CN114777999A - Dynamic balance experiment platform and dynamic balance experiment measuring point selection method - Google Patents
Dynamic balance experiment platform and dynamic balance experiment measuring point selection method Download PDFInfo
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- CN114777999A CN114777999A CN202210359330.4A CN202210359330A CN114777999A CN 114777999 A CN114777999 A CN 114777999A CN 202210359330 A CN202210359330 A CN 202210359330A CN 114777999 A CN114777999 A CN 114777999A
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M1/00—Testing static or dynamic balance of machines or structures
- G01M1/14—Determining imbalance
- G01M1/16—Determining imbalance by oscillating or rotating the body to be tested
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Abstract
The application provides a dynamic balance experiment platform and a dynamic balance experiment measuring point selection method, wherein the dynamic balance experiment platform comprises: the bearing block is used for supporting a rotor (100) to be tested, and the rotor (100) to be tested comprises a wheel disc group; the displacement sensors are used for measuring the vibration displacement of the rotor (100) to be measured at a point to be measured, the displacement sensors are arranged in a plurality, and each displacement sensor comprises a displacement sensor for measuring the rotor (100) to be measured near the bearing seat and a displacement sensor for measuring the wheel disc group.
Description
Technical Field
The application relates to an experimental inspection device of a rotor, in particular to a dynamic balance experiment platform and a dynamic balance experiment measuring point selection method.
Background
The rotor is widely used in various fields of industrial production due to the influence of factors such as machining errors, machining processes and assembly precision. The rotor inevitably has initial unbalanced mass after the assembly, and this kind of unbalanced mass once surpasss certain limit, not only probably leads to rotor structure bending itself, and the rotor also can produce great vibration in the operation in addition, very easily causes the damage of rotor structure and the destruction of bearing, and then leads to the emergence of accident. Therefore, the rotor needs to be subjected to a dynamic balance test before actual use so as to ensure that the vibration of the rotor is within a permissible reasonable range.
For a common rigid rotor, the operation is usually below a first-order critical rotation speed, so that the rotor only needs to be subjected to a dynamic balance test at the operation rotation speed. However, for heavy duty gas turbine rotors, the operating speed is typically above the second order critical speed of the rotor system, which is typically a flexible rotor. Since it is necessary to overcome the first-stage and second-stage critical rotational speeds when the rotational speed is increased to the operating rotational speed, there is a more severe demand for dynamic balance of the rotor, and it is necessary to control the vibration of the rotor due to resonance when the rotational speed exceeds the critical rotational speed, while reducing the vibration caused by the unbalanced mass of the rigid body of the rotor itself.
Because gas turbine rotors are typically large and expensive to manufacture, dynamic balance testing and research on actual gas turbine rotors is often impractical. Therefore, the dynamic balance test and research of the gas turbine rotor model under the laboratory condition is an important dynamic balance research method.
At present, various dynamic balance experiment systems of rotors exist, however, the experiment systems still have the following defects:
firstly, the existing rotor dynamic balance experiment system can perform dynamic balance experiment of the rigid rotor and the first-order critical rotating speed, and is difficult to realize dynamic balance experiment of the second-order critical rotating speed of the rotor.
Second, the measuring devices such as the sensors of the existing rotor dynamic balance experiment system are often connected with the dynamic balance device or the computer in a wired connection mode, and the use is complex.
Disclosure of Invention
The application aims at providing a dynamic balance experiment platform which can realize dynamic balance of first-order and high-order critical rotating speeds of a rotor according to the unbalanced mass of a rigid body of the rotor to be measured and the vibration mode of the rotor.
The application provides a dynamic balance experiment platform, dynamic balance experiment platform includes:
the bearing block is used for supporting a rotor to be tested, and the rotor to be tested comprises a wheel disc set; and
the displacement sensors are used for measuring the vibration displacement of the rotor to be measured at a point to be measured, the displacement sensors are arranged in a plurality of numbers, and each displacement sensor comprises a displacement sensor for measuring the rotor to be measured near the bearing seat and a displacement sensor for measuring the wheel disc group.
Preferably, the wheel disc group comprises a plurality of wheel discs, and the displacement sensor for measuring the wheel disc group comprises two displacement sensors respectively aligned with two wheel discs at two axial ends of the wheel disc group.
