Aviation alternating-current generator with initial phase adjustment limiting structure and power generation system

Abstract

The invention relates to the technical field of aviation alternating-current generators, in particular to an aviation alternating-current generator with an initial phase adjusting and limiting structure and a power generation system.The aviation alternating-current generator comprises a phasing gasket, the phasing gasket comprises an inner ring gasket and an outer ring gasket, and the inner ring gasket and the outer ring gasket are connected through a connecting rib; the connecting rib is provided with a breaking structure convenient to snap, the inner ring gasket is fixedly sleeved on a rotating shaft of a rotor assembly of the generator, and the outer ring gasket is uniformly provided with a plurality of arc-shaped adjusting through grooves; the relative positions of the stator assembly and the rotor assembly are adjusted, and bolts penetrate through the arc-shaped adjusting through grooves to connect the rotor assembly, the phasing gasket and the stator assembly, so that the initial phase of the generator is limited. The initial phases of the alternating-current generators are the same, parallel operation of the synchronous generators is guaranteed, and the power supply quality of a power supply system is improved.

Description

Technical Field

[0001] The present invention relates to the technical field of aviation AC generators, and in particular to an aviation AC generator with an initial phase adjustment limit structure and a power generation system. Background Art

[0002] With the rapid development of modern aircraft, the number of onboard electrical equipment has increased significantly, requiring the capacity of the power supply system to continue to increase. The parallel power supply system reduces the fluctuation of grid voltage and frequency, improves the power supply quality, and increases the reliability of the system.

[0003] The parallel operation of aircraft AC generators must meet the requirements of the same voltage waveform, phase sequence, amplitude, frequency, and the same phase of the instantaneous voltage when put into parallel. At present, a large number of aircraft use the same type of AC generators in parallel, with the same waveform, and the distortion coefficient and crest factor are specified to be within a certain range; the rated frequency and phase sequence of the AC power supply depend on the speed and direction of the aircraft engine. When the engine speed is constant and the direction does not change, its frequency, phase sequence, and waveform can meet the parallel requirements. Therefore, it is important that the instantaneous voltage phase of the generator is the same when it is put into parallel, and the phase difference of the same-name phase voltage should not be too large, so as to avoid excessive impact current and vibration, affecting the normal operation of electrical equipment.

[0004] Therefore, it is necessary to provide an aviation AC generator and a power generation system with an initial phase adjustment limit structure to solve the above problems. Summary of the invention

[0005] The invention provides an aviation AC generator and a power generation system with an initial phase adjustment limit structure to solve the existing problems.

[0006] An aviation AC generator with an initial phase adjustment and limiting structure of the present invention adopts the following technical scheme, including: a rotor assembly, a stator assembly and a phase-fixing washer, the phase-fixing washer includes: an inner ring washer and an outer ring washer, and the inner ring washer and the outer ring washer are connected by a connecting rib, and a disconnection structure for easy pulling is provided on the connecting rib, the inner ring washer is fixed on the rotating shaft of the rotor assembly of the generator, and a plurality of arc-shaped adjustment through grooves are evenly distributed on the outer ring washer; The relative positions of the stator assembly and the rotor assembly are adjusted, and then the rotor assembly, the phase-fixing gasket and the stator assembly are connected by bolts passing through the arc-shaped adjustment slots to limit the initial phase of the generator.

[0007] Preferably, the rotating shaft of the rotor assembly of the generator is a hollow shaft, and an elastic shaft assembly is arranged inside the hollow shaft, one end of the elastic shaft assembly is used to be key-connected to the engine accessory casing, and the other end of the elastic shaft assembly is transmission-connected to the inner wall of the hollow shaft, wherein the outer ring of the hollow shaft is connected to the inner ring of the stator assembly through the bearing assembly.

[0008] Preferably, the disconnection structure is a disconnection groove provided on the connecting rib.

[0009] Preferably, the bearing assembly includes a bearing, the inner ring of the bearing is fixedly mounted on a hollow shaft, the outer ring of the bearing is fixedly mounted on an inner ring of a stator assembly, a bearing end cover assembly is provided on the bearing, and the bearing end cover assembly is connected between a phasing gasket and an end face of the stator assembly.

