A brushless three-level excitation generator rectification system and generator

Abstract

The present invention discloses a rectifier system for an aviation brushless three-level excitation generator, comprising a plurality of mounting platforms, a plurality of rectifiers, a positive electrode bus ring, a negative electrode bus ring, a wire, a terminal block and a wind hood, wherein the plurality of mounting platforms are arranged in a ring shape and are arranged on the outer shell of the generator, a plurality of rectifiers are mounted on the mounting platforms and are supported overhead by the mounting platforms, a positive electrode bus ring is connected to the positive electrodes of the plurality of rectifiers, a plurality of negative electrode bus rings are connected to the negative electrodes of the plurality of rectifiers, a terminal block is arranged on the generator, a terminal block is provided on the terminal block, one end of the wire is connected to the positive electrode bus ring and the negative electrode bus ring, and the other end is connected to the terminal block, a wind hood is installed on the outer shell of the generator and covers the plurality of rectifiers, a cooling air inlet is arranged on one side of the wind hood, and a plurality of guide plates for guiding the wind direction are arranged on the inner wall of the wind hood. The present invention also discloses a generator. Compared with the prior art, the present invention greatly reduces the volume space occupied by the rectifier and has a good heat dissipation capacity.

Description

Technical Field

[0001] The invention relates to the technical field of generators, and in particular to an aviation brushless three-level excitation generator rectification system and a generator. Background Art

[0002] In the aviation field, the reliability, weight and volume of aircraft power systems are crucial. Currently, brushless three-level excitation generators are commonly used in aircraft power systems to provide power.

[0003] The brushless three-stage excitation generator generates three-phase alternating current. Since the motor itself cannot rectify or filter the current, the generated current needs to be passed into the controller first. In the controller, the current undergoes complex processing such as rectification and filtering before it can be used by the aircraft power system. However, this method has many problems.

[0004] First, the current ripple of the conventional three-phase brushless three-level excitation generator is large. If used directly, it will damage the aircraft electrical appliances. To solve this problem, large capacitors are needed for filtering. However, large capacitors are large and heavy, which not only increases the weight and volume of the system, but also takes up valuable space. Moreover, the more components there are, the higher the probability of problems in the system, which reduces the reliability of the system.

[0005] Secondly, there are many rectifiers and they generate a lot of heat. In the prior art, rectifiers are usually placed inside the controller, which requires special structural parts to install the rectifiers, and also requires a separate heat dissipation structure. As a result, the rectifier module of the controller is large in size and weight, which makes it difficult to meet the strict requirements of the aviation field on the weight and volume of devices. If the rectifier does not dissipate heat properly, it will burn out, which will lead to the destruction of the entire controller, seriously affecting the reliability of the aircraft's power system.

[0006] Furthermore, the generator and controller need to be connected by a large cable. The cable occupies a large amount of system weight and increases the load of the aircraft. At the same time, the long cable connection itself is a point prone to failure, and the current will also have a voltage drop when passing through the cable, affecting the efficiency and stability of power transmission.

[0007] Finally, the main motor output wires of the generator need to be connected to the terminal on the casing, which requires a long end space to be reserved for the main motor winding, which greatly occupies the internal space of the motor and reduces the power density and efficiency of the motor.

[0008] In summary, there are many problems in the application of existing brushless three-level excitation generators in aircraft power systems, and a new technical solution is urgently needed to solve these problems in order to improve the reliability of aircraft power systems and reduce weight and volume. Summary of the invention

[0009] The object of the present invention is to provide an aviation brushless three-level excitation generator rectifier system and a generator, which, compared with the prior art, greatly reduces the volume space occupied by the rectifier and has better heat dissipation capacity.

[0010] The above technical objectives of the present invention are achieved through the following technical solutions:

[0011] A rectifier system for an aviation brushless three-stage excitation generator comprises a plurality of mounting platforms, a plurality of rectifiers, a positive electrode slip ring, a negative electrode slip ring, a wire, a terminal block and a wind hood. The plurality of mounting platforms are arranged in a ring shape and are disposed on the outer shell of the generator. The plurality of rectifiers are mounted on the mounting platforms and supported overhead by the mounting platforms. The positive electrode slip ring is connected to the positive electrodes of the plurality of rectifiers, and the negative electrode slip rings are connected to the negative electrodes of the plurality of rectifiers. The terminal block is disposed on the generator, and a terminal block is disposed on the terminal block. One end of the wire is connected to the positive electrode slip ring and the negative electrode slip ring, and the other end is connected to the terminal block. The wind hood is mounted on the outer shell of the generator and covers the plurality of rectifiers. A cooling air inlet is disposed on one side of the wind hood, and a plurality of guide plates for guiding the wind direction are disposed on the inner wall of the wind hood.

