A testing device for local micro-strain-axial deformation relationship of a gas turbine front support

Abstract

A kind of gas turbine front support local micro-strain-axial deformation relationship testing device, it is related to gas turbine technical field.For solving the problem that when the existing thermal expansion superimposed measurement method is used to measure gas turbine front support, due to the non-linear deformation caused by ignoring the factors such as flange stiffness, bolt pre-tightening constraint, temperature gradient inhomogeneity, local cooling, and the axial additional displacement caused by casing bending and torsional deformation has not been considered, the measurement error is large.The present application avoids the inherent limitations of the existing gas turbine axial deformation expansion superposition method, by measuring the real-time measurement of the local micro-strain of the measured intermediate stand plate on the intake side and the measured intermediate stand plate on the exhaust side of the gas turbine front support, the total axial deformation of the casing is obtained.The device is simple to assemble, low in cost, and can be modularly replaced according to different types of gas front support structure, while improving the accuracy of the measurement data.The present application is suitable for testing the local micro-strain of the gas turbine front support.

Description

Technical Field

[0001] This invention relates to the field of gas turbine technology, and more specifically to a device for testing the relationship between local micro-strain and axial deformation of the front support of a gas turbine. Background Technology

[0002] As a core load-bearing and positioning component of the gas turbine unit, the front support of the gas turbine plays a crucial role in bearing the weight of the unit, buffering operational vibrations, compensating for thermal deformation, and limiting axial displacement. The local micro-strain and axial deformation generated under high temperature, high pressure, and alternating load coupling conditions directly affect the alignment accuracy of the gas turbine rotor, the stability of the gap between dynamic and static components, and the overall operational safety and reliability of the unit.

[0003] Currently, the most common method for testing the axial displacement of gas turbine casings is the thermal expansion superposition measurement method. Its core logic is that the entire casing is composed of multiple flanged sections, such as the low-pressure compressor casing, load-bearing casing, high-pressure compressor casing, and combustion chamber casing. Each section expands independently based on its own axial fixed support point, and the total axial displacement of the entire casing is equal to the linear superposition of the axial expansion of each individual section. However, the thermal expansion superposition method ignores nonlinear deformation caused by factors such as flange stiffness, bolt preload constraints, uneven temperature gradients, and localized cooling. Furthermore, it does not consider the additional axial displacement caused by casing bending and torsional deformation. Therefore, the test error is relatively large, and the measured axial deformation of the casing can only be used as a reference value, failing to accurately describe the true axial deformation of the casing. In addition, the thermal expansion superposition measurement method requires a large number of measurement points, and the wiring and bracket installation of high-temperature probes are labor-intensive, further increasing the pre-processing time and testing costs.

[0004] In summary, the existing thermal expansion superposition measurement method for measuring the front support of a gas turbine has significant errors because it ignores nonlinear deformation caused by factors such as flange stiffness, bolt preload constraints, uneven temperature gradient, and local cooling, and does not consider the additional axial displacement caused by casing bending and torsional deformation. Summary of the Invention

[0005] This invention addresses the problem that existing thermal expansion superposition measurement methods for measuring the front support of gas turbines suffer from large measurement errors due to neglecting nonlinear deformation caused by factors such as flange stiffness, bolt preload constraints, uneven temperature gradients, and local cooling, and also failing to consider the additional axial displacement caused by casing bending and torsional deformation. Therefore, this invention proposes a testing device for the local micro-strain-axial deformation relationship of the front support of a gas turbine.

[0006] The present invention provides a testing device for the local micro-strain-axial deformation relationship of the front support of a gas turbine, which comprises a motor support frame 17, a servo electric cylinder 18, a first slide rail support frame, a first slide rail 21, a square slider 23, a strip slider 24, a second slide rail 25, a second slide rail support frame, and a workpiece clamping assembly.

