System for inspecting turbin blade

Abstract

In order to efficiently inspect the circumferential balance of a plurality of turbine blades, the present invention provides a turbine blade inspection system for inspecting the circumferential arrangement balance of a plurality of turbine blades, comprising: a gauge plate formed of a circular plate material having a plurality of fastening portions to which a fastening means is fastened on one side of an upper surface; a jig device having a lower portion selectively fastened and fixed to the fastening portion, and a jig device that contacts and supports the upper and lower portions of a dovetail portion of a turbine blade at an upper portion spaced apart from the fastening portion by a predetermined distance so that the free end of the turbine blade is spaced apart from the upper surface of the gauge plate; a measuring device disposed at the lower portion of the gauge plate and having a plurality of measuring means inside to detect a difference in pressure applied from the gauge plate; and a calculation unit that calculates the rotational torque of each turbine blade through the difference in load detected by the plurality of measuring means.

Description

Technology Field

[0001] The present invention relates to a turbine blade inspection system, and more specifically, to a turbine blade inspection system that efficiently inspects circumferential balance. Background Technology

[0002] In general, machines made of metal, such as turbines and presses, are used in various industrial settings. Among these, the aforementioned turbine refers to a machine that converts the energy of fluids, such as water, gas, or steam, into useful mechanical work. In other words, a turbine is a turbo-type machine that rotates at high speeds by embedding multiple blades around the circumference of a rotating body and blowing steam or gas onto them. As industry develops, the aforementioned turbines, such as steam and gas turbines, are becoming increasingly larger, hotter, and more high-pressure.

[0003] The turbine comprises a plurality of cantilever-shaped blades arranged to extend radially with a predetermined spacing along the circumferential direction around a reference axis. Here, the plurality of blades are installed at a predetermined angular spacing on the outer circumference of the rotor rotation axis of the turbine.

[0004] At this time, due to minute tolerances during the manufacturing process, the loads on each blade were formed to be slightly different. Therefore, although the minute load differences between individual blades are negligible, when more than 20 of them are installed along the circumferential direction of the rotor shaft, the clustered dynamic load differences cause excessive eccentric loads on the rotor shaft, resulting in a problem of significantly reduced durability.

[0005] Consequently, although the eccentric load was measured with all multiple blades attached to the rotor shaft, there was a problem in that the process of separating and rearranging the already attached blades was complex and caused damage to the product when the eccentric load exceeded the allowable standard.

[0006] In addition, there was a problem in that it was difficult to apply a compatible tester for measuring eccentric loads, etc., because the size and type of the blades coupled to the rotor shaft were different. Prior art literature

[0007] Korean Registered Patent No. 10-2343808 The problem to be solved

[0008] To solve the above-mentioned problems, the present invention has as its objective to provide a turbine blade inspection system that efficiently inspects circumferential balance. means of solving the problem

[0009] To solve the above problem, the present invention provides a turbine blade inspection system for inspecting the circumferential arrangement balance of a plurality of turbine blades, comprising: a gauge plate formed of a circular plate material having a plurality of fastening portions to which a fastening means is fastened on one side of an upper surface; a jig device having its lower portion selectively fastened and fixed to the fastening portion, and which contacts and supports the upper and lower portions of the dovetail portion of the turbine blade at an upper portion spaced apart from the fastening portion by a predetermined distance so that the free end of the turbine blade is spaced apart from the upper surface of the gauge plate; and a measuring device disposed at the lower portion of the gauge plate, having a plurality of measuring means inside to detect the difference in pressure load applied from the gauge plate.and includes a calculation unit that calculates the rotational torque of each turbine blade through the load difference detected by a plurality of the above-mentioned measuring means, wherein the jig device comprises a rear jig having a hook-shaped catch portion extending along the upper side in the transverse direction to catch the upper end of the rear end of the dovetail portion of the turbine blade, the lower part of which is selectively fixed to the upper surface of the gauge plate by a first fastening means, and a front jig having a support roller positioned forward from the hook-shaped catch portion to support the lower surface of the dovetail portion of the turbine blade, the lower part of which is selectively fixed to the upper surface of the gauge plate by a second fastening means, wherein the rear jig includes an upper jig and a lower jig so that the gap between the hook-shaped catch portion and the support roller can be adjusted, wherein the lower part of the upper jig is inserted and coupled into a slide groove formed recessed in the upper part of the lower jig so that it can slide up and down, and a first rail projection extending along the front and rear directions is protruded on the lower surface of the rear jig, and the front jig A turbine blade inspection system is provided, characterized by comprising: a second rail projection extending along the left-right direction is formed on the lower surface; a first rail groove extending along the front-rear direction is formed on the rear portion of the gauge plate to guide the insertion and front-rear movement of the first rail projection; a second rail groove extending along the left-right direction is formed on the front side of the first rail groove to guide the insertion and left-rear movement of the second rail projection; a plurality of first fastening holes are formed on both sides of the first rail groove spaced apart along the front-rear direction to fasten the first fastening means; and a plurality of second fastening holes are formed on both sides of the second rail groove spaced apart along the left-right direction to fasten the second fastening means.