[0012] In a preferred embodiment, the guide plate is inclined from one end of the wind cover where the cooling air inlet is located toward the other end.

[0013] In a preferred embodiment, a side air inlet is provided on the edge of the cooling air inlet, an air inlet channel connected to the side air inlet is provided in the inner wall of the wind cover, an inner cavity connected to the air inlet channel is provided inside the guide plate, an opening is provided on the side of the inner cavity, an elastic flap is provided on the opening, and an air nozzle is provided between the edge of the elastic flap and the edge of the opening.

[0014] In a preferred embodiment, the elastic strap is made of rubber material or silicone material.

[0015] In a preferred embodiment, the opening is arranged on a side of the inner cavity away from the cooling air inlet.

[0016] In a preferred embodiment, the deflector is fixed to the inner wall of the wind shield by bonding.

[0017] In a preferred embodiment, a first flexible magnet and a second flexible magnet that attract each other are provided on the air outlet, wherein the first flexible magnet is provided on the edge of the elastic strap, and the second flexible magnet is provided on the edge of the opening.

[0018] In a preferred embodiment, the air inlet passage comprises a large diameter section and a small diameter section connected to each other near the cooling air inlet, and the small diameter section is closer to the cooling air inlet than the large diameter section.

[0019] In a preferred embodiment, the plurality of guide plates are distributed in at least two rows, and the positions of the guide plates in at least two rows are staggered.

[0020] In a preferred embodiment, the plurality of mounting platforms are distributed in at least two rings to form a support platform, and a first fixing screw hole is provided on the support platform. A first fixing bolt is provided in cooperation with the first fixing screw hole to fix the rectifier.

[0021] In a preferred embodiment, it further comprises a plurality of first copper bars, wherein the first copper bars connect the positive electrodes and the negative electrodes of adjacent rectifiers.

[0022] In a preferred embodiment, a second fixing screw hole is provided on the rectifier, and a second fixing bolt is provided in cooperation with the second fixing screw hole for fixing the first copper busbar.

[0023] In a preferred embodiment, the positive electrode bus ring includes a plurality of second copper bars, and the negative electrode bus ring includes a plurality of third copper bars.

[0024] In a preferred embodiment, the number of the rectifiers is 12.

[0025] A generator comprises the above-mentioned aviation brushless three-level excitation generator rectification system.

[0026] In a preferred embodiment, the outer shell includes a large column section and a small column section, the aviation brushless three-level excitation generator rectifier system is arranged on the small column section, and the large column section is provided with an air duct ventilation hole on one side close to the small column section.

[0027] In a preferred embodiment, a threading hole is provided on the side wall of the large column section.

[0028] In a preferred embodiment, the generator is provided with fan blades inside, and the fan blades rotate synchronously with the main shaft of the generator.

[0029] Compared with the prior art, the present invention has outstanding technical effects as follows:

[0030] From the perspective of volume optimization, the traditional brushless three-level excitation generator needs to place the rectifier in the controller, which not only requires special structural parts to install the rectifier, but also requires a separate heat dissipation structure, resulting in a bulky controller rectifier module. The new rectifier system installs multiple rectifiers on the mounting platform on the generator casing. The mounting platform is arranged in a ring and protrudes on the outer surface of the casing, and the bottom of the rectifier is suspended to form a ventilation duct. This design effectively utilizes the external space of the generator, avoids occupying a large amount of space in the controller, and greatly reduces the overall occupied volume. The setting of the wind hood is also relatively reasonable. It not only covers multiple rectifiers for protection, but also guides the cooling air through the cooling air inlet on one side and the guide plate on the inner wall to efficiently dissipate heat from the rectifier, further optimizing space utilization.