[0010] Preferably, the bearing end cover assembly includes: a bearing cover, a first nut is inserted into the bearing cover mounting hole, the first nut is threadedly connected to the hollow shaft, the bearing cover is located between the phase-fixing washer and the end face of the stator assembly, the bolt passes through the arc-shaped adjustment groove of the outer ring washer to connect the bearing cover and the stator assembly, and the end face of the first nut is provided with an annular mounting groove for installing the inner ring washer, and a plurality of grooves are evenly distributed on the annular mounting groove.

[0011] Preferably, two sections of threads with opposite rotation directions are arranged on the outer peripheral surface along the axial direction of the first nut.

[0012] Preferably, a second nut is further provided on the hollow shaft between the generator front end cover and the phase-fixing washer, and a plurality of clamping grooves for clamping with a wrench are provided on the outer peripheral surface of the second nut.

[0013] Preferably, an exciter rotor assembly is mounted on the hollow shaft, an exciter balance bracket assembly is fixedly mounted on the outer ring of the exciter rotor assembly, a positioning plate is provided on the outer circumference of the exciter balance bracket assembly, the positioning plate is mounted in the rear end cover assembly of the generator, and one end of the positioning plate facing the exciter balance bracket assembly is a pointed end.

[0014] Preferably, the exciter balance bracket assembly includes: an annular member, the end surface of the annular member facing the rear end cover assembly is provided with an annular groove, the annular groove is provided with an opening groove, and the opening groove is used to load the corresponding balancing block from the opening groove according to the balancing amount when balancing the rotor assembly.

[0015] An AC power generation system comprises a plurality of aviation AC generators with an initial phase adjustment and limiting structure according to the present invention, wherein the plurality of aviation AC generators are connected in parallel.

[0016] The beneficial effects of the present invention are: The position of the rotor assembly of the generator is adjusted according to the initial phase, so that the rotor assembly is fixed at a certain angle relative to the stator assembly; during the adjustment process, the position of the connecting ribs of the phase-fixing gasket is adjusted to adjust and compensate the relative positions of the stator assembly and the rotor assembly, thereby ensuring the adjustability of the initial phase of the generator; finally, after the initial phase is adjusted, the rotor assembly, the phase-fixing gasket and the stator assembly are connected by bolts, thereby locking the geometric position of the rotor assembly and preventing the rotor assembly from rotating freely, thereby realizing the adjustment limit of the initial phase of the generator, that is, the present invention makes the initial phases of the AC generators the same, ensures the parallel operation of the synchronous generators, and improves the power supply quality of the power supply system; the generators in the parallel system serve as each other's backup power supply, increases the emergency power supply capacity, and improves the system power supply reliability. BRIEF DESCRIPTION OF THE DRAWINGS

[0017] In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings required for use in the embodiments or the description of the prior art will be briefly introduced below. Obviously, the drawings described below are only some embodiments of the present invention. For ordinary technicians in this field, other drawings can be obtained based on these drawings without paying creative work.

[0018] Figure 1 It is an internal schematic diagram of an aviation AC generator with an initial phase adjustment and limiting structure of the present invention; Figure 2 A partial view of an aviation AC generator with an initial phase adjustment and limiting structure according to the present invention; Figure 3 Schematic diagram of the structure of a phase-fixing gasket in an embodiment of the present invention; Figure 4 This is a schematic diagram of the structure of a first nut in an embodiment of the present invention; Figure 5 This is a schematic diagram of the adjustment state of the phasing gasket in an embodiment of the present invention; Figure 6 is a schematic structural diagram of a second nut in an embodiment of the present invention; Figure 7 It is a structural schematic diagram of a positioning plate in an embodiment of the present invention; Figure 8 Schematic diagram of the structure of the exciter balance bracket assembly in an embodiment of the present invention.

[0019] In the figure: 1, rotor assembly; 2, first nut; 3, second nut; 4, phasing washer; 41, inner ring washer; 42, outer ring washer; 43, arc-shaped adjustment groove; 5, stop washer; 6, bearing cover; 7, stator assembly; 8, positioning plate; 9, exciter balance bracket assembly; 10, rear end cover assembly; 11, first rear static ring; 12, first rear damping ring; 13, second rear static ring; 14, second rear damping ring; 15, front damping ring; 16, front static ring; 17, disconnect groove; 18, groove; 19, annular groove. DETAILED DESCRIPTION

[0020] The following will be combined with the drawings in the embodiments of the present invention to clearly and completely describe the technical solutions in the embodiments of the present invention. Obviously, the described embodiments are only part of the embodiments of the present invention, not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of the present invention.

