Blade vibration fatigue test clamping device design method and blade clamping device

Abstract

The invention relates to the technical field of aero-engine tests, and discloses a blade vibration fatigue test clamping device design method and a blade clamping device.The blade vibration fatigue test clamping device design method comprises the steps that an existing switching section device is used for clamping a tested blade for a vibration fatigue test; mechanical drawing software and finite element analysis software are used for simulating that an existing switching section device is used for clamping a tested blade, and finite element harmonic response analysis is carried out; defects of an existing switching section device are found, and on the basis of overcoming the defects, the blade clamping device for the vibration fatigue test is designed. The vibration test result of the tested blade clamped by the existing switching section device is taken as a reference, the blade clamping device design based on harmonic response analysis is carried out, and the reasonable analysis design of the blade clamping device is realized in the design stage in a quantitative manner; vibration energy output by the vibration table is effectively transmitted to the blade body, the tested blade is subjected to fatigue damage, and higher vibration transmission efficiency is achieved.

Description

Technical Field

[0001] The present invention relates to the technical field of aero-engine test technology, and particularly relates to a design method for a blade vibration fatigue test clamping device and a blade clamping device. Background Art

[0002] The blade is one of the key parts of an aero-engine; due to the harsh working environment of the blade, the design technology and test technology are complex, and the processing requirements and detection technology requirements for the blade are high. Therefore, the blade belongs to a product intensive in knowledge and technology. In the design process of an aero-engine, the vibration fatigue problem of the blade is particularly prominent. The vibration fatigue failure of the blade often means that a large amount of time in the design stage is wasted, so that the blade needs to be redesigned. Since conducting the vibration fatigue test of the blade can expose the defects affecting the fatigue performance of the blade; the defects include: structural design defects, processing technology defects, material blank defects, etc.; therefore, the vibration fatigue test of the blade is of great significance for saving design time.

[0003] The vibration fatigue test of the blade is generally carried out in the following manner: performing fixed-frequency excitation on the tested blade to make it reach the resonance state, and then causing high-cycle fatigue failure. The above-mentioned method for the vibration fatigue test of the blade is based on the resonance principle, making the excitation frequency of the excitation system equal to a certain natural frequency of the tested blade after being fixedly installed, and the magnitude of the excitation force is controlled according to the test purpose and the structural characteristics of the tested blade. In the vibration fatigue test of the blade, it is required that the stress value at the maximum vibration stress point of the blade body remains unchanged at a certain stress level exceeding the high-cycle fatigue limit of the blade until the blade shows high-cycle fatigue failure. In the vibration fatigue test of the blade, devices such as a vibration displacement measuring instrument, a strain measuring instrument, and a dynamic signal analyzer are generally used to monitor the vibration state of the tested blade. Currently, the excitation source widely used for the vibration fatigue test of blade-like parts is an electrodynamic vibration table 1, as Figure 1 shown. For a general blade vibration fatigue test system, the connection schematic diagram is as Figure 2 shown. The existing adapter section device 3 for clamping the tested blade 2 is fixed at the center of the table surface of the electrodynamic vibration table 1. A sensor 4 is provided on the table surface of the electrodynamic vibration table 1, the sensor 4 is connected to a charge amplifier 5, the charge amplifier 5 is connected to a controller 6, the controller 6 is connected to a power amplifier 7, and the power amplifier 7 is connected to the electrodynamic vibration table 1. Figure 2 The arrows in Figure 3As shown, before the vibration test starts, a suitable existing adapter device 3 is designed and processed to clamp the clamping section of the tested blade 2. Then, the existing adapter device 3 and the tested blade 2 are installed and fixed together at the center of the tabletop of the electrodynamic vibration table 1, and the blade body of the tested blade 2 is in a cantilever fixed support state. For the existing adapter device 3, the clamping section of the tested blade 2 is located between the pressing block 8 and the cushion block 9; the pressing block 8 and the cushion block 9 are connected by fastening bolts 10 at positions close to the edge.

