propulsion system 50 during transient operations. More specifically, the propulsion system 50 including one or more energy storage devices 55 is able to respond more quickly to speed change demands.

[0072] Now, especially referencing Figure 1 and Figure 3The exemplary propulsion system 50 also includes a second propulsion assembly 54 located or configured to be located at a position spaced apart from the first propulsion assembly 52. ​​More specifically, for the illustrated embodiment, the second propulsion system 54 is mounted laterally L away from the first propulsion assembly 52, such that it draws in different airflows in the lateral direction L. However, in other embodiments, both the first propulsion assembly 52 and the second propulsion assembly 54 can be mounted on the aircraft 10 using a common mounting bracket. However, with these configurations, the first propulsion assembly 52 and the second propulsion assembly 54 can still be positioned on the mounting bracket such that they are spaced apart from each other, for example, in the lateral direction L, such that they draw in different airflows in the lateral direction L.

[0073] Still referencing Figure 1 and Figure 3 In an exemplary embodiment, the second thruster assembly 54 is mounted to the second side 26 of the aircraft 10, or to the second wing 22 of the aircraft 10. See particularly... Figure 3 The second thruster assembly 54 is generally configured as an electric thruster assembly, which includes an electric motor and a thruster. More specifically, for the illustrated embodiment, the electric thruster assembly includes a fan 200, which includes an electric motor 206 and a thruster / fan 204. The fan 200 defines an axial direction A2 and a radial direction R2 extending along a longitudinal centerline axis 202 (through which for reference). For the illustrated embodiment, the fan 204 is rotatable about the centerline axis 202 by the electric motor 206.

[0074] Fan 204 includes a plurality of fan blades 208 and a fan shaft 210. The plurality of fan blades 208 are attached to / rotatable with the fan shaft 210 and are generally spaced apart along the circumferential direction (not shown) of the fan 200. In some exemplary embodiments, the plurality of fan blades 208 may be fixedly attached to the fan shaft 210, or alternatively, the plurality of fan blades 208 may be rotatable relative to the fan shaft 210 (e.g., in the illustrated embodiment). For example, each of the plurality of fan blades 208 defines a corresponding pitch axis P2, and in the illustrated embodiment, the plurality of fan blades are attached to the fan shaft 210 such that the pitch of each of the plurality of fan blades 208 can be changed, for example, simultaneously by a pitch mechanism 211. Changing the pitch of the plurality of fan blades 208 can improve the efficiency of the second thruster assembly 54 and / or allow the second thruster assembly 54 to achieve a desired thrust distribution. Through these exemplary embodiments, fan 204 may be referred to as a variable-pitch fan.

[0075] Furthermore, in the illustrated embodiment, the illustrated fan 200 also includes a fan housing or external nacelle 212, which is attached to the core 214 of the fan 200 via one or more supports or outlet guide vanes 216. In the illustrated embodiment, the external nacelle 212 substantially completely surrounds the fan 204, and specifically surrounds a plurality of fan blades 208. Furthermore, in the illustrated embodiment, the fan 200 may be referred to as a ducted electric fan.

[0076] Still refer to Figure 3 The fan shaft 210 is mechanically connected to the motor 206 within the core 214, such that the motor 206 drives the fan 204 via the fan shaft 210. The fan shaft 210 is supported by one or more bearings 218, such as one or more roller bearings, ball bearings, or any other suitable bearings. Alternatively, the motor 206 may be an internal rotor motor (i.e., including a rotor positioned radially inside the stator) or alternatively, an external rotor motor (i.e., including a stator positioned radially inside the rotor).

[0077] As briefly described above, the power source (i.e., generator 56 and first thruster assembly 52 in the illustrated embodiment) is electrically connected to the electric propulsion assembly (i.e., motor 206 and fan 204 of fan 200 in the illustrated embodiment) to provide electrical power to the electric propulsion assembly. More specifically, motor 206 of fan 200 is electrically connected to generator 56 via power bus 58, and more specifically via cable or wire 60 extending therethrough.