[0021] An embodiment of an aviation AC generator with an initial phase adjustment limit structure of the present invention is as follows: Figure 1 As shown, it includes: a rotor assembly 1, a stator assembly 7 and a phase-fixing gasket 4, as shown in Figure 3 As shown, the phase-fixing gasket 4 includes: an inner ring gasket 41 and an outer ring gasket 42, and the inner ring gasket 41 and the outer ring gasket 42 are connected by connecting ribs, and a disconnection structure for easy pulling is provided on the connecting ribs, and the inner ring gasket 41 is fixed on the rotating shaft of the rotor assembly 1 of the generator; a plurality of arc-shaped adjustment grooves 43 are evenly distributed on the outer ring gasket 42, and the arc-shaped adjustment grooves 43 are used to connect with the stator assembly 7 of the generator through bolts, wherein, by adjusting the relative position of the stator assembly 7 and the rotor assembly 1, the rotating shaft of the rotor assembly 1, the phase-fixing gasket 4 and the stator assembly are connected by bolts passing through the arc-shaped adjustment grooves 43, wherein a stop gasket 5 is provided between the bolts and the phase-fixing gasket 4 to limit the initial phase of the generator. It should be noted that, according to the initial phase requirement, the position of the rotor assembly 1 of the generator is adjusted by adjusting the connecting ribs at different positions in the groove 18 on the end face of the first nut 2, so that the rotor assembly 1 is fixed at a certain angle relative to the stator assembly 7; the arc-shaped adjustment through slot 43 compensates and adjusts the relative positions of the stator assembly 7 and the rotor assembly 1, thereby ensuring the adjustability of the initial phase of the generator, and the rotor assembly 1, the phase-fixing gasket 4 and the stator assembly 7 are connected by bolts, thereby locking the geometric position of the rotor assembly 1, making it impossible for the rotor assembly 1 to rotate freely, thereby realizing the adjustment limit of the initial phase of the generator.

[0022] like Figure 1As shown, the rotating shaft of the rotor assembly 1 of the generator is a hollow shaft, and an elastic shaft assembly is coaxially connected to the hollow shaft. One end of the elastic shaft assembly is used to be key-connected to the engine accessory casing, and the other end of the elastic shaft assembly is transmission-connected to the inner wall of the hollow shaft, wherein the outer ring of the hollow shaft is connected to the inner ring of the stator assembly 7 through the bearing assembly.

[0023] like Figure 3 As shown, in this embodiment, the disconnection structure is a disconnection groove 17 provided on the connecting rib, that is, the thinnest part of the connecting rib is 2 mm by providing the disconnection groove 17, so as to ensure that the rotor assembly 1 of the generator is broken in time when rotating, so that the rotor assembly 1 can rotate freely; wherein, in this embodiment, the outer ring washer 42 of the phase-fixing washer 4 is provided with three weight-reducing grooves, a tooth is formed between every two weight-reducing grooves, and an arc-shaped adjustment groove 43 is provided on the tooth. The arc of the arc-shaped adjustment groove 43 in this embodiment is 36°, and the arc-shaped adjustment groove 43 is used to meet the need for adjusting the geometric position between the stator assembly 7 and the rotor assembly 1, to ensure the requirements of the initial phase of the generator, and also to enable the rotor assembly 1 to rotate smoothly against the stator assembly 7 during the phase change process. The end surface is provided with a groove to reduce the weight of the phase-fixing washer.

[0024] Specifically, the bearing assembly includes a bearing, the inner ring of the bearing is fixedly mounted on a hollow shaft, the outer ring of the bearing is fixedly mounted on an inner ring of a stator assembly 7, a bearing end cover assembly is arranged on the bearing, and the bearing end cover assembly is connected between a phasing gasket 4 and an end face of the stator assembly 7.