[0004] As Figure 3 The existing adapter device 3 shown has obvious structural defects, resulting in low vibration transfer efficiency. It is difficult to effectively transfer the vibration energy output by the electrodynamic vibration table 1 to the blade body of the tested blade 2 in the high-frequency state. The tested blade 2 is difficult to reach the fatigue failure state. After the excitation frequency exceeds 3000 Hz, the vibration transfer efficiency is even lower, and it is difficult to carry out the vibration fatigue test of the tested blade 2, resulting in severely limited application scope of the existing adapter device 3 in engineering. Summary of the Invention

[0005] In view of this, the present invention provides a design method for a clamping device for blade vibration fatigue test to solve the problem that the existing adapter device has obvious structural defects, resulting in low vibration transfer efficiency, being difficult to effectively transfer the vibration energy output by the electrodynamic vibration table to the blade body of the tested blade in the high-frequency state, the tested blade being difficult to reach the fatigue failure state, the vibration transfer efficiency being even lower after the excitation frequency exceeds 3000 Hz, and it being difficult to carry out the vibration fatigue test of the tested blade, resulting in severely limited application scope of the existing adapter device in engineering.

[0006] In the first aspect, the present invention provides a design method for a clamping device for blade vibration fatigue test, including:

[0007] Using the existing adapter device to clamp the tested blade and fixing and installing them together on the vibration table;

[0008] Starting the blade vibration fatigue test system, conducting a vibration fatigue test on the tested blade, obtaining the corresponding relationship between the basic displacement excitation value and the blade body strain response value of the tested blade, so as to obtain the first response characteristic analysis result;

[0009] Using mechanical drawing software and finite element analysis software to simulate clamping the tested blade with the existing adapter device, and combining the corresponding relationship between the basic displacement excitation value and the blade body strain response value of the tested blade, conducting a finite element harmonic response analysis on the vibration fatigue test of the tested blade, and obtaining the blade body response characteristics of the tested blade under the action of a unit basic displacement excitation force;

[0010] Find the defects of the existing adapter device, and on the basis of overcoming the above defects, design a blade clamping device for vibration fatigue tests. Beneficial effects: By adopting the above technical solution, this application uses the vibration test debugging results of the existing adapter device clamping the tested blade as a reference object to carry out the design of a blade clamping device for vibration fatigue tests based on harmonic response analysis, and can quantitatively analyze and design the rationality of the blade clamping device for vibration fatigue tests at the design stage; even at high frequencies, it can effectively transfer the vibration energy output by the vibration table to the blade body, so that the tested blade reaches the fatigue failure state, realizing that after the excitation frequency exceeds 3000 Hz, the blade clamping device has a higher vibration transfer efficiency and expands the engineering application range of the blade clamping device.

[0011] Optionally, it further includes:

[0012] Use mechanical drawing software and finite element analysis software to simulate the vibration characteristics analysis and finite element harmonic response analysis of the vibration fatigue test of the tested blade by using the blade clamping device to clamp the tested blade, and ensure that the natural frequency of the blade clamping device in the excitation direction is above the set frequency; at the same time, obtain the blade body response characteristics of the tested blade under the action of the unit base displacement excitation force. Beneficial effects: By adopting the above technical solution, when carrying out high-frequency vibration fatigue tests, this application ensures that there is a certain resonance margin between the natural frequency of the blade clamping device and the excitation frequency of the test, ensuring the stable and reliable progress of the vibration fatigue test.

[0013] Optionally, it further includes:

[0014] Use the blade clamping device to clamp the tested blade and fixedly install them together on the vibration table;

[0015] Start the blade vibration fatigue test system, conduct a vibration fatigue test on the tested blade, obtain the corresponding relationship between the base displacement excitation value and the blade body strain response value of the tested blade, so as to obtain the second response characteristic analysis result;

[0016] Compare the first response characteristic analysis result with the second response characteristic analysis result to confirm the improvement amplitude of the blade vibration fatigue test effect. Beneficial effects: By adopting the above technical solution, this application effectively evaluates the rationality of the blade clamping device structure design by comparing the first response characteristic analysis result with the second response characteristic analysis result.

[0017] Optionally, the set frequency is 6000 Hz. Beneficial effects: By adopting the above technical solution, by limiting the set frequency, when carrying out high-frequency vibration fatigue tests, this application ensures the resonance margin between the natural frequency of the blade clamping device and the excitation frequency of the test, ensuring the stable and reliable progress of the vibration fatigue test.

[0018] Optionally, the excitation frequency of the vibration table is not less than 3000 Hz.