[0078] The propulsion system according to one or more embodiments of the above embodiments may be referred to as a gas-electric or hybrid propulsion system, assuming that the first thruster assembly is configured as a turbofan engine mounted on the first side of the aircraft and the second thruster assembly is configured as an electrically driven fan mounted on the second side of the aircraft.

[0079] However, it should be understood that in other exemplary embodiments, the exemplary propulsion system may have any other suitable configuration and may also be integrated into the aircraft 10 in any other suitable manner. For example, in other exemplary embodiments, the propulsion system may include a plurality of fans. One or more of these fans may be mounted, for example, to the wing of a stabilizer at the rear of the aircraft or to the fuselage. Other embodiments are also contemplated.

[0080] For reference Figure 4 and Figure 5 A motor 300 according to an exemplary embodiment of the present invention is provided. Specifically, Figure 4 A schematic cross-sectional view of an exemplary motor 300 is provided. Figure 5An axial schematic cross-sectional view of the motor 300 is provided. In some exemplary embodiments, the described motor 300 may be configured as a generator, for example, as shown above with reference to... Figure 2 The generator 56 is described. In this exemplary embodiment, the motor 300 can therefore be configured to be powered by an aircraft combustion engine (e.g., Figure 2 The exemplary turbofan engine 100 is used for driving. However, it should be recognized that, alternatively, in other exemplary embodiments, the motor 300 may be configured as an electric motor, for example, as shown above with reference to... Figure 3 The exemplary electric motor 206 is described. Therefore, in these exemplary embodiments, the motor 300 may be configured as part of the electric thruster assembly 358, and may also be configured to drive the thrusters of the electric thruster assembly 358, as shown above. Figure 3 The exemplary fan 204 is described.

[0081] As depicted, the motor 300 generally defines a longitudinal centerline axis 302, a radial direction R3 relative to the longitudinal centerline axis 302, and a circumferential direction C3, which extends around the longitudinal centerline axis 302 (see, for example, [reference needed]). Figure 5 Furthermore, the motor 300 includes a rotor 304 and a stator 306. The rotor 304 extends along a longitudinal centerline axis 302 and is rotatable about the longitudinal centerline axis 302, i.e., in the circumferential direction C3. For the depicted embodiment, the rotor 304 is positioned within the stator 306 in the radial direction R3, such that the motor 300 can generally be referred to as an "in-runner" motor 300. However, it should be recognized that in other exemplary embodiments, the stator 306 may instead be positioned within the rotor 304 in the radial direction R, such that the motor 300 can be referred to as an "outer-runner" motor 300.

[0082] The rotor 304 and stator 306 of the motor 300 are enclosed within a housing 308. Furthermore, in the depicted embodiment, the rotor 304 is rotatably mounted within the housing 308 using a plurality of bearing assemblies 310. The plurality of bearing assemblies 310 may include, for example, rolling bearings, ball bearings, or any other suitable type of bearing. As also shown, in the described embodiment, the rotor 304 is integrally formed with a drive shaft 312 extending outward from the housing 308 of the motor 300. When used as an electric motor, the drive shaft 312 may be coupled to, for example, a propeller, or when used as a generator, to an aircraft combustion engine.

[0083] It should be understood that, in the described embodiments, rotor 304 is configured as a permanent magnet rotor including a plurality of permanent magnets 314. More specifically, rotor 304 is configured as a surface permanent magnet rotor, with the plurality of permanent magnets 314 positioned on the radially outer surface 316 of rotor 304. However, it should be understood that, in other exemplary embodiments, rotor 304 may instead include internal permanent magnets 314 (i.e., permanent magnets recessed from the radially outer surface 316 of rotor 304). Furthermore or alternatively, in other embodiments, rotor 304 may use electromagnets.