Preferably, the rotor to be tested comprises a plurality of wheel disc groups and a connecting shaft for connecting two adjacent wheel disc groups, and the displacement sensor comprises a displacement sensor aligned with the connecting shaft.
Preferably, the displacement sensor includes:
a displacement sensor aligned with a shaft on the side of the bearing block; and
and the displacement sensor is aligned with the position at which the ratio of the shaft equivalent radius of the rotor to be measured to the shaft radius of the mounting bearing of the rotor to be measured is greater than 5.
Preferably, the displacement sensor is not arranged at a position where the first-order or high-order amplitude of the rotor to be measured is less than one fifth of the maximum value of the first-order or high-order amplitude of the rotor to be measured.
Preferably, the dynamic balance experiment platform further comprises a hall sensor, the rotor to be tested comprises a key phase device, and the hall sensor is aligned to the key phase device.
The application also provides a dynamic balance experiment measuring point selecting method, the dynamic balance experiment is used for measuring a rotor to be measured, the rotor to be measured is supported by a bearing seat, the rotor to be measured comprises a wheel disc set, and the dynamic balance experiment measuring point selecting method comprises the following steps:
selecting a location corresponding to a vicinity of the bearing seat;
selecting a position corresponding to the set of wheels; and
and selecting a position at which the ratio of the shaft equivalent radius of the rotor to be tested to the shaft radius of the mounting bearing of the rotor to be tested is greater than 5.
Preferably, the method for selecting the dynamic balance test point further comprises the following steps: a position corresponding to a connecting shaft for connecting two adjacent sets of discs is selected.
Preferably, the positions of the two discs corresponding to the axial ends of the disc pack are selected.
Preferably, of the measuring points, measuring points in which 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.
By adopting the technical scheme, the displacement sensors are arranged at a plurality of specific positions of the rotor to be detected for detection, and the rigid body balance, the first order and the high order dynamic balance of the rotor can be realized through the obtained data.
Drawings
Fig. 1 shows a schematic structural diagram of an experiment performed on a rotor to be tested by a dynamic balance experiment platform according to an embodiment of the present application.
Fig. 2 shows a schematic structural view of a turbine disk set of a rotor to be measured.
Fig. 3 shows a schematic representation of the structure of the first turbine disk of the turbine disk stack of the rotor to be measured.
Fig. 4 shows a schematic representation of the fourth turbine disk of the turbine disk stack of the rotor to be measured.
Fig. 5 shows a schematic structural diagram of the compressor disk set of the rotor to be tested.
Fig. 6 shows a schematic structural diagram of a first-stage compressor disk of a compressor disk set of a rotor to be tested.
Fig. 7 shows a schematic structural diagram of a fourth stage compressor disk of a compressor disk stack of a rotor under test.
Description of the reference numerals
100 rotor 101 turbine shaft to be measured
102 turbine disk set 102A first stage turbine disk 102A1 first stage turbine disk dynamic balance hole 102B second stage turbine disk 102C third stage turbine disk 102D fourth stage turbine disk 102D1 fourth stage turbine disk dynamic balance hole
103 connecting shaft
104 compressor disk set 104A first stage compressor disk 104A1 first stage compressor disk dynamic balance hole 104B second stage compressor disk 104C third stage compressor disk 104D fourth stage compressor disk 104D1 fourth stage compressor disk dynamic balance hole
105 compressor shaft 106 key phase device
1 base 11 first bearing housing 12 second bearing housing
2 drive motor 21 shaft coupling
3 frequency converter
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
5 Hall sensor
6 signal acquisition module
7 calculation analysis module
8 wireless transmission module
C circumferential direction
Detailed Description
In order to more clearly illustrate the above objects, features and advantages of the present application, a detailed description of the present application is provided in this section in conjunction with the accompanying drawings. This application is capable of embodiments in addition to those described herein, and is intended to cover such departures from the present disclosure as come within known or customary practice in the art to which this application pertains and which fall within the limits of the appended claims. The protection scope of the present application shall be subject to the claims.
As shown in fig. 1 to 7, the present application provides a dynamic balance experiment platform, which includes a base 1, a driving 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.
