Turbine blade clamping device, high-cycle torsional fatigue test system and test method

Abstract

The invention provides a turbine blade clamping device, a high-cycle torsional fatigue test system and a test method. Belongs to the technical field of turbine blade testing. The high-cycle torsional fatigue system comprises a clamping device; the clamping device comprises a first fixing assembly and a second fixing assembly. The first fixing assembly is connected with the blade tenon and used for fixing the blade tenon. The second fixing assembly is connected with the blade body and used for fixing the blade body. And the second fixing assembly can be driven by the outside to move, so that the turbine blade is subjected to torsional deformation. The turbine blade test system can perform high-cycle torsional fatigue test on the turbine blade.

Description

Technical Field

[0001] The present disclosure relates to the technical field of turbine blade detection, and more particularly, to a clamping device, a test system, and a test method for a turbine blade. Background Art

[0002] During operation, the turbine blades of an aeroengine are subjected to the combined action of mechanical loads and thermal loads, and are prone to high-cycle fatigue failure under the action of high-frequency airflow excitation loads. Research shows that high-cycle fatigue failure accounts for about 70% of blade fracture accidents. To address the fatigue failure problem of aeroengine turbine blades, current research mainly focuses on studying the high-cycle fatigue performance of turbine blades through material-level high-cycle fatigue tests, or analyzing the blade performance through blade component-level bending fatigue tests, while lacking means for high-cycle torsional fatigue tests at the blade component level. In response to the need for high-cycle torsional fatigue tests of aeroengine turbine blades, there is an urgent need to develop a test device and method that can apply high-cycle torsional fatigue loads to turbine blades.

[0003] It should be noted that the information disclosed in the above background art section is only used to enhance the understanding of the background of the present disclosure, and thus may include information that does not constitute the prior art known to those of ordinary skill in the art. Summary of the Invention

[0004] The purpose of the present disclosure is to overcome the deficiencies of the above prior art and provide a clamping device for a turbine blade and a turbine blade test system, so as to perform high-cycle torsional fatigue experiments on the turbine blade.

[0005] According to a first aspect of the present disclosure, there is provided a clamping device for a turbine blade, the turbine blade including a blade body and a blade tenon; the clamping device includes a first fixing component and a second fixing component;

[0006] The first fixing component is connected to the blade tenon and is used to fix the blade tenon;

[0007] The second fixing component is connected to one end side of the blade body away from the blade tenon and is used to fix the blade body; and the second fixing component can be driven by an external force to move, so that the turbine blade undergoes torsional deformation.

[0008] According to an embodiment of the present disclosure, the first fixing component includes symmetrically arranged fixing jigs and a first mounting member for fixing the fixing jigs;

[0009] The symmetrically arranged fixing jigs form a clamping space for the blade tenon.

[0010] According to an embodiment of the present disclosure, the fixing jig includes a support section and a clamping section;

[0011] One end of the clamping section is connected to the support section, and the other end has a clamping groove adapted to one side of the blade tenon head.

[0012] The first mounting member is used to fix the symmetrically arranged clamping sections.

[0013] The support section is used to support the clamping section.

[0014] According to an embodiment of the present disclosure, the first mounting member includes a mounting bolt.

[0015] When the blade tenon head is in a fixed state, the end of the mounting bolt contacts the end of the blade tenon head away from the blade body side.

[0016] According to an embodiment of the present disclosure, the second fixing assembly includes a fixing clamp block and a second mounting member.

[0017] The fixing clamp block is connected to one end of the blade body away from the blade tenon head through the second mounting member.

[0018] The fixing clamp block can move under external drive so that the turbine blade undergoes torsional deformation.

[0019] According to an embodiment of the present disclosure, the fixing clamp block has a fixing groove.

[0020] The blade body extends into the fixing groove and is connected to the side wall of the fixing groove.

[0021] The second mounting member is used to fixedly connect the blade body to the side wall of the fixing groove.

[0022] According to a second aspect of the present disclosure, a high-cycle torsional fatigue test system is provided, including the turbine blade clamping device described above.