[0010] Here, the above-mentioned operation unit preferably further includes a rotational torque arrangement means for displaying rotational torque result values ​​of each turbine blade, calculated by individually inspecting each turbine blade in the order in which they are arranged along the circumferential direction, in order along the circumferential direction, and a rotational torque balance control unit for adjusting the circumferential arrangement order so that the deviation along the circumferential direction from the arrangement state of the rotational torque result values ​​of a plurality of turbine blades is set within a preset deviation range.

[0011] delete

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[0013] delete Effects of the invention

[0014] Through the above-mentioned means of solution, the present invention provides the following effects.

[0015] First, the load applied to multiple measuring means is measured differently depending on the installed position of the jig device in which the turbine blades are individually installed and the type of the blades, and since the longitudinal and transverse rotational torques are calculated from these differences in load, the rotational torques of the blades of different sizes can be measured economically and precisely by interchangeability.

[0016] Second, since the rotational torque value for each blade based on the center of the rotor to be actually installed can be accurately calculated through the forward / backward and left / right movement and variable fixing of the rear jig and the front jig, the difference and deviation in rotational torque values ​​caused by the machining tolerances of multiple turbine blades arranged along the circumferential direction can be accurately verified.

[0017] Third, the rotational torque arrangement means displays the rotational torque result value of each turbine blade in the order arranged along the circumferential direction to efficiently check for eccentricity on one side, and the rotational torque balance adjustment unit can significantly improve production economics by minimizing the amount of defective waste through recycling by rearranging the circumferential position of each blade. Brief explanation of the drawing

[0018] FIG. 1 is a perspective view of a turbine blade inspection system according to an embodiment of the present invention. FIG. 2 is a side view of a turbine blade inspection system according to an embodiment of the present invention. FIG. 3 is a plan view of a gauge plate of a turbine blade inspection system according to an embodiment of the present invention. FIG. 4 is an exemplary diagram of a rotational torque arrangement means for a plurality of blades inspected by a turbine blade inspection system according to an embodiment of the present invention. Specific details for implementing the invention

[0019] Hereinafter, a turbine blade inspection system according to a preferred embodiment of the present invention will be described in detail with reference to the attached drawings.

[0020] FIG. 1 is a perspective view of a turbine blade inspection system according to an embodiment of the present invention, FIG. 2 is a side view of a turbine blade inspection system according to an embodiment of the present invention, FIG. 3 is a plan view of a gauge plate of a turbine blade inspection system according to an embodiment of the present invention, and FIG. 4 is a rotational torque arrangement diagram of a plurality of blades inspected by a turbine blade inspection system according to an embodiment of the present invention.

[0021] As shown in FIGS. 1 and 2, a turbine blade inspection system (100) according to one embodiment of the present invention includes a gauge plate (10), a jig device (20), a measuring device (30), and a calculation unit (51).

[0022] At this time, the turbine blade inspection system (100) is a device for inspecting the circumferential arrangement balance of a plurality of turbine blades (1), and the gauge plate (10) is provided with a fastening part (11 in FIG. 3) including a plurality of fastening holes on one side of the upper surface to which a fastening means is fastened.