[0031] Secondly, in the traditional method, there are many rectifiers with high heat generation. If they are placed in the controller without adequate heat dissipation, they are easily burned, which in turn causes the entire controller to be destroyed. However, this rectifier system suspends the rectifier through the mounting platform, providing sufficient space for the passage of cooling air. After the cooling air enters the wind cover from the air inlet, it can flow through the rectifier comprehensively and evenly under the guidance of the guide plate, completely taking away the heat generated by the rectifier, ensuring that the rectifier always works at an appropriate temperature, greatly improving the reliability and stability of the system, and effectively avoiding failures caused by overheating.

[0032] Furthermore, the output wiring of the generator is directly connected to the rectifier, and the positive and negative bus rings connected to the rectifier are then connected to the terminal block. This connection method eliminates the cables between the generator and the controller, which reduces the weight index of the system and reduces the load on the aircraft. On the other hand, it eliminates the long cable connection, which is a point prone to failure, avoids the problem of voltage drop caused by current passing through the cable, and improves the efficiency and stability of power transmission. At the same time, the generator directly outputs direct current, which can be directly supplied to aircraft electrical appliances without the need for complex controller rectification and filtering processing, which simplifies the structure of the aircraft power system and improves the response speed and reliability of the system. BRIEF DESCRIPTION OF THE DRAWINGS

[0033] Figure 1 The present invention is a partial structural schematic diagram of a generator.

[0034] Figure 2 The present invention is a partial structural schematic diagram of a generator.

[0035] Figure 3 The present invention is a partial structural schematic diagram of a generator.

[0036] Figure 4 The present invention is a partial structural schematic diagram of a generator.

[0037] Figure 5The invention relates to a structural schematic diagram of a generator.

[0038] Figure 6 The invention relates to a schematic diagram of the wind shield structure of a generator.

[0039] Figure 7 The invention relates to a schematic diagram of the longitudinal section structure of a wind shield of a generator.

[0040] Figure 8 The invention relates to a structural schematic diagram of a guide plate of a generator.

[0041] Fig. 9 The invention relates to a schematic diagram of a main motor winding of a generator.

[0042] Fig.10 The invention relates to a schematic diagram of an exciter winding of a generator.

[0043] Large column section 1; terminal block 2; terminal block 3; air duct ventilation hole 4; threading hole 5; small column section 6; mounting platform 7; first fixing screw hole 8; first fixing bolt 9; rectifier 10; positive electrode bus ring 11; negative electrode bus ring 12; first copper busbar 13; second fixing bolt 14; wire 15; wind cover 16; cooling air inlet 17; side air inlet 18; air inlet channel 19; small diameter section 20; large diameter section 21; guide plate 22; inner cavity 23; elastic strap 24; air outlet 25; first flexible magnet 26; second flexible magnet 27. DETAILED DESCRIPTION

[0044] The present invention is further described in detail below in conjunction with the accompanying drawings.

[0045] This specific embodiment is merely an explanation of the present invention and is not a limitation of the present invention. After reading this specification, those skilled in the art may make non-creative modifications to the present embodiment as needed. However, as long as they are within the scope of the claims of the present invention, they are protected by the patent law. Example

[0046] like Figures 1 to 8As shown, a brushless three-stage excitation generator rectifier system for aviation includes a plurality of mounting platforms 7, a plurality of rectifiers 10, a positive electrode slip ring 11, a negative electrode slip ring 12, a wire 15, a terminal block 2 and a wind shield 16. The plurality of mounting platforms 7 are arranged in a ring shape and are arranged on the housing of the generator. The plurality of rectifiers 10 are mounted on the mounting platforms 7 and supported overhead by the mounting platforms 7. The positive electrode slip ring 11 is connected to the positive electrodes of the plurality of rectifiers 10, and the plurality of negative electrode slip rings 12 are connected to the positive electrodes of the plurality of rectifiers 10. The negative poles of the plurality of rectifiers 10 are connected, the terminal block 2 is arranged on the generator, and the terminal block 2 is provided with a terminal post 3. One end of the wire 15 is connected to the positive electrode collector ring 11 and the negative electrode collector ring 12, and the other end is connected to the terminal post 3. The wind hood 16 is installed on the outer shell of the generator and covers the plurality of rectifiers 10. A cooling air inlet 17 is arranged on one side of the wind hood 16, and a plurality of guide plates 22 for guiding the wind direction are arranged on the inner wall of the wind hood 16.