The dynamic balance test platform is used for performing a dynamic balance test on the rotor 100 to be tested, and in this embodiment, the rotor 100 to be tested is used for simulating a gas turbine rotor.
As shown in fig. 1, the rotor 100 to be tested may include a turbine shaft 101, a turbine disk set 102, a connecting shaft 103, a compressor disk set 104, a compressor shaft 105, and a phase key 106. The turbine shaft 101 is connected to the turbine disk set 102, two ends of the connecting shaft 103 are respectively connected to the turbine disk set 102 and the compressor disk set 104, the compressor shaft 105 is connected to the compressor disk set 104, and the phase key 106 can be connected to the compressor shaft 105.
As shown in fig. 2 to 4, the turbine disk group 102 includes a first stage turbine disk 102A, a second stage turbine disk 102B, a third stage turbine disk 102C, and a fourth stage turbine disk 102D, and the first stage turbine disk 102A, the second stage turbine disk 102B, the third stage turbine disk 102C, and the fourth stage turbine disk 102D may be coaxially connected together. The first stage turbine disk 102A and the fourth stage turbine disk 102D are located at both axial ends of the turbine disk group 102. The first stage turbine disk 102A may be provided with a plurality of first stage turbine disk dynamic balance holes 102A1, the first stage turbine disk dynamic balance holes 102A1 are located at an outer edge portion of the first stage turbine disk 102A, and the plurality of first stage turbine disk dynamic balance holes 102A1 may be arranged along the circumferential direction C of the first stage turbine disk 102A. The fourth stage turbine disk 102D may be provided with a plurality of fourth stage turbine disk dynamic balance holes 102D1, the fourth stage turbine disk dynamic balance holes 102D1 may be located at an outer edge portion of the fourth stage turbine disk 102D, and a plurality of fourth stage turbine disk dynamic balance holes 102D1 may be arranged along the circumferential direction C of the fourth stage turbine disk 102D. The number of the first stage turbine disk dynamic balance holes 102a1 and the number of the fourth stage turbine disk dynamic balance holes 102D1 may be set to be greater than or equal to 60, and the first stage turbine disk dynamic balance holes 102a1 and the fourth stage turbine disk dynamic balance holes 102D1 are used for connecting dynamic balance pieces such as bolts.
As shown in fig. 5 to 7, the compressor disk group 104 includes a first-stage compressor disk 104A, a second-stage compressor disk 104B, a third-stage compressor disk 104C, and a fourth-stage compressor disk 104D, and the first-stage compressor disk 104A, the second-stage compressor disk 104B, the third-stage compressor disk 104C, and the fourth-stage compressor disk 104D may be coaxially connected together. The first-stage compressor disk 104A and the fourth-stage compressor disk 104D are located at both axial ends of the compressor disk group 104. The first-stage compressor disk 104A may be provided with a plurality of first-stage compressor disk dynamic balance holes 104A1, the first-stage compressor disk dynamic balance holes 104A1 may be located at an outer edge portion of the first-stage compressor disk 104A, and the plurality of first-stage compressor disk dynamic balance holes 104A1 may be arranged along a circumferential direction C of the first-stage compressor disk 104A. The fourth stage compressor disk 104D may be provided with a plurality of fourth stage compressor disk dynamic balance holes 104D1, the fourth stage compressor disk dynamic balance holes 104D1 may be provided at an outer edge portion of the fourth stage compressor disk 104D, and the plurality of fourth stage compressor disk dynamic balance holes 104D1 may be arranged in the circumferential direction C of the fourth stage compressor disk 104D. The number of the first-stage compressor wheel disc dynamic balance holes 104A1 and the number of the fourth-stage compressor wheel disc dynamic balance holes 104D1 can be more than or equal to 60, and the first-stage compressor wheel disc dynamic balance holes 104A1 and the fourth-stage compressor wheel disc dynamic balance holes 104D1 are used for connecting dynamic balance pieces such as bolts.
It is to be understood that in the present embodiment, the turbine and compressor disk sets 102 and 104 each include 4 disk structures, however in other possible embodiments, the number of disk structures of the turbine and compressor disk sets may be greater or lesser, and the number of disk structures of the turbine and compressor disk sets may be the same or different.
