Aircraft generator stator winding structure and motor assembly

Abstract

The invention discloses an aircraft generator stator winding structure and a motor assembly. The generator stator winding structure comprises a stator and a plurality of sets of windings. The stator is provided with a plurality of stator teeth along the circumferential direction, a stator slot is formed between every two adjacent stator teeth, each set of winding is arranged on the stator, each set of winding comprises an A-phase winding coil, a B-phase winding coil and a C-phase winding coil, the phases of the A-phase winding coils of the sets of windings are equal, the phases of the B-phase winding coils of the sets of windings are equal, and the phases of the C-phase winding coils of the sets of windings are equal. In the A-phase winding coil, the B-phase winding coil and the C-phase winding coil, the phase difference between every two adjacent coils is 120 degrees. According to the generator stator winding, the design of multiple sets of three-phase windings is adopted, each set of winding works independently, the multi-margin design is adopted, and the system safety is improved. The design of multiple sets of three-phase windings is adopted, the load current of the power device connected with a single set of three-phase windings can be reduced, and the requirement of the system for the power device is reduced.

Description

Technical Field

[0001] The present invention relates to the technical field of motor design, and in particular to an aircraft generator stator winding structure and a motor assembly. Background Art

[0002] Traditional motor stator windings can be categorized as centralized or distributed. Distributed winding is a stator winding method that effectively reduces harmonics and their associated losses, thereby improving motor efficiency and is of great significance in the field of high-speed motors.

[0003] Traditional distributed winding motors have three three-phase wires with an electrical angle of 120° offset from each other at their input. In the event of a fault, such as a short circuit in one of the three phases, the motor will not operate normally due to the missing phase. To prevent this, traditional distributed winding motor solutions typically increase the insulation level and withstand voltage rating of the winding insulation layer to minimize the probability of phase failure, thereby reducing the possibility of motor failure. However, existing solutions cannot address existing faults in three-phase motors, such as short circuits, and the motor will not operate, rendering it inoperative.

[0004] In view of this, the present invention is proposed. Summary of the Invention

[0005] To solve one of the above technical problems, the present invention provides an aircraft generator stator winding design and a motor assembly.

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

[0007] The first object of the present application is to provide an aircraft generator stator winding design, comprising:

[0008] A stator, wherein the stator is provided with a plurality of stator teeth along a circumferential direction, and stator slots are formed between adjacent stator teeth;

[0009] Multiple sets of windings, each set of windings is arranged on the stator, and each set of windings is arranged in sequence 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 around a corresponding stator tooth. The phases of the A-phase winding coils in each set of windings 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°.

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

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

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

[0013] Each phase winding coil is first wound multiple times between two designated stator slots at intervals, and then wound multiple times between two adjacent stator slots of the two designated stator slots.

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

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

[0016] Optionally, each set of windings is electrically isolated from each other, so that when any one set of windings fails, the other sets of windings can maintain normal operation.

[0017] A second object of the present application is to provide a motor assembly, comprising:

[0018] A drive controller connected to a plurality of three-phase circuits;

[0019] In the above-mentioned aircraft generator stator winding structure, the A-phase winding coil, the B-phase winding coil and the C-phase winding coil in each set of windings in the aircraft generator stator winding structure are respectively 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 windings in this application utilize multiple sets of three-phase windings, each operating independently. This provides a multi-redundancy design and improves system safety. This multiple-set three-phase winding design reduces the load current of power devices connected to a single set of three-phase windings, lowering the system's requirements for these devices.

[0022] The specific embodiments of the present invention will be described in further detail below with reference to the accompanying drawings. BRIEF DESCRIPTION OF THE DRAWINGS

[0023] The accompanying drawings are part of this application and are used to provide a further understanding of the present invention. The exemplary embodiments of the present invention and their descriptions are used to explain the present invention, but do not constitute an undue limitation of the present invention. Obviously, the drawings described below are only some embodiments. For those of ordinary skill in the art, other drawings can be obtained based on these drawings without inventive effort. In the accompanying drawings:

[0024] Figure 1 A schematic diagram showing the stator winding structure of an aircraft generator provided by an embodiment of the present disclosure.

