Aviation brushless three-stage excitation generator rectification system and generator

Abstract

The utility model discloses an aviation brushless three-stage excitation generator rectification system, which comprises a plurality of mounting tables, a plurality of rectifiers, a positive collector ring, a negative collector ring, a lead, a wire holder and a fan cover, and is characterized in that the plurality of mounting tables are annularly arranged and arranged on a shell of a generator, the plurality of rectifiers are mounted on the mounting tables and supported by the mounting tables in an overhead manner, and the positive collector ring and the negative collector ring are arranged on the mounting tables; the positive collector ring is connected with the positive electrodes of the rectifiers, the negative collector rings are connected with the negative electrodes of the rectifiers, the wire holder is arranged on the generator, the wire holder is provided with a binding post, one end of the wire is connected with the positive collector ring and the negative collector rings, and the other end of the wire is connected with the binding post. And a cooling air inlet is formed in one side of the fan cover. The utility model further discloses a generator. Compared with the prior art, the rectifier has the advantages that the volume space occupied by the rectifier is greatly reduced, and good heat dissipation capability is achieved.

Description

Technical Field

[0001] The present 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 size of aircraft electrical systems are crucial. Currently, brushless three-level excitation generators are commonly used to provide power in aircraft electrical systems.

[0003] Brushless three-stage excitation generators generate three-phase AC power. Because the motor itself cannot rectify or filter the current, the generated current must first be fed into a controller. Within the controller, the current undergoes complex processing, including rectification and filtering, before it can be used by the aircraft's electrical systems. However, this approach presents numerous problems.

[0004] First, conventional three-phase brushless, three-stage excitation generators generate high current ripple. If used directly, this can damage aircraft electrical equipment. To address this issue, large capacitors are required for filtering. However, large capacitors are bulky and heavy, increasing the weight and volume of the system while also occupying valuable space. Furthermore, the more components a system has, the higher the probability of system failure, reducing reliability.

[0005] Secondly, the large number of rectifiers generates high heat. In existing technology, rectifiers are typically placed within the controller, requiring specialized structural components to mount the rectifiers and a separate heat dissipation structure. This results in a bulky and heavy controller rectifier module, making it difficult to meet the stringent weight and volume requirements of the aviation industry. If the rectifiers are not properly cooled, they can burn out, potentially damaging the entire controller and severely impacting the reliability of the aircraft's electrical system.

[0006] Furthermore, the generator and controller require a large cable connection. This cable contributes significantly to the system's weight, increasing the aircraft's load. Furthermore, long cables are inherently prone to failure, and the voltage drop across the cable affects the efficiency and stability of power transmission.

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

[0008] In summary, there are many problems with the application of existing brushless three-level excitation generators in aircraft power systems. 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 purpose of the present invention is to provide an aviation brushless three-level excitation generator rectifier system and generator, which greatly reduces the volume space occupied by the rectifier compared with the existing technology 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-level excitation generator comprises a plurality of mounting platforms, a plurality of rectifiers, a positive slip ring, a negative slip ring, a conductor, a terminal block and a wind hood. The plurality of mounting platforms are arranged in a ring and are provided on the outer casing of the generator. The plurality of rectifiers are mounted on the mounting platforms and supported overhead by the mounting platforms. The positive slip ring is connected to the positive poles of the plurality of rectifiers, and the plurality of negative slip rings are connected to the negative poles of the plurality of rectifiers. The terminal block is provided on the generator and is provided with a terminal post. One end of the conductor is connected to the positive slip ring and the negative slip ring, and the other end is connected to the terminal post. The wind hood is installed on the outer casing of the generator and covers the plurality of rectifiers. A cooling air inlet is provided on one side of the wind hood.

[0012] In a preferred embodiment, 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, and a first fixing bolt is provided in conjunction with the first fixing screw hole to fix the rectifier.

[0013] In a preferred embodiment, the device further comprises a plurality of first copper bars, wherein the first copper bars connect the positive electrodes and the negative electrodes of adjacent rectifiers.

[0014] 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.

[0015] In a preferred embodiment, the positive electrode slip ring includes a plurality of second copper bars, and the negative electrode slip ring includes a plurality of third copper bars.

[0016] In a preferred embodiment, the number of the rectifiers is 12.