[0047] Compared with the prior art, the aviation brushless three-level excitation generator rectification system of this embodiment has outstanding technical effects as follows:

[0048] From the perspective of volume optimization, the traditional brushless three-level excitation generator needs to place the rectifier 10 in the controller, which not only requires a special structural part to install the rectifier 10, but also requires a separate heat dissipation structure, resulting in a bulky controller rectifier module. The new rectifier system installs multiple rectifiers 10 on the mounting platform 7 on the generator housing. The mounting platform 7 is arranged in a ring and protrudes on the outer surface of the housing, and the bottom of the rectifier 10 is suspended to form a ventilation duct. This design effectively utilizes the external space of the generator, avoids occupying a large amount of space in the controller, and greatly reduces the overall occupied volume. The setting of the wind hood 16 is also relatively reasonable. It not only covers multiple rectifiers 10 and plays a protective role, but also guides the cooling air through the cooling air inlet 17 on one side and the guide plate 22 on the inner wall to efficiently dissipate the heat of the rectifier 10, further optimizing the space utilization.

[0049] Secondly, in the traditional method, the number of rectifiers 10 is large and the heat generation is high. If they are placed in the controller without adequate heat dissipation, they are easily burned, which in turn causes the entire controller to be destroyed. However, the rectifier system of this invention suspends the rectifier 10 through the mounting platform 7, providing sufficient space for the passage of cooling air. After the cooling air enters the wind cover 16 from the air inlet, it can flow through the rectifier 10 comprehensively and evenly under the guidance of the guide plate 22, completely taking away the heat generated by the rectifier 10, ensuring that the rectifier 10 always works at a suitable temperature, greatly improving the reliability and stability of the system, and effectively avoiding failures caused by overheating.

[0050] Furthermore, the output wiring of the generator is directly connected to the rectifier 10, and the positive bus ring 11 and the negative bus ring 12 connected to the rectifier 10 are then connected to the terminal block 2. This connection method eliminates the cables between the generator and the controller, which reduces the weight index of the system and reduces the load on the aircraft. On the other hand, it eliminates the long cable connection, which is a point prone to failure, avoids the problem of voltage drop caused by current passing through the cable, and improves the efficiency and stability of power transmission. At the same time, the generator directly outputs direct current, which can be directly supplied to aircraft electrical appliances without the need for complex controller rectification and filtering processing, which simplifies the structure of the aircraft power system and improves the response speed and reliability of the system.

[0051] Furthermore, the guide plate 22 is inclined from one end of the wind cover 16 where the cooling air inlet 17 is located to the other end. Such a change in the direction of the air flow allows the cooling air to contact the rectifier 10 more fully. Through the guidance of the guide plate 22, the air flow can flow through various parts of the rectifier 10 in a more optimized path, without leaving out any area that may generate heat. Sufficient contact brings higher heat exchange efficiency. The large-area and multi-angle contact between the cooling air and the rectifier 10 allows heat to be transferred from the rectifier 10 to the cooling air more quickly, thereby effectively reducing the temperature of the rectifier 10. Good heat exchange efficiency further improves the cooling effect. The setting of the inclined guide plate 22 ensures that the cooling air fully cools the rectifier 10, so that the rectifier 10 is always kept within a suitable operating temperature range, providing a guarantee for the stable output of the generator and the normal operation of the aircraft power system.