[0023] Here, the gauge plate (10) is formed from a circular plate material and is configured so that each component constituting the turbine blade inspection system (100) is connected or fixed. Additionally, it is preferable that an installation part be provided on the lower surface to support or fix the turbine blade inspection system (100) in contact with the ground.

[0024] Next, the lower part of the jig device (20) is selectively fastened and fixed to the fastening part (11 in FIG. 3), and the upper part is fixed and supported by fixing the dovetail part (1a) of the turbine blade (1). That is, the jig device contacts and supports the upper and lower parts of the dovetail part of the turbine blade at an upper part spaced apart from the fastening part by a predetermined distance so that the free end of the turbine blade is spaced apart from the upper surface of the gauge plate.

[0025] Specifically, the jig device (20) includes a rear jig (21) and a front jig (25).

[0026] Here, the rear jig (21) is provided with a hook-shaped catch (21c) extending downward from an end extending forward so as to catch the upper end of the rear end of the dovetail portion (1a) of the turbine blade (1) on the upper side, extending along the transverse direction, and the lower side can be selectively fixed to the upper surface of the gauge plate (10) by a first fastening means (22a).

[0027] In addition, the front jig (25) is provided with a support roller (25a) at its upper end, which is positioned forward from the hook-shaped catch (21c) and supports the lower portion of the dovetail part (1a) of the turbine blade (1), and the lower end can be selectively fixed to the upper surface of the gauge plate (10) by a second fastening means (26a).

[0028] Accordingly, the lower surface of the dovetail portion (1a) is seated on the support roller (25a) of the front jig (25), and the upper rear end of the dovetail portion (1a) can be fixed by being hooked onto the hook-shaped catch portion (21c) of the rear jig (21).

[0029] Meanwhile, it is preferable that a first rail projection (22) extending along the front-rear direction is formed downward on the lower surface of the rear jig (21), and a second rail projection (26) extending along the left-right direction is formed downward on the lower surface of the front jig (25).

[0030] Additionally, it is preferable that a first rail groove (11) is formed extending along the front-rear direction to guide the insertion and front-rear movement of the first rail projection (22) at the rear portion of the gauge plate (10), and a second rail groove (15) is formed extending along the left-right direction to guide the insertion and left-right movement of the second rail projection (26) at the front portion of the first rail groove (11).

[0031] Through this, turbine blades (1) of various sizes and types can be compatiblely fixed to the jig device (20). That is, since the size of the dovetail portion (1a) that is coupled to the rotor at the end of the turbine blade (1) is different, the rear jig (21) and the front jig (25) can be moved along the first rail groove (11) and the second rail groove (15) to vary the fixing position and enable compatible application.

[0032] Specifically, the rear jig (21) can be moved back and forth along the first rail groove (11) to be adjusted in response to changes in the size and length of the dovetail portion (1a) and then fixed. Additionally, the front jig (25) can be moved left and right along the second rail groove (15) to be adjusted to a position corresponding to the widthwise center of the dovetail portion (1a) and then fixed.

[0033] Through this, assembly efficiency and inspection convenience can be improved by efficiently moving the front jig (25) and the rear jig (21) left and right / forward and fastening the assembly.

[0034] At this time, the hook-shaped locking part (21c) of the rear jig (21) is formed to extend laterally and longer than the left-right movement range of the front jig (25), so that the dovetail part (1a) of the large turbine blade (1) can also be stably fixed between the rear jig (21) and the front jig (25).

[0035] Meanwhile, on the upper surface of the gauge plate (10) on both sides of the first rail groove (11), a plurality of first fastening holes (11a) may be formed through, spaced apart in multiple stages along the front-rear direction, to which the first fastening means (22a) are fastened. Additionally, on the upper surface of the gauge plate (10) on both sides of the second rail groove (15), a plurality of second fastening holes (15a) may be formed through, spaced apart in multiple stages along the left-right direction, to which the second fastening means (26a) are fastened.