[0017] A generator comprises the above-mentioned aviation brushless three-level excitation generator rectification system.

[0018] 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.

[0019] In a preferred embodiment, a threading hole is provided on the side wall of the large column section.

[0020] 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.

[0021] Compared with the existing technology, the present invention has outstanding technical effects as follows:

[0022] From the perspective of volume optimization, the traditional brushless three-level excitation generator needs to place the rectifier inside 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 a mounting platform on the generator casing. The mounting platform is arranged in a ring and protrudes from 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 to efficiently dissipate heat from the rectifier, further optimizing space utilization.

[0023] Secondly, the traditional approach involves numerous rectifiers that generate high amounts of heat. If placed within the controller, these rectifiers are not properly cooled and can easily burn out, potentially damaging the entire controller. This rectifier system, however, uses a mounting platform to suspend the rectifiers, providing ample space for cooling air. After entering the hood from the air inlet, the cooling air is guided by deflectors to flow uniformly through the rectifiers, completely dissipating the heat generated by the rectifiers and ensuring they operate at a constant, optimal temperature. This significantly improves system reliability and stability, effectively preventing failures caused by overheating.

[0024] Furthermore, the generator's output wiring connects directly to the rectifier, and the positive and negative slip rings connected to the rectifier are then connected to the terminal block. This connection method eliminates the need for cables between the generator and the controller, reducing system weight and lightening the aircraft's load. Furthermore, it eliminates the long cables, a common point of failure, and avoids the voltage drop caused by current flowing through the cables, thereby improving the efficiency and stability of power transmission. Furthermore, the generator directly outputs DC power, which can be directly used by aircraft electrical appliances, eliminating the need for complex controller rectification and filtering. This simplifies the aircraft's power system architecture and improves its responsiveness and reliability. BRIEF DESCRIPTION OF THE DRAWINGS

[0025] Figure 1 The present invention is a partial structural schematic diagram of a generator.

[0026] Figure 2 The present invention is a partial structural schematic diagram of a generator.

[0027] Figure 3The present invention is a partial structural schematic diagram of a generator.

[0028] Figure 4 The present invention is a partial structural schematic diagram of a generator.

[0029] Figure 5 The invention relates to a schematic structural diagram of a generator.

[0030] Figure 6 The present invention relates to a schematic diagram of a main motor winding of a generator.

[0031] Figure 7 The present invention relates to a schematic diagram of an exciter winding of a generator.

[0032] In the picture

[0033] Large column section 1; terminal block 2; terminal post 3; air duct vent 4; threading hole 5; small column section 6; mounting platform 7; first fixing screw hole 8; first fixing bolt 9; rectifier 10; positive slip ring 11; negative slip ring 12; first copper bus 13; second fixing bolt 14; wire 15; air hood 16; cooling air inlet 17. DETAILED DESCRIPTION

[0034] The present invention will be further described in detail below with reference to the accompanying drawings.

[0035] This specific embodiment is merely an explanation of the present invention and is not intended to limit the present invention. After reading this specification, those skilled in the art may make non-creative modifications to this embodiment as needed. However, as long as such modifications are within the scope of the claims of the present invention, they are protected by patent law.

[0036] Example 1:

[0037] like Figures 1 to 5 As shown, a rectifier system of an aviation brushless three-level excitation generator includes multiple mounting platforms 7, multiple rectifiers 10, positive slip rings 11, negative slip rings 12, wires 15, terminal blocks 2 and wind hoods 16. The multiple mounting platforms 7 are arranged in a ring and are provided on the casing of the generator. The multiple rectifiers 10 are mounted on the mounting platforms 7 and supported overhead by the mounting platforms 7. The positive slip rings 11 are connected to the positive poles of the multiple rectifiers 10, and the multiple negative slip rings 12 are connected to the negative poles of the multiple rectifiers 10. The terminal block 2 is provided on the generator, and a terminal post 3 is provided on the terminal block 2. One end of the wire 15 is connected to the positive slip ring 11 and the negative slip ring 12, and the other end is connected to the terminal post 3. The wind hood 16 is installed on the casing of the generator and covers the multiple rectifiers 10. A cooling air inlet 17 is provided on one side of the wind hood 16.

