A High-Temperature Strain Gauge Wiring Method for a High-Pressure Turbine Rotor Blade

Abstract

The present invention provides a high-temperature strain gauge wire routing method for a high-pressure turbine rotor blade, which relates to the field of testing of high-pressure turbine rotor blades of an aeroengine, and includes: pasting a strain gauge on the rotor blade, and leading the grid wire of the strain gauge to the root of the leading edge of the blade; leading the grid wire into the side plate of the blade basin along the edge plate of the blade tenon, and performing the transfer of the grid wire and the glass fiber wire under the side plate of the blade basin; leading the glass fiber wire to the turbine disk along the position of the rim bump, leading it along the way to the inner side of the rear baffle of the turbine disk, and entering the outer side of the rear baffle, and then routing it along the way to the rear section of the turbine disk; entering the labyrinth ring lead hole along the rear mounting edge of the turbine disk and passing through the lead hole of the rear turbine shaft, penetrating into the inner side of the rear turbine shaft, and then penetrating into the internal lead shaft of the telemetry system, and finally leading out the lead shaft of the telemetry system, and connecting the glass fiber wire to the telemetry system. The present invention realizes the lead-out of the high-temperature strain gauge under the condition that no hole can be opened due to cracks at the bottom of the blade tenon, and lays a foundation for realizing the high-temperature dynamic stress test of the high-pressure turbine rotor blade.

Description

Technical Field

[0001] The present invention relates to the field of high-temperature dynamic stress testing of high-pressure turbine rotor blades of aero-engines, and particularly relates to a method for routing high-temperature strain gauges on high-pressure turbine rotor blades. Background Art

[0002] With the requirements of "three highs" (high temperature, high pressure, and high speed) in engine development, failures of high-pressure turbine rotor blades have become prominent. During the engine development process, high-temperature spray-bonded contact high-temperature strain gauges are usually used, and the dynamic strain signals are led out through a telemetry or slip ring signal transmission system. Therefore, the routing method from the grid wires of the high-temperature strain gauge to the high-temperature wire and finally to the telemetry system is very important.

[0003] For aero-engines, it is very difficult to route the strain gauges during the dynamic stress testing of high-pressure turbine rotor blades. The main reason is that due to the structural limitations of the engine, the telemetry module can only be installed at the rear section of the entire turbine disk. The structure of the turbine end of the engine is complex, and the strain gauge leads need to be fixed and protected throughout the process to ensure the integrity of the signals. Therefore, the traditional routing method in front of the turbine disk cannot achieve the dynamic stress testing of high-pressure turbine rotor blades.

[0004] Therefore, it is very difficult to route the high-temperature strain gauges on high-pressure turbine rotor blades, and there is no unified standard and specification at present. Summary of the Invention

[0005] In view of this, the embodiment of the present application provides a method for routing high-temperature strain gauges on high-pressure turbine rotor blades, which realizes the pasting and routing of high-temperature strain gauges on high-pressure turbine rotor blades, proposes a routing method for the convex blocks on the rim of the turbine disk, and realizes the lead-out of the high-temperature strain gauge under the condition that there are cracks at the bottom of the blade tenon and holes cannot be drilled, laying a foundation for realizing the high-temperature dynamic stress testing of high-pressure turbine rotor blades.

[0006] The embodiment of the present application provides the following technical solutions: A method for routing high-temperature strain gauges on high-pressure turbine rotor blades, comprising:

[0007] Using a flame spraying process to paste a high-temperature strain gauge on the high-pressure turbine rotor blade, leading the grid wires of the strain gauge to the root position of the leading edge of the blade; then leading the grid wires of the strain gauge into the lower side of the blade basin side plate along the prefabricated lead groove on the tenon flange of the blade for the transfer of the grid wires of the strain gauge and the glass fiber wire;