[0019] In a second aspect, the present invention further provides a blade clamping device designed by using the design method of the blade vibration fatigue test clamping device, including:

[0020] A base adapted to be fixedly connected to the tabletop of the vibration table;

[0021] A boss fixedly arranged on the base, and a blind hole is provided on the side surface of the boss;

[0022] An elastic clamping block is arranged in the blind hole, and a placement groove is provided on the side surface of the elastic clamping block; the placement groove is adapted to clamp the clamping section of the blade to be tested;

[0023] At least one threaded fastener is screwed into the blind hole from the top surface of the boss and abuts against the top surface of the elastic clamping block. Beneficial effects: By adopting the above technical solution, the present application uses a blade clamping device similar to a pyramid, and each component effectively contributes to the improvement of the overall stiffness, and maximally avoids the increase of redundant mass. On the premise of meeting the stiffness and frequency requirements, the overall weight is controlled within an acceptable range; moreover, the structure of the blade clamping device is stable, highly reliable and durable.

[0024] Optionally, at least one reinforcing rib is provided on the outer circumference of the boss. Beneficial effects: By adopting the above technical solution, the reinforcing rib is used to enhance the overall stiffness of the blade clamping device in all directions.

[0025] Optionally, the shape of the reinforcing rib is triangular.

[0026] Optionally, the number of the reinforcing ribs is four, and the four reinforcing ribs are radially distributed with the center of the top surface of the boss as the center point. Beneficial effects: By adopting the above technical solution, an open installation space and a test space are provided for subsequent installation parts.

[0027] Optionally, the threaded fastener is a compression bolt. Description of the Drawings

[0028] In order to more clearly illustrate the specific embodiments of the present invention or the technical solutions in the prior art, the following will briefly introduce the drawings required for use in the description of the specific embodiments or the prior art. Obviously, the following drawings are some embodiments of the present invention. For those of ordinary skill in the art, other drawings can be obtained based on these drawings without creative efforts.

[0029] Figure 1 It is a three-dimensional structural schematic diagram of an electrodynamic vibration table in the prior art;

[0030] Figure 2 It is a connection schematic diagram of a blade vibration fatigue test system in the prior art;

[0031] Figure 3 It is a three-dimensional structure schematic diagram of an existing adapter section device in the prior art;

[0032] Figure 4 It is a partial three-dimensional structure schematic diagram of a blade clamping device provided in an embodiment of the present invention;

[0033] Figure 5 It is a top view structure schematic diagram of a blade clamping device provided in an embodiment of the present invention;

[0034] Figure 6 It is a three-dimensional structure schematic diagram of an elastic clamping block provided in an embodiment of the present invention;

[0035] Figure 7 It is a flow schematic diagram of a design method for a blade vibration fatigue test clamping device provided in an embodiment of the present invention.

[0036] Explanation of reference numerals:

[0037] 1. Electro-dynamic vibration table; 2. Tested blade; 3. Existing adapter section device; 4. Sensor; 5. Charge amplifier; 6. Controller; 7. Power amplifier; 8. Pressure block; 9. Spacer block; 10. Fastening bolt; 11. Base; 12. Boss; 13. Blind hole; 14. Elastic clamping block; 15. Reinforcing rib; 16. Threaded hole; 17. Mounting hole. Specific embodiments

[0038] To make the objectives, technical solutions, and advantages of the embodiments of the present invention clearer, the technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings in the embodiments of the present invention. Obviously, the described embodiments are some, but not all, of the embodiments of the present invention. Based on the embodiments of the present invention, all other embodiments obtained by those of ordinary skill in the art without creative efforts shall fall within the protection scope of the present invention.