[0025] like Figure 4 As shown, the bearing end cover assembly includes: a bearing cover 6, a first nut 2 and an outer ring of a hollow shaft are mounted inside the bearing cover 6, specifically, the first nut 2 is threadedly connected to the outer ring of the hollow shaft, the bearing cover 6 is located between the phase washer 4 and the end face of the stator assembly 7, the end face of the first nut 2 is provided with an annular mounting groove for installing an inner ring washer 41, and eight grooves 18 are evenly distributed on the annular mounting groove, and the eight grooves 18 are evenly distributed along the circumference of the first nut 2 at 45°, the inner ring washer 41 of the phase washer 4 is located in the annular mounting groove on the end face of the first nut 2, and the connecting ribs and the grooves 18 are clearance-matched. When adjusting, the starting position can be started from any groove 18 from grooves 1 to 8, and the position of the rotor assembly 1 is rotated, such as Figure 5 As shown, there are 8 adjustment installation states, adjust in sequence, such as Figure 4As shown, the phase washer 4 is rotated to adjust the connecting rib of the inner ring washer 41 of the phase washer 4 to be installed in the groove 18 of the end face of the first nut 2 until the initial phase requirement is met, and the inner ring washer 41 of the phase washer 4 is fixed in the annular mounting groove of the end face of the first nut 2. Specifically, in this embodiment, the lug on the outer surface of the bearing cover 6 is fixed between the phase washer 4 and the stator assembly 7, and the end face of the bearing cover 6 is provided with an oil port groove to facilitate the replacement of grease, that is, to meet the requirements of the first overhaul period of the aircraft generator, the bearing of the generator adopts an oil storage bearing. Under the premise of not disassembling the motor, the grease is injected into the oil port groove of the end face of the bearing cover 6 from the oil filling channel inside the casing, and passes through the oil storage bearing to realize the regular replacement of the generator bearing grease; the bolt passes through the arc-shaped adjustment slot 43 of the outer ring washer 42 of the phase washer 4 to connect the bearing cover 6 and the stator assembly 7.

[0026] In order to seal the grease in the bearing, prevent the leakage of lubricating oil during the rotation of the generator, and avoid the drying and loss of the generator under long-term working conditions, two sections of threads with opposite rotation directions are arranged on the outer peripheral surface along the axial direction of the first nut 2 in this embodiment. When the grease is in the space contained by the thread and the bearing cover, the thread at one end causes the grease to move axially when the first nut 2 rotates, and continuously returns to the bearing chamber to prevent the bearing grease from leaking and overflowing. The bearing adopts a "labyrinth" sealing structure, such as Figure 1 As shown, the front damping ring 15, the first rear damping ring 12, and the second rear damping ring 14 are provided with annular sealing grooves of different diameters, and the matching front static ring 16, the first rear static ring 11, and the second rear static ring 13 are also provided with annular sealing grooves of different diameters. A series of interception gaps are formed between the annular sealing grooves, and the grease generates resistance when passing through the gaps of the tortuous labyrinth, effectively preventing leakage between the rotating front damping ring 15, the first rear damping ring 12, and the second rear damping ring 14 and the fixed front static ring 16, the first rear static ring 11, and the second rear static ring 13.

[0027] like Figure 1 As shown, a second nut 3 is also provided on the hollow shaft between the generator front end cover and the phase washer 4. Figure 6 As shown, a plurality of clamping grooves for clamping with a wrench are provided on the outer circumference of the second nut 3, and the second nut 3 is fixed by clamping the clamping grooves with a wrench. Figure 6 As shown, the end face of the second nut 3 is provided with a thin-wall curling punch point, which is pressed into the groove of the hollow shaft to prevent loosening.

[0028] like Figure 1 As shown, an exciter rotor assembly 1 is mounted on the hollow shaft, an exciter balance bracket assembly 9 is fixedly mounted on the outer ring of the exciter rotor assembly 1, a positioning plate 8 is arranged on the outer side of the exciter balance bracket assembly 9, and the positioning plate 8 is installed in the rear end cover assembly 10 of the generator, as shown in FIG. Figure 7As shown, in order to facilitate the clear marking line after phasing, the positioning plate 8 is a bent plate, one end of the bent plate is fixed to the rear end cover assembly 10, and the end of the bent plate facing the exciter balance bracket assembly 9 is a pointed end. Figure 8 As shown, the exciter balance bracket assembly 9 includes: a ring member, the end face of the ring member facing the rear end cover assembly 10 is provided with a ring groove 19, and the ring groove 19 is provided with an open groove, and the open groove is used to load the corresponding balance block from the open groove according to the balance amount when the rotor assembly is balanced; when the exciter balance bracket assembly 9 is hot pressed to the excitation bracket of the exciter rotor assembly 1, the center of the open groove of the ring groove 19 on the exciter balance bracket assembly 9 should be aligned with the center of the keyway of the excitation bracket to ensure the consistency of the position of the rotor assembly 1. After the generator is phased, a marking line is made on the end face of the balance bracket assembly to facilitate the re-phasing of the generator after disassembly and smooth grid connection. In order to prevent the excitation coil from short-circuiting, an insulating paint is provided on the surface of the ring member; it should be noted that by rotating the rotor assembly 1 to adjust the initial phase of the generator, then, a marking line is made according to the pointing position of the sharp end of the positioning plate 8 on the ring member of the exciter balance bracket assembly 9, and then, the stator assembly 7 and the rotor assembly 1 are connected by bolts through the directional washer 4 to achieve the generator phase.

