Rotor and stator gap measuring device for aviation permanent magnet alternating-current generator

Abstract

The utility model provides a rotor and stator gap measuring device used for an aviation permanent magnet AC generator, comprising a stator, a rotor, a signal processing device, a data acquisition recording device and at least two gap sensors, the stator is provided with at least two sensor mounting seats, and an included angle is arranged between the two sensor mounting seats; the rotor is connected to a driving shaft of the alternating-current generator, the rotor is used for rotating in the stator, and a gap is formed between the rotor and the stator; the gap sensor is arranged in the sensor mounting seat and is used for measuring a gap value between the rotor and the stator in real time; the signal processing equipment is connected or electrically connected with the gap sensor through an optical fiber; and the data acquisition recording equipment is electrically connected with the signal processing equipment. The problems that the rotor and stator gap of a traditional alternating-current generator cannot be measured in real time and the optimal rotor and stator gap value of the alternating-current generator cannot be found out are solved, and after the rotor and stator collision and abrasion fault occurs, the accurate moment when the collision and abrasion fault occurs is found out in a fault reproduction test.

Description

Technical Field

[0001] The utility model relates to the technical field of alternators for aeroengine control systems, and particularly relates to a measuring device for the rotor-stator clearance of an aviation permanent magnet alternator. Background Technique

[0002] Due to the advantages of simple structure, small volume and light weight of the permanent magnet alternator, the aeroengine will use the permanent magnet alternator as the power supply for the engine control system during operation to ensure the power consumption requirements of electrical equipment such as controllers on the engine.

[0003] The permanent magnet alternators used on aeroengines generally use rare earth permanent magnet materials as the rotor, and the coils are wound in the stator housing. To improve the power generation efficiency, the clearance between the rotor and the stator is generally less than 1 mm. The rotor is installed on the rotating shaft and the rotational speed can reach 20,000 - 30,000 revolutions per minute.

[0004] Due to the accumulation of various errors during the manufacturing of the alternator rotor, there is a residual unbalance amount. Moreover, the aeroengine operates in an environment of high temperature and high vibration. In extreme cases, it may cause the distance between the alternator rotor and the axis to be greater than the clearance between the rotor and the stator, resulting in rubbing and damage between the alternator rotor and the stator.

[0005] Therefore, real-time measurement of the rotor-stator clearance of the alternator under full rotational speed and extreme working conditions can effectively identify the main reasons for the deviation of the alternator rotor from the axis and avoid rubbing and damage between the alternator rotor and the stator.

[0006] At present, the permanent magnet alternators on aeroengines mainly have the following technical problems:

[0007] First, to avoid the rubbing fault between the rotor and the stator and ensure the power generation efficiency, the clearance between the alternator rotor and the stator is generally designed to be less than 1 mm according to experience, and it cannot be measured during the ground test. Therefore, the optimal clearance value between the alternator rotor and the stator cannot be found.

[0008] Second, when the rubbing fault between the rotor and the stator occurs in extreme cases, due to the lack of monitoring, the exact moment of the fault occurrence and the trajectory of the alternator rotor at this moment cannot be known.

[0009] In view of this, the inventor of the present application designed a measuring device for the rotor-stator clearance of an aviation permanent magnet alternator in order to overcome the above technical problems. Summary of the Utility Model

[0010] The technical problem to be solved by the present utility model is to overcome the defect that in the prior art, various errors accumulate during the manufacturing of the rotor of an alternator, resulting in a residual unbalance amount. Moreover, when an aeroengine operates in an environment of high temperature and high vibration, in extreme cases, the distance between the rotor of the alternator and the axis may deviate by more than the clearance between the rotor and the stator, thereby causing rubbing between the rotor and the stator of the alternator and resulting in damage. The present utility model provides a rotor-stator clearance measuring device for an aero permanent magnet alternator.