[0038] Compared with the prior art, the aviation brushless three-level excitation generator rectification system of this embodiment has outstanding technical effects as follows:

[0039] 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 special structural parts 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 casing. The mounting platform 7 is arranged in a ring and protrudes from the outer surface of the casing, 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 for protection, but also guides the cooling air through the cooling air inlet 17 on one side to efficiently dissipate heat from the rectifier 10, further optimizing space utilization.

[0040] Secondly, in traditional methods, rectifiers 10 are numerous and generate high amounts of heat. If placed inside a controller, they are prone to burning due to inadequate heat dissipation, potentially damaging the entire controller. However, this rectifier system suspends the rectifiers 10 via a mounting platform 7, providing ample space for cooling air to pass through. After entering the hood 16 from the air inlet, the cooling air, guided by the guide plates 22, flows uniformly and comprehensively through the rectifiers 10, completely removing the heat generated by the rectifiers 10 and ensuring that the rectifiers 10 always operate at an appropriate temperature. This significantly improves the system's reliability and stability, effectively preventing failures caused by overheating.

[0041] Furthermore, the generator's output wiring is directly connected to the rectifier 10, and the positive and negative slip rings 11 and 12 connected to the rectifier 10 are then connected to the terminal block 2. This connection method eliminates the need for cables between the generator and the controller, reducing the system's weight and lightening the aircraft's load. Furthermore, it eliminates the long cables, a common point of failure, and avoids the voltage drop caused by current passing through the cables, thereby improving the efficiency and stability of power transmission. Furthermore, the generator directly outputs direct current, which can be directly used by the aircraft's electrical appliances, eliminating the need for complex controller rectification and filtering. This simplifies the structure of the aircraft's electrical system and improves its response speed and reliability.

[0042] Furthermore, the plurality of mounting platforms 7 are arranged in at least two rings to form a support platform. The support platform is provided with first fixing screw holes 8. First fixing bolts 9 are provided in conjunction with the first fixing screw holes 8 to secure the rectifier 10. This structure provides stable support and fixation for the rectifier 10, preventing displacement of the rectifier 10 due to vibration and other factors during operation, ensuring that the rectifier 10 is always in the correct position, ensuring stable system operation, and improving system reliability and safety.

[0043] The brushless excitation generator rectifier system of this embodiment also includes multiple first copper bars 13, which connect the positive and negative electrodes of adjacent rectifiers 10. The copper bars have excellent electrical and thermal conductivity, enabling stable and efficient connections between rectifiers 10. This reduces connection resistance, minimizes energy loss, and ensures stable current transmission. Furthermore, the copper bars' robust structure can withstand certain mechanical stresses, ensuring connection reliability and improving overall system performance and stability.

[0044] 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 .

[0045] Furthermore, the positive electrode slip ring 11 includes multiple second copper bars, and the negative electrode slip ring 12 includes multiple third copper bars. This structural arrangement facilitates assembly and disassembly of the multiple copper bars, allowing individual bars to be operated independently during repair or component replacement, reducing operational complexity and time costs. This also improves the system's flexibility and maintainability, ensuring rapid restoration of normal operation should any issues arise.

[0046] Specifically, in this embodiment, the number of the rectifiers 10 is 12.

[0047] Example 2:

[0048] like Figures 1 to 5 As shown, a generator includes the aviation brushless three-level excitation generator rectification system described in Example 1.

[0049] Furthermore, its housing includes a large column section 1 and a small column section 6. The aviation brushless three-level excitation generator rectifier system is mounted on the small column section 6. A duct vent 4 is provided on the side of the large column section 1 near the small column section 6. With this structural arrangement, air from the wind shield 16 can enter the generator through the duct vent 4, dissipating heat within the generator and preventing excessive internal temperatures from affecting its performance and lifespan. Furthermore, the duct vent 4 can also be used to thread the wires 15, making wiring more rational and neat. This design improves the overall heat dissipation performance and ease of use of the generator, enhancing the stability and reliability of the system.

[0050] 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 .