[0029] In addition, in this embodiment, the hollow shaft of the rotor assembly 1 is equipped with bearings, a main generator rotor assembly, an exciter rotor assembly, a fan assembly, a front damping ring, and a rear damping ring. The main generator rotor assembly, the exciter rotor assembly, the fan assembly and the hollow shaft are connected by keys to ensure the reliability of the rotor running at high speed and the uniqueness of the assembly position. The stator assembly 7 includes a casing, a main generator stator assembly and an exciter stator assembly, wherein the main generator stator is embedded and wound and the three-phase lead wires are welded as required, the exciter coil is wrapped and installed on the exciter stator assembly, and after the positive and negative lead wires are led out as required, it is pressed into the casing and circumferentially locked with screws to ensure that the positioning and lead-out positions of the main generator stator assembly and the exciter stator assembly are consistent, and the adjustability of the initial phase is ensured. The permanent magnet machine stator assembly is mounted in the exciter stator assembly and fixed to the rear end cover assembly 10 with nuts. A flange is installed on the front end cover assembly of the casing, and the generator is fixed to the engine with a clamp. The front damping ring 15, the first rear damping ring 12, and the second rear damping ring 14 are provided with annular sealing grooves of different diameters, and the matching front static ring 16, the first rear static ring 11, and the second rear static ring 13 are also provided with annular sealing grooves of different diameters. A series of "labyrinth" sealing grooves with intercepting gaps are formed between such annular sealing grooves, and the grease generates resistance when passing through the tortuous "labyrinth" sealing grooves. In addition, the rotor assembly 1 and the stator assembly 7 are both conventional structures of existing generators, and will not be described in detail in this embodiment.

[0030] An AC power generation system, the embodiment discloses a plurality of aviation AC generators with initial phase adjustment and limiting structures, and the plurality of aviation AC generators are connected in parallel. That is, the initial phases of the aviation AC generators with initial phase adjustment and limiting structures are the same. When all generators are connected to the grid, the generator controller is used to adjust the output voltage of the generator, and the voltage difference △U≤10V is satisfied by adjusting the magnitude of the excitation current; the generator generates AC power by rotating the generator rotor assembly driven by the engine, and the frequency can satisfy the frequency difference △f≤3Hz by adjusting the engine speed. Therefore, when the generators are connected in parallel, large impact currents and mechanical vibrations of the rotor assembly caused by large currents will not be generated, thus avoiding generator failures, and even serious failures due to failure to be pulled into synchronization.

[0031] How it works According to the initial phase, adjust the connecting rib of the phase-fixing washer 4 to Figure 4 The position of the rotor assembly 1 of the generator is adjusted by adjusting the position of the 8 grooves 18 in the 8 grooves 18, that is, rotating the hollow shaft of the rotor assembly 1 of the generator so that the rotor assembly 1 is fixed at a certain angle relative to the stator assembly 7; then, the bolt is passed through the outer arc-shaped adjustment slot 43 and connected to the stator assembly 7, so that the relative position of the stator assembly 7 and the rotor assembly 1 is positioned by the phase-fixing washer 4, and the ring is marked for use when re-phasing. During operation, when the engine drags the hollow shaft of the rotor assembly 1 of the generator to rotate through the elastic shaft assembly, the torque generated causes the phase-fixing washer 4 to be stressed, and the connecting ribs between the inner ring washer 41 and the outer ring washer 42 of the phase-fixing washer 4 are broken along the disconnection groove 17. At this time, the rotor assembly 1 is free to rotate, the generator works, and generates three-phase alternating current. It should be noted that re-phasing can be completed by assembling a new phase-fixing washer 4 so that the pointed end of the positioning plate 8 on the rear end cover assembly 10 is aligned with the marking line on the rotor assembly exciter balance bracket assembly 9, and the phase is completed.

