Dynamic balancing test platform and dynamic balancing test measurement point selection method

Abstract

The present application proposes a dynamic balancing experiment platform and a method for selecting measurement points for a dynamic balancing experiment. The dynamic balancing experiment platform comprises: a bearing seat, the bearing seat being used to support a rotor to be measured (100), the rotor to be measured (100) comprising a wheel group; and a displacement sensor, the displacement sensor being used to measure the vibration displacement of the rotor to be measured (100) at a point to be measured, wherein a plurality of displacement sensors are provided, and the displacement sensors include a displacement sensor for measuring the rotor to be measured (100) near the bearing seat and a displacement sensor for measuring the wheel group.

Description

Technical Field

[0001] The present application relates to an experimental inspection device for a rotor, and in particular to a dynamic balancing experimental platform and a method for selecting measurement points for a dynamic balancing experiment. Background Art

[0002] Rotors are widely used in various fields of industrial production. Due to factors such as machining errors, processing technology, and assembly accuracy, rotors inevitably have initial imbalance after assembly. Once this imbalance exceeds a certain limit, it may not only cause the rotor structure to bend, but also generate large vibrations during operation, which can easily cause damage to the rotor structure and bearings, leading to accidents. Therefore, rotor dynamic balancing tests are required before actual use to ensure that the rotor vibration is within a reasonable allowable range.

[0003] For general rigid rotors, they often operate below the first-order critical speed. Therefore, dynamic balancing of the rotor only needs to be tested at the operating speed. However, for heavy-duty gas turbine rotors, their operating speed is usually above the second-order critical speed of the rotor system, and the rotor in this case is usually a flexible rotor. When accelerating to the operating speed, it is necessary to cross the first-order and second-order critical speeds. Therefore, there are more stringent requirements for the dynamic balancing of the rotor. Not only must the vibration caused by the unbalanced mass of the rigid body of the rotor itself be reduced, but the vibration caused by resonance when the rotor crosses the critical speed must also be controlled.

[0004] Since gas turbine rotors are typically large and expensive to manufacture, it is often unrealistic to conduct dynamic balancing tests and research on actual gas turbine rotors. Therefore, conducting dynamic balancing tests and research on gas turbine rotor models under laboratory conditions is an important dynamic balancing research method.

[0005] Currently, there are many rotor dynamic balancing test systems. However, these test systems still have the following shortcomings:

[0006] 1. The existing rotor dynamic balancing test system can perform dynamic balancing tests on rigid rotors and first-order critical speeds, but it is difficult to perform dynamic balancing tests on rotors at second-order critical speeds.

[0007] Second, existing rotor dynamic balancing test systems, such as sensors and other measuring equipment, often need to be connected to the dynamic balancing equipment or computer using wired connections, which is complicated to use. Summary of the Invention

[0008] This application aims to propose a dynamic balancing experimental platform that can achieve dynamic balancing of the rotor's first-order and higher-order critical speeds based on the rigid body unbalanced mass of the rotor to be tested and the vibration mode of the rotor.

[0009] This application proposes a dynamic balancing experimental platform, which includes:

[0010] a bearing seat, the bearing seat being used to support a rotor to be tested, the rotor to be tested comprising a wheel assembly; and

[0011] A displacement sensor is used to measure the vibration displacement of the rotor to be measured at the measured point. There are multiple displacement sensors, including a displacement sensor for measuring the rotor to be measured near the bearing seat and a displacement sensor for measuring the wheel assembly.

[0012] Preferably, the wheel disc group includes a plurality of wheel discs, and the displacement sensor for measuring the wheel disc group includes two displacement sensors respectively aligned with two wheel discs at two axial ends of the wheel disc group.

[0013] Preferably, the rotor to be measured includes a plurality of wheel disc groups and a connecting shaft connecting two adjacent wheel disc groups, and the displacement sensor includes a displacement sensor aligned with the connecting shaft.

[0014] Preferably, the displacement sensor comprises:

[0015] a displacement sensor of the shaft aligned to the side of the bearing seat; and

[0016] A displacement sensor is aligned at a position where the ratio of the shaft equivalent radius of the rotor to be measured to the shaft radius at the mounting bearing of the rotor to be measured is greater than 5.

[0017] Preferably, the displacement sensor is not provided at a position where the first-order or higher-order amplitude of the rotor to be measured is less than one-fifth of the maximum value of the first-order or higher-order amplitude of the rotor to be measured.