[0007] The motor support frame 17, the first slide rail support frame, the workpiece clamping assembly, and the second slide rail support frame are arranged in a collinear manner from left to right. The motor support frame 17 is equipped with a servo electric cylinder 18. The top of the first slide rail support frame is equipped with a first slide rail 21, and the top of the second slide rail support frame is equipped with a second slide rail 25. A groove is machined along the length direction in the middle of the bottom surface of the strip slider 24. The groove at the bottom of one end of the strip slider 24 is slidably connected with the first slide rail 21, and the groove at the bottom of the other end of the strip slider 24 is slidably connected with the second slide rail 25. The output end of the servo electric cylinder 18 is connected to the center of the end face of the strip slider 24. A square groove is machined along the center of the long side end face of the strip slider 24. A square slider 23 is embedded inside the square groove. The square slider 23 is connected to the pressure end of the workpiece clamping assembly.

[0008] Furthermore, the workpiece fixture assembly includes a fixture base 1, a T-shaped connecting seat 2, a bottom pad 3, a top pad 6, a top disc 7, and bolts 8;

[0009] The upper surface of the fixture base 1 is provided with a T-shaped connecting seat 2, and a top disc 7 is provided directly above the T-shaped connecting seat 2. The two end faces between the T-shaped connecting seat 2 and the top disc 7 are respectively installed with the middle vertical plate 4 on the intake side and the middle vertical plate 5 on the exhaust side. The top ends of the middle vertical plate 4 on the intake side and the middle vertical plate 5 on the exhaust side are rigidly fixed to the bottom of the top disc 7 through the top gasket 6 and the bolt 8. The bottom ends of the middle vertical plate 4 on the intake side and the middle vertical plate 5 on the exhaust side are rigidly fixed to the top of the T-shaped connecting seat 2 through the bottom gasket 3 and the bolt 8.

[0010] Furthermore, a circular groove is machined at the center of the end face of the square slider 23, and the top disc 7 of the workpiece clamping assembly is nested and connected with the circular groove of the square slider 23, and is rigidly fixed by at least four bolts 8.

[0011] Furthermore, the upper side of the middle vertical plate 4 on the measured air intake side is uniformly provided with J1 air intake side strain gauge 9 and J2 air intake side strain gauge 10 along the width direction, and J1 air intake side strain gauge 9 is connected to the first air intake side strain gauge 11 through a wire, and J2 air intake side strain gauge 10 is connected to the second air intake side strain gauge 12 through a wire.

[0012] Furthermore, the lower side of the middle vertical plate 5 on the tested exhaust side is uniformly provided with P1 exhaust side strain gauge 13 and P2 exhaust side strain gauge 14 along the width direction, and P1 exhaust side strain gauge 13 is connected to the first exhaust side strain gauge 15 through a wire, and P2 exhaust side strain gauge 14 is connected to the second exhaust side strain gauge 16 through a wire.

[0013] Furthermore, the first slide rail support frame includes an electric cylinder telescopic arm support plate 19, a first base 20, and a first slide rail bracket 22. The electric cylinder telescopic arm support plate 19 is provided at one end of the upper surface of the first base 20, and the first slide rail bracket 22 is provided at the other end of the upper surface of the first base 20. A U-shaped groove is machined at the center of the top surface of the electric cylinder telescopic arm support plate 19, and the U-shaped groove is slidably connected to the outer surface of the telescopic arm of the servo electric cylinder 18.

[0014] Furthermore, the electric cylinder telescopic arm support plate 19, the first base 20, and the first slide rail bracket 22 are integrally formed;

[0015] Furthermore, the second slide rail support frame includes a second slide rail bracket 26 and a second base 27, with the second slide rail bracket 26 located in the middle of the upper surface of the second base 27.

[0016] Furthermore, the second slide rail bracket 26 and the second base 27 are integrally formed;

[0017] Furthermore, the sum of the heights of the second slide rail bracket 26 and the second base 27 is equal to the sum of the heights of the first base 20 and the first slide rail bracket 22.