[0008] Leading the transferred glass fiber wire to the high-pressure turbine disk along the prefabricated lead groove at the position of the convex block on the rim of the high-pressure turbine disk, leading the glass fiber wire along the way to the inner side position of the rear baffle of the high-pressure turbine disk, and leading it out of the high-pressure turbine disk through the prefabricated lead hole on the rear baffle into the outer side of the rear baffle, then routing it along the way to the rear section of the high-pressure turbine disk, and fixing the glass fiber wire along the way;

[0009] Feed the glass fiber thread into the labyrinth ring lead hole through the prefabricated lead groove on the rear mounting edge of the high-pressure turbine disk and out of the rear shaft lead hole of the high-pressure turbine. Then, route the glass fiber thread along the rear shaft of the high-pressure turbine to the prefabricated lead groove and penetrate it into the inner side of the rear shaft of the high-pressure turbine. Next, pass through the prefabricated radial lead hole on the telemetry system lead shaft and enter the interior of the telemetry system lead shaft. Finally, pass through the prefabricated axial lead hole on the telemetry system lead shaft and lead it out backward from the telemetry system lead shaft. Connect the glass fiber thread to the telemetry system located at the rear side to complete the pasting and routing of the high-temperature strain gauge.

[0010] According to an embodiment of the present application, the method further includes: when leading the strain gauge grid wire to the root position of the blade leading edge, performing a chamfering treatment on the blade leading edge blade concave side, and fixing the strain gauge grid wire to the chamfered position of the blade leading edge blade concave side by flame spraying.

[0011] According to an embodiment of the present application, the chamfering size of the blade leading edge blade concave side is 2*2 mm.

[0012] According to an embodiment of the present application, the slotting size of the prefabricated lead groove on the blade tenon head flange is 2.5*1.9 mm.

[0013] According to an embodiment of the present application, the slotting size of the prefabricated lead groove at the position of the high-pressure turbine disk rim bump is 2 mm in width and 1.9 mm in depth, and the entire plane of the lead groove is polished and chamfered by 0.1 mm.

[0014] According to an embodiment of the present application, the slotting size of the prefabricated lead groove on the rear mounting edge of the high-pressure turbine disk is as follows: if 1 glass fiber thread is routed in the lead groove, the slotting width is 5 mm and the depth is 2 mm; if 2 or more glass fiber threads are routed in the lead groove, the slotting width is 11 mm and the depth is 2 mm.

[0015] According to an embodiment of the present application, the corresponding position at the radial end of the rear mounting edge of the high-pressure turbine disk is the uppermost edge of the lead groove opening. A lead hole is opened on the labyrinth ring, and a lead hole is also opened at the corresponding position on the rear shaft mounting edge of the high-pressure turbine to pass the glass fiber thread out of the rear shaft lead hole of the high-pressure turbine. Among them, if 1 glass fiber thread is routed in the lead hole, the aperture of the opening is 2.5 mm; if 2 or more glass fiber threads are routed in the lead hole, the lead holes on the labyrinth ring and the lead holes on the rear shaft mounting edge of the high-pressure turbine are both waist-shaped holes with a length of 5.5 mm and a width of 2.6 mm.

[0016] According to an embodiment of the present application, the opening diameter of the rear shaft lead hole of the high-pressure turbine is 2 mm, the opening diameter of the prefabricated radial lead hole on the telemetry system lead shaft is 3 mm, and the opening diameter of the prefabricated axial lead hole on the telemetry system lead shaft is 3 mm.

[0017] According to an embodiment of the present application, the process of connecting the strain gauge grid wire and the glass fiber wire includes: sandblasting at the connection position, applying ceramic cement glue in the sandblasted area, spot-welding the glass fiber wires reserved on the blade and the disk to the glass fiber wires respectively to form two non-touching welding heads, covering insulating felts at the two welding heads, and fixing the insulating felts with a metal skin.

[0018] According to an embodiment of the present application, the metal skin is made of a titanium alloy metal sheet.