[0023] The test system further includes a transmission device, an exciter device, and a heating device.

[0024] The exciter device is connected to the fixing clamp block through the transmission device, wherein the exciter device is configured to generate an exciting force.

[0025] The transmission device is configured to transmit the power generated by the exciter device to the turbine blade.

[0026] The heating device is configured to regulate the test temperature of the turbine blade.

[0027] According to an embodiment of the present disclosure, the transmission device includes a driving rack and a driving gear.

[0028] The driving gear is arranged on one side of the fixed clamping block;

[0029] One end of the driving rack is connected to the output end of the exciter device, and the driving rack meshes with the driving gear. Wherein, the moving direction of the driving rack is perpendicular to the length direction of the blade body.

[0030] According to an embodiment of the present disclosure, the transmission device includes a third mounting member;

[0031] One side of the fixed clamping block has a mounting groove;

[0032] The driving gear is detachably arranged in the mounting groove through the third mounting member.

[0033] According to a third aspect of the present disclosure, a turbine blade test method is provided, including:

[0034] Providing a turbine blade test piece;

[0035] Clamping and fixing the blade tenon of the turbine blade to a fixed fixture;

[0036] Connecting the blade body of the turbine blade to the fixed clamping block and connecting it to the exciter device through a transmission device.

[0037] Turning on the exciter device and recording relevant data of the turbine blade through the equipment. Description of the Drawings

[0038] The drawings herein are incorporated into the specification and form a part of this specification, showing embodiments consistent with the present disclosure, and are used together with the specification to explain the principles of the present disclosure. Obviously, the drawings in the following description are only some embodiments of the present disclosure. For those of ordinary skill in the art, other drawings can be obtained based on these drawings without creative efforts.

[0039] Figure 1 It is a schematic structural diagram of a turbine blade in an embodiment of the present disclosure.

[0040] Figure 2 It is a schematic structural diagram of a high-cycle torsional fatigue test system in an embodiment of the present disclosure.

[0041] Figure 3 It is a schematic structural diagram of a clamping device in an embodiment of the present disclosure.

[0042] Figure 4 It is a schematic structural diagram of a clamping section and a first mounting member in an embodiment of the present disclosure.

[0043] Figure 5In an embodiment of the present disclosure, it is a schematic diagram of the clamping section clamping the blade tenon head.

[0044] Figure 6 In an embodiment of the present disclosure, it is a schematic diagram of the clamping section clamping the blade tenon head and the connection of the pre-fixed clamp block of the blade body.

[0045] Figure 7 In an embodiment of the present disclosure, it is a schematic diagram of the second fixing component clamping the blade body.

[0046] Figure 8 In an embodiment of the present disclosure, it is a schematic diagram of the structure of the transfer device and the fixed clamp block.

[0047] Figure 9 In an embodiment of the present disclosure, it is a schematic diagram of the connection between the support rod and the driving gear.

[0048] Figure 10 In an embodiment of the present disclosure, it is a schematic diagram of the steps for testing the turbine blade.

[0049] Explanation of reference numerals: 1. Clamping device; 11. First fixing component; 111. Fixed fixture; 1111. Clamping section; 11111. Clamping groove; 1112. Support section; 11121. Horizontal part; 11122. Vertical part; 1113. Enlarging part; 112. First mounting member; 1121. Mounting bolt; 12. Second fixing component; 121. Fixed clamp block; 1211. Fixed groove; 1212. Mounting groove; 122. Second mounting member; 2. Vibration exciter device; 3. Heating device; 4. Transfer device; 41. Driving rack; 42. Driving gear; 43. Third mounting member; 44. Support rod; 5. Turbine blade; 51. Blade body; 52. Blade tenon head. Detailed implementation manners

[0050] Now, the exemplary embodiments will be described more comprehensively with reference to the accompanying drawings. However, the exemplary embodiments can be implemented in various forms and should not be construed as being limited to the embodiments set forth herein; on the contrary, these embodiments are provided so that this disclosure will be thorough and complete, and the concept of the exemplary embodiments will be fully conveyed to those skilled in the art. The same reference numerals in the drawings denote the same or similar structures, and thus their detailed descriptions will be omitted. In addition, the drawings are only schematic illustrations of the present disclosure and are not necessarily drawn to scale.