[0025] Figure 2 A diagram showing the arrangement of the A-phase winding coils in the four winding sets in the aircraft generator stator winding structure provided by an embodiment of the present disclosure is shown;

[0026] Figure 3 A diagram showing the arrangement of the B-phase winding coils in the four winding sets in the aircraft generator stator winding structure provided by an embodiment of the present disclosure is shown;

[0027] Figure 4 A diagram showing the arrangement of the C-phase winding coils in the four winding sets in the aircraft generator stator winding structure provided by an embodiment of the present disclosure is shown;

[0028] Figure 5 A detailed diagram of winding lines in a stator winding structure of an aircraft generator provided by an embodiment of the present disclosure is shown;

[0029] Figure 6 A schematic structural diagram of a motor assembly provided by an embodiment of the present disclosure is shown;

[0030] Figure 7 A schematic diagram showing the structure of four sets of three-phase, double-layer short-spacing distributed windings provided in an embodiment of the present disclosure is shown;

[0031] Figure 8 A schematic diagram showing the structure of four sets of three-phase, concentrated windings in the related art is shown;

[0032] Figure 9 Shown separately Figure 7 and Figure 8 The simulation data comparison table of the winding shown in .

[0033] In the figure: 1. stator; 11. stator teeth; 12. stator slots; 2. winding.

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

[0035] In order to make the purpose, technical solutions and advantages of the embodiments of the present invention clearer, the technical solutions in the embodiments will be clearly and completely described below in conjunction with the drawings in the embodiments of the present invention. The following embodiments are used to illustrate the present invention but are not used to limit the scope of the present invention.

[0036] In the description of the present invention, it should be noted that the terms "upper", "lower", "inside", "outside", etc. indicate orientations or positional relationships based on the orientations or positional relationships shown in the accompanying drawings. They are only for the convenience of describing the present invention and simplifying the description, and do not indicate or imply that the device or component referred to must have a specific orientation, be constructed and operated in a specific orientation. Therefore, they cannot be understood as limitations on the present invention.

[0037] In the description of the present invention, it should be noted that, unless otherwise specified or limited, the terms "mounted" and "connected" should be understood broadly. For example, they can refer to fixed, detachable, or integral connections; mechanical or electrical connections; and direct or indirect connections through an intermediary. Those skilled in the art will understand the specific meanings of the above terms in the present invention based on the specific circumstances.

[0038] like Figures 1 to 9 As shown, an embodiment of the present application provides an aircraft generator stator winding structure, comprising: a stator 1 and a plurality of windings 2. The stator 1 is provided with a plurality of stator teeth 11 along the circumferential direction, and stator slots 12 are formed between adjacent stator teeth 11. Each set of windings 2 is arranged on the stator 1, and each set of windings 2 is arranged in sequence along the circumference of the stator 1. Each set of windings 2 includes an A-phase winding coil (such as A1, A2, A3, A4), a B-phase winding coil (such as B1, B2, B3, B4) and a C-phase winding coil (such as C1, C2, C3, C4). The winding coils of each phase are respectively wound on the corresponding stator teeth 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 windings in this application utilize multiple three-phase windings, each operating independently. This provides a multi-redundancy design and enhances system safety. Each winding circuit is isolated, so if one winding circuit is disconnected, the others remain conductive. This multiple three-phase winding design reduces the load current of power devices connected to a single three-phase winding, lowering the system's requirements for these 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 stator 1 winding structure of the present application is a distributed winding, which can effectively reduce harmonics, improve system power generation efficiency, and thus increase system power density.

[0041] In some possible implementations, the multiple windings are double-layer distributed windings, with each stator slot 12 housing a coil side of a two-phase winding coil. The double-layer distributed winding design employed in the stator windings of the motor of the present application can reduce harmonics, significantly improve the efficiency of high-power motors, and thereby increase power density.