[0018] Furthermore, during use, firstly, attach strain gauges to the middle positions of the top of the air intake side and the bottom of the exhaust side of the front support's intermediate vertical plate, ensuring that the spacing between the strain gauges on the air intake and exhaust sides is the same, and that they are at the same distance from the edge of the intermediate vertical plate. Connect the strain gauges on the air intake and exhaust sides to a strain gauge, and adjust the strain gauge to ensure that the initial strain value of the strain gauge is zero.

[0019] Then, the components of the axial loading device are assembled and installed on a cast iron test bench. The telescopic arm of the servo electric cylinder 18 is precisely controlled by the PLC programming operation box to move along the axial direction by different distances. This pushes the strip slider 24 to transmit the axial thrust through the square slider 23 to the top of the top disk 7. At this time, the top disk 7 of the workpiece fixture assembly transmits the thrust to the middle vertical plate 4 on the intake side and the middle vertical plate 5 on the exhaust side. Even if the middle vertical plate 4 on the intake side and the middle vertical plate 5 on the exhaust side produce the same axial deformation, the strain data displayed by the strain gauge under different axial deformations are recorded. The experiment is then repeated to form an experimental database.

[0020] Finally, using the strain data measured in the experiment as the independent variable and the axial deformation value displayed by the PLC programming controller as the dependent variable, a functional relationship between the two was obtained through linear fitting, realizing the numerical conversion of the axial deformation of the gas turbine into a local strain variable, such as... Figure 5 As shown. During the operation of the gas turbine, the axial deformation data of the gas turbine casing can be monitored in real time by measuring and fitting the functional relationship based on the device of this invention and recording the strain gauge data in real time.

[0021] Compared with the prior art, the present invention has the following advantages:

[0022] This invention overcomes the shortcomings of existing technologies. The measurement device of this structure avoids the inherent limitations of the existing superposition method for axial deformation and expansion of gas turbines. It fully considers the nonlinear deformation caused by factors such as flange stiffness, bolt preload constraints, uneven temperature gradients, and localized cooling. It also considers the additional axial displacement caused by casing bending and torsional deformation. By measuring the local micro-strain of the intermediate vertical plates on the inlet and exhaust sides of the gas turbine's front support in real time, the total axial deformation of the casing is calculated. The device is simple to assemble, low in cost, and can be modularly replaced according to different gas turbine front support structures. It also improves the accuracy of measurement data, minimizing measurement errors, thus providing data support for gas turbine fault diagnosis and prediction, and has broad application prospects. Attached Figure Description

[0023] Figure 1 This is a three-dimensional structural diagram of the workpiece fixture assembly in the gas turbine front support local micro-strain-axial deformation relationship testing device described in this invention.

[0024] Figure 2 This is a front view of the workpiece fixture assembly in the gas turbine front support local micro-strain-axial deformation relationship testing device described in this invention;

[0025] Figure 3 This is a rear view of the workpiece fixture assembly in the gas turbine front support local micro-strain-axial deformation relationship testing device described in this invention;

[0026] Figure 4 This is a three-dimensional structural schematic diagram of a gas turbine front support local micro-strain-axial deformation relationship testing device according to the present invention;

[0027] Figure 5 The maximum principal strain of the gas turbine front support on the intake and exhaust sides is captured by the local micro-strain-axial deformation relationship testing device described in this invention, which is used to capture the change curve of the random casing axial displacement of the random casing axial displacement of the specific grid nodes on the intake and exhaust sides of the gas turbine front support. Detailed Implementation

[0028] Specific implementation method one: Combining Figures 1 to 5 This embodiment describes a gas turbine front support local micro-strain-axial deformation relationship testing device, which comprises a motor support frame 17, a servo electric cylinder 18, a first slide rail support frame, a first slide rail 21, a square slider 23, a strip slider 24, a second slide rail 25, a second slide rail support frame, and a workpiece clamping assembly.