[0018] Preferably, the dynamic balancing experimental platform further includes a Hall sensor, the rotor to be tested includes a key phase device, and the Hall sensor is aligned with the key phase device.

[0019] The present application also proposes a method for selecting measuring points for a dynamic balancing experiment. The dynamic balancing experiment is used to measure a rotor to be measured. The rotor to be measured is supported by a bearing seat and includes a wheel assembly. The method for selecting measuring points for the dynamic balancing experiment includes:

[0020] Selecting a position corresponding to the vicinity of the bearing seat;

[0021] selecting a position corresponding to the set of roulette wheels; and

[0022] A position is selected where the ratio of the shaft equivalent radius of the rotor to be measured to the shaft radius at the mounting bearing of the rotor to be measured is greater than 5.

[0023] Preferably, the method for selecting measurement points for the dynamic balancing experiment further comprises: selecting a position corresponding to a connecting shaft, wherein the connecting shaft is used to connect two adjacent wheel disc groups.

[0024] Preferably, the positions of the two wheel discs corresponding to the axial ends of the wheel disc group are selected.

[0025] Preferably, among the measuring points, measuring points where the first-order or higher-order amplitude of the rotor to be measured is less than one-fifth of the maximum value of the first-order or higher-order amplitude of the rotor to be measured are excluded.

[0026] By adopting the above technical solution, displacement sensors are set at multiple specific positions of the rotor to be tested for detection. Through the data obtained, the rigid body balance, first-order and high-order dynamic balance of the rotor can be achieved. BRIEF DESCRIPTION OF THE DRAWINGS

[0027] Figure 1 A structural schematic diagram of a dynamic balancing experimental platform for conducting an experiment on a rotor to be tested according to an embodiment of the present application is shown.

[0028] Figure 2 The figure shows the structural diagram of the turbine wheel disc group of the rotor to be tested.

[0029] Figure 3 The figure shows the structure of the first-stage turbine disc of the turbine disc group of the rotor to be tested.

[0030] Figure 4 A schematic structural diagram of the fourth-stage turbine disc of the turbine disc assembly of the rotor to be tested is shown.

[0031] Figure 5 A schematic structural diagram of the compressor wheel assembly of the rotor to be tested is shown.

[0032] Figure 6 A schematic structural diagram of the first-stage compressor wheel of the compressor wheel assembly of the rotor to be tested is shown.

[0033] Figure 7 A schematic structural diagram of the fourth-stage compressor wheel of the compressor wheel group of the rotor to be tested is shown.

[0034] Description of Reference Numerals

[0035] 100 Rotor to be tested 101 Turbine shaft

[0036] 102 Turbine disc assembly 102A First stage turbine disc 102A1 First stage turbine disc dynamic balancing hole 102B Second stage turbine disc 102C Third stage turbine disc 102D Fourth stage turbine disc 102D1 Fourth stage turbine disc dynamic balancing hole

[0037] 103 connecting shaft

[0038] 104 Compressor wheel assembly 104A First stage compressor wheel 104A1 First stage compressor wheel dynamic balancing hole 104B Second stage compressor wheel 104C Third stage compressor wheel 104D Fourth stage compressor wheel 104D1 Fourth stage compressor wheel dynamic balancing hole

[0039] 105 Compressor shaft 106 Key phase device

[0040] 1 Base 11 First bearing seat 12 Second bearing seat

[0041] 2 Drive motor 21 Coupling

[0042] 3. Frequency Converter

[0043] 4 Laser displacement sensor 41 First laser displacement sensor 42 Second laser displacement sensor 43 Third laser displacement sensor 44 Fourth laser displacement sensor 45 Fifth laser displacement sensor 46 Sixth laser displacement sensor 47 Seventh laser displacement sensor

[0044] 5 Hall sensor

[0045] 6 Signal acquisition module

[0046] 7 Computational Analysis Module

[0047] 8 Wireless transmission module

[0048] C Circumferential DETAILED DESCRIPTION

[0049] In order to more clearly illustrate the above-mentioned purposes, features and advantages of the present application, this section describes in detail the specific embodiments of the present application in conjunction with the accompanying drawings. In addition to the various embodiments described in this section, the present application can also be implemented in other different ways. Without violating the spirit of the present application, those skilled in the art can make corresponding improvements, deformations and substitutions. Therefore, the present application is not limited to the specific embodiments disclosed in this section. The scope of protection of this application shall be based on the claims.