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

[0043] The aircraft generator stator winding structure of the present application adopts a short-pitch winding design, which can reduce the length of the winding end and the system volume, thereby improving 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-distance distributed design.

[0045] In some possible embodiments, such as Figures 1 to 5 As shown, the stator 1 includes 24 stator slots 12 , the multiple sets of windings include four sets of windings, each stator slot 12 accommodates the coil sides of a two-phase winding coil, each coil pitch 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 Figure 1 shows a stator winding design for a two-pole-pair aircraft generator according to an embodiment of the present application. The stator has 24 slots (12) and the winding is a double-layer, short-pitch distributed winding. The figure shows 12 winding coils, with winding coils A1, A2, A3, and A4 having equal phases, designated as Phase A. Winding coils B1, B2, B3, and B4 have equal phases, designated as Phase B. Winding coils C1, C2, C3, and C4 have equal phases, designated as Phase C. Phases A, B, and C are 120° apart in electrical angle.

[0047] Figure 4 A winding breakdown diagram showing the motor winding structure, Figures 1 to 5The figure 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 around slot 6 for the designed number of turns, exits from the bottom of slot 6, then continues into the bottom of slot 2, winds around slots 2 and 7 for the designed number of turns, and finally exits from the bottom of slot 7, completing the A4 winding coil. The same process is repeated for the remaining 11 winding coils.

[0048] Each stator slot 12 of the stator 1 accommodates the coil sides of two winding coils, each with a pitch of five stator slots 12 and a pole pitch of six stator slots 12, forming a distributed double-layer 5 / 6 short-pitch winding. Distributed winding effectively reduces harmonics, improves system power generation efficiency, and thus increases system power density. Short-pitch winding reduces the length of the winding ends, thereby reducing system volume and increasing system power density.

[0049] Optionally, in two adjacent windings, the coils of the same phase winding are separated by 6 stator slots 12, the electrical angle of each stator slot 12 is 30°, the electrical phase difference caused by the spatial displacement between the two adjacent windings is 180°, and the energization directions of the two adjacent windings are opposite. Figure 5 As shown, the same phase of two adjacent windings is separated by 6 stator slots 12. For example, the B1 winding enters from the 21st slot and exits from the 15th stator slot 12, and the B2 winding enters from the 9th stator slot 12 and exits from the 15th stator slot 12. The two windings are separated by 6 stator slots 12. The motor is a 2-pole 24-slot motor, and the electrical angle of each slot is 30°. Therefore, the electrical phase difference caused by the spatial displacement between the two adjacent windings is 180°. In this winding, the power supply directions of the two adjacent windings are opposite. Figure 2 As shown, A1 is energized in opposite directions from A2 and A4, but in the same direction as A3. Therefore, the electrical phase difference between adjacent windings due to the current flow direction is 180°. Consequently, the electrical phase difference between adjacent motor windings is canceled out, and all four three-phase windings are in phase. This design simplifies the motor controller. 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 implementation schemes, each set of winding circuits is isolated from each other, and when any one set of windings is disconnected, the other sets of windings remain in a conducting state.

[0051] In other words, each set of windings is electrically isolated from each other, and when any set of windings fails, the other sets of windings can maintain normal operation.

[0052] The present application also provides a motor assembly, comprising: a drive controller and the above-mentioned aircraft generator stator winding design, wherein the drive controller is connected to multiple three-phase circuits, and 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 respectively 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 form the same unit, designated as unit one (the first winding set). A2, B2, and C2 form the same unit, designated as unit two (the second winding set); A3, B3, and C3 form the same unit, designated as unit three (the third winding set). A4, B4, and C4 form the same unit, designated as unit four (the fourth winding set). There are four units in total, each of which is independent of the others.