[0011] The present utility model solves the above technical problem through the following technical solutions:

[0012] The present utility model provides a rotor-stator clearance measuring device for an aero permanent magnet alternator, which is characterized in that the clearance measuring device includes a stator, a rotor, a signal processing device, a data acquisition and recording device, and at least two clearance sensors. At least two sensor mounting seats are arranged on the stator, and there is an included angle between the two sensor mounting seats; the rotor is connected to the drive shaft of the alternator, the rotor is used to rotate inside the stator, and there is a clearance between the rotor and the stator; the clearance sensors are arranged in the sensor mounting seats and are used to measure the clearance value between the rotor and the stator in real time; the signal processing device is connected to the clearance sensors through optical fibers or electrically; the data acquisition and recording device is electrically connected to the signal processing device.

[0013] According to one or more embodiments of the present utility model, the stator includes a stator housing and a coil, the sensor mounting seats are arranged on the stator housing, and the coil is arranged inside the stator housing.

[0014] According to one or more embodiments of the present utility model, the included angle between the two sensor mounting seats is 90 degrees.

[0015] According to one or more embodiments of the present utility model, the sensor mounting seats are arranged at one end of the rotor away from the alternator.

[0016] According to one or more embodiments of the present utility model, a sensor mounting hole is opened at the center of the sensor mounting seat for the clearance sensor to extend into the inside of the stator housing, and the sensor mounting seat and the clearance sensor are fixedly connected through a connecting piece.

[0017] According to one or more embodiments of the present utility model, the clearance sensor passes through the coil and extends near the rotor.

[0018] According to one or more embodiments of the present utility model, a gasket is arranged between the clearance sensor and the sensor mounting seat.

[0019] According to one or more embodiments of the present utility model, the gap between the probe of the gap sensor and the rotor is 0.1 mm to 5 mm.

[0020] According to one or more embodiments of the present utility model, the gap sensor is a fiber optic gap sensor, and the signal processing device is connected to the gap sensor through an optical fiber.

[0021] According to one or more embodiments of the present utility model, the gap sensor is a capacitive gap sensor or an eddy current gap sensor, and the signal processing device is electrically connected to the gap sensor through a low-noise signal cable.

[0022] The positive and progressive effects of the present utility model are as follows:

[0023] The stator-rotor gap measuring device for an aviation permanent magnet alternator of the present utility model has at least the following advantages:

[0024] First, the gap measuring device of the present utility model can monitor the stator-rotor gap of the alternator in real time, which is convenient for finding the optimal stator-rotor gap value of the alternator.

[0025] Second, by monitoring the stator-rotor gap of the alternator in real time, emergency measures can be taken to avoid rubbing when the gap becomes abnormally small. Description of the Drawings

[0026] The above-mentioned and other features, properties, and advantages of the present utility model will become more obvious through the following description in conjunction with the drawings and embodiments. In the drawings, the same reference numerals always represent the same features, where:

[0027] Figure 1 is a schematic structural diagram of the stator of the stator-rotor gap measuring device for an aviation permanent magnet alternator of the present utility model.

[0028] Figure 2 is a schematic sectional structural diagram of the stator-rotor gap measuring device for an aviation permanent magnet alternator of the present utility model.

[0029] Figure 3 is a schematic diagram of the installation angle of the gap sensor of the stator-rotor gap measuring device for an aviation permanent magnet alternator of the present utility model.

[0030] Figure 4 is a schematic structural diagram of the sensor mounting seat of the stator-rotor gap measuring device for an aviation permanent magnet alternator of the present utility model.

[0031]

Reference Numerals

[0032] Stator 100

[0033] Stator housing 110

[0034] Sensor mounting base 111

[0035] First sensor mounting base 111a

[0036] Second sensor mounting base 111b

[0037] Sensor mounting hole 112

[0038] Connecting piece 113

[0039] Coil 120

[0040] Rotor 200

[0041] Signal processing device 300

[0042] Sensor cable 310

[0043] Data acquisition and recording device 400

[0044] Transmission cable 410

[0045] Gap sensor 500

[0046] First gap sensor 500a

[0047] Second gap sensor 500b

[0048] Gasket 510 Detailed implementation manners

[0049] To make the above objects, features and advantages of the present utility model more obvious and understandable, the following detailed description of the specific implementation manners of the present utility model is provided in conjunction with the accompanying drawings.