[0039] As Figure 3As shown, when using the existing adapter section device 3 for the vibration fatigue test of large-sized blades, the existing adapter section device 3 often experiences fatigue fracture of the fastening bolts 10 and permanent bending deformation of the pressure block 8. The stability and reliability of the existing adapter section device 3 are very poor. The existing adapter section device 3 clamps the tested blade 2 through the upper pressure block 8 and the lower spacer 9. The clamped section of the tested blade 2 fits with the pressure block 8 and the middle section of the spacer 9. The fastening bolts 10 at both ends of the pressure block 8 are responsible for the fastening installation of the tested blade 2 and the connection with the electrodynamic vibration table 1. The above installation method mainly bears the tightening force by the pressure block 8 and the fastening bolts 10, and there is also an obvious suspended structure between the pressure block 8 and the spacer 9, resulting in the following four structural defects of the existing adapter section device 3: First, it is very difficult to design the natural frequency of the existing adapter section device 3 too high in the excitation direction. When carrying out the high-frequency vibration fatigue test, it is difficult to ensure the resonance margin between the natural frequency and the excitation frequency of the existing adapter section device 3. Second, the pressing force applied by the pressure block 8 to the clamped section of the tested blade 2 is determined by the bending stiffness of the pressure block 8 itself, so that the pressing force that can be applied is limited, that is, it may not be able to provide sufficient clamping force; at the same time, the pressure block 8 may also undergo obvious bending deformation during the process of tightening the fastening bolts 10. When carrying out the high-frequency vibration fatigue test in the case where the pressure block 8 cannot provide sufficient clamping force and may undergo bending deformation, the clamped section of the tested blade 2 will experience fretting, resulting in a significant loss of excitation energy. Third, the suspended structure between the pressure block 8 and the spacer 9 results in limited stiffness of the existing adapter section device 3. When carrying out the high-frequency vibration fatigue test, the tested blade 2 generates a large reaction force on the pressure block 8 in the high-frequency resonance state, causing high-frequency vibration deformation of both ends of the pressure block 8 and the fastening bolts 10, resulting in a significant consumption of excitation energy. Fourth, in the installed and tightened state, the fastening bolts 10 bear a steady-state tensile force. In the vibration fatigue test state, the fastening bolts 10 bear a dynamic torque applied by the tested blade 2 through the pressure block 8. If the size of the tested blade 2 is relatively large, the fastening bolts 10 are prone to fatigue fracture under the combined action of the steady-state tensile force and the dynamic torque. The phenomenon of fatigue fracture of the fastening bolts 10 is quite common in engineering.

[0040] The first three of the above four defects will significantly reduce the vibration transfer efficiency of the existing adapter section device 3. In the high-frequency vibration state, it is more difficult to effectively transfer the vibration energy output by the electrodynamic vibration table 1 to the blade body of the tested blade 2, so that the tested blade 2 can achieve fatigue failure. The application range of the existing adapter section device 3 in engineering is severely limited. The fourth defect will seriously interfere with the normal progress of the vibration fatigue test and seriously affect the test progress. For the above reasons, the present application proposes a design method for a clamping device for a blade vibration fatigue test and a blade clamping device.

[0041] As Figures 4 to 7A specific implementation of the design method for the blade vibration fatigue test clamping device includes the following steps:

[0042] S1. Use the existing adapter section device 3 to clamp the tested blade 2, and fix and install them together on the vibration table. Specifically, the vibration table can be an electrodynamic vibration table 1. The excitation frequency of the vibration table is not less than 3000 Hz.

[0043] S2. Start the blade vibration fatigue test system, conduct a vibration fatigue test on the tested blade 2, obtain the corresponding relationship between the base displacement excitation value and the blade body strain response value of the tested blade 2, so as to obtain the first response characteristic analysis result.

[0044] S3. Use mechanical drawing software and finite element analysis software to simulate the clamping of the tested blade 2 by the existing adapter section device 3, and combine the corresponding relationship between the base displacement excitation value and the blade body strain response value of the tested blade 2 to conduct a finite element harmonic response analysis on the vibration fatigue test of the tested blade 2, and obtain the blade body response characteristics of the tested blade 2 under the action of a unit base displacement excitation force.

[0045] S4. Find the defects of the existing adapter section device 3, and on the basis of overcoming the above defects, design a blade clamping device for vibration fatigue tests.

[0046] As Figure 7 shown, the design method for the blade vibration fatigue test clamping device of the present application further includes:

[0047] S5. Use mechanical drawing software and finite element analysis software to simulate the clamping of the tested blade 2 by the blade clamping device, conduct vibration characteristic analysis and finite element harmonic response analysis on the vibration fatigue test of the tested blade 2, and ensure that the natural frequency of the blade clamping device in the excitation direction is above the set frequency; at the same time, obtain the blade body response characteristics of the tested blade 2 under the action of a unit base displacement excitation force. Specifically, the set frequency is 6000 Hz.

[0048] As Figure 7 shown, the design method for the blade vibration fatigue test clamping device of the present application further includes:

[0049] S6. Use the blade clamping device to clamp the tested blade 2, and fix and install them together on the vibration table;

[0050] S7. Start the blade vibration fatigue test system, conduct a vibration fatigue test on the tested blade 2, obtain the corresponding relationship between the base displacement excitation value and the blade body strain response value of the tested blade 2, so as to obtain the second response characteristic analysis result.

[0051] S8. Compare the first response characteristic analysis result with the second response characteristic analysis result to confirm the improvement amplitude of the blade vibration fatigue test effect. The specific improvement amplitude meets the engineering requirements, and the specific requirements for the improvement amplitude can be estimated according to the vibration test debugging results of the existing adapter device 3 clamping the tested blade 2 and the maximum output capacity of the vibration table.