[0051] In the related art, most of the fatigue tests on turbine blades are carried out by applying a cyclic load in a single straight line direction, and it is impossible to apply a high-cycle torsional fatigue load to conduct a torsional fatigue experiment on them, which means that it is impossible to simulate the rotation during the service process of the turbine blade.

[0052] Based on this, seeFigure 1 , Figure 2 and Figure 3 , embodiments of the present disclosure provide a clamping device 1 for a turbine blade 5, and this clamping device 1 can be used to perform a torsional fatigue test on the turbine blade 5. The turbine blade 5 includes a blade body 51 and a blade tenon 52; the clamping device 1 includes a first fixing component 11 and a second fixing component 12; the first fixing component 11 is connected to the blade tenon 52 and is used to fix the blade tenon 52; the second fixing component 12 is connected to one end side of the blade body 51 away from the blade tenon 52 and is used to fix the blade body 51; and the second fixing component 12 can move under the drive of the outside world so that the turbine blade 5 undergoes torsional deformation.

[0053] In the embodiments of the present disclosure, the blade tenon 52 is fixed by the first fixing component 11, the blade body 51 is fixed by the second fixing component 12, and at the same time, the second fixing component 12 can move under the drive of the outside world, so that the turbine blade 5 also has the movement trend of the second fixing component 12, so that the turbine blade 5 in this movement state can be detected, thereby realizing the torsional fatigue test on the turbine blade 5 under high torsional fatigue load.

[0054] See Figure 2 , Figure 3 , Figure 4 , Figure 5 , in some embodiments of the present disclosure, the first fixing component 11 includes symmetrically arranged fixing jigs 111 and a first mounting member 112 for fixing the fixing jigs 111; the symmetrically arranged fixing jigs 111 form a clamping space for the blade tenon 52. Thus, when it is necessary to fix the blade tenon 52, the blade tenon 52 is placed between the fixing jigs 111, and the relatively arranged fixing jigs 111 approach each other. When the fixing jigs 111 complete the state of clamping the blade tenon 52, the first mounting member 112 is adjusted, and the first mounting member 112 fixes the fixing jigs 111 on both sides of the blade tenon 52, thereby realizing the fixing of the blade tenon 52.

[0055] See Figure 5 , it should be noted that Figure 4 only a schematic diagram of a turbine blade 5 with double-row sawteeth is exemplified. In other embodiments, the turbine blade 5 can be single-row sawteeth (not specifically shown in the drawings of this application). Correspondingly, when the turbine blade 5 is single-row sawteeth, the fixing jigs 111 will also change accordingly, and the embodiments of the present disclosure will not elaborate on this.

[0056] In some embodiments of the present disclosure, the fixing fixture 111 includes a support section 1112 and a clamping section 1111; one end of the clamping section 1111 is connected to the support section 1112, and the other end has a clamping groove 11111 adapted to one side of the blade tenon 52; the first mounting member 112 is used to fix the symmetrically arranged clamping sections 1111; the support section 1112 is used to support the clamping section 1111. Thus, when fixing the blade tenon 52, the clamping section 1111 is brought close to the blade tenon 52, and the clamping sections 1111 on both sides of the blade tenon 52 gradually approach the blade tenon 52. When the serrations on the blade tenon 52 extend into the clamping groove 11111 and abut against the side wall of the clamping groove 11111, the first mounting member 112 is used to fix the clamping sections 1111 on both sides of the blade tenon 52 to achieve the fixation of the blade tenon 52.

[0057] In this embodiment, the clamping groove 11111 provided at one end of the clamping section 1111 increases the contact area between the blade tenon 52 and the clamping section 1111, thereby increasing the frictional force on the test piece. At the same time, the mutual fitting of the clamping section 1111 and the blade tenon 52 can also achieve the positioning of the turbine blade 5, avoiding the phenomenon of loading offset of the turbine blade 5 during the test.