[0032] The above description is only a preferred embodiment of the present invention and is not intended to limit the present invention. Any modifications, equivalent substitutions, improvements, etc. made within the spirit and principle of the present invention should be included in the protection scope of the present invention.

Claims

1. An aviation AC generator with an initial phase adjustment and limiting structure, comprising a rotor assembly and a stator assembly, characterized in that: Also includes: A phasing gasket, comprising: an inner ring gasket and an outer ring gasket, wherein the inner ring gasket and the outer ring gasket are connected by a connecting rib, the connecting rib is provided with a disconnection structure for easy pulling off, the inner ring gasket is fixed on the rotating shaft of the rotor assembly of the generator, and the outer ring gasket is evenly provided with a plurality of arc-shaped adjustment slots; The relative positions of the stator assembly and the rotor assembly are adjusted, and then the rotor assembly, the phase-fixing gasket and the stator assembly are connected by bolts passing through the arc-shaped adjustment slots to limit the initial phase of the generator.

2. The aviation AC generator with an initial phase adjustment and limiting structure according to claim 1, characterized in that: The rotating shaft of the rotor assembly of the generator is a hollow shaft, and an elastic shaft assembly is arranged inside the hollow shaft. One end of the elastic shaft assembly is used to be key-connected to the engine accessory casing, and the other end of the elastic shaft assembly is transmission-connected to the inner wall of the hollow shaft, wherein the outer ring of the hollow shaft is connected to the inner ring of the stator assembly through the bearing assembly.

3. The aviation AC generator with an initial phase adjustment and limiting structure according to claim 1, characterized in that: The disconnect structure is a disconnect groove opened on the connecting rib.

4. The aviation AC generator with an initial phase adjustment and limiting structure according to claim 2, characterized in that: The bearing assembly comprises a bearing, the inner ring of the bearing is fixedly mounted on a hollow shaft, the outer ring of the bearing is fixedly mounted on an inner ring of a stator assembly, a bearing end cover assembly is arranged on the bearing, and the bearing end cover assembly is connected between a phase-fixing washer and an end face of the stator assembly.

5. The aviation AC generator with an initial phase adjustment and limiting structure according to claim 4, characterized in that: The bearing end cover assembly includes: a bearing cover, a first nut is sleeved in the bearing cover mounting hole, the first nut is threadedly connected to the hollow shaft, the bearing cover is located between the phase-fixing washer and the end face of the stator assembly, the bolt passes through the arc-shaped adjustment groove of the outer ring washer to connect the bearing cover and the stator assembly, and the end face of the first nut is provided with an annular mounting groove for installing the inner ring washer, and a plurality of grooves are evenly distributed on the annular mounting groove.

6. The aviation AC generator with an initial phase adjustment and limiting structure according to claim 5, characterized in that: Two sections of threads with opposite rotation directions are arranged on the outer peripheral surface along the axial direction of the first nut.

7. The aviation AC generator with an initial phase adjustment and limiting structure according to claim 6, characterized in that: A second nut is also arranged on the hollow shaft between the generator front end cover and the phase-fixing washer, and a plurality of clamping grooves for clamping with a wrench are arranged on the outer peripheral surface of the second nut.

8. The aviation AC generator with an initial phase adjustment and limiting structure according to claim 2, characterized in that: An exciter rotor assembly is installed on the hollow shaft, and an exciter balance bracket assembly is fixedly mounted on the outer ring of the exciter rotor assembly. A positioning plate is provided on the outer side of the exciter balance bracket assembly. The positioning plate is installed in the rear end cover assembly of the generator, and the end of the positioning plate facing the exciter balance bracket assembly is a pointed end.

9. The aviation AC generator with an initial phase adjustment and limiting structure according to claim 8, characterized in that: The exciter balance bracket assembly includes: a ring member, the end surface of the ring member facing the rear end cover assembly is provided with a ring groove, the ring groove is provided with an opening groove, and the opening groove is used to load the corresponding balancing block from the opening groove according to the balancing amount when the rotor assembly is balanced.

10. An AC power generation system, characterized in that: It comprises a plurality of aviation AC generators with initial phase adjustment and limiting structures as described in any one of claims 1 to 9, and the plurality of aviation AC generators are connected in parallel.

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