[0054] Figure 6 This is a diagram of the multi-unit winding topology of a motor assembly. If a circuit fault occurs in any of the four units, such as Unit 1 (A1, B1, or C1 are open), Unit 1 ceases operation, while Units 2, 3, and 4 continue to operate normally. The motor's single-phase output voltage remains the same as the original voltage; the motor's single-phase output current is 75% of the original current; and the motor's total operating output power is 75% of the original total output power, meaning the motor can maintain normal operation at 75% of its original output capacity. Similarly, if two of the four units fail, the motor's total operating output power is 50% of the original total output power, meaning the motor can maintain normal operation at 50% of its original output capacity. If three of the four units fail, the motor's total operating output power is 25% of the original total output power, meaning the motor can maintain normal operation at 25% of its original output capacity. The motor's loss of output capacity occurs when all four units fail simultaneously.

[0055] This application can split the winding of a double-layer short-distance distributed winding motor into four equal units, with a total of twelve wires and twelve paths. This solution can improve system safety, efficiency and power density, and reduce the system's requirements for power devices.

[0056] To demonstrate the superiority of the aircraft generator stator winding structure provided by this application, the present embodiment provides two sets of aircraft motor models with a rated power of 620kW, which respectively adopt four sets of three-phase, double-layer short-distance distributed design and four sets of three-phase, centralized design, with other motor parameters remaining the same. Figure 7 As shown, the centralized design Figure 8 The simulation condition is set to 620kW rated power and the typical speed of the aircraft cruise generator is 18000rpm. Figure 9A comparison table of simulation experimental parameters of the two windings is shown in the figure. From the data in the table, it can be seen that under rated operating conditions, the copper loss and iron loss of the double-layer short-distance 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 can demonstrate the superiority of the structural design of the present application.

[0057] In this application, the aircraft generator stator winding structure features multiple sets of three-phase, double-layer, short-pitch distributed windings. This independent, multiple-set three-phase design improves system reliability and safety, while reducing power device requirements. The double-layer, short-pitch distributed design improves system efficiency, reduces size, and ultimately increases system power density.

[0058] The above description is merely a preferred embodiment of the present invention and does not constitute any form of limitation to the present invention. Although the present invention has been disclosed as above in terms of a preferred embodiment, it is not intended to limit the present invention. Any technician familiar with this patent can make slight changes or modifications to equivalent embodiments using the above-mentioned technical contents without departing from the scope of the technical solution of the present invention. However, any simple modifications, equivalent changes and modifications made to the above embodiments based on the technical essence of the present invention without departing from the content of the technical solution of the present invention are still within the scope of the solution of the present invention.

Claims

1. An aircraft generator stator winding structure, characterized in that: include: A stator, wherein the stator is provided with a plurality of stator teeth along a circumferential direction, and stator slots are formed between adjacent stator teeth; Multiple sets of windings, each set of windings is arranged on the stator, and each set of windings is arranged in sequence 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 around a corresponding stator tooth. The phases of the A-phase winding coils in each set of windings 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°.

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

3. The aircraft generator stator winding structure according to claim 2, characterized in that: The multiple sets of windings are double-layer distributed windings, and each stator slot contains coil sides of two-phase winding coils.

4. The aircraft generator stator winding structure according to claim 3, characterized in that: The multiple sets of windings are short-distance windings; Each phase winding coil is first wound one turn between two spaced designated stator slots, and then wound one turn between two adjacent stator slots of the two designated stator slots.

5. The aircraft generator stator winding structure according to claim 4, characterized in that: The stator includes 24 stator slots, the multiple sets of windings include four sets of windings, each stator slot accommodates a coil side of a two-phase winding coil, each coil pitch is 5 stator slots, and the pole pitch is 6 stator slots.

6. The aircraft generator stator winding structure according to claim 5, characterized in that: In two adjacent sets of windings, the coils of the same phase winding are separated by 6 stator slots, the electrical angle of each stator slot is 30°, the electrical phase difference caused by spatial displacement between the two adjacent sets of windings is 180°, and the power supply directions of the two adjacent sets of windings are opposite.

7. The aircraft generator stator winding structure according to any one of claims 1 to 6, characterized in that: Each set of windings is electrically isolated from each other. When any set of windings fails, the other sets of windings can maintain normal operation.

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

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