[0058] In some embodiments of the present disclosure, the first mounting member 112 can be a mounting bolt 1121. When the blade tenon 52 is in a fixed state, the end of the mounting bolt 1121 contacts the end of the blade tenon 52 on the side away from the blade body 51. The mounting bolt 1121 arranged in this way can provide an upward supporting force to the blade tenon 52, making the blade tenon 52 fit more closely and firmly with the side wall of the clamping groove 11111 on the clamping section 1111, improving the fixing efficiency of the blade tenon 52 and ensuring the accuracy of the test.

[0059] Specifically, the blade tenon 52 is placed between adjacent clamping sections 1111, and the two clamping sections 1111 approach each other. The side wall of the clamping groove 11111 contacts the blade tenon 52. When the clamping section 1111 abuts against the blade tenon 52 and the positioning is completed, through the mounting bolt 1121, the mounting bolt 1121 fixes the two clamping sections 1111, thereby realizing the fixation of the blade tenon 52.

[0060] As an example, the following method can be used to fix the blade tenon 52: One end of the clamping section 1111 (the side without the clamping groove 11111) can be first fixed to the support section 1112, and then the symmetrically arranged clamping sections 1111 are brought close to the blade tenon 52. When the side wall of the clamping groove 11111 on the clamping section 1111 fits with the blade tenon 52, the blade tenon 52 on both sides and the clamping section 1111 are fixed through the first mounting member 112.

[0061] Of course, it is also possible to first fix the symmetrically arranged clamping sections 1111 and the blade tenon 52, and then fix the other ends of the two clamping sections 1111 to their respective corresponding support sections 1112. It should be noted that in other embodiments, there may be other steps to fix the blade tenon 52, and the present application does not make specific limitations thereto.

[0062] See Figure 3 、 Figure 7 , in some embodiments of the present disclosure, the fixing fixture 111 further includes an enlarging portion 1113; one end of the clamping section 1111 is fixedly connected to the support section 1112 through the enlarging portion 1113. With such a setting, the connection area between the clamping section 1111 and the support section 1112 can be increased, thereby improving the connection strength between the clamping section 1111 and the support section 1112, and further ensuring the accuracy of the detection test of the turbine blade 5.

[0063] In some embodiments of the present disclosure, the support section 1112 includes a horizontal portion 11121 and a vertical portion 11122; the horizontal portion 11121 is connected to the vertical portion 11122, and the length direction of the horizontal portion 11121 is perpendicular to the length direction of the vertical portion 11122; one end of the clamping section 1111 is fixedly connected to the vertical portion 11122 through the enlarging portion 1113.

[0064] Furthermore, the horizontal portion 11121 can be fixed to the test platform by bolts to further ensure the stability of the clamping of the turbine blade 5 during the detection of the turbine blade 5, and improve the detection accuracy of the turbine blade 5.

[0065] See Figure 2 、 Figure 6 , in some embodiments of the present disclosure, the second fixing assembly 12 includes a fixing clamp block 121 and a second mounting member 122; the fixing clamp block 121 is connected to one end of the blade body 51 of the turbine blade 5 away from the blade tenon 52 through the second mounting member 122; the fixing clamp block 121 can move under the external drive so that the turbine blade 5 undergoes torsional deformation.

[0066] Specifically, after the blade tenon 52 of the turbine blade 5 is fixed, one end of the blade body 51 of the turbine blade 5 away from the blade tenon 52 is connected to the fixing clamp block 121 through the second mounting member 122. When performing a high-cycle torsion test on the turbine blade 5, the fixing clamp block 121 is driven to move, and the fixing clamp block 121 drives the turbine blade 5 to move. In this way, the moving turbine blade 5 can be detected, and thus the high-cycle torsion test of the turbine blade 5 can be realized.

[0067] Alternatively, the fixing clip block 121 can be fixed to one end of the blade body 51 away from the blade tenon 52 through the second mounting member 122 first, and then the blade tenon 52 can be fixed through the first fixing assembly 11. When performing a high-cycle torsion test on the turbine blade 5, the fixing clip block 121 is driven to move, and the fixing clip block 121 drives the turbine blade 5 to move. In this way, the moving turbine blade 5 can also be detected, and then the torsion fatigue test of the turbine blade 5 can be realized.