[0029] The motor support frame 17, the first slide rail support frame, the workpiece clamping assembly, and the second slide rail support frame are arranged in a collinear manner from left to right. The motor support frame 17 is equipped with a servo electric cylinder 18. The top of the first slide rail support frame is equipped with a first slide rail 21, and the top of the second slide rail support frame is equipped with a second slide rail 25. A groove is machined along the length direction in the middle of the bottom surface of the strip slider 24. The groove at the bottom of one end of the strip slider 24 is slidably connected with the first slide rail 21, and the groove at the bottom of the other end of the strip slider 24 is slidably connected with the second slide rail 25. The output end of the servo electric cylinder 18 is connected to the center of the end face of the strip slider 24. A square groove is machined along the center of the long side end face of the strip slider 24. A square slider 23 is embedded inside the square groove. The square slider 23 is connected to the pressure end of the workpiece clamping assembly.

[0030] In this specific embodiment, the axial extension distance of the servo electric cylinder 18 is precisely controlled by programming through a PLC controller, that is, the axial deformation of the top of the top disc 7 in the workpiece fixture assembly is precisely controlled. The servo electric cylinder 18 is placed horizontally on the motor support frame 17. The first slide rail 21 provides guidance for the large slider to slide axially along the y-axis, so that the strip slider 24 slides strictly along the y-axis and does not deviate in the x-axis direction. A square groove is machined at the center of the long side end face of the strip slider 24, and a square slider 23 is embedded inside the square groove. Due to the restriction of the strip slider 24, the square slider 23 can only translate along the y-axis and z-axis, but cannot rotate along the x-axis. The groove at the bottom of one end of the strip slider 24 is slidably connected to the first slide rail 21, and the groove at the bottom of the other end of the strip slider 24 is slidably connected to the second slide rail 25, so that the large slider can translate strictly in the y-axis direction. A square slider 23 is embedded in the center of the strip slider 24, allowing the square slider 23 to move along the y-axis and the z-axis following the strip slider 24. Furthermore, the strip slider 24 also restricts the rotation of the square slider 23, preventing it from rotating along the x-axis. The dovetail groove, the first slide rail 21, and the second slide rail 25 in the strip slider 24 achieve extremely high fitting precision. The second slide rail 25 provides guidance for the axial sliding of the strip slider 24 along the y-axis, ensuring that the strip slider 24 slides strictly along the y-axis without any offset in the x-axis direction.

[0031] Specific Implementation Method Two: Combining Figures 1 to 5 This embodiment further defines the testing device described in Specific Embodiment 1. The gas turbine front support local micro-strain-axial deformation relationship testing device described in this embodiment includes a workpiece fixture assembly comprising a fixture base 1, a T-shaped connecting seat 2, a bottom pad 3, a top pad 6, a top disc 7, and bolts 8.

[0032] The upper surface of the fixture base 1 is provided with a T-shaped connecting seat 2, and a top disc 7 is provided directly above the T-shaped connecting seat 2. The two end faces between the T-shaped connecting seat 2 and the top disc 7 are respectively installed with the middle vertical plate 4 on the intake side and the middle vertical plate 5 on the exhaust side. The top ends of the middle vertical plate 4 on the intake side and the middle vertical plate 5 on the exhaust side are rigidly fixed to the bottom of the top disc 7 through the top gasket 6 and the bolt 8. The bottom ends of the middle vertical plate 4 on the intake side and the middle vertical plate 5 on the exhaust side are rigidly fixed to the top of the T-shaped connecting seat 2 through the bottom gasket 3 and the bolt 8.

[0033] In this specific embodiment, the top disc 7 is integrally formed with an I-beam, and at least four through holes are uniformly machined on the end face of the disc along the circumferential direction, with a bolt inside each through hole.