[0084] As also depicted, the stator 306 of the motor 300 further includes a plurality of winding assemblies 318. The plurality of winding assemblies 318 are spaced apart along the longitudinal centerline axis 302 of the motor 300, and each winding assembly 318 is capable of operating independently of adjacent winding assemblies 318 with the rotor 304 during operation of the motor 300. For example, in some embodiments, the stator 306 may include two to, for example, approximately thirty winding assemblies 318. For example, in some exemplary embodiments, the stator 306 may include at least three winding assemblies 318. More specifically, for the depicted embodiment, the stator 306 includes a first winding assembly 318A, a second winding assembly 318B, and a third winding assembly 318C spaced apart along the longitudinal centerline axis 302 of the motor 300.

[0085] See details Figure 5 Provided along Figure 4 A cross-sectional view of the exemplary motor 300 shown in line 5-5 illustrates the first winding assembly 318A in more detail. As depicted, the first winding assembly 318A of the stator 306 includes a plurality of teeth 320 to which windings 322 are attached. Each winding 322 may be formed by a length of wire freely wound around a corresponding tooth 320. Thus, it should be understood that the first winding assembly 318A includes a set of windings 322 dedicated to the first winding assembly 318A. As used herein, reference to winding 332 is used when "dedicated" means that the windings 322 of one winding assembly 318 are not directly electrically connected to the windings 322 of another separate winding assembly 318. Furthermore, when used as a generator, it should be understood that the mechanical rotation of the plurality of permanent magnets 314 of the rotor 304 generates the movement of charge present in the wires of its windings 322, constituting an electrical power output. In contrast, when used as an electric motor, it should be recognized that the movement of the permanent magnet 314 of the rotor 304 is generated by the charge of the winding 322, which in turn generates the movement of the rotor 304.

[0086] In addition, please refer to the specific details now. Figure 4It should be recognized that, in the described embodiments, the rotor 304 extends continuously between the first winding assembly 318A, the second winding assembly 318B, and the third winding assembly 318C. For example, the described exemplary rotor 304 includes a core 324 (the core 324 defines an outer surface 316; shown as a dashed line below the permanent magnet 314), which extends continuously between the plurality of winding assemblies 318. Furthermore, for Figure 4 The exemplary rotor 304 described in the embodiments further includes a plurality of permanent magnets 314 extending continuously between a plurality of winding assemblies 318. However, it is worth noting that in other embodiments, the rotor 304 may instead include separate permanent magnets 314 for each corresponding winding assembly 318 of the stator 306.

[0087] However, it should be understood that in other exemplary embodiments, the propulsion system 300 may have any other suitable configuration. For example, in other exemplary embodiments, the propulsion system 300 may be configured to generate direct current (DC) power or alternating current (AC) power (e.g., two-phase power or three-phase power). Alternatively or alternatively, the propulsion system 300 may be configured as a synchronous motor or an asynchronous motor, and may also be a permanent magnet motor (as illustrated) or an electromagnetic motor.

[0088] Now refer to Figure 6 A schematic diagram of a propulsion system 300 according to an exemplary embodiment of the present invention is provided. Figure 6 An exemplary propulsion system 350 is schematically depicted, which may be substantially similar to the one referenced above. Figures 1 to 3 The exemplary propulsion system 50 described is configured in the same manner. For example, the exemplary propulsion system 350 generally includes a power source 352, which includes a combustion engine 354 (e.g., a gas turbine engine, such as a turbofan engine, turboshaft engine, turboprop engine, etc.) and a generator 356 driven by the combustion engine 354. The exemplary propulsion system 350 further includes an electric thruster assembly 358, which includes an electric motor 360 and a fan 362 driven by the electric motor 360. The electric motor 360 of the electric thruster assembly 358 is electrically connected to the generator 356 of the power source 352. More specifically, the exemplary propulsion system 350 includes a power bus 364 that electrically connects the generator 356 of the power source 352 to the electric motor 360 of the electric thruster assembly 358.