[0050] like Figures 1 to 7 As shown, the present application proposes a dynamic balancing experimental platform, which includes a base 1, a drive motor 2, a frequency converter 3, a displacement sensor, a Hall sensor 5, a signal acquisition module 6, a calculation and analysis module 7, a wireless transmission module 8 and a computer 9.

[0051] The dynamic balancing experimental platform is used to perform a dynamic balancing test experiment on the rotor 100 to be tested. In this embodiment, the rotor 100 to be tested is used to simulate a gas turbine rotor.

[0052] like Figure 1 As shown, the rotor to be tested 100 may include a turbine shaft 101, a turbine wheel assembly 102, a connecting shaft 103, a compressor wheel assembly 104, a compressor shaft 105, and a key phaser 106. The turbine shaft 101 is connected to the turbine wheel assembly 102, the two ends of the connecting shaft 103 are respectively connected to the turbine wheel assembly 102 and the compressor wheel assembly 104, the compressor shaft 105 is connected to the compressor wheel assembly 104, and the key phaser 106 may be connected to the compressor shaft 105.

[0053] like Figures 2 to 4 As shown, the turbine wheel assembly 102 includes a first-stage turbine wheel 102A, a second-stage turbine wheel 102B, a third-stage turbine wheel 102C, and a fourth-stage turbine wheel 102D. The first-stage turbine wheel 102A, the second-stage turbine wheel 102B, the third-stage turbine wheel 102C, and the fourth-stage turbine wheel 102D may be coaxially connected together. The first-stage turbine wheel 102A and the fourth-stage turbine wheel 102D are located at axial ends of the turbine wheel assembly 102. The first-stage turbine wheel 102A may be provided with a plurality of first-stage turbine wheel dynamic balancing holes 102A1 located at the outer edge of the first-stage turbine wheel 102A. The plurality of first-stage turbine wheel dynamic balancing holes 102A1 may be arranged along the circumference C of the first-stage turbine wheel 102A. The fourth-stage turbine disc 102D may be provided with a plurality of fourth-stage turbine disc dynamic balancing holes 102D1. The fourth-stage turbine disc dynamic balancing holes 102D1 may be located at the outer edge of the fourth-stage turbine disc 102D and may be arranged along the circumferential direction C of the fourth-stage turbine disc 102D. The first-stage turbine disc dynamic balancing holes 102A1 and the fourth-stage turbine disc dynamic balancing holes 102D1 may each be provided with greater than or equal to 60. The first-stage turbine disc dynamic balancing holes 102A1 and the fourth-stage turbine disc dynamic balancing holes 102D1 are used to connect dynamic balancing components, such as bolts.

[0054] like Figures 5 to 7As shown, the compressor wheel assembly 104 includes a first-stage compressor wheel 104A, a second-stage compressor wheel 104B, a third-stage compressor wheel 104C, and a fourth-stage compressor wheel 104D. The first-stage compressor wheel 104A, the second-stage compressor wheel 104B, the third-stage compressor wheel 104C, and the fourth-stage compressor wheel 104D may be coaxially connected together. The first-stage compressor wheel 104A and the fourth-stage compressor wheel 104D are located at the axial ends of the compressor wheel assembly 104. The first-stage compressor impeller 104A may be provided with a plurality of first-stage compressor impeller dynamic balancing holes 104A1. The first-stage compressor impeller dynamic balancing holes 104A1 may be located at the outer edge of the first-stage compressor impeller 104A and may be arranged along the circumferential direction C of the first-stage compressor impeller 104A. The fourth-stage compressor impeller 104D may be provided with a plurality of fourth-stage compressor impeller dynamic balancing holes 104D1. The fourth-stage compressor impeller dynamic balancing holes 104D1 may be located at the outer edge of the fourth-stage compressor impeller 104D and may be arranged along the circumferential direction C of the fourth-stage compressor impeller 104D. The number of the first-stage compressor impeller dynamic balancing holes 104A1 and the fourth-stage compressor impeller dynamic balancing holes 104D1 can be set to be greater than or equal to 60. The first-stage compressor impeller dynamic balancing holes 104A1 and the fourth-stage compressor impeller dynamic balancing holes 104D1 are used to connect dynamic balancing parts such as bolts.