[0034] Specific implementation method three: Combining Figures 1 to 5 This embodiment is a further limitation of the testing device described in Specific Embodiment Two. The gas turbine front support local micro-strain-axial deformation relationship testing device described in this embodiment has a circular groove machined at the center of the end face of the square slider 23, and the top disk 7 of the workpiece clamping assembly is nested and connected with the circular groove of the square slider 23, and is rigidly fixed by at least four bolts 8.

[0035] In this specific embodiment, the top disc 7 of the workpiece clamping assembly is nested and connected with the circular groove of the square slider 23. Combined with the axial thrust of the servo electric cylinder 18, the top disc 7 can disperse the axial thrust into forces along the x, y, and z axes, thereby applying forces in different directions to the middle vertical plate 4 on the intake side and the middle vertical plate 5 on the exhaust side.

[0036] Specific implementation method four: Combination Figures 1 to 5This embodiment further defines the testing device described in Specific Embodiment Two. In this embodiment, a testing device for the local micro-strain-axial deformation relationship of a gas turbine front support is provided. J1 intake side strain gauge 9 and J2 intake side strain gauge 10 are uniformly provided on the upper side of the middle vertical plate 4 on the test intake side along the width direction. J1 intake side strain gauge 9 is connected to the first intake side strain gauge 11 through a wire, and J2 intake side strain gauge 10 is connected to the second intake side strain gauge 12 through a wire.

[0037] Specific Implementation Method Five: Combining Figures 1 to 5 This embodiment further defines the testing device described in Specific Embodiment 4. The gas turbine front support local micro-strain-axial deformation relationship testing device described in this embodiment has P1 exhaust side strain gauge 13 and P2 exhaust side strain gauge 14 uniformly arranged along the width direction on the lower side of the side of the middle vertical plate 5 on the exhaust side being tested. P1 exhaust side strain gauge 13 is connected to the first exhaust side strain gauge 15 through a wire, and P2 exhaust side strain gauge 14 is connected to the second exhaust side strain gauge 16 through a wire.

[0038] In this specific embodiment, after obtaining the strain data of the first intake-side strain gauge 11, the second intake-side strain gauge 12, the first exhaust-side strain gauge 15, and the second exhaust-side strain gauge 16, and the corresponding axial deformation of the top disc of the front support, the strain value is used as the independent variable and the axial deformation as the dependent variable to fit a functional relationship between the two. Since strain gauges are attached at four locations, four fitting curves are obtained, such as... Figure 5 As shown.

[0039] Specific Implementation Method Six: Combination Figures 1 to 5 This embodiment further defines the testing device described in Specific Embodiment 1. The gas turbine front support local micro-strain-axial deformation relationship testing device described in this embodiment includes an electric cylinder telescopic arm support plate 19, a base 20, and a slide rail bracket 22. The electric cylinder telescopic arm support plate 19 is provided at one end of the upper surface of the base 20, and the slide rail bracket 22 is provided at the other end of the upper surface of the base 20. A U-shaped groove is machined at the center of the top surface of the electric cylinder telescopic arm support plate 19, and the U-shaped groove is slidably connected to the outer surface of the telescopic arm of the servo electric cylinder 18.

[0040] In this specific embodiment, the electric cylinder telescopic arm support plate 19 provides vertical support for the telescopic arm of the servo electric cylinder 18, and a U-shaped groove is machined at the center of the top surface of the electric cylinder telescopic arm support plate 19. The U-shaped groove is slidably connected to the outer surface of the telescopic arm of the servo electric cylinder 18 to limit the rigid movement of the telescopic arm of the servo electric cylinder 18 along the x-axis.

[0041] Specific implementation method seven: Combination Figures 1 to 5 This embodiment further defines the testing device described in Specific Embodiment Six. The gas turbine front support local micro-strain-axial deformation relationship testing device described in this embodiment is an integrally set electric cylinder telescopic arm support plate 19, base 20 and slide rail bracket 22.