[0050] Embodiments of the present utility model will now be described in detail with reference to the drawings. Preferred embodiments of the present utility model will now be described in detail, and examples thereof are shown in the drawings. Whenever possible, the same reference numerals will be used throughout the drawings to refer to the same or like parts. In addition, although the terms used in the present utility model are selected from well-known and commonly used terms, some of the terms mentioned in the specification of the present utility model may be selected by the applicant according to his or her judgment, and their detailed meanings are described in the relevant parts of the description herein. In addition, it is required to understand the present utility model not only through the actual terms used, but also through the meaning implied by each term.

[0051] As Figures 1 to 4 shown, the present utility model provides a rotor-stator gap measuring device for an aviation permanent magnet alternator, and the gap measuring device includes a stator 100, a rotor 200, a signal processing device 300, a data acquisition and recording device 400, and at least two gap sensors 500.

[0052] At least two sensor mounts 111 are provided on the stator 100, and there is an included angle between the two sensor mounts 111;

[0053] The rotor 200 is connected to the drive shaft of the alternator and is used to rotate inside the stator 100. There is a gap between the rotor 200 and the stator 100;

[0054] The gap sensor 500 is arranged inside the sensor mount 111 and is used to measure the gap value between the rotor 200 and the stator 100 in real time;

[0055] The signal processing device 300 is connected to the gap sensor 500 by optical fiber or electrically;

[0056] The data acquisition and recording device 400 is electrically connected to the signal processing device 300.

[0057] The rotor 200 of the alternator is installed on the alternator drive shaft of the engine accessory gearbox and is driven by the engine to rotate, generating a rotating magnetic field.

[0058] The gap sensor 500 extends near the rotor 200 of the alternator to ensure that the gap between the rotor 200 and the stator 100 is within the measurement range of the gap sensor 500. Compared with the scheme of using only one gap sensor 500 to measure the gap change in one direction, the scheme of using two gap sensors 500 arranged at an included angle can measure the deflection distances of the rotor 200 of the alternator in two directions at the same time. Therefore, the deflection trajectory of the rotor 200 of the alternator can be drawn in real time.

[0059] Preferably, the signal processing device 300 processes the signal generated by the gap sensor 500 into a voltage value of 0 to 10V. The data acquisition and recording device 400 can record the voltage value in real time. Through the corresponding relationship between the gap and the voltage, the real-time monitoring of the gap between the rotor and stator of the alternator can be realized.

[0060] According to the cooling method of the alternator, different types of gap sensors 500 are selected. Preferably, when the alternator uses ventilation cooling, a capacitive or fiber optic gap sensor can be used; when the alternator uses oil cooling, an eddy current gap sensor can be used.

[0061] The signal processing device 300 is preferably connected to the gap sensor 500 through a sensor cable 310, and the data acquisition and recording device 400 is preferably connected to the signal processing device 300 through a transmission cable 410.

[0062] The stator-rotor clearance measuring device for an aviation permanent magnet alternator of the present utility model solves the problems that the stator-rotor clearance of a traditional alternator cannot be measured in real time and the optimal stator-rotor clearance value of the alternator cannot be found. It can also find the exact moment when the stator-rotor rubbing fault occurs in the fault reproduction test when the stator-rotor rubbing fault occurs in the alternator, so as to support finding out the cause of the problem.

[0063] As Figures 1 to 4 shown, as a preferred embodiment of the stator-rotor clearance measuring device for an aviation permanent magnet alternator of the present utility model, the stator 100 includes a stator housing 110 and a coil 120. A sensor mounting seat 111 is provided on the stator housing 110, and the coil 120 is provided inside the stator housing 110.