[0052] As Figures 4 to 6 shown, the present application also provides a blade clamping device designed by using the blade vibration fatigue test clamping device design method described above, including: a base 11, a boss 12, an elastic clamping block 14, and at least one threaded fastener.

[0053] As Figure 4 and Figure 6 shown, the base 11 is adapted to be fixedly connected to the tabletop of the vibration table; specifically, the base 11 can be circular, and eight mounting holes 17 are uniformly arranged at positions near the edge of the circular base 11, and are fixed to the center of the tabletop of the vibration table by bolts passing through the mounting holes 17 and being tightened. The boss 12 is fixedly arranged on the base 11; specifically, the boss 12 can be a square platform and is fixedly arranged at the center of the top surface of the base 11. A blind hole 13 is provided on the side surface of the boss 12, and the blind hole 13 can be a square hole. The elastic clamping block 14 is arranged in the blind hole 13, and a placement groove is provided on the side surface of the elastic clamping block 14; the placement groove is adapted to clamp the clamping section of the tested blade 2. The threaded fastener is screwed into the blind hole 13 from the top surface of the boss 12 and abuts against the top surface of the elastic clamping block 14. Specifically, threaded holes 16 penetrating through to the blind hole 13 are provided on the top surface of the boss 12, and the number can be two rows, a total of five.

[0054] Further, as Figure 4 and Figure 5As shown, at least one reinforcing rib 15 is provided on the outer circumference of the boss 12. Specifically, the shape of the reinforcing rib 15 is triangular. The number of the reinforcing ribs 15 is four, and the four reinforcing ribs 15 are radially distributed with the center of the top surface of the boss 12 as the center point; they are respectively located at the four right-angle edges of the boss 12, giving the subsequent test blade 2 with a cantilever installation an open installation space and a test space. The threaded fastener is a compression bolt made of metal. The compression bolt is selected with a large-size specification bolt, and the lower end surface of the compression bolt directly presses against the elastic clamping block 14. The magnitude of the pressing force that the elastic clamping block 14 can exert on the test blade 2 is determined by the overall structural stiffness of the boss 12. Since a blind hole 13 is provided in the middle of the boss 12 and reinforcing ribs 15 are provided at the four corners of the boss 12 to enhance the support stiffness, the overall structural stiffness of the boss 12 can be fully ensured to reach a very high level, so as to ensure that the compression bolt can exert sufficient pressing force on the test blade 2 to meet the engineering requirements and avoid the occurrence of fretting phenomenon in the clamping section of the test blade 2 during the vibration fatigue test, resulting in the loss of excitation energy. During the vibration fatigue test, the reaction force generated by the test blade 2 in the high-frequency resonance state is borne by the compression bolt and the boss 12. As mentioned above, the overall structural stiffness of the boss 12 can reach a very high level, so the boss 12 will not produce obvious high-frequency vibration deformation, and at the same time, the compression bolt will not produce obvious high-frequency vibration deformation either. Therefore, there will be no phenomenon that the blade clamping device consumes vibration energy due to high-frequency vibration deformation. In the installed and fastened state, the compression bolt bears the steady-state pressure. In the vibration fatigue test state, the compression bolt bears the dynamic reaction force from the test blade 2 at the same time. This dynamic reaction force passes through the central axis of the compression bolt and will not form a dynamic moment on the compression bolt. The compressive strength of the compression bolt made of metal is much higher than its tensile strength. Therefore, during the vibration fatigue test, the compression bolt will not show the phenomenon of fatigue fracture. The layout method of the compression bolt is determined according to the shape and size of the clamping section of the test blade 2 and the elastic clamping block 14 to form a good pressing state, which not only provides a strong pressing force on the test blade 2 to prevent fretting, but also avoids the high-cycle fatigue fracture of the compression bolt caused by the vibration reaction force of the test blade 2.

[0055] The overall blade clamping device of the present application is similar to a pyramid. Each component is effectively used to improve the overall stiffness, and at the same time, it tries to avoid the increase of redundant mass, resulting in excessive weight. The natural frequency in the excitation direction can be designed to be within the high-frequency vibration range, that is, above 6000 Hz, so as to ensure that the resonance margin with the vibration test frequency meets the engineering requirements.