[0052] Further, the edge of the cooling air inlet 17 is provided with a side air inlet 18, the inner wall of the wind shield 16 is provided with an air inlet channel 19 connected to the side air inlet 18, the guide plate 22 is provided with an inner cavity 23 connected to the air inlet channel 19, the side of the inner cavity 23 is provided with an opening, the opening is provided with an elastic flap 24, and an air jet 25 is provided between the edge of the elastic flap 24 and the edge of the opening. After the above structure is set, during operation, most of the cooling air enters the wind shield 16 through the cooling air inlet 17, providing the main airflow for the conventional cooling of the rectifier 10. At the same time, a small part of the air enters the air inlet channel 19 through the side air inlet 18, and then flows into the inner cavity 23 of the guide plate 22. When the inner cavity 23 is continuously filled with air flow, the air pressure gradually increases, and the elastic flap 24 is in a contracted state to close the opening under normal circumstances due to its elasticity, and the air jet 25 is in a closed state at this time. As the air pressure continues to increase, the elastic flap 24 gradually expands. When it expands to a certain extent, the air outlet 25 is stretched open, and the air jet is instantly realized. This air jet action greatly improves the airflow operation efficiency, allowing the airflow to contact the rectifier 10 at a higher speed and pressure. The air jet not only improves the contact effect between the airflow and the rectifier 10, but also enhances the heat dissipation capacity. The high-speed airflow can quickly take away the heat generated by the rectifier 10, prevent heat accumulation, and keep the rectifier 10 working within a suitable temperature range. At the same time, continuous airflow blowing can also have a certain cleaning effect. During long-term use, if there is only a stable airflow blowing, it is easy to form stains on the rectifier 10, affecting the heat dissipation effect and equipment performance. The air jet action can prevent the accumulation of stains with a strong impact force, keep the surface of the rectifier 10 clean, and further ensure the stability of the heat dissipation effect.

[0053] Specifically, the elastic strap 24 is made of rubber material or silicone material. Such material arrangement has good elasticity and is conducive to achieving the design goal.

[0054] Further, the opening is arranged on the side of the inner cavity 23 away from the cooling air inlet 17. The opening is arranged on the side of the inner cavity 23 away from the cooling air inlet 17. This avoids the adverse effect of air flow movement on the expansion of the elastic flap 24, ensuring the normal operation of the elastic flap 24. At the same time, it is conducive to the guide plate 22 to play a good guiding effect, so that the airflow flows through the rectifier 10 according to the designed path.

[0055] Furthermore, the deflector 22 is fixed to the inner wall of the wind shield 16 by bonding, which is conducive to the convenient installation of the deflector 22 .

[0056] Furthermore, the air outlet 25 is provided with a first flexible magnet 26 and a second flexible magnet 27 that attract each other, wherein the first flexible magnet 26 is provided on the edge of the elastic flap 24, and the second flexible magnet 27 is provided on the edge of the opening. The first flexible magnet 26 and the second flexible magnet 27 that attract each other are provided at the air outlet 25. The first flexible magnet 26 is at the edge of the elastic flap 24, and the second flexible magnet 27 is at the edge of the opening, providing a stable closing force for the air outlet 25. This ensures that the air outlet 25 is tightly closed when the jet pressure is not reached, and that the jet effect can be accurately generated when the air pressure in the inner cavity 23 increases, thereby improving the airflow operation efficiency and the heat dissipation effect, and ensuring the stable operation of the system.

[0057] Further, the air inlet channel 19 includes a small diameter section 20 and a large diameter section 21 connected to each other near the cooling air inlet 17, and the small diameter section 20 is closer to the cooling air inlet 17 than the large diameter section 21. The air inlet channel 19 is provided with a large diameter section 21 and a small diameter section 20 near the cooling air inlet 17, and the small diameter section 20 is closer to the cooling air inlet 17. This structure enables the airflow to generate a higher flow rate when passing through the small diameter section 20. A high flow rate is conducive to achieving air spraying and improving the airflow operation efficiency.

[0058] Furthermore, the plurality of guide plates 22 are arranged in at least two rows, and the positions of the guide plates 22 in at least two rows are staggered. This design enables the cooling air to be guided at different levels and angles, increasing the contact area and contact time between the airflow and the rectifier 10. The staggered distribution effectively avoids the straight-line flow of the airflow, allowing the airflow to cover the rectifier 10 more evenly, thereby achieving a better guiding effect, improving the heat exchange efficiency and heat dissipation performance, and ensuring the stable operation of the system.

[0059] Furthermore, the plurality of mounting platforms 7 are distributed in at least two rings to form a support platform, and the support platform is provided with a first fixing screw hole 8, and a first fixing bolt 9 is provided in cooperation with the first fixing screw hole 8 to fix the rectifier 10. This structure provides a stable support and fixation for the rectifier 10, prevents the rectifier 10 from shifting due to vibration and other factors during operation, ensures that the rectifier 10 is always in the correct position, ensures stable operation of the system, and improves system reliability and safety.