[0055] It can be understood that in this embodiment, the turbine wheel group 102 and the compressor wheel group 104 both include 4 wheel structures. However, in other possible embodiments, the number of wheel structures of the turbine wheel group and the compressor wheel group may be more or less, and the number of wheel structures of the turbine wheel group and the compressor wheel group may be the same or different.

[0056] The base 1 is provided with a first bearing seat 11 and a second bearing seat 12. Both the first bearing seat 11 and the second bearing seat 12 are equipped with bearings. The bearings are mounted on the rotor 100 to be tested, so that the first bearing seat 11 and the second bearing seat 12 support the rotor 100 to be tested. The first bearing seat 11 can be used to support the turbine shaft 101, and the second bearing seat 12 can be used to support the compressor shaft 105.

[0057] It can be understood that in this embodiment, the rotor to be tested 100 is supported by the first bearing seat 11 and the second bearing seat 12 , while in other possible embodiments, a greater number of bearing seats may be used to support the rotor to be tested.

[0058] The rotor 100 to be tested can be connected to the output shaft of the drive motor 2 via the coupling 21, so that the drive motor 2 drives the rotor 100 to rotate. The inverter 3 is connected to the drive motor 2 and can control the drive motor 2 to rotate at a set speed required for the experiment.

[0059] The displacement sensor may be a laser displacement sensor 4 , which can measure the displacement of the rotor 100 to be measured during rotation in a non-contact manner.

[0060] It can be understood that the high-order critical speed includes the second-order critical speed, the third-order critical speed and higher-order critical speeds. In the following description, the high-order critical speed is sometimes referred to as high-order.

[0061] The positions and number of the measuring points of the laser displacement sensor 4 can be obtained in the following manner.

[0062] (Step 1) Determine the number C of diameter mutation structures of the rotor shaft (including the turbine shaft 101, the connecting shaft 103 and the compressor shaft 105) of the rotor to be tested 100 S A sudden diameter change structure refers to a ratio Pi of the equivalent radius of the rotor 100 to the shaft radius at the mounting bearing of the rotor 100 being greater than 5. When the sudden diameter change structure includes an irregular non-rotating structure, the radius is difficult to measure directly, and the equivalent radius can be calculated from the moment of inertia.

[0063] It can be understood that the sudden diameter change structure of the rotor 100 to be measured may affect the dynamic balance, so a laser displacement sensor is required to measure the position.

[0064] (Step 2) Determine the number C of rotor disc groups comb , the number of roulette wheels in the roulette wheel group is Ni, among which the number of roulette wheel groups with Ni greater than 1 is C comb1 ; The number of roulette sets with Ni equal to 1 is C comb2 .

[0065] It can be understood that for a wheel group with a single wheel, a displacement sensor needs to be arranged. For a wheel group with multiple wheels, a displacement sensor needs to be arranged on each of the two wheels at the axial ends of the wheel axle group, so that the dynamic balancing test platform can achieve high-order dynamic balancing of the rotor 100 to be tested.

[0066] (Step 3) Determine the number C of bearing seats supporting the rotor 100 to be tested b .

[0067] (Step 4) Using the bearing seat position of the rotor 100 to be tested as the calculation node, calculate the vibration modes of the rotor 100 to be tested that need to be balanced, and obtain the following parameters

[0068] Calculate the maximum value A of the vibration amplitude of each order of the rotor max, calculate the diameter mutation structure of the rotor 100 to be tested and the amplitude A of the corresponding measuring point position of the wheel. Statistical rotor amplitude A of each order is less than 1 / 5A max The number of corresponding measuring points C a This step can filter out measuring points with smaller amplitudes, that is, measuring points that have little impact on dynamic balance.

[0069] C s 、C comb1 、C comb2 、C b 、C a The steps 1 to 4 can be obtained in any order.

[0070] (Step 5) Determine the total number of laser displacement sensor measurement points required, L total , where L total The calculation is as follows:

[0071] L total =C s +2C comb1 +C comb2 +C b -C a

[0072] In this embodiment, the laser displacement sensor 4 includes a first laser displacement sensor 41 , a second laser displacement sensor 42 , a third laser displacement sensor 43 , a fourth laser displacement sensor 44 , a fifth laser displacement sensor 45 , a sixth laser displacement sensor 46 and a seventh laser displacement sensor 47 .