[0019] Compared with the prior art, the beneficial effects that can be achieved by at least one of the above technical solutions adopted in the embodiments of this specification at least include: The embodiments of the present invention realize the pasting and wiring of high-temperature strain gauges on high-pressure turbine rotor blades, overcome the difficulty of wiring under the condition of blade tenon groove cracks, and realize the method of high-pressure turbine rotor blades under a complex high-pressure turbine disk structure. The dynamic stress data of high-pressure turbine rotor blades in the entire working speed range of the full working state are obtained, and the survival rate of the strain gauges reaches more than 90%, laying a solid technical foundation for realizing the life prediction of high-pressure turbine rotor blades. Description of the Drawings

[0020] In order to more clearly illustrate the technical solutions of the embodiments of the present application, the drawings required for use in the embodiments will be briefly introduced below. Obviously, the drawings in the following description are only some embodiments of the present application. For those of ordinary skill in the art, without creative efforts, other drawings can also be obtained based on these drawings.

[0021] Figure 1 Schematic diagram of the method for routing high-temperature strain gauges on high-pressure turbine rotor blades in the embodiments of the present invention;

[0022] Wherein, 1 - high-pressure turbine rotor blade; 2 - high-temperature strain gauge; 3 - strain gauge grid wire; 4 - blade leading edge chamfer position; 5 - blade tenon head flange prefabricated groove; 6 - blade concave side flange; 7 - high-pressure turbine disk rim convex block; 8 - blade-disk rim convex block lead groove; 9 - rear baffle; 10 - turbine disk rear mounting edge lead groove; 11 - labyrinth ring lead hole; 12 - high-pressure turbine rear shaft lead hole; 13 - high-pressure turbine rear shaft radial lead hole; 14 - telemetry system lead shaft; 15 - telemetry system lead shaft lead hole. Detailed Embodiments

[0023] The embodiments of the present application will be described in detail below with reference to the drawings.

[0024] The following describes the embodiments of the present application through specific examples, and those skilled in the art can easily understand other advantages and effects of the present application from the contents disclosed in this specification. Obviously, the described embodiments are only a part of the embodiments of the present application, rather than all the embodiments. The present application can also be implemented or applied through other different specific embodiments, and the details in this specification can also be modified or changed in various ways based on different viewpoints and applications without departing from the spirit of the present application. It should be noted that, in the absence of conflict, the features in the following embodiments and embodiments can be combined with each other. Based on the embodiments in the present application, all other embodiments obtained by those of ordinary skill in the art without making creative work are within the scope of protection of this application.

[0025] like Figure 1 As shown, an embodiment of the present invention provides a high-temperature strain gauge routing method for a high-pressure turbine rotor blade, comprising: pasting a high-temperature strain gauge on a high-pressure turbine rotor blade using a flame spraying process, and leading the strain gauge grid wire to the root position of the leading edge of the blade; then leading the strain gauge grid wire along the prefabricated lead groove on the blade tenon edge plate into the bottom of the blade basin side edge plate to transfer the strain gauge grid wire and the glass fiber wire; leading the transferred glass fiber wire along the prefabricated lead groove on the rim bump position of the high-pressure turbine disk to the high-pressure turbine disk, leading the glass fiber wire along the way to the inner side position of the high-pressure turbine disk rear baffle, and leading it out of the high-pressure turbine through the prefabricated lead hole on the rear baffle. The disk enters the outside of the rear baffle, and then routes along the way to the rear section of the high-pressure turbine disk, and fixes the glass fiber line along the way; the glass fiber line enters the grate ring lead hole along the prefabricated lead groove on the rear mounting edge of the high-pressure turbine disk and passes through the high-pressure turbine rear shaft lead hole, and then the glass fiber line is routed along the high-pressure turbine rear shaft to the prefabricated lead groove and penetrates into the inner side of the high-pressure turbine rear shaft, and then passes through the prefabricated radial lead hole on the telemetry system lead shaft into the inside of the telemetry system lead shaft, and finally passes through the prefabricated axial lead hole on the telemetry system lead shaft to lead out of the telemetry system lead shaft backward, and the glass fiber line is connected to the telemetry system located on the rear side to complete the high-temperature strain gauge pasting and routing.