[0042] Specific implementation method eight: Combination Figures 1 to 5 This embodiment further defines the testing device described in Specific Embodiment Six. The gas turbine front support local micro-strain-axial deformation relationship testing device described in this embodiment includes a second slide rail support frame 26 and a second base 27. The second slide rail support 26 is provided in the middle of the upper surface of the second base 27.

[0043] Specific Implementation Method Nine: Combining Figures 1 to 5 This embodiment further defines the testing device described in Specific Embodiment Eight. In this embodiment, a gas turbine front support local micro-strain-axial deformation relationship testing device is provided, wherein the No. 2 slide rail bracket 26 and the No. 2 base 27 are integrally set.

[0044] Specific Implementation Method Ten: Combining Figures 1 to 5 This embodiment further defines the testing device described in Specific Embodiment Eight. In this embodiment, the sum of the heights of the second slide rail bracket 26 and the second base 27 is equal to the sum of the heights of the first base 20 and the first slide rail bracket 22.

[0045] Working principle

[0046] In use, first attach strain gauges to the middle positions of the top of the air intake side and the bottom of the exhaust side of the middle support plate. Ensure that the spacing between the strain gauges on the air intake and exhaust sides is the same, and that they are equidistant from the edge of the middle support plate. Connect the strain gauges on the air intake and exhaust sides to a strain gauge and adjust the strain gauge to ensure that the initial strain value of the strain gauge is zero.

[0047] Then, the components of the axial loading device are assembled and installed on a cast iron test bench. The telescopic arm of the servo electric cylinder 18 is precisely controlled by the PLC programming operation box to move along the axial direction by different distances. This pushes the strip slider 24 to transmit the axial thrust through the square slider 23 to the top of the top disk 7. At this time, the top disk 7 of the workpiece fixture assembly transmits the thrust to the middle vertical plate 4 on the intake side and the middle vertical plate 5 on the exhaust side. Even if the middle vertical plate 4 on the intake side and the middle vertical plate 5 on the exhaust side produce the same axial deformation, the strain data displayed by the strain gauge under different axial deformations are recorded. The experiment is then repeated to form an experimental database.

[0048] Finally, using the strain data measured in the experiment as the independent variable and the axial deformation value displayed by the PLC programming controller as the dependent variable, a functional relationship between the two was obtained through linear fitting, realizing the numerical conversion of the axial deformation of the gas turbine into a local strain variable, such as... Figure 5 As shown. During the operation of the gas turbine, the axial deformation data of the gas turbine casing can be monitored in real time by measuring and fitting the functional relationship based on the device of this invention and recording the strain gauge data in real time.

Claims

1. A testing device for the local micro-strain-axial deformation relationship of a gas turbine front support, characterized in that: It includes a motor support frame (17), a servo electric cylinder (18), a first slide rail support frame, a first slide rail (21), a square slider (23), a strip slider (24), a second slide rail (25), a second slide rail support frame, and a workpiece clamping assembly; The motor support frame (17), the first slide rail support frame, the workpiece fixture assembly, and the second slide rail support frame are arranged in a collinear manner from left to right. The motor support frame (17) is equipped with a servo electric cylinder (18). The top of the first slide rail support frame is equipped with a first slide rail (21), and the top of the second slide rail support frame is equipped with a second slide rail (25). The bottom surface of the strip slider (24) has a groove processed along the length direction. The groove at the bottom of one end of the strip slider (24) is slidably connected with the first slide rail (21). The groove at the bottom of the other end of the strip slider (24) is slidably connected with the second slide rail (25). The output end of the servo electric cylinder (18) is connected to the center of the end face of the strip slider (24). The strip slider (24) has a square groove processed along the center of the long side end face. A square slider (23) is embedded inside the square groove. The square slider (23) is connected to the pressure end of the workpiece fixture assembly.