[0073] The first laser displacement sensor 41 can be installed near the first bearing seat 11 , and the first laser displacement sensor 41 is aligned with the turbine shaft 101 near the first bearing seat 11 , and is used to monitor the vibration amplitude and phase of the turbine shaft 101 near the first bearing seat 11 .

[0074] The second laser displacement sensor 42 may be aimed at the fourth-stage turbine disk 102D of the turbine disk assembly 102 to monitor the vibration amplitude and phase of the fourth-stage turbine disk 102D.

[0075] The third laser displacement sensor 43 can be aimed at the first-stage turbine disk 102A of the turbine disk assembly 102 to monitor the vibration amplitude and phase of the first-stage turbine disk 102A.

[0076] The fourth laser displacement sensor 44 may be aligned with the connecting shaft 103 to monitor the vibration amplitude and phase of the connecting shaft 103 .

[0077] The fifth laser displacement sensor 45 may be aimed at the fourth-stage compressor wheel 104D of the compressor wheel assembly 104 to monitor the vibration amplitude and phase of the fourth-stage compressor wheel 104D.

[0078] The sixth laser displacement sensor 46 may be aligned with the first-stage compressor wheel 104A of the compressor wheel assembly 104 to monitor the vibration amplitude and phase of the first-stage compressor wheel 104A.

[0079] The seventh laser displacement sensor 47 can be installed near the second bearing seat 12 , and the seventh laser displacement sensor 47 is aligned with the compressor shaft 105 near the second bearing seat 12 to monitor the vibration amplitude and phase of the compressor shaft 105 near the second bearing seat 12 .

[0080] Signal acquisition module 6 is connected to the seven laser displacement sensors 4 and the Hall effect sensors 5. It can synchronously collect pulse signals from the Hall effect sensors 5 and the vibration electrical signals from the laser displacement sensors 4. A calculation and analysis module 7 is connected to signal acquisition module 6. This module can calculate and analyze the amplitude and phase of the vibration displacement signals at each measurement point of the laser displacement sensors 4 in real time. A wireless transmission module 8 is connected to this module. This module can wirelessly transmit the amplitude and phase information calculated by this module to a computer 9.

[0081] (Working process of measuring the rotor to be tested using the dynamic balancing experimental platform of this application)

[0082] The drive motor 2, whose speed is controlled by a frequency converter 3, can rotate the rotor 100 under test and accelerate it to near the first-order critical speed. The pulse electrical signals collected by the Hall effect sensor 5 are output to the signal acquisition module 6, and the vibration electrical signals collected by the laser displacement sensors at each measuring point are simultaneously output to the signal acquisition module 6. The signal acquisition module 6 outputs the collected pulse electrical signals and vibration electrical signals to the calculation and analysis module 7, which calculates the speed of the rotor 100 under test and the vibration amplitude and phase at each laser displacement sensor measuring point based on the pulse electrical signals and vibration electrical signals. This data is transmitted to the computer 9 via the wireless transmission module 8, which calculates the dynamic balancing mass and phase required for dynamic balancing at that speed. Based on the calculated data, dynamic balancing parts are installed at the corresponding locations of the first-stage compressor wheel dynamic balancing hole 104A1, the fourth-stage compressor wheel dynamic balancing hole 104D1, the first-stage turbine wheel dynamic balancing hole 102A1, and the fourth-stage turbine wheel dynamic balancing hole 102D1 to increase the balancing mass. Thus, dynamic balancing at the first critical speed is completed. The inverter 3 then controls the drive motor 2 to increase the speed of the rotor 100 to near the second critical speed. The above steps are repeated to balance at the second critical speed. After balancing is complete, the inverter 3 can continue to control the drive motor 2 to increase the speed of the rotor 100 to above the second critical speed.

[0083] The present application comprehensively considers the structure and simulated vibration mode of the rotor 100 to be tested to determine the number and position of the measuring points of the displacement sensor. In this way, the measuring points can be arranged at positions where vibration is greater due to the vibration mode of the rotor, and a high-order dynamic balancing test can be performed on the rotor 100 to be tested, thereby achieving a better dynamic balancing effect.

[0084] The dynamic balancing experimental platform of this application has the following advantages:

[0085] 1. This application obtains the number and positions of measuring points by calculation based on the structure of the rotor to be measured, and sets multiple measuring points for monitoring at specific positions. Therefore, it can not only achieve the rigid body balance of the rotor, but also achieve the first-order and high-order dynamic balance of the rotor.

