A stator winding structure for an aircraft generator and a motor assembly

Abstract

This application discloses a stator winding structure and motor assembly for an aircraft generator. The generator stator winding structure includes a stator and multiple sets of windings. The stator has multiple stator teeth arranged circumferentially, with stator slots formed between adjacent teeth. Each set of windings is disposed on the stator, and each set of windings includes an A-phase winding coil, a B-phase winding coil, and a C-phase winding coil. The phases of the A-phase winding coils, B-phase winding coils, and C-phase winding coils in each set of windings are equal. The phase difference between adjacent A-phase, B-phase, and C-phase winding coils is 120°. The generator stator winding of this application adopts a multi-set three-phase winding design, with each set of windings operating independently, providing a multi-margin design and improving system safety. The multi-set three-phase winding design adopted in this application can reduce the load current of power devices connected to a single set of three-phase windings, thus reducing the system's requirements for power devices.

Description

Technical Field

[0001] This utility model relates to the field of motor design technology, and in particular to a stator winding structure and motor assembly for an aircraft generator. Background Technology

[0002] Traditional motor stator windings can be divided into concentrated windings and distributed windings. Distributed windings, as a stator winding mode that can effectively reduce harmonics and their corresponding losses, and improve motor efficiency, are of great significance in the field of high-speed motors.

[0003] Traditional distributed winding motors have three-phase input lines with a 120° electrical angle difference. In case of a fault, such as an open circuit in any of the three phases, the motor will not operate normally due to the missing phase. To avoid this, traditional distributed winding motor solutions typically increase the insulation level and withstand voltage of the winding insulation layers to minimize the probability of a phase failure and reduce the likelihood of motor malfunction. However, existing solutions cannot address pre-existing faults in three-phase motors, such as open circuits, and the motor will remain inoperable.

[0004] In view of the above, this utility model is hereby proposed. Utility Model Content

[0005] To solve one of the above-mentioned technical problems, this utility model provides a stator winding design for an aircraft generator and a motor assembly.

[0006] The present invention adopts the following technical solution:

[0007] The primary objective of this application is to provide a stator winding design for an aircraft generator, including:

[0008] The stator has multiple stator teeth arranged circumferentially, and stator slots are formed between adjacent stator teeth;

[0009] Multiple sets of windings are provided, each set of windings is provided on the stator, and each set of windings is arranged sequentially along the circumference of the stator. Each set of windings includes an A-phase winding coil, a B-phase winding coil, and a C-phase winding coil. Each phase winding coil is wound on the corresponding stator teeth. The phases of the A-phase winding coils, the B-phase winding coils, and the C-phase winding coils in each set of windings are equal. The phase difference between adjacent A-phase winding coils, B-phase winding coils, and C-phase winding coils is 120°.

[0010] Optionally, the multiple sets of windings are distributed windings, with each phase winding coil wound around at least two stator teeth.

[0011] Optionally, the multiple sets of windings are double-layer distributed windings, with each stator slot containing the coil sides of two-phase winding coils.

[0012] Optionally, the multiple sets of windings are short-pitch windings;

[0013] Each phase winding coil is first wound multiple turns between two spaced designated stator slots, and then wound multiple turns between two adjacent stator slots.

[0014] Optionally, the stator includes 24 stator slots, and the multiple sets of windings include four sets of windings. Each stator slot contains the coil side of two-phase winding coils, and each coil pitch is 5 stator slots, with a pole pitch of 6 stator slots.

[0015] Optionally, in two adjacent sets of windings, the coils of the same phase winding are spaced 6 stator slots apart, the electrical angle of each stator slot is 30°, the electrical phase difference between the two adjacent sets of windings caused by spatial displacement is 180°, and the energizing directions of the two adjacent sets of windings are opposite.

[0016] Optionally, the windings are electrically isolated from each other, so that if any one winding fails, the other windings can continue to operate normally.