[0036] Here, it is preferable that the first fastening hole (11a) and the second fastening hole (15a) be formed in multiple locations in the shape of elongated holes so as to finely adjust the longitudinal fixing position. Of course, the first fastening hole (11a) and the second fastening hole (15a) may be formed in a single row on both edges of the first rail groove (11) and the second rail groove (15), but they may also be formed in two rows each to reinforce the support force.

[0037] Additionally, the first fastening means (22a) and the second fastening means (26a) may each be provided with a fastening bolt. Through this, the rear jig (21) can be moved in the forward and backward directions and then fixed by fastening the first fastening means (22a) to one of the first fastening holes (11a) on the upper surface of the gauge plate (10).

[0038] Additionally, the front jig (25) can be fixed by moving it in the left and right directions and then fastening the body 2 fastening means (26a) to one of the body 2 fastening holes (15a) on the upper surface of the gauge plate (10).

[0039] At this time, the jig device (20) may fix the dovetail portion (1a) of the turbine blade (1) to an upper side spaced apart from the upper surface of the gauge plate (10) by a predetermined distance so that the free end of the turbine blade (1) is spaced apart from the upper surface of the gauge plate (10).

[0040] To this end, the rear jig (21) and the front jig (25) are each extended upward, and it is preferable that at least one of the rear jig (21) and the front jig (25) is configured so that the upper height is adjustable. Through this, the gap between the hook-shaped catch (21c) and the support roller (25a) is adjusted so that dovetail parts (1a) of various sizes can be inserted between them and secured by being caught.

[0041] Specifically, the rear jig (21) preferably includes an upper jig (21a) and a lower jig (21b). Here, a slide groove (22c) is formed in the upper part of the lower jig (21b), and the lower part of the upper jig (21a) is inserted and coupled into the slide groove (22c) so that it can slide up and down. Through this, the height of the hook-shaped locking part (21c) that locks the dovetail part (1a) can be adjusted and fixed in the vertical direction.

[0042] Here, the first fastening means (22a) may be provided as a long bolt with screw threads formed on its outer circumference and configured to penetrate the rear jig (21). At this time, the head portion of the first fastening means (22a) is secured to the upper end of the upper jig, and the lower portion of the first fastening means (22a) may be screw-fastened and coupled to the first fastening hole (11a) with female screw threads formed on its inner circumference.

[0043] Additionally, it is preferable that a connecting nut (22c) be provided in the central part of the above-mentioned first fastening means (22a) to fasten the upper surface of the lower jig (21b) by pressing downward to fix it. That is, the lower jig (21b) can be stably fixed in the correct position between the fixing nut at the bottom and the connecting nut (22c).

[0044] By doing so, by adjusting the lifting height of the upper jig (21a), it is possible to apply it interchangeably in response to changes in the upper and lower thickness of the dovetail portion (1a) of the turbine blade (1).

[0045] In this way, compatibility can be improved by adjusting the jig device (20) to be compatible with a size corresponding to the size of the dovetail portion (1a) of the turbine blade (1). Additionally, the support roller (25a) performs the function of preventing scratches from occurring while allowing the upper jig (21) and the lower jig (25) to be selectively combined and separated.

[0046] Through this, the rotational torque of various types of turbine blades (1) with individually different sizes of the dovetail portion (1a) can be measured economically and interchangeably.

[0047] At this time, it is preferable that the installation hole (33) mediating the connection with the lower device of the gauge plate be spaced apart from the fastening holes (11a, 15a in FIG. 3).

[0048] And, the measuring device (30) is positioned below the gauge plate (10) and includes a plurality of measuring means (31) inside for detecting the difference in pressure applied from the gauge plate (10).

[0049] At this time, the measuring device (30) is connected to a calculation unit (51) that calculates the rotational torque of each turbine blade (1) through the load difference detected by a plurality of the measuring means (31), and the measuring means (31) may be equipped with a load cell that measures the displacement difference of a metal material according to the load.

[0050] Here, it is desirable to understand that the rotational torque (moment, M) is a force for bending and can be calculated as a vector value using the formula M = F * R [kgf*m], which is the concept of a physical quantity multiplied by the vertical distance from a reference point or axis to the location of the physical quantity.