[0086] 2. The wireless transmission module can transmit vibration amplitude, phase and other data to the computer in real time without cable connection, avoiding the space limitations of wired connection and greatly reducing operation complexity.

[0087] In other possible embodiments, the structure of the rotor to be tested may be different from the above specific embodiments. For example, the rotor to be tested may have a wheel (Pi is greater than 5) near the key phase device 106 outside the second bearing seat 12, and the vibration amplitude calculated by the vibration mode is larger (A is greater than 1 / 5A max The position and number of the measuring points of the laser displacement sensor 4 can be obtained according to the above steps. s =0, Ccomb1 =2, C comb2 =1, C b =2, C a = 0. Therefore, according to the above formula, it can be calculated that the required number of laser sensors is at least 7. In addition to the six positions of the first to third laser displacement sensors 41 to 43 and the fifth to seventh laser displacement sensors 45 to 47 in the above specific embodiment, a laser displacement sensor can also be installed at the wheel position near the key phaser.

[0088] While the present application has been described in detail using the above-described embodiments, it will be apparent to those skilled in the art that the present application is not limited to the embodiments described in this specification. The present application can be modified and implemented as modified embodiments without departing from the subject matter and scope of the present application as defined by the claims. Therefore, the descriptions in this specification are for illustrative purposes only and do not have any limiting meaning with respect to the present application.

Claims

1. A dynamic balance experimental platform, characterized in that: The dynamic balance experimental platform comprises: A bearing seat, the bearing seat is used to support a rotor to be tested (100), the rotor to be tested (100) comprising a wheel assembly; and A displacement sensor is used to measure the vibration displacement of the rotor (100) to be measured at a point to be measured. A plurality of displacement sensors are provided, including a displacement sensor for measuring the rotor (100) to be measured near the bearing seat and a displacement sensor for measuring the wheel assembly. The wheel disc group includes a plurality of wheel discs, and the displacement sensor for measuring the wheel disc group includes two displacement sensors respectively aligned with two wheel discs at two axial ends of the wheel disc group. The displacement sensor comprises: a displacement sensor of the shaft aligned to the side of the bearing seat; and A displacement sensor is aligned at a position where the ratio of the shaft equivalent radius of the rotor to be measured (100) to the shaft radius at the mounting bearing of the rotor to be measured (100) is greater than 5.

2. The dynamic balancing experimental platform according to claim 1, characterized in that: The rotor to be measured (100) comprises a plurality of wheel disc groups and a connecting shaft (103) connecting two adjacent wheel disc groups, and the displacement sensor further comprises a displacement sensor aligned with the connecting shaft (103).

3. The dynamic balancing experimental platform according to claim 1 or 2, characterized in that: The displacement sensor is not provided at a position where the first-order or higher-order amplitude of the rotor to be measured (100) is less than one-fifth of the maximum value of the first-order or higher-order amplitude of the rotor to be measured (100).

4. The dynamic balancing experimental platform according to claim 1, characterized in that: The dynamic balancing experimental platform further comprises a Hall sensor (5), the rotor to be tested (100) comprises a key phase device (106), and the Hall sensor (5) is aligned with the key phase device (106).

5. A method for selecting measuring points for a dynamic balance experiment, characterized in that: The dynamic balancing experiment is used to measure a rotor to be measured (100), the rotor to be measured (100) is supported by a bearing seat, and the rotor to be measured (100) includes a wheel disc assembly. The dynamic balancing experiment measurement point selection method includes: Selecting a position corresponding to the vicinity of the bearing seat; selecting a position corresponding to the set of roulette wheels; and Selecting a position where the ratio of the shaft equivalent radius of the rotor to be measured (100) to the shaft radius of the bearing at which the rotor to be measured (100) is mounted is greater than 5, The dynamic balancing experiment measurement point selection method further includes: selecting a position corresponding to a connecting shaft (103), wherein the connecting shaft (103) is used to connect two adjacent wheel disc groups.

6. The method for selecting measuring points for dynamic balancing experiments according to claim 5, characterized in that: The positions of the two wheel discs corresponding to the axial ends of the wheel disc group are selected.

7. The method for selecting measuring points for a dynamic balancing experiment according to claim 5 or 6, wherein: Among the measuring points, measuring points where the first-order or higher-order amplitude of the rotor (100) to be measured is less than one-fifth of the maximum value of the first-order or higher-order amplitude of the rotor (100) to be measured are excluded.

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