[0060] The rectifier system of an aviation brushless excitation generator of this embodiment also includes a plurality of first copper bars 13, which connect the positive and negative electrodes of the adjacent rectifiers 10. The copper bar has good electrical conductivity and thermal conductivity, and can achieve stable and efficient connection between the rectifiers 10. It reduces the connection resistance, reduces energy loss, and ensures stable current transmission. At the same time, the solid structure of the copper bar can withstand certain mechanical stress, ensure the reliability of the connection, and improve the overall performance and stability of the system.

[0061] Furthermore, a second fixing screw hole is provided on the rectifier 10 , and a second fixing bolt 14 is provided in cooperation with the second fixing screw hole for fixing the first copper busbar 13 .

[0062] Furthermore, the positive electrode bus ring 11 includes a plurality of second copper bars, and the negative electrode bus ring 12 includes a plurality of third copper bars. Under such a structural setting, the plurality of copper bars are easy to disassemble and assemble, and a single copper bar can be operated separately when repairing or replacing parts, reducing the difficulty of operation and time cost. In addition, the flexibility and maintainability of the system are improved, ensuring that the system can quickly resume normal operation when problems occur.

[0063] Specifically, in this embodiment, the number of the rectifiers 10 is 12. Example

[0064] like Figures 1 to 8 As shown, a generator includes the aviation brushless three-level excitation generator rectification system described in Example 1.

[0065] Furthermore, its shell includes a large column section 1 and a small column section 6, the rectification system of the aviation brushless three-level excitation generator is arranged on the small column section 6, and the large column section 1 is provided with a duct vent 4 on one side close to the small column section 6. Under this structural setting, the wind in the wind cover 16 can enter the interior of the generator through the duct vent 4 to dissipate heat inside the generator, preventing the internal temperature from being too high and affecting the performance and life of the generator. On the other hand, the duct vent 4 can also be used for threading the wire 15, making the wiring more reasonable and neat. This design improves the overall heat dissipation performance and ease of use of the generator, and enhances the stability and reliability of the system.

[0066] Furthermore, a threading hole 5 is provided on the side wall of the large column section 1 , and the threading hole 5 cooperates with the air duct ventilation hole 4 to realize the threading of the wire 15 .

[0067] Furthermore, the generator is provided with a fan blade inside, and the fan blade rotates synchronously with the main shaft of the generator. First, the fan blade rotates synchronously with the main shaft of the generator, forming a suction effect on the rear of the generator. This means that when the generator starts working, the fan blade rotates, and the ventilation duct inside the motor is immediately formed, without the need to wait or start other devices to establish a heat dissipation channel, which greatly improves the timeliness of heat dissipation. In conventional practices, all structural parts such as support and heat dissipation of the rectifier module can be omitted, reducing the complexity and weight of the system and optimizing the spatial layout. Secondly, the heat dissipation effect of the rectifier 10 is greatly improved. On the one hand, the rectifier 10 has both forced air cooling from the outside, and a stable cooling airflow is provided for the rectifier 10 through structures such as the wind cover 16 and the cooling air inlet 17; on the other hand, there is cooling air provided by the fan blade inside the motor. The dual cooling mechanism works together to ensure that the rectifier 10 can dissipate heat in a timely and effective manner during operation and remain within a suitable temperature range, thereby extending the service life of the rectifier 10 and improving the stability and reliability of the system. Furthermore, even if there is no cooling air outside, cooling air can be provided as long as the motor is working, which greatly improves the reliability of the system. Under various working environments, the rectifier 10 can be cooled to a certain extent, reducing the risk of failure due to poor heat dissipation and providing a solid guarantee for the continuous and stable operation of the aircraft power system.

[0068] The main motor winding of a generator in this embodiment adopts a 6-phase double Y winding, 30° phase belt, Fig. 9 ; The exciter adopts two-phase double-layer winding, Fig.10 ; The auxiliary exciter is a three-phase permanent magnet motor; therefore, the entire power generation system eliminates the filter capacitor, saving a lot of space and weight.