[0051] In detail, the resultant force in the vertical direction at the cross-section of the blade (1) is zero, and a region subjected to tensile stress and compressive stress exists simultaneously to generate a bending moment. That is, a bending moment is generated based on the center of gravity of the blade (1). Therefore, the bending moment and shear force act simultaneously inside the blade (1).

[0052] Furthermore, a tangential force acting at a distance R from the axis of the blade (1) rotates the blade (1) clockwise. At this time, when a torsional moment is applied to the axis of the blade (1) fixed to the dovetail portion (1a), twisting occurs in the axis of the blade (1). Additionally, as the force acts horizontally on the surface of the axis of the blade (1), torsional stress is generated.

[0053] In addition, as shown in FIG. 3, the measuring means (31) can measure the longitudinal and left-right rotational torque of the turbine blade (1).

[0054] In detail, it is preferable that each of the above measuring means (31) be positioned at four locations: a first position behind the center of the fastening part (11), a second position spaced apart from the first position and the center at an equal distance from each other, and a third position and a fourth position spaced orthogonally from the first position and the second position and the center.

[0055] That is, each of the above-mentioned measuring means (31) is formed at an equal distance in the radial direction from the center of the circular gauge plate (10), and each of the above-mentioned measuring means (31) is arranged at a distance from each other along a mutually orthogonal horizontal line and a vertical line.

[0056] Through this, the measuring device (30) calculates the longitudinal and lateral bending load rotational torque of the individual blade (1) through the load detected by the plurality of measuring means (31) spaced apart to be vertically opposite at the four locations.

[0057] In addition, the load detected by each of the above-mentioned measuring means (31) is transmitted to the above-mentioned calculation unit (51) via a signal line. That is, the above-mentioned calculation unit (51) calculates the rotational torque of each of the above-mentioned turbine blades (1) through the difference in loads detected by a plurality of the above-mentioned measuring means (31).

[0058] Specifically, the calculation unit (51) calculates the rotational torque by considering the relative spacing of each measuring means (31) based on a support position set equally for each type of blade, including the fixed height of the dovetail portion (1a) of the blade (1). That is, the load applied to each measuring means (31) is measured differently depending on the change in the position where the jig device (20) is installed on the gauge plate (10) and the type of the blade (1), and the rotational torque in the longitudinal and left-right directions of each blade (1) can be calculated by numerically analyzing this difference in load.

[0059] In detail, after the rotational torque is fixed to the gauge plate (10) and the jig device (20), the detection value of each of the measuring means (31) can be reset to '0'. Then, when each of the blades (1) is installed on the jig device (20), the longitudinal and left-right rotational torque of each of the blades (1) can be calculated through the difference in load detected by each of the measuring means (31).

[0060] At this time, the relative difference in rotational torque values ​​of multiple blades can be confirmed through the difference in load values ​​measured by each of the above-mentioned measuring means (31).

[0061] Through this, the difference in rotational torque values ​​applied by each blade (1) based on the center (G) of the virtual rotor (2) regarding the target on which the blade (1) is to be installed during the subsequent assembly process may be calculated separately. That is, through variable fixing of the rear jig and the front jig, the rotational torque value for each blade (1) when installed on the actual rotor can be accurately calculated. Through this, the difference in rotational torque values ​​caused by the machining tolerance of the plurality of blades (1) arranged along the circumferential direction can be accurately verified.

[0062] Ultimately, the load applied to the plurality of measuring means (31) is measured differently depending on the installed position of the jig device (20) where the turbine blade (1) is individually installed and the type of the blade (1), and since the longitudinal and left-right rotational torque is calculated from this difference in load, the rotational torque of the individual blade can be measured economically and precisely.

[0063] Meanwhile, it is preferable that the above-mentioned operation unit (51) further includes a rotational torque arrangement means (52) and a rotational torque balance control unit (53).

[0064] Here, the rotational torque arrangement means (52) displays the rotational torque result values ​​of each turbine blade, calculated by individually inspecting each turbine blade in the order in which they are arranged along the circumferential direction, in order along the circumferential direction.