[0017] A second objective of this application is to provide a motor assembly, comprising:

[0018] A drive controller, which is connected to multiple three-phase circuits;

[0019] In the aforementioned stator winding structure of the aircraft generator, the A-phase winding coil, B-phase winding coil, and C-phase winding coil in each set of windings are electrically connected to the three-phase lines of the corresponding three-phase circuit.

[0020] By adopting the above technical solution, this application has the following beneficial effects:

[0021] The generator stator winding of this application adopts a multi-set three-phase winding design, with each set of windings operating independently, providing a multi-margin design and improving system safety. The multi-set three-phase winding design used in this application can reduce the load current of power devices connected to a single set of three-phase windings, thus reducing the system's requirements for power devices.

[0022] The specific embodiments of this utility model will be described in further detail below with reference to the accompanying drawings. Attached Figure Description

[0023] The accompanying drawings, which form part of this application, are used to provide a further understanding of the present invention. The illustrative embodiments and descriptions of the present invention are used to explain the present invention, but do not constitute an undue limitation of the present invention. Obviously, the drawings described below are merely some embodiments; those skilled in the art can obtain other drawings based on these drawings without creative effort. In the drawings:

[0024] Figure 1 A schematic diagram of the stator winding structure of an aircraft generator provided in an embodiment of this disclosure is shown.

[0025] Figure 2 This diagram shows the coil arrangement of the A-phase winding in the four sets of windings in the stator winding structure of the aircraft generator provided in this embodiment of the present disclosure.

[0026] Figure 3 This diagram shows the coil arrangement of the B-phase winding in the four sets of windings in the stator winding structure of the aircraft generator provided in this embodiment of the present disclosure.

[0027] Figure 4 This diagram shows the arrangement of the C-phase winding coils in the four sets of windings in the stator winding structure of an aircraft generator provided in this embodiment of the present disclosure.

[0028] Figure 5 This diagram illustrates a detailed breakdown of the winding lines in the stator winding structure of an aircraft generator provided in an embodiment of this disclosure.

[0029] Figure 6 This diagram illustrates the structure of the motor assembly provided in an embodiment of the present disclosure.

[0030] Figure 7 This diagram shows the structure of four sets of three-phase, double-layer short-pitch distributed windings provided in the embodiments of this disclosure;

[0031] Figure 8 The diagram shows the structure of four sets of three-phase, centralized windings in the relevant technology;

[0032] Figure 9 Show respectively Figure 7 and Figure 8 The simulation data comparison table for the windings shown is provided.

[0033] In the diagram: 1. Stator; 11. Stator tooth; 12. Stator slot; 2. Winding.

[0034] It should be noted that these accompanying drawings and textual descriptions are not intended to limit the scope of the present invention in any way, but rather to illustrate the concept of the present invention to those skilled in the art by referring to specific embodiments. Detailed Implementation

[0035] To make the objectives, technical solutions, and advantages of the embodiments of this utility model clearer, the technical solutions in the embodiments will be clearly and completely described below with reference to the accompanying drawings. The following embodiments are used to illustrate this utility model, but are not intended to limit the scope of this utility model.

[0036] In the description of this utility model, it should be noted that the terms "upper", "lower", "inner", "outer", etc., indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings. They are only for the convenience of describing this utility model and simplifying the description, and do not indicate or imply that the device or component referred to must have a specific orientation, or be constructed and operated in a specific orientation. Therefore, they should not be construed as limitations on this utility model.

[0037] In the description of this utility model, it should be noted that, unless otherwise explicitly specified and limited, the terms "installation" and "connection" should be interpreted broadly. For example, they can refer to a fixed connection, a detachable connection, or an integral connection; they can refer to a mechanical connection or an electrical connection; they can refer to a direct connection or an indirect connection through an intermediate medium. Those skilled in the art can understand the specific meaning of the above terms in this utility model based on the specific circumstances.