The base 1 is provided with a first bearing seat 11 and a second bearing seat 12, the first bearing seat 11 and the second bearing seat 12 are both provided with bearings, and 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 housing 11 may be used to support the turbine shaft 101 and the second bearing housing 12 may be used to support the compressor shaft 105.
It is understood that in the present embodiment, the rotor 100 to be tested is supported by the first bearing housing 11 and the second bearing housing 12, while in other possible embodiments, a greater number of bearing housings may be used to support the rotor to be tested.
The rotor 100 to be tested can be connected to the output shaft of the driving motor 2 through the coupler 21, so that the driving motor 2 drives the rotor 100 to be tested to rotate. The frequency converter 3 is connected to the driving motor 2, and the frequency converter 3 can control the driving motor 2 to rotate according to the set rotating speed required by the experiment.
The displacement sensor may be a laser displacement sensor 4, and the laser displacement sensor 4 may measure the displacement of the rotor 100 to be measured in a non-contact manner during rotation.
It is understood that the higher-order critical rotation speed includes a second-order critical rotation speed, a third-order critical rotation speed, and a higher-order critical rotation speed, and in the following description, the higher-order critical rotation speed is sometimes simply referred to as the higher order.
The spot positions and the number of the laser displacement sensors 4 can be obtained in the following manner.
(step 1) determining the number C of diameter mutation structures of a rotor shaft (comprising a turbine shaft 101, a connecting shaft 103 and a compressor shaft 105) of a rotor 100 to be testedSThe diameter mutation structure means that the ratio Pi of the equivalent radius of the rotor 100 to be measured to the radius of the shaft of the rotor 100 to be measured where the bearing is installed is greater than 5. When the diameter abrupt change structure comprises an irregular non-revolving structure, the radius is difficult to directly measure, and the equivalent radius can be calculated through the moment of inertia.
It can be understood that the abrupt diameter change structure of the rotor 100 to be measured may have an influence on the dynamic balance, and thus a laser displacement sensor is required for measuring the position.
(step 2) determining the number C of rotor disk setscombThe number of the wheel discs in the wheel disc set is Ni, wherein the number of the wheel disc sets with Ni larger than 1 is Ccomb1(ii) a The number of the wheel disc sets with Ni equal to 1 is Ccomb2。
It can be understood that a displacement sensor needs to be arranged for the wheel disc set of a single wheel disc, and a displacement sensor needs to be arranged for the two wheel discs at the two axial ends of the wheel shaft set for the wheel disc sets of a plurality of wheel discs respectively, so that the dynamic balance experimental platform can realize high-order dynamic balance for the rotor 100 to be tested.
(step 3) determining the number C of bearing seats supporting the rotor 100 to be measuredb。
(step 4) calculating each order vibration mode of the rotor 100 to be measured which needs to be balanced by taking the bearing seat of the rotor 100 to be measured as a calculation node, and obtaining the following parameters
Calculating maximum value A of each order vibration mode amplitude of rotormaxAnd calculating the diameter mutation structure of the rotor 100 to be measured and the amplitude A of the position of the corresponding measuring point of the wheel disc. The statistical rotor amplitude A of each order is less than 1/5AmaxNumber of corresponding measuring points Ca. This step allows to screen out the measurement points with smaller amplitude, i.e. the measurement points with less influence on the dynamic balance.
Cs、Ccomb1、Ccomb2、Cb、CaCan be obtained without any sequence, namely, the step 1 to the step 4 are not in sequence.
(step 5) determining the total number L of the required measuring points of the laser displacement sensortotalWherein L istotalThe calculation method is as follows:
Ltotal＝Cs+2Ccomb1+Ccomb2+Cb-Ca
in the present 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.
The first laser displacement sensor 41 may be mounted near the first bearing housing 11, with the first laser displacement sensor 41 aligned with the turbine shaft 101 near the first bearing housing 11 for monitoring the amplitude and phase of vibration of the turbine shaft 101 at a location near the first bearing housing 11.
The second laser displacement sensor 42 may be aligned with the fourth turbine disk 102D of the turbine disk set 102 for monitoring the amplitude and phase of the vibrations of the fourth turbine disk 102D.
The third laser displacement sensor 43 may be aligned with the first stage turbine disk 102A of the turbine disk set 102 for monitoring the vibration amplitude and phase of the first stage turbine disk 102A.