[0068] In some embodiments of the present disclosure, the fixing clip block 121 has a fixing groove 1211; the blade body 51 extends into the fixing groove 1211 and is connected to the side wall of the fixing groove 1211; the second mounting member 122 is used to fixedly connect the blade body 51 to the side wall of the fixing groove 1211.

[0069] Specifically, when fixing one end of the blade body 51 away from the blade tenon 52, the blade body 51 is extended into the fixing groove 1211, and the blade body 51 slides in the fixing groove 1211. After the blade body 51 moves to a suitable position, the second mounting member 122 is used to fix the blade body 51 to the side wall of the fixing groove 1211 to realize the fixation of the blade body 51. In the disclosed embodiments, through the provided fixing groove 1211, the fixation of the blade body 51 can be better realized, thereby improving the fixing effect on the turbine blade 5 and ensuring the accuracy of the torsion fatigue test on the turbine blade 5.

[0070] See Figure 8 , further, in some embodiments, the fixing groove 1211 is provided as a semi-closed groove, that is, one end of the fixing groove 1211 is open for the blade body 51 to extend into the fixing groove 1211, and the other end of the fixing groove 1211 is closed or semi-closed. In this way, when the blade body 51 moves to a certain position, the blade body 51 cannot move forward. At this time, the blade body 51 can be fixed by the second mounting member 122.

[0071] As an example, the second mounting member 122 can be a bolt. Specifically, when the blade body 51 moves to a specified position, a bolt is passed through the fixing clip block 121, and the end of the bolt abuts against the blade body 51, thereby achieving the purpose of fixing the blade body 51.

[0072] See Figure 2, embodiments of the present disclosure also provide a high-cycle torsional fatigue test system. The high-cycle torsional fatigue test system is used to test turbine blades. The test system includes a transmission device 4, an exciter device 2, a heating device 3, and the clamping device 1 described above. Among them, the exciter device 2 is connected to the fixed clamp block 121 through the transmission device 4, and the exciter device 2 is configured to generate an exciting force; the transmission device 4 is configured to transmit the power generated by the exciter device 2 to the turbine blade 5; the heating device 3 is configured to regulate the test temperature of the turbine blade 5.

[0073] As an example, the heating device 3 can be an inductive graphite thermal radiation heating device 3, and this heating device 3 can regulate the real temperature when the simulated blade is in service. During heating, the temperature of the test piece should not exceed the upper limit allowed by the specified temperature. During the entire heating process, the force on the test piece should not exceed the material yield strength. At the same time, the test should start after maintaining the test temperature for at least a period of time.

[0074] In some embodiments of the present disclosure, the transmission device 4 includes a driving rack 41 and a driving gear 42; the driving gear 42 is arranged on one side of the sleeve; one end of the driving rack 41 is connected to the output end of the exciter device 2, and the driving rack 41 meshes with the driving gear 42. Among them, the movement direction of the driving rack 41 is perpendicular to the length direction of the blade body 51. In this way, when the exciter device 2 is turned on, the output end of the exciter device 2 generates power. The power generated by the exciter device 2 drives the driving rack 41 to move linearly. The movement of the driving rack 41 drives the driving gear 42 to move. The movement of the driving gear 42 drives the fixed clamp block 121 to move. The movement of the fixed clamp block 121 drives the turbine blade 5 to move. The equipment records the values of force, deformation, and temperature at the maximum and minimum values of stress and strain of the turbine blade 5 and at the start and end of the holding time.

[0075] For example, a fatigue testing machine can be used to test the test piece. Specifically, the fatigue testing machine includes a control system and a data acquisition system; among them, the control system is used to accurately control variables such as load, frequency, and temperature during the test process; the data acquisition system is used to record test data in real time.