[0038] like Figures 1 to 9 As shown in the figure, this application embodiment provides an aircraft generator stator winding structure, including: a stator 1 and multiple sets of windings 2. The stator 1 is provided with multiple stator teeth 11 along the circumferential direction, and stator slots 12 are formed between adjacent stator teeth 11. Each set of windings 2 is disposed on the stator 1, and each set of windings 2 is arranged sequentially along the circumference of the stator 1. Each set of windings 2 includes an A-phase winding coil (e.g., A1, A2, A3, A4), a B-phase winding coil (e.g., B1, B2, B3, B4), and a C-phase winding coil (e.g., C1, C2, C3, C4). Each phase winding coil is wound on the corresponding stator tooth 11. The phases of the A-phase winding coils in each set of windings 2 are equal, the phases of the B-phase winding coils in each set of windings are equal, and the phases of the C-phase winding coils in each set of windings are equal. The phase difference between adjacent A-phase winding coils, B-phase winding coils, and C-phase winding coils is 120°.

[0039] The generator stator winding of this application adopts a multi-set three-phase winding design, with each set of windings operating independently, providing a multi-margin design and improving system safety. The circuits of each set of windings are isolated; when any set of windings is open-circuited, the other sets remain conductive. The multi-set three-phase winding design used in this application can reduce the load current of power devices connected to a single set of three-phase windings, thus reducing the system's requirements for power devices.

[0040] In some possible implementations, the multiple windings are distributed windings, with each phase winding coil wound around at least two stator teeth 11. The distributed winding structure of the stator 1 in this application can effectively reduce harmonics, improve system power generation efficiency, and thus increase system power density.

[0041] In some possible implementations, multiple sets of windings are double-layer distributed windings, with each stator slot 12 accommodating the coil sides of two-phase winding coils. The double-layer distributed winding design adopted by the motor stator 1 winding of this application can reduce harmonics, significantly improve the efficiency of high-power motors, and thus increase power density.

[0042] In some possible implementations, multiple sets of windings are short-pitch windings, and each phase winding coil is first wound once between two spaced designated stator slots 12, and then wound once between the two adjacent stator slots 12 of the two designated stator slots 12.

[0043] The stator winding structure of the aircraft generator in this application adopts a short-pitch winding design, which can reduce the length of the winding ends, reduce the system volume, and thus improve the power density.

[0044] This application uses multiple sets of three-phase windings, each set of windings is independent of each other, and each set of windings adopts a double-layer short-pitch distributed design.

[0045] In some possible implementations, such as Figures 1 to 5 As shown, the stator 1 includes 24 stator slots 12, and the multiple sets of windings include four sets of windings. Each stator slot 12 contains the coil side of a two-phase winding coil. The pitch of each coil is 5 stator slots 12, and the pole pitch is 6 stator slots 12.

[0046] like Figures 1 to 5 as well as Figure 7 The diagram illustrates a stator winding design for a 2-pole pair aircraft generator according to an embodiment of this application. The stator slot 12 has 24 slots, and the winding is a double-layer short-pitch distributed winding. There are 12 winding coils in total. Winding coils A1, A2, A3, and A4 have equal phase, designated as phase A. Winding coils B1, B2, B3, and B4 have equal phase, designated as phase B. Winding coils C1, C2, C3, and C4 have equal phase, designated as phase C. Phases A, B, and C differ by 120° electrical degrees.

[0047] Figure 4 A detailed diagram of the motor winding structure is shown. Figures 1 to 5The diagram shows the specific locations of the 12 winding coils: A1, A2, A3, A4, B1, B2, B3, B4, C1, C2, C3, and C4. Taking A4 as an example, the copper wire enters from the bottom of slot 1, winds between slot 6 with the designed number of turns, exits from the bottom of slot 6, then continues into the bottom of slot 2, winds between slot 2 and slot 7 with the designed number of turns, and finally exits from the bottom of slot 7, forming the complete A4 winding coil. The remaining 11 winding coils follow the same principle.