[0065] To this end, it is preferable that the turbine blades have a circumferential arrangement order (1b) marked on them to prevent errors during the inspection process. Additionally, the rotational torque arrangement means (52) may provide an arrangement diagram that arranges the rotational torque values ​​of a plurality of inspected blades (1) along the circumferential direction in the order of inspection.

[0066] As shown in FIG. 4, the rotational torque arrangement means (52) can display the rotational torque values ​​measured by each of the turbine blades in the circumferential arrangement order according to the circumferential arrangement order of the plurality of blades (1). In addition, the rotational torque arrangement means (52) can calculate the average value of the measured rotational torque values ​​of all turbine blades included in the circumferential arrangement order.

[0067] Through this, the deviation between the rotational torque value of each turbine blade according to the arrangement order and the average value can be calculated so that eccentricity does not occur on one side of the circumferential direction in the arrangement diagram displayed in the circumferential arrangement order and is uniform. The circumferential position of a turbine blade with a deviation calculated in this way that is greater than the preset value is adjusted by the rotational torque balance adjustment unit (53). That is, it is preferable that the arrangement order of the blade (B9) with a high rotational torque value is mutually swapped and changed with that of the blade (B17) with a low rotational torque value.

[0068] Additionally, the rotational torque balance control unit (53) calculates rotational torque statistical information including the average and standard deviation of the rotational torque values, and the average and standard deviation of the rotational torque can be calculated from a plurality of rotational torque values ​​sequentially stored in the memory unit of the rotational torque array means (52) by the rotational torque balance control unit (53).

[0069] At this time, torsional stress is generated by the torsional rotational torque, and since the actual blade (1) is not a completely rigid body, shear strain is caused. This shear strain is amplified between the two ends of each blade (1). That is, it is desirable to perform an adjustment process for circumferential uniformity by considering changes in rotational torque values ​​in the width direction as well as the length direction of each blade.

[0070] Meanwhile, the rotational torque balance control unit (53) can adjust the arrangement order by replacing and changing it when the deviation along the circumferential direction from the arrangement state of the rotational torque result values ​​of the plurality of turbine blades is significantly concentrated in a specific arc direction. That is, it is preferable that the arrangement order of the blade (1) measured in a specific arc direction be mutually replaced and changed from the blade with high rotational torque (B9) to the blade with low rotational torque (B17) so that eccentricity does not occur and the blade is uniform.

[0071] In this way, the rotational torque balance control unit can adjust the circumferential arrangement order so that the deviation along the circumferential direction is set within a preset deviation range for each region, from the arrangement state of the rotational torque result values ​​of the plurality of turbine blades, so that the deviation is not concentrated on one side.

[0072] In this way, the individual rotational torque of the plurality of blades (1) arranged along the circumferential direction of the rotor (2) is measured, and the magnitude of the measured rotational torque values ​​is distinguished so that the rotational torque load is distributed and rearranged so that it is not concentrated on one side along the circumferential direction but is equalized within a preset deviation range.

[0073] Accordingly, the occurrence of excessive eccentric load on one side of the rotation axis of the rotor (2), in which a plurality of blade arrays are installed along the circumferential direction, can be prevented in advance, thereby significantly improving durability.

[0074] In this way, the individual rotational torque of the turbine blade is precisely measured through the difference in load values ​​measured by load cells placed at multiple locations, and the rotational torque arrangement means (52) displays the rotational torque result values ​​of each turbine blade in order along the circumferential direction so that it can be easily confirmed whether the rotational torque load is concentrated on one side of the circumferential direction.

[0075] In addition, the rotational torque balance control unit (53) can prevent excessive eccentric load on the rotor rotation axis in advance by repurposing turbine blades that were previously discarded due to exceeding the rotational torque value standard, thereby minimizing the amount of defective waste and significantly improving the durability of the rotor and production economics through material cost reduction.