The fourth laser displacement sensor 44 may be aligned with the connecting shaft 103 for monitoring the amplitude and phase of vibration of the connecting shaft 103.
The fifth laser displacement sensor 45 may be aligned with the fourth stage compressor disk 104D of the compressor disk group 104, and is configured to monitor the vibration amplitude and phase of the fourth stage compressor disk 104D.
The sixth laser displacement sensor 46 may be aligned with the first stage compressor disk 104A of the compressor disk set 104 for monitoring the amplitude and phase of vibration of the first stage compressor disk 104A.
A seventh laser displacement sensor 47 may be mounted adjacent the second bearing housing 12, the seventh laser displacement sensor 47 being aligned with the compressor shaft 105 adjacent the second bearing housing 12 for monitoring the amplitude and phase of vibration of the compressor shaft 105 at a location adjacent the second bearing housing 12.
The signal acquisition module 6 is connected with the 7 laser displacement sensors 4 and the Hall sensor 5, and the signal acquisition module 6 can synchronously acquire pulse signals of the Hall sensor 5 and vibration electric signals of the laser displacement sensors 4. The calculation and analysis module 7 is connected with the signal acquisition module 6, and the calculation and analysis module 7 can calculate and analyze the amplitude and the phase of the vibration displacement signal of each measuring point of the laser displacement sensor 4 in real time. The wireless transmission module 8 is connected with the calculation and analysis module 7, and the wireless transmission module 8 can wirelessly transmit the amplitude and phase information calculated by the calculation and analysis module 7 to the computer 9.
(working process of measuring rotor to be measured by dynamic balance experiment platform of the application.)
The driving motor 2 is controlled by the frequency converter 3 to rotate, and the driving motor 2 can drive the rotor 100 to be tested to rotate and increase the speed to be near the first-order critical speed. Pulse electric signals collected by the Hall sensor 5 are output to the signal collection module 6, and vibration electric signals collected by the laser displacement sensors at each measuring point are synchronously output to the signal collection module 6. The signal acquisition module 6 outputs the acquired pulse electrical signal and the acquired vibration electrical signal to the calculation and analysis module 7, and the calculation and analysis module 7 calculates the rotating speed of the rotor 100 to be measured and the vibration amplitude and phase of each measuring point of the laser displacement sensor according to the pulse electrical signal and the vibration electrical signal. The data is sent to the computer 9 through the wireless transmission module 8, and the computer 9 calculates the dynamic balance mass and phase required by the dynamic balance at the rotating speed. And respectively installing dynamic balance pieces at corresponding positions of the dynamic balance hole 104A1 of the first-stage compressor wheel disc, the dynamic balance hole 104D1 of the fourth-stage compressor wheel disc, the dynamic balance hole 102A1 of the first-stage turbine wheel disc and the dynamic balance hole 102D1 of the fourth-stage turbine wheel disc according to the calculated data, and increasing the balance mass. Thereby, the dynamic balance of the first-stage critical rotational speed is completed. And then controlling the driving motor 2 through the frequency converter 3 to accelerate the rotor 100 to be tested to be close to the second-order critical rotating speed, and repeating the steps to balance the second-order critical rotating speed. After the balance is finished, the frequency converter 3 can be used for controlling the driving motor 2 to accelerate the rotor 100 to be measured to the second-stage critical rotation speed.
The method and the device comprehensively consider the structure and the simulated vibration mode of the rotor 100 to be tested to determine the number and the positions of the measuring points of the displacement sensor, so that the measuring points can be arranged at the position with larger vibration caused by the vibration mode of the rotor, the high-order dynamic balance test can be performed on the rotor 100 to be tested, and a better dynamic balance effect can be realized.
The dynamic balance experiment platform has the following advantages:
1. according to the method, the number and the positions of the measuring points are obtained through calculation based on the structure of the rotor to be measured, and a plurality of measuring points are arranged at specific positions for monitoring, so that not only can the rigid body balance of the rotor be realized, but also the first-order and high-order dynamic balance of the rotor can be realized.
2. The wireless transmission module can transmit data such as vibration amplitude, phase and the like to a computer in real time without cable connection, so that the space limitation of a wired connection mode is avoided, and the operation complexity is greatly reduced.