[0048] Each stator slot 12 of stator 1 accommodates the coil sides of two sets of winding coils. The pitch of each coil is five stator slots 12, and the pole pitch of the winding coils is six stator slots 12, forming a distributed double-layer 5 / 6 short-pitch winding. The distributed winding can effectively reduce harmonics, improve system power generation efficiency, and thus increase system power density, while the short-pitch winding can reduce the length of the winding ends, thereby reducing system volume and increasing system power density.

[0049] Optionally, in two adjacent winding sets, the coils of the same phase winding are spaced 6 stator slots 12 apart, each stator slot 12 has an electrical angle of 30°, the electrical phase difference between two adjacent winding sets caused by spatial displacement is 180°, and the energizing directions of two adjacent winding sets are opposite. For example... Figure 5 As shown, adjacent windings are separated by 6 stator slots 12 for the same phase. For example, winding B1 enters from slot 21 and exits from slot 15 12, while winding B2 enters from slot 9 12 and exits from slot 15 12. The two windings are separated by 6 stator slots 12. This motor is a 2-pole 24-slot motor, so the electrical angle of each slot is 30°. Therefore, the electrical phase difference between adjacent windings caused by spatial displacement is 180°. In this winding, the energizing directions of adjacent windings are opposite. For example... Figure 2 As shown, A1 is energized in the opposite direction to A2 and A4, but in the same direction as A3. Therefore, the phase difference between adjacent windings caused by the energizing direction is 180°. Consequently, the phase differences between adjacent windings cancel each other out, and all four three-phase windings are in the same phase. This design simplifies the motor controller design. Since there is no phase difference between the four windings, they can share a single control signal, reducing the number of drive circuits, saving costs, and reducing the size of the controller.

[0050] In some possible implementations, the circuits of each winding are isolated, and when any one winding is disconnected, the other windings remain conductive.

[0051] In other words, the windings are electrically isolated from each other, so that if any one winding fails, the other windings can continue to operate normally.

[0052] This application also provides a motor assembly, including: a drive controller and the above-mentioned aircraft generator stator winding design. The drive controller is connected to multiple three-phase circuits. The A-phase winding coil, B-phase winding coil and C-phase winding coil in each set of windings in the aircraft generator stator winding structure are electrically connected to the three-phase lines of the corresponding three-phase circuits.

[0053] In the generator stator winding structure, among the 12 winding coils, A1, B1, and C1 belong to the same unit, designated as Unit 1 (the first winding). A2, B2, and C2 belong to the same unit, designated as Unit 2 (the second winding); A3, B3, and C3 belong to the same unit, designated as Unit 3 (the third winding); and A4, B4, and C4 belong to the same unit, designated as Unit 4 (the fourth winding). There are a total of four units, each independent of the others.

[0054] Figure 6 This is a multi-unit winding topology diagram of a motor assembly. When some of the four units experience a circuit fault, such as any one unit (e.g., unit 1) failing (any open circuit in A1, B1, or C1), unit 1 stops working. Units 2, 3, and 4 continue to operate normally. The single-phase voltage output by the motor remains the same as before; the single-phase current output is 75% of its original value; and the total output power is 75% of its original capacity. Similarly, if two units fail, the total output power is 50% of its original capacity. If three units fail, the total output power is 25% of its original capacity. The motor has no output capacity when all four units fail simultaneously.

[0055] This application allows the windings of a double-layer short-pitch distributed winding motor to be divided into four equal units, totaling twelve wires and twelve paths. This solution can improve system safety, efficiency, and power density, while reducing the system's requirements for power devices.