[0089] also, Figure 6 The propulsion system 350 includes a motor 300, configured according to embodiments of the present disclosure. More specifically, the motor 300 is configured as a motor 360 of an electric thruster assembly 358. (Referring to the above...) Figure 4 and Figure 5The exemplary motor 300 and exemplary electric motor 360 described include a rotor 304 rotatable about a longitudinal centerline axis 302 and a stator 306 having a plurality of winding assemblies 318. More specifically, for Figure 6 In one embodiment, the stator 306 of the motor 360 includes a first winding assembly 318A, a second winding assembly 318B, and a third winding assembly 318C.

[0090] In addition, for Figure 6 In one embodiment, each of the plurality of winding assemblies 318 of the stator 306 of the motor 360 is separately electrically connected to the power bus 364. For the depicted embodiment, each winding assembly 318 of the stator 306 of the motor 360 is separately connected in parallel to the power bus 364 using appropriate wiring. More specifically, a first winding assembly 318A is electrically connected to the power bus 364 via a first set of leads 366A, a second winding assembly 318B is electrically connected to the power bus via a second set of leads 366B, and a third winding assembly 318C is electrically connected to the power bus via a third set of leads 366C. Therefore, in the event of a failure in one of the plurality of winding assemblies 318 (e.g., a short circuit in one of the windings 322), the remaining winding assemblies 318 can continue to operate to provide at least a portion of the desired power to the fan 362 of the electric thruster assembly 358.

[0091] In this configuration, the motor 300 can generally operate as multiple separate motors 300 using a common housing 308, rotor 304, etc. Therefore, this configuration provides an additional layer of redundancy without increasing the weight and / or cost of including multiple separate motors 300.

[0092] However, it should be understood that in other exemplary embodiments, the propulsion system 350 may have any other suitable configuration. For example, in other exemplary embodiments, the generator 356 may additionally or alternatively be configured according to exemplary embodiments of this disclosure to include a stator 306 having a plurality of winding assemblies 318. Moreover, the propulsion system 350 may have any suitable configuration, as may the power bus 364.

[0093] Furthermore, in other embodiments, the power bus 364 can be electrically connected to one or more motors 300 in any other suitable manner. For example, now refer to Figure 7 The image depicts a propulsion system 350 according to another exemplary embodiment of the present invention. Figure 7 The exemplary propulsion system 350 is generally similar to the one described above. Figure 6 The propulsion system 350 described is configured in the same way.

[0094] For example, Figure 7An exemplary propulsion system 350 generally includes a power source 352, an electric propulsion system 350, and a power bus 364. The power source 352 has a combustion engine 354 and a generator 356, the electric propulsion system 350 has an electric motor 360 and a fan 362, and the power bus 364 electrically connects the generator 356 of the power source 352 to the electric motor 360 of the electric thruster assembly 358. Additionally, for Figure 7 In an embodiment of the present disclosure, an electric motor 360 is configured. More specifically, the electric motor 360 includes a rotor 304 and a stator 306, the stator 306 including a plurality of winding assemblies 318 (i.e., first, second, and third winding assemblies 318A, 318B, and 318C in the described embodiment). Moreover, in the described embodiment, the plurality of winding assemblies 318A, 318B, and 318C are electrically connected separately to a power bus 364 via corresponding leads 366A, 366B, and 366C.