[0076] Further, referring to Figure 2 、 Figure 9 , the transmission device 4 further includes a support rod 44. One end of the support rod 44 is fixedly connected to the driving gear 42 by key connection, and the other end can be installed on the test platform. Such a setting can prevent the driving gear 42 from shaking during the test, and thus can improve the accuracy of the test.

[0077] In some embodiments of the present disclosure, the transfer device 4 includes a third mounting member 43; one side of the fixed clamping block 121 has a mounting groove 1212; the driving gear 42 is detachably disposed in the mounting groove 1212 through the third mounting member 43. Thus, when the turbine blade 5 needs to move, the vibrator device 2 drives the driving rack 41 to move, the driving rack 41 drives the driving gear 42 to move, and the movement of the driving gear 42 drives the fixed clamping block 121 to move, achieving the purpose of driving the turbine blade 5 to move.

[0078] Furthermore, a mounting groove 1212 is provided on one side of the fixed clamping block 121, and the driving gear 42 is fixed in the mounting groove 1212 through the third mounting member 43. The provided mounting groove 1212 can improve the fixing strength between the driving gear 42 and the fixed clamping block 121, contributing to improving the stability of the force generated by the vibrator device 2 being transmitted to the fixed clamping block 121.

[0079] See Figure 8 , as an example, the third mounting member 43 can be a bolt. Specifically, one end of the driving gear 42 is placed in the mounting groove 1212, and the driving gear 42 is fixed to the side wall of the mounting groove 1212 through a bolt. Thus, when the test is not required, the driving gear 42 can be disassembled and stored.

[0080] See Figure 10 , the embodiments of the present disclosure also provide a test method for turbine blades, including the following steps:

[0081] S1: Provide a test piece of the turbine blade 5.

[0082] Specifically, when providing the test piece of the turbine blade 5, it is first necessary to determine the test piece to see if it meets the requirements of this test. For example, visually determine whether there are any fine fractures or damages on the test piece. If so, it does not meet the requirements of this test. If the appearance of the test piece is normal, it is necessary to classify and process the test and make relevant markings for subsequent tests.

[0083] S2: Clamp and fix the blade tenon 52 of the turbine blade 5 to the fixed fixture 111.

[0084] Specifically, the two clamping sections 1111 can be brought close to the blade tenon 52 of the turbine blade 5. When the side wall of the clamping groove 11111 abuts against the blade tenon 52, the two sides of the blade tenon 52 and the clamping section 1111 are fixed through the first mounting member 112. After the blade tenon 52 is fixed, the clamping section 1111 is fixed to the corresponding support section 1112 through the enlarging portion 1113, and then the support section 1112 is fixed to the test bench.

[0085] S3: Connect the blade body 51 of the turbine blade 5 to the fixed clamping block 121, and connect it to the vibrator device 2 through the transmission device 4.

[0086] Specifically, install the fixed clamping block 121 at one end of the blade body 51 away from the blade tenon 52, and connect the fixed clamping block 121 to the vibrator device 2 through the transmission device 4.

[0087] S4: Turn on the vibrator device 2, and record the relevant data (such as the torsional angle, torsional frequency, etc.) of the turbine blade 5 through the device.

[0088] During the test of the test piece, the frequency of applying the force cycle to the test piece depends on the type of testing machine used, and in many cases depends on the stiffness of the test piece. The selection of the frequency depends on the combination of the material, the test piece and the testing machine. If the frequency depends on the dynamic characteristics of the combination of the test piece and the testing machine, it is necessary to measure the stiffness of the test piece before the test; at the same time, the force application procedure for each test piece in a group of test pieces remains the same. The average force and the force value range should be kept within a reasonable range of the force value. The embodiments of the present disclosure will not be elaborated here.

[0089] It should be noted that if it is found that there are fractures or large deformations on the test piece after the test, it is necessary to take a new test piece (this test piece is of the same type as the test piece with problems) for the test. At the same time, during the experiment, the force, deformation, and temperature should be continuously recorded at the key turning points within the test cycle, that is, at the maximum and minimum values of stress and strain and at the beginning and end of the holding time.