[0051] Furthermore, the generator is equipped with internal fan blades that rotate synchronously with the generator's main shaft. First, the fan blades rotate synchronously with the generator's main shaft, creating a wind suction effect at the rear of the generator. This means that as soon as the generator begins operating, the fan blades rotate, instantly forming an internal ventilation duct within the motor. This eliminates the need for additional waiting or activating other devices to establish a heat dissipation channel, significantly improving the timeliness of heat dissipation. Conventional components such as the rectifier module's support and heat dissipation components are eliminated, reducing system complexity and weight and optimizing spatial layout. Second, the heat dissipation efficiency of the rectifier 10 is significantly enhanced. On the one hand, the rectifier 10 is cooled by forced air from the outside, providing a stable cooling airflow through structures such as the fan cover 16 and the cooling air inlet 17. On the other hand, cooling air is also supplied by the fan blades within the motor. This dual cooling mechanism works synergistically to ensure that the rectifier 10 dissipates heat promptly and effectively during operation, maintaining it within a suitable temperature range. This extends the service life of the rectifier 10 and improves the stability and reliability of the system. Furthermore, even if there is no external cooling air, cooling air is provided as long as the motor is operating, significantly enhancing system reliability. 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.

[0052] The main motor winding of a generator in this embodiment adopts a 6-phase double Y winding with a 30° phase belt. Figure 6 ; The exciter adopts two-phase double-layer winding, Figure 7 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.

[0053] It should be noted that, in this document, relational terms such as first and second, etc., are used solely to distinguish one entity or operation from another, and do not necessarily require or imply any actual relationship or order between these entities or operations. Furthermore, the terms "include," "comprise," or any other variations thereof are intended to encompass non-exclusive inclusion, such that a process, method, article, or terminal device comprising a series of elements includes not only those elements, but also other elements not explicitly listed, or elements inherent to such process, method, article, or terminal device. Without further limitation, elements defined by the phrase "include..." or "comprising..." do not exclude the presence of additional elements in the process, method, article, or terminal device comprising the elements. Furthermore, in this document, "greater than," "less than," "exceeding," etc., are understood to exclude the number itself; "above," "below," "within," etc., are understood to include the number itself.

[0054] The above description of the embodiments is intended to facilitate understanding and application of the present invention by those skilled in the art. It is apparent that those skilled in the art can readily make various modifications to the embodiments and apply the general principles described herein to other embodiments without requiring creative effort. Therefore, the present invention is not limited to the above-described 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 scope of protection of the present invention.

Claims

1. An aviation brushless three-level excitation generator rectifier system, characterized in that: It includes multiple mounting platforms, multiple rectifiers, positive slip rings, negative slip rings, wires, terminal blocks and wind hoods. The multiple mounting platforms are arranged in a ring and are set on the outer casing of the generator. The multiple rectifiers are installed on the mounting platforms and supported overhead by the mounting platforms. The positive slip ring is connected to the positive poles of the multiple rectifiers, and the multiple negative slip rings are connected to the negative poles of the multiple rectifiers. The terminal block is set on the generator, and a terminal post is set on the terminal block. One end of the wire is connected to the positive slip ring and the negative slip ring, and the other end is connected to the terminal post. The wind hood is installed on the outer casing of the generator and covers the multiple rectifiers. A cooling air inlet is set on one side of the wind hood.

2. The aviation brushless three-level excitation generator rectifier system according to claim 1, 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 provided in conjunction with the first fixing screw hole to fix the rectifier.

3. The aviation brushless three-level excitation generator rectifier system according to claim 2, characterized in that: It also includes a plurality of first copper bars, wherein the first copper bars connect the positive poles and the negative poles of adjacent rectifiers.

4. The aviation brushless three-level excitation generator rectifier system according to claim 3, characterized in that: The rectifier is provided with a second fixing screw hole, and a second fixing bolt is provided in conjunction with the second fixing screw hole for fixing the first copper busbar.

5. The aviation brushless three-level excitation generator rectifier system according to claim 3, 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.

6. The aviation brushless three-level excitation generator rectifier system according to claim 1, characterized in that: The number of the rectifiers is 12.

7. A generator, characterized in that: The invention comprises the aviation brushless three-level excitation generator rectifier system according to any one of claims 1 to 6.

8. The generator according to claim 7, characterized in that: Its 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. The large column section is provided with an air duct ventilation hole on one side close to the small column section.

9. The generator according to claim 8, characterized in that: The side wall of the large column section is provided with a threading hole.

10. The generator according to claim 8, characterized in that: The generator is provided with fan blades inside, and the fan blades rotate synchronously with the main shaft of the generator.

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