[0076] In this context, terms such as "include," "compose," or "equip" as described above, unless specifically stated otherwise, mean that the relevant component may be inherent; therefore, they should be interpreted as allowing for the inclusion of additional components rather than excluding them. All terms, including technical or scientific terms, have the same meaning as generally understood by those skilled in the art to which the present invention pertains, unless otherwise defined. Terms commonly used, such as those defined in advance, should be interpreted in accordance with their meaning in the context of the relevant technology and, unless explicitly defined in the present invention, should not be interpreted in an ideal or overly formal sense.

[0077] As explained above, the present invention is not limited to each of the embodiments described above, and modifications can be made by those skilled in the art without departing from the scope claimed in the claims of the present invention, and such modifications fall within the scope of the present invention. Explanation of the symbols

[0078] 100: Turbine blade inspection system 1: Turbine blade 1a: Dovetail section 10: Gauge plate 11: 1st rail groove 11a: 1st fastening hole 15: Second rail groove 15a: Second fastening hole 20: Jig device 21: Rear jig 21c: Hook-type locking part 22: First rail projection 22a: First fastening means 25: Front jig 25a: Support roller 26: Second rail projection 26a: Second fastening means 30: Measuring device 31: Measuring means 51: Calculation unit 52: Rotational torque arrangement means 53: Rotational torque balancing control unit

Claims

Claim 1 A turbine blade inspection system for inspecting the circumferential alignment balance of multiple turbine blades, comprising: a gauge plate formed of a circular plate material having a plurality of fastening portions to which fastening means are fastened on one side of an upper surface; a jig device having its lower portion selectively fastened and fixed to the fastening portion, and which contacts and supports the upper and lower portions of the dovetail portion of the turbine blade at an upper portion spaced apart from the fastening portion by a predetermined distance so that the free end of the turbine blade is spaced apart from the upper surface of the gauge plate; and a measuring device disposed at the lower portion of the gauge plate, having a plurality of measuring means inside to detect differences in pressure loads applied from the gauge plate.The device includes a calculation unit that calculates the rotational torque of each turbine blade through the load difference detected by a plurality of the above-mentioned measuring means, wherein the jig device comprises a rear jig having a hook-shaped catch portion extending along the upper side in the transverse direction to catch the upper end of the rear end of the dovetail portion of the turbine blade, the lower part of which is selectively fixed to the upper surface of the gauge plate by a first fastening means, and a front jig having a support roller positioned forward from the hook-shaped catch portion to support the lower surface of the dovetail portion of the turbine blade, the lower part of which is selectively fixed to the upper surface of the gauge plate by a second fastening means, wherein the rear jig comprises an upper jig and a lower jig so that the gap between the hook-shaped catch portion and the support roller can be adjusted, wherein the lower part of the upper jig is inserted and coupled into a slide groove formed recessed in the upper part of the lower jig so that it can slide up and down, and a first rail projection extending along the front and rear directions is formed on the lower surface of the rear jig, and the A turbine blade inspection system characterized by comprising: a second rail projection extending along the left-right direction is formed on the lower surface of a front jig; a first rail groove extending along the front-rear direction is formed on the rear portion of the gauge plate to guide the insertion and front-rear movement of the first rail projection; a second rail groove extending along the left-right direction is formed on the front side of the first rail groove to guide the insertion and left-rear movement of the second rail projection; a plurality of first fastening holes are formed on both sides of the first rail groove, spaced apart along the front-rear direction, to which the first fastening means are fastened; and a plurality of second fastening holes are formed on both sides of the second rail groove, spaced apart along the left-right direction, to which the second fastening means are fastened. Claim 2 delete Claim 3 delete Claim 4 delete Claim 5 A turbine blade inspection system according to claim 1, wherein the calculation unit further comprises a rotational torque arrangement means for displaying rotational torque result values ​​of each turbine blade in a rotational direction in a rotational direction, calculated by individually inspecting each turbine blade in the order in which they are arranged along the circumferential direction, and a rotational torque balance control unit for adjusting the rotational torque balance control unit to change the rotational arrangement order so that the deviation along the circumferential direction from the arrangement state of the rotational torque result values ​​of a plurality of turbine blades is set within a preset deviation range.

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