[0056] The vibration fatigue test using the blade clamping device designed in this application has been successfully applied to the vibration fatigue test of the 5th stage working blade of a certain type of turboshaft engine compressor with a frequency exceeding 3500 Hz, providing a reliable reference for understanding and mastering the vibration fatigue strength characteristics of the working blade of this type of compressor, and making a positive contribution to the model development. During the application process, this blade clamping device is not only easy to operate but also convenient to implement, and can be popularized and applied to the development of other types of aero gas turbine engines and related research topics. The blade clamping device designed in this application has produced good economic and social benefits in terms of improving the vibration fatigue test technology ability of aero engine blade parts and enhancing the structural reliability of aero engine blade parts.

[0057] Although the embodiments of the present invention have been described in conjunction with the accompanying drawings, those skilled in the art can make various modifications and variations without departing from the spirit and scope of the present invention, and such modifications and variations fall within the scope defined by the appended claims.

Claims

1. A design method for a clamping device in blade vibration fatigue tests, characterized in that, Comprising: Using the existing adapter device (3) to clamp the tested blade (2), and fixedly installing them together on the vibration table; Starting the blade vibration fatigue test system, conducting a vibration fatigue test on the tested blade (2), obtaining the corresponding relationship between the basic displacement excitation value and the blade body strain response value of the tested blade (2), thereby obtaining the first response characteristic analysis result; Using mechanical drawing software and finite element analysis software to simulate the clamping of the tested blade (2) by the existing adapter device (3), and combining the above corresponding relationship between the basic displacement excitation value and the blade body strain response value of the tested blade (2), conducting a finite element harmonic response analysis on the vibration fatigue test of the tested blade (2), and obtaining the blade body response characteristics of the tested blade (2) under the action of a unit basic displacement excitation force; Searching for the defects of the existing adapter device (3), and on the basis of overcoming the above defects, designing a blade clamping device for vibration fatigue tests.

2. The design method of the blade vibration fatigue test clamping device according to claim 1, characterized in that, Also comprising: Using mechanical drawing software and finite element analysis software to simulate the clamping of the tested blade (2) by the blade clamping device, conducting vibration characteristic analysis and finite element harmonic response analysis on the vibration fatigue test of the tested blade (2), ensuring that the natural frequency of the blade clamping device in the excitation direction is above the set frequency; meanwhile, obtaining the blade body response characteristics of the tested blade (2) under the action of a unit basic displacement excitation force.

3. The design method of the blade vibration fatigue test clamping device according to claim 2, characterized in that Also comprising: Using the blade clamping device to clamp the tested blade (2), and fixedly installing them together on the vibration table; Starting the blade vibration fatigue test system, conducting a vibration fatigue test on the tested blade (2), obtaining the corresponding relationship between the basic displacement excitation value and the blade body strain response value of the tested blade (2), thereby obtaining the second response characteristic analysis result; Comparing the first response characteristic analysis result with the second response characteristic analysis result to confirm the improvement amplitude of the blade vibration fatigue test effect.

4. The method for designing a clamping device for blade vibration fatigue test according to claim 2 or 3, characterized in that, The set frequency is 6000 Hz.

5. The design method of the blade vibration fatigue test clamping device according to any one of claims 1-3, characterized in that The excitation frequency of the vibration table is not less than 3000 Hz.

6. A blade clamping device designed by using the design method of the blade vibration fatigue test clamping device described in any one of claims 1-5, characterized in that, Comprising: A base (11), adapted to be fixedly connected to the tabletop of the vibration table; A boss (12), fixedly arranged on the base (11), and a blind hole (13) is provided on the side surface of the boss (12); An elastic clamping block (14), arranged in the blind hole (13), and a placement groove is provided on the side surface of the elastic clamping block (14); the placement groove is adapted to clamp the clamping section of the tested blade (2); At least one threaded fastener, screwed into the blind hole (13) from the top surface of the boss (12) and abutted against the top surface of the elastic clamping block (14).

7. The blade clamping device according to claim 6, characterized in that, At least one reinforcing rib (15) is provided on the outer circumference of the boss (12).

8. The blade clamping device according to claim 7, characterized in that, The shape of the reinforcing rib (15) is triangular.

9. The blade clamping device according to claim 7 or 8, characterized in that, The number of the reinforcing ribs (15) is four, and the four reinforcing ribs (15) are radially distributed with the center of the top surface of the boss (12) as the center point.

10. The blade clamping device according to any one of claims 6-8, characterized in that, The threaded fastener is a compression bolt.

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