2. The gas turbine front support local micro-strain-axial deformation relationship testing device according to claim 1, characterized in that: The workpiece fixture assembly includes a fixture base (1), a T-shaped connector (2), a bottom gasket (3), a top gasket (6), a top disc (7), and bolts (8). The upper surface of the fixture base (1) is provided with a T-shaped connecting seat (2), and a top disc (7) is provided directly above the T-shaped connecting seat (2). The two end faces between the T-shaped connecting seat (2) and the top disc (7) are successively equipped with the middle vertical plate (4) of the air intake side to be tested and the middle vertical plate (5) of the air exhaust side to be tested. The top ends of the middle vertical plate (4) of the air intake side to be tested and the middle vertical plate (5) of the air exhaust side to be tested are rigidly fixed to the bottom of the top disc (7) through the top gasket (6) and the bolt (8). The bottom ends of the middle vertical plate (4) of the air intake side to be tested and the middle vertical plate (5) of the air exhaust side to be tested are rigidly fixed to the top of the T-shaped connecting seat (2) through the bottom gasket (3) and the bolt (8).

3. The gas turbine front support local micro-strain-axial deformation relationship testing device according to claim 2, characterized in that: The square slider (23) has a circular groove machined at the center of its end face, and the top disc (7) of the workpiece fixture assembly is nested and connected with the circular groove of the square slider (23), and is rigidly fixed by at least four bolts (8).

4. The gas turbine front support local micro-strain-axial deformation relationship testing device according to claim 2, characterized in that: The upper side of the middle vertical plate (4) of the air intake side is uniformly provided with J1 air intake side strain gauge (9) and J2 air intake side strain gauge (10) along the width direction. J1 air intake side strain gauge (9) is connected to the first air intake side strain gauge (11) through a wire, and J2 air intake side strain gauge (10) is connected to the second air intake side strain gauge (12) through a wire.

5. The testing device for the local micro-strain-axial deformation relationship of the front support of a gas turbine according to claim 4, characterized in that: The lower side of the middle vertical plate (5) of the exhaust side under test is uniformly provided with P1 exhaust side strain gauge (13) and P2 exhaust side strain gauge (14) along the width direction. P1 exhaust side strain gauge (13) is connected to the first exhaust side strain gauge (15) through a wire, and P2 exhaust side strain gauge (14) is connected to the second exhaust side strain gauge (16) through a wire.

6. The testing device for the local micro-strain-axial deformation relationship of the front support of a gas turbine according to claim 1, characterized in that: The first slide rail support frame includes an electric cylinder telescopic arm support plate (19), a first base (20), and a first slide rail bracket (22). The electric cylinder telescopic arm support plate (19) is provided at one end of the upper surface of the first base (20), and the first slide rail bracket (22) is provided at the other end of the upper surface of the first base (20). A U-shaped groove is machined at the center of the top surface of the electric cylinder telescopic arm support plate (19), and the U-shaped groove is slidably connected to the outer surface of the telescopic arm of the servo electric cylinder (18).

7. The gas turbine front support local micro-strain-axial deformation relationship testing device according to claim 6, characterized in that: The electric cylinder telescopic arm support plate (19), the No. 1 base (20), and the No. 1 slide rail bracket (22) are integrated into one unit.

8. The gas turbine front support local micro-strain-axial deformation relationship testing device according to claim 6, characterized in that: The second slide rail support frame includes a second slide rail bracket (26) and a second base (27), with the second slide rail bracket (26) located in the middle of the upper surface of the second base (27).

9. The testing device for the local micro-strain-axial deformation relationship of the front support of a gas turbine according to claim 8, characterized in that: The No. 2 slide rail bracket (26) and the No. 2 base (27) are integrated.

10. The gas turbine front support local micro-strain-axial deformation relationship testing device according to claim 8, characterized in that: The sum of the heights of the second slide rail bracket (26) and the second base (27) is equal to the sum of the heights of the first base (20) and the first slide rail bracket (22).

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