[0095] However, in the described embodiment, one or more of the plurality of winding assemblies 318A, 318B, 318C are selectively electrically connected to the power bus 364. More specifically, for Figure 7 In some embodiments, each of the plurality of winding assemblies 318A, 318B, 318C is selectively electrically connected to the power bus 364. For example, in the described embodiment, a plurality of switches 368 are equipped with leads 366 to selectively electrically connect specific winding assemblies 318A, 318B, 318C of the stator 306 of the motor 360 to the power bus 364. For example, a first pair of switches 368A is equipped with leads 366A to electrically connect the first winding assembly 318A of the stator 306 to the power bus 364, a second pair of switches 368B is equipped with leads 366B to electrically connect the second winding assembly 318B of the stator 306 to the power bus 364, and a third pair of switches 368C is equipped with leads 366C to electrically connect the third winding assembly 318C of the stator 306 to the power bus 364. Each of these switches 368A, 368B, and 368C is movable between an on and off position, in which current can flow through the switch and in which current cannot flow through the switch. For the described embodiment, the first pair of switches 368A and the second pair of switches 368B are shown as being in the off position, while the third pair of switches 368C is shown as being in the on position. Therefore, in Figure 7 In one embodiment, the first and second winding assemblies 318A and 318B may not receive electrical power from the power bus 364, while the third winding assembly 318C may receive electrical power from the power bus 364.

[0096] It should be recognized that this configuration allows for selective operation of one or more winding assemblies 318 of the motor 300, for example, during a fault in one of the winding assemblies 318, or in an operating mode where the electrical power used is less than the electrical power generated or required by the motor 300. Therefore, in the latter case, the temperature of the motor 300 can be reduced in the operating mode requiring less electrical power.

[0097] Furthermore, it should be recognized that although exemplary motors have been discussed in the context of propulsion systems, and more specifically, aircraft propulsion systems, in other embodiments, the motor may be used for any other suitable purpose. For example, in other embodiments, the motor may be any other electric motor (or generator) suitable for vehicles (e.g., automobiles, aircraft, etc.). Moreover, in other embodiments, the motor may be used in other fields, such as industry or other sectors.

[0098] This specification uses examples to disclose the invention, including the best mode, and also enables those skilled in the art to practice the invention, including making and using any apparatus or system and performing any incorporated methods. The patentable scope of the invention is defined by the claims and may include other examples that may occur to those skilled in the art. Such other examples are deemed 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 are not substantially different from the literal language of the claims.

Claims

1. A propulsion system (10) for an aircraft, the propulsion system comprising: Combustion engine; The propellers are positioned spaced apart from the combustion engine, such that they each draw in different airflows; as well as An electric motor (300) configured to drive the thruster, the motor (300) defining an axis (302) and including: A rotor (304) extending along and rotatable about the axis (302); and The stator (306) includes a plurality of winding assemblies (318) spaced apart along the axis (302) of the motor (300), and each winding assembly (318) is capable of working with the rotor (304) independently of the adjacent winding assembly (318) during operation of the motor (300). The plurality of winding assemblies (318) include a first winding assembly (318A) and a second winding assembly (318B) spaced apart along the axis (302) of the motor (300); The rotor (304) includes a plurality of permanent magnets (314), and the plurality of permanent magnets (314) extend continuously along the axis (302) between the first winding assembly (318A) and the second winding assembly (318B). The propulsion system further includes a power bus, wherein each of the plurality of winding assemblies (318) is separately electrically connected to the power bus (304); and One or more of the plurality of winding assemblies (318) are selectively electrically connected to the power bus (304).

2. The propulsion system according to any of the preceding claims, wherein, The stator (306) includes at least three winding assemblies (318) and up to thirty winding assemblies (318).

3. The propulsion system according to any of the preceding claims, wherein, The rotor (304) is positioned within the stator (306).

4. The propulsion system according to any of the preceding claims, wherein, Each winding assembly (318) includes a set of windings (322) dedicated to the winding assembly (318).

5. The propulsion system according to any of the preceding claims, wherein, The motor (300) is an electric motor configured to drive the propulsion system, wherein the propulsion system further includes a generator configured to be driven by the combustion engine, and wherein the generator is electrically connected to the electric motor.

6. The propulsion system according to any of the preceding claims, wherein, The plurality of winding assemblies (318) are separately connected in parallel with the power bus (364).

7. The propulsion system according to any of the preceding claims, wherein, The motor (300) includes a housing (308), wherein the rotor (304) and the stator (306) are both positioned within the housing (308).

Images