[0069] It should be noted that, in this article, relational terms such as first and second, etc. are only used to distinguish one entity or operation from another entity or operation, and do not necessarily require or imply any such actual relationship or order between these entities or operations. Moreover, the terms "include", "comprise" or any other variants thereof are intended to cover non-exclusive inclusion, so that the process, method, article or terminal device including a series of elements includes not only those elements, but also other elements not explicitly listed, or also includes elements inherent to such process, method, article or terminal device. In the absence of further restrictions, the elements defined by the sentence "include..." or "comprise..." do not exclude the existence of other elements in the process, method, article or terminal device including the elements. In addition, in this article, "greater than", "less than", "exceed" and the like are understood to exclude the number itself; "above", "below", "within" and the like are understood to include the number itself.

[0070] The above description of the embodiments is to facilitate the understanding and use of the present invention by those skilled in the art. It is obvious that those skilled in the art can easily make various modifications to the embodiments and apply the general principles described herein to other embodiments without creative work. Therefore, the present invention is not limited to the above embodiments. Improvements and modifications made by those skilled in the art based on the disclosure of the present invention without departing from the scope of the present invention should be within the protection scope of the present invention.

Claims

1. An aviation brushless three-level excitation generator rectification system, characterized in that: The invention comprises a plurality of mounting platforms, a plurality of rectifiers, a positive electrode bus ring, a negative electrode bus ring, a wire, a terminal block and a wind hood. The plurality of mounting platforms are arranged in a ring shape and are arranged on the outer shell of the generator. The plurality of rectifiers are mounted on the mounting platforms and supported overhead by the mounting platforms. The positive electrode bus ring is connected to the positive electrodes of the plurality of rectifiers, and the negative electrode bus ring is connected to the negative electrodes of the plurality of rectifiers. The terminal block is arranged on the generator, and a terminal post is arranged on the terminal block. One end of the wire is connected to the positive electrode bus ring and the negative electrode bus ring, and the other end is connected to the terminal post. The wind hood is mounted on the outer shell of the generator and covers the plurality of rectifiers. A cooling air inlet is arranged on one side of the wind hood. , a plurality of guide plates for guiding wind direction are provided on the inner wall of the wind hood; a side air inlet is provided at the edge of the cooling air inlet, an air inlet channel connected to the side air inlet is provided in the inner wall of the wind hood, an inner cavity connected to the air inlet channel is provided inside the guide plate, an opening is provided on the side of the inner cavity, an elastic flap is provided on the opening, and an air jet is provided between the edge of the elastic flap and the edge of the opening; the opening is provided on a side of the inner cavity away from the cooling air inlet; a first flexible magnet and a second flexible magnet that attract each other are provided on the air jet, the first flexible magnet is provided on the edge of the elastic flap, and the second flexible magnet is provided on the edge of the opening.

2. According to claim 1, a brushless three-level excitation generator rectifier system for aviation, characterized in that: The guide plate is inclined from one end of the wind cover where the cooling air inlet is located toward the other end.

3. According to claim 1, a brushless three-level excitation generator rectifier system for aviation, characterized in that: The air inlet passage includes a large diameter section and a small diameter section connected to each other near the cooling air inlet, and the small diameter section is closer to the cooling air inlet than the large diameter section.

4. An aviation brushless three-level excitation generator rectifier system according to any one of claims 1 to 3, characterized in that: The plurality of mounting platforms are distributed in at least two rings to form a support platform. The support platform is provided with a first fixing screw hole. A first fixing bolt is matched with the first fixing screw hole to fix the rectifier.

5. The aviation brushless three-level excitation generator rectifier system according to claim 4, characterized in that: It also includes a plurality of first copper bars, wherein the first copper bars connect the positive electrodes and the negative electrodes of the adjacent rectifiers.

6. The aviation brushless three-level excitation generator rectifier system according to claim 5, characterized in that: The positive electrode bus ring includes a plurality of second copper bars, and the negative electrode bus ring includes a plurality of third copper bars.

7. A generator, characterized in that: The invention comprises an aviation brushless three-level excitation generator rectifier system as described in any one of claims 1 to 6, wherein the casing comprises a large column section and a small column section, the aviation brushless three-level excitation generator rectifier system is arranged on the small column section, a side of the large column section close to the small column section is provided with an air duct ventilation hole, and a fan blade is arranged inside the generator, and the fan blade rotates synchronously with the main shaft of the generator.

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