[0064] The stator housing 110 of the alternator is installed on the engine accessory gearbox casing, and the coil 120 inside it cuts the magnetic field to generate electromotive force.

[0065] As Figures 1 to 4 shown, as a preferred embodiment of the stator-rotor clearance measuring device for an aviation permanent magnet alternator of the present utility model, the included angle between the two sensor mounting seats 111 is 90 degrees.

[0066] As Figure 1 shown, the sensor mounting seat 111 includes a first sensor mounting seat 111a and a second sensor mounting seat 111b, and the included angle between the first sensor mounting seat 111a and the second sensor mounting seat 111b is 90 degrees. As Figure 3 shown, a first gap sensor 500a is arranged inside the first sensor mounting seat 111a, and a second gap sensor 500b is arranged inside the second sensor mounting seat 111b, so that the first gap sensor 500a and the second gap sensor 500b are arranged at 90 degrees. The first sensor mounting seat 111a is preferably arranged at the top of the stator housing 110, so that the first gap sensor 500a arranged inside the first sensor mounting seat 111a can measure the longitudinal deflection distance of the rotor 200; the second sensor mounting seat 111b is preferably arranged on the side of the stator housing 110, so that the second gap sensor 500b arranged inside the second sensor mounting seat 111b can measure the lateral deflection distance of the rotor 200.

[0067] The scheme of arranging two sensors at 90 degrees can measure the lateral and longitudinal deflection distances of the rotor 200 of the alternator at the same time, so the deflection trajectory of the rotor 200 of the alternator can be drawn in real time.

[0068] As Figures 1 to 4As shown in the figure, as a preferred embodiment of the rotor-stator gap measuring device for an aviation permanent magnet alternator of the present utility model, the sensor mounting base 111 is arranged at one end of the rotor 200 away from the alternator.

[0069] Since the alternator on the engine is mounted in a cantilever beam manner, the deflection of the distal end of the rotor 200 of the alternator is the most severe during operation. Therefore, the sensor mounting base 111 is preferably located at the distal end of the housing of the alternator, facing the distal end of the rotor 200 of the alternator.

[0070] As Figures 1 to 4 shown in the figure, as a preferred embodiment of the rotor-stator gap measuring device for an aviation permanent magnet alternator of the present utility model, a sensor mounting hole 112 is provided at the center of the sensor mounting base 111 for the gap sensor 500 to extend into the interior of the stator housing 110, and the sensor mounting base 111 and the gap sensor 500 are fixedly connected through a connecting member 113.

[0071] A sensor mounting hole 112 is provided at the center of the mounting base as the insertion hole for the gap sensor 500, and there are also 4 connecting screws as the connecting member 113 for connecting the gap sensor 500 and the sensor mounting base 111.

[0072] As Figures 1 to 4 shown in the figure, as a preferred embodiment of the rotor-stator gap measuring device for an aviation permanent magnet alternator of the present utility model, the gap sensor 500 passes through the coil 120 and extends near the rotor 200.

[0073] As Figures 1 to 4 shown in the figure, as a preferred embodiment of the rotor-stator gap measuring device for an aviation permanent magnet alternator of the present utility model, a gasket 510 is provided between the gap sensor 500 and the sensor mounting base 111.

[0074] As Figures 1 to 4 shown in the figure, as a preferred embodiment of the rotor-stator gap measuring device for an aviation permanent magnet alternator of the present utility model, the gap between the probe of the gap sensor 500 and the rotor 200 is 0.1 mm to 5 mm.

[0075] The gap sensor 500 passes through the coil 120 and extends near the rotor 200 of the alternator. A gasket 510 is used to adjust the distance between the gap sensor 500 and the sensor mounting base 111, so that the gap between the probe of the gap sensor 500 and the rotor 200 of the alternator is adjustable within the range of 0.1 mm to 5 mm to adapt to different alternator sizes.