In other possible embodiments, the structure of the rotor to be tested may be different from the above-described embodiments, for example, the rotor to be tested may have a disk (Pi) near the key phase device 106 outside the second bearing housing 12Greater than 5) and the mode shape calculated has a large amplitude (a is greater than 1/5 a)max). The positions and the number of the measuring points of the laser displacement sensor 4 can be obtained according to the steps Cs＝0，Ccomb1＝2，Ccomb2＝1，Cb＝2，Ca0. Therefore, the required number of laser sensors can be calculated to be at least 7 according to the above formula, and in addition to the 6 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 embodiment, laser displacement sensors may be provided at the disk positions near the key phase.
While the present application has been described in detail with reference to the above embodiments, it will be apparent to those skilled in the art that the present application is not limited to the embodiments described in the present specification. The present application can be modified and implemented as a modified embodiment without departing from the spirit and scope of the present application defined by the claims. Therefore, the description in this specification is for illustrative purposes and does not have any limiting meaning for the present application.
Claims (10)
1. A dynamic balance experiment platform, characterized in that, the dynamic balance experiment platform includes:
the bearing block is used for supporting a rotor (100) to be tested, and the rotor (100) to be tested comprises a wheel disc group; and
the displacement sensors are used for measuring the vibration displacement of the rotor (100) to be measured at a point to be measured, the number of the displacement sensors is multiple, and the displacement sensors comprise displacement sensors for measuring the rotor (100) to be measured near the bearing block and displacement sensors for measuring the wheel disc group.
2. The dynamic balance experiment platform of claim 1, wherein the wheel set comprises a plurality of wheels, and the displacement sensor for measuring the wheel set comprises two displacement sensors respectively aligned with two wheels at two axial ends of the wheel set.
3. The dynamic balance experiment platform according to claim 1, wherein the rotor (100) to be tested comprises a plurality of wheel disk sets and a connecting shaft (103) connecting two adjacent wheel disk sets, and the displacement sensor further comprises a displacement sensor aligned with the connecting shaft (103).
4. The dynamic balance experiment platform of claim 1, wherein the displacement sensor comprises:
a displacement sensor aligned with a shaft on the side of the bearing block; and
the displacement sensor is aligned to a position where the ratio of the shaft equivalent radius of the rotor (100) to be measured to the shaft radius of the mounting bearing of the rotor (100) to be measured is greater than 5.
5. A dynamic balance experiment platform according to any one of claims 1 to 4, characterized in that the displacement sensor is not provided at a position where the first or higher order amplitude of the rotor under test (100) is less than one fifth of the maximum value of the first or higher order amplitude of the rotor under test (100).
6. The dynamic balance test platform of claim 1, further comprising a hall sensor (5), wherein the rotor (100) under test comprises a phase key (106), and wherein the hall sensor (5) is aligned with the phase key (106).
7. The method for selecting the measuring points in the dynamic balance experiment is characterized in that the dynamic balance experiment is used for measuring a rotor (100) to be measured, the rotor (100) to be measured is supported by a bearing seat, the rotor (100) to be measured comprises a wheel disc group, and the method for selecting the measuring points in the dynamic balance experiment comprises the following steps:
selecting a location corresponding to a vicinity of the bearing seat;
selecting a position corresponding to the set of wheels; and
and selecting a position where the ratio of the shaft equivalent radius of the rotor (100) to be tested to the shaft radius of the position of the bearing of the rotor (100) to be tested is greater than 5.
8. The method for selecting the dynamic balance test points according to claim 7, wherein the method for selecting the dynamic balance test points further comprises: selecting a position corresponding to a connecting shaft (103), wherein the connecting shaft (103) is used for connecting two adjacent wheel disc groups.
9. The method for selecting the test points for dynamic balance test according to claim 7, wherein the positions of the two discs corresponding to the two axial ends of the disc group are selected.
10. The method for selecting the dynamic balance test point according to any one of claims 7 to 9, characterized in that, among the test points, the test points in which the first order or higher order amplitude of the rotor (100) to be tested is less than one fifth of the maximum value of the first order or higher order amplitude of the rotor (100) to be tested are excluded.
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