[0056] To demonstrate the superiority of the aircraft generator stator winding structure provided in this application, embodiments of this application provide two aircraft motor models with a rated generating power of 620kW, employing four sets of three-phase, double-layer short-pitch distributed designs and four sets of three-phase, centralized designs, respectively, with other motor parameters remaining consistent. The double-layer short-pitch distributed design is as follows: Figure 7 As shown, the centralized design is as follows Figure 8 As shown. The simulation conditions are set to a rated power of 620kW and a typical speed of 18,000rpm for the aircraft cruise generator. Figure 9The table shows a comparison of simulation test parameters for the two types of windings. The data in the table shows that, under rated operating conditions, the copper loss and iron loss of the double-layer short-pitch distributed winding are significantly lower than those of the centralized winding, and the overall power generation efficiency is 2.31% higher than that of the centralized winding, which demonstrates the superiority of the structural design of this application.

[0057] In this application, the stator winding structure of the aircraft generator employs a winding method consisting of multiple sets of three-phase, double-layer short-pitch distributed windings. The multiple sets of three-phase design, each independent of the others, improve system reliability and safety, reduce the system's power device requirements, and the double-layer short-pitch distributed design improves system efficiency, reduces size, and thus increases system power density.

[0058] The above description is merely a preferred embodiment of the present utility model and is not intended to limit the present utility model in any way. Although the present utility model has been disclosed above with reference to a preferred embodiment, it is not intended to limit the present utility model. Any person skilled in the art can make some modifications or alterations to the above-described technical content to create equivalent embodiments without departing from the scope of the present utility model. Any simple modifications, equivalent changes, and alterations made to the above embodiments based on the technical essence of the present utility model without departing from the scope of the present utility model shall still fall within the scope of the present utility model.

Claims

1. An aircraft generator stator winding structure, characterized by, include: The stator has multiple stator teeth arranged circumferentially, and stator slots are formed between adjacent stator teeth; Multiple sets of windings are provided, each set of windings is provided on the stator, and each set of windings is arranged sequentially along the circumference of the stator. Each set of windings includes an A-phase winding coil, a B-phase winding coil, and a C-phase winding coil. Each phase winding coil is wound on the corresponding stator teeth. The phases of the A-phase winding coils, the B-phase winding coils, and the C-phase winding coils in each set of windings are equal. The phase difference between adjacent A-phase winding coils, B-phase winding coils, and C-phase winding coils is 120°.

2. An aircraft generator stator winding structure according to claim 1, characterised in that, The multiple sets of windings are distributed windings, with each phase winding coil wound around at least two stator teeth.

3. An aircraft generator stator winding structure according to claim 2, characterised in that, The multiple sets of windings are double-layer distributed windings, with each stator slot containing the coil sides of two-phase winding coils.

4. An aircraft generator stator winding arrangement according to claim 3, characterised in that, The multiple sets of windings are short-pitch windings; Each phase winding coil is first wound once between two spaced designated stator slots, and then wound once between two adjacent stator slots.

5. An aircraft generator stator winding arrangement according to claim 4, characterised in that, The stator includes 24 stator slots, and the multiple sets of windings include four sets of windings. Each stator slot contains the coil side of two-phase winding coils. Each coil pitch is 5 stator slots, and the pole pitch is 6 stator slots.

6. An aircraft generator stator winding arrangement according to claim 5, characterised in that, In two adjacent sets of windings, the coils of the same phase winding are spaced 6 stator slots apart, the electrical angle of each stator slot is 30°, the electrical phase difference between the two adjacent sets of windings caused by spatial displacement is 180°, and the energizing directions of the two adjacent sets of windings are opposite.

7. The stator winding structure of an aircraft generator according to any one of claims 1-6, characterized in that, The windings are electrically isolated from each other, so that if any one winding fails, the other windings can continue to operate normally.

8. A motor assembly, characterized in that, include: A drive controller, which is connected to multiple three-phase circuits; According to any one of claims 1-7, in the stator winding structure of the aircraft generator, the A-phase winding coil, the B-phase winding coil and the C-phase winding coil in each set of windings of the aircraft generator stator winding structure are respectively electrically connected to the three-phase lines of the corresponding three-phase circuit.

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