[0076] As Figures 1 to 4As shown, as a preferred embodiment of the rotor-stator gap measuring device for an aviation permanent magnet alternator of the present utility model, the gap sensor 500 is a fiber optic type gap sensor, and the signal processing device 300 is connected to the gap sensor 500 through an optical fiber.

[0077] As Figures 1 to 4 As shown, as a preferred embodiment of the rotor-stator gap measuring device for an aviation permanent magnet alternator of the present utility model, the gap sensor 500 is a capacitive gap sensor or an eddy current type gap sensor, and the signal processing device 300 is electrically connected to the gap sensor 500 through a low-noise signal cable.

[0078] The gap sensor 500 can be of fiber optic type, capacitive type, or eddy current type according to the usage environment. For example, according to the cooling method of the alternator, the selected type of the gap sensor 500 is different. Preferably, when the alternator uses ventilation cooling, a capacitive or fiber optic type gap sensor can be used; when the alternator uses oil cooling, an eddy current type gap sensor can be used.

[0079] Preferably, the gap signal measured by the gap sensor 500 is transmitted to the signal processing device 300 through the sensor cable 310. If the selected type is a fiber optic type gap sensor, the sensor cable 310 is an optical fiber cable; if the selected type is a capacitive or eddy current type gap sensor, the sensor cable 310 is a low-noise signal cable.

[0080] The signal processing device 300 is responsible for providing the excitation source for the gap sensor 500, and at the same time processes the optical signal or electrical signal fed back by the gap sensor 500 into a standard voltage signal. The smaller the gap between the probe of the gap sensor 500 and the rotor 200 of the alternator, the larger the voltage signal; conversely, the larger the gap between the probe of the gap sensor 500 and the rotor 200 of the alternator, the smaller the voltage signal.

[0081] The data acquisition and recording device 400 is preferably connected to the signal processing device 300 through a transmission cable 410. The transmission cable 410 can use a communication cable to transmit the collected voltage value to the data acquisition and recording device 400 for real-time display and recording. This voltage signal can be calibrated in advance by a standard gap test bench to obtain the corresponding relationship between the voltage value and the gap value. Therefore, the real-time acquisition, display, and recording of the rotor-stator gap of the alternator can be realized.

[0082] When using the gap measuring device of one of the preferred solutions of the rotor-stator gap measuring device for an aviation permanent magnet alternator of the present utility model to measure the gap, the measurement steps are as follows:

[0083] Step S1: Install the rotor 200 of the alternator on the rotor drive shaft of the alternator.

[0084] Step S2: Install the gap sensor 500 onto the sensor mounting seat 111 of the stator housing 110 of the alternator.

[0085] Step S3: Install the stator 100 of the alternator on the engine accessory case or other mounting surfaces.

[0086] Step S4: Connect the gap sensor 500 and the signal processing device 300 using the sensor cable 310.

[0087] Step S5: Connect the signal processing device 300 and the data acquisition and recording device 400 using the transmission cable 410.

[0088] Step S6: Turn on the power supplies of the signal processing device 300 and the data acquisition and recording device 400, and the gap measurement device starts to work.

[0089] When the rotor 200 of the alternator rotates, due to the deflection of the rotor shaft of the alternator in actual operation, by measuring the gap between the probe of the gap sensor 500 and the rotor 200 of the alternator in real time, the deflection value of the rotor 200 of the alternator can be recorded in real time.

[0090] During the test run of a certain type of engine, a stator-rotor rubbing fault occurred in the alternator. Since the stator-rotor gap of the engine alternator cannot be directly observed after installation, in order to investigate the cause of the fault, the stator-rotor gap measurement device for an aviation permanent magnet alternator of the present utility model was used to monitor the stator-rotor gap of the running alternator in real time according to the above measurement steps. It was found that the stator-rotor gap of the alternator decreased abnormally at a specific frequency, which was analyzed to be caused by the deflection of the rotor drive shaft of the alternator due to resonance, thus realizing fault location and supporting subsequent improvements.