[0090] After the test of the turbine blade 5 is completed, it is necessary to turn off the heating device 3 to end the test. Specifically, after the test is completed, the heating system should be turned off immediately to reduce the oxidation degree of the test piece and the crack surface before the post-test inspection. If it is terminated before the experimental fracture, it is necessary to avoid overloading the test piece during the cooling process of the heating equipment as much as possible.

[0091] It should be noted that in the test method of the turbine blade 5 provided in the embodiments of the present disclosure, the order of steps S2 and S3 can be adjusted, and the embodiments of the present application do not make specific limitations. As long as the fixing effect on the turbine blade 5 can be achieved.

[0092] Those skilled in the art will readily think of other embodiments of the present disclosure after considering the specification and practicing the invention disclosed herein. This application is intended to cover any variations, uses, or adaptations of the present disclosure, which follow the general principles of the present disclosure and include common general knowledge or conventional technical means in the technical field not disclosed in the present disclosure. The specification and the embodiments are only regarded as exemplary, and the true scope and spirit of the present disclosure are pointed out by the appended claims.

Claims

1. A clamping device for a turbine blade, characterized in that, The turbine blade includes a blade body and a blade tenon; the clamping device includes a first fixing component and a second fixing component; The first fixing component is connected to the blade tenon and is used for fixing the blade tenon; The second fixing component is connected to one end side of the blade body away from the blade tenon and is used for fixing the blade body; and the second fixing component can move under external driving so that the turbine blade undergoes torsional deformation.

2. The clamping device for turbine blades according to claim 1, characterized in that, The first fixing component includes symmetrically arranged fixing jigs and a first mounting member for fixing the fixing jigs; The symmetrically arranged fixing jigs form a clamping space for the blade tenon.

3. The clamping device for turbine blades according to claim 2, wherein The fixing jig includes a support section and a clamping section; One end of the clamping section is connected to the support section, and the other end has a clamping groove adapted to one side of the blade tenon; The first mounting member is used for fixing the symmetrically arranged clamping sections; The support section is used for supporting the clamping section.

4. The clamping device for turbine blades according to claim 3, characterized in that, The first mounting member includes a mounting bolt; When the blade tenon is in a fixed state, the end of the mounting bolt contacts the end of the blade tenon on the side away from the blade body.

5. The clamping device for turbine blades according to claim 1, characterized in that, The second fixing component includes a fixing block and a second mounting member; The fixing block is connected to one end of the blade body away from the blade tenon through the second mounting member; The fixing block can move under external driving so that the turbine blade undergoes torsional deformation.

6. The clamping device for turbine blades according to claim 5, characterized in that, The fixing block has a fixing groove; The blade body extends into the fixing groove and is connected to the side wall of the fixing groove; The second mounting member is used for fixedly connecting the blade body and the side wall of the fixing groove.

7. A high-cycle torsional fatigue test system, characterized in that, Including the turbine blade clamping device according to any one of claims 1 to 6; The test system further includes a transmission device, an exciter device, and a heating device; The exciter device is connected to the fixing block through the transmission device, wherein the exciter device is configured to generate an exciting force; The transmission device is configured to transmit the power generated by the exciter device to the turbine blade; The heating device is configured to regulate the test temperature of the turbine blade.

8. The high-cycle torsional fatigue test system according to claim 7, wherein The transmission device includes a driving rack and a driving gear; The driving gear is arranged on one side of the fixing block; One end of the driving rack is connected to the output end of the exciter device, and the driving rack meshes with the driving gear, wherein the moving direction of the driving rack is perpendicular to the length direction of the blade body.

9. The high-cycle torsional fatigue test system according to claim 8, characterized in that, The transmission device includes a third mounting member; One side of the fixing block has a mounting groove; The driving gear is detachably arranged in the mounting groove through the third mounting member.

10. A turbine blade test method, characterized in that, Including: Providing a turbine blade test piece; Clamping and fixing the blade tenon of the turbine blade to the fixing jig; Connecting the blade body of the turbine blade to the fixing block and connecting it to the exciter device through the transmission device; Turning on the exciter device and recording relevant data of the turbine blade through the equipment.

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