[0091] The stator-rotor gap measurement device for an aviation permanent magnet alternator of the present utility model uses the gap sensor 500 to measure the gap between the stator and rotor of the alternator in real time, and can measure the gap between the stator and rotor of the alternator within the full speed range and various working conditions of the alternator, so as to find the maximum deflection amount of the rotor of the alternator and further set the most appropriate stator-rotor gap of the alternator.

[0092] By using the gap sensor 500 in the gap measurement device of the present utility model to measure the gap between the stator and rotor of the alternator in real time, the abnormal moment of the stator-rotor gap of the alternator can be accurately monitored and an alarm can be given in time.

[0093] In summary, the stator-rotor gap measurement device for an aviation permanent magnet alternator of the present utility model has the following many beneficial effects:

[0094] 1. The clearance measuring device of the present utility model can monitor the clearance between the rotor and stator of the alternator in real time, facilitating the finding of the optimal clearance value between the rotor and stator of the alternator.

[0095] 2. By monitoring the clearance between the rotor and stator of the alternator in real time, emergency measures can be taken to avoid rubbing when the clearance becomes abnormally small.

[0096] Although the specific implementation manners of the present utility model have been described above, those skilled in the art should understand that these are only examples. The protection scope of the present utility model is defined by the appended claims. Without departing from the principles and essence of the present utility model, those skilled in the art can make various changes or modifications to these implementation manners, but these changes and modifications all fall within the protection scope of the present utility model.

Claims

1. A rotor-stator gap measuring device for an aviation permanent magnet AC generator, characterized in that: The gap measuring device includes a stator, a rotor, a signal processing device, a data acquisition and recording device, and at least two gap sensors. At least two sensor mounting seats are arranged on the stator, and an angle is formed between the two sensor mounting seats; The rotor is connected to a driving shaft of the AC generator, the rotor is used to rotate inside the stator, and there is a gap between the rotor and the stator; The gap sensor is arranged in the sensor mounting seat and is used for measuring the gap value between the rotor and the stator in real time; The signal processing device is connected to the gap sensor via an optical fiber or electrically; The data acquisition and recording device is electrically connected to the signal processing device.

2. The rotor-stator gap measuring device for an aviation permanent magnet alternator according to claim 1, characterized in that: The stator comprises a stator housing and a coil. The sensor mounting seat is arranged on the stator housing, and the coil is arranged in the stator housing.

3. The rotor-stator gap measuring device for an aviation permanent magnet AC generator according to claim 1, characterized in that: The angle between the two sensor mounting seats is 90 degrees.

4. The rotor-stator gap measuring device for an aviation permanent magnet alternator according to claim 1, characterized in that: The sensor mounting seat is arranged at an end of the rotor away from the AC generator.

5. The rotor-stator gap measuring device for an aviation permanent magnet alternator according to claim 2, characterized in that: A sensor mounting hole is provided at the center of the sensor mounting seat for allowing the gap sensor to extend into the interior of the stator housing. The sensor mounting seat is fixedly connected to the gap sensor via a connecting piece.

6. The rotor-stator gap measuring device for an aviation permanent magnet alternator according to claim 5, characterized in that: The gap sensor extends through the coil to the vicinity of the rotor.

7. The rotor-stator gap measuring device for an aviation permanent magnet alternator according to claim 6, characterized in that: A gasket is arranged between the gap sensor and the sensor mounting seat.

8. The rotor-stator gap measuring device for an aviation permanent magnet alternator according to claim 6, characterized in that: The gap between the probe of the gap sensor and the rotor is 0.1 mm to 5 mm.

9. The rotor-stator gap measuring device for an aviation permanent magnet alternator according to claim 1, characterized in that: The gap sensor is an optical fiber gap sensor, and the signal processing device is connected to the gap sensor via an optical fiber.

10. The rotor-stator gap measuring device for an aviation permanent magnet alternator according to claim 1, characterized in that: The gap sensor is a capacitive gap sensor or an eddy current gap sensor, and the signal processing device is electrically connected to the gap sensor via a low-noise signal cable.

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