[0026] When implementing it specifically, Figure 1 As shown, the high-pressure turbine under test is a single-stage one. The embodiment of the present invention adopts the following technical solutions:

[0027] First, a high-temperature strain gauge 2 is pasted on the high-pressure turbine rotor blade 1 using a high-temperature spraying process, and the strain gauge grid wire 3 is led to the root position of the blade leading edge. To reduce the impact on the blade strength and to protect the strain leads, chamfering treatment is performed on the blade leading edge blade concave side to form the blade leading edge chamfer position 4. Then, a prefabricated lead groove is formed at the blade tenon flange position to form the blade tenon flange prefabricated groove 5. After the strain gauge grid wire 3 is fixed to the chamfer position of the blade leading edge blade concave side by flame spraying, it enters under the side flange 6 of the blade concave through the blade tenon flange prefabricated groove 5, and the connection between the grid wire and the glass fiber wire is carried out.

[0028] Optionally, the size of the glass fiber wire of the strain gauge is 1.6 mm in diameter. Therefore, chamfering treatment is performed on the blade leading edge blade concave side to form the blade leading edge chamfer position 4, and the chamfer size starts from the blade concave edge and is 2*2 mm.

[0029] Optionally, a prefabricated lead groove is formed at the blade tenon flange position, and the groove size is 2.5*1.9 mm.

[0030] Specifically, the connection steps of the strain gauge grid wire 3 and the glass fiber wire on the blade tenon under the blade flange include: sandblasting at the connection position, applying ceramic cement glue in the sandblasted area, and using a spot welding tip and a pen tip spot welding head to respectively spot weld the glass fiber wires reserved on the blade and the disk to the glass fiber wires to form two welded joints, and the two welded joints should not be in contact; after covering the two welded joints with insulating felt, fix the metal skin to the insulating felt.

[0031] The connected glass fiber wire is spot welded to the tenon groove position along the skin, and then the glass fiber wire is led to the high-pressure turbine disk along the prefabricated lead groove (blade disk rim lug lead groove 8) at the position of the high-pressure turbine disk rim lug 7. After routing, it is fixed by the skin spot welding method. To reduce the suspended section of the glass fiber wire, the high-pressure turbine disk tenon needs to have an arc-shaped opening, that is, on the premise of ensuring the strength of the high-pressure turbine disk rim, it is as close as possible to the blade tenon groove position.

[0032] Optionally, the slotting of the high-pressure turbine disk rim lug 7 starts from the center position, the slot size is 2 mm wide and 1.9 mm deep, which is used for routing and skin spot welding, and the entire plane is ground and cut off by 0.1 mm to prevent the glass fiber wire from being crushed after the baffle is installed. The arc of the top slot is 32° from the radial center line, and the fillet diameter is 6 mm.

[0033] After the rear baffle 9 is installed with the high-pressure turbine disk, the glass fiber wire is led along the way to the inner side position of the rear baffle, led out of the high-pressure turbine disk through the prefabricated lead hole and into the outer side of the rear baffle, and then routed along the way to the rear section of the high-pressure turbine disk and fixed along the way.

[0034] Optionally, to prevent the lead wires from being suspended, the opening position of the rear baffle 9 should be selected to match the mating surface of the high-pressure turbine disk. However, this will cause significant wear to the fiberglass wires during the installation process. Therefore, the opening is made at a position about 5 mm above the mating surface of the high-pressure turbine disk and the rear baffle, reducing the damage to the fiberglass wires during the installation of the rear baffle and also reducing the suspended section of the lead wires during the routing of the fiberglass wires.

[0035] Optionally, the diameter of the fiberglass wire is 1.6 mm, and one hole is opened for each lead wire of the strain gauge. The opening size of the rear baffle 9 is 2 mm in diameter.

[0036] When the rear mounting edge of the high-pressure turbine disk, the labyrinth ring mounting edge, and the high-pressure turbine rear shaft are connected by bolts, the fiberglass wires need to be routed. By means of skin spot welding, the fiberglass wires enter the labyrinth ring lead hole 11 along the lead wire groove 10 on the rear mounting edge of the turbine disk and pass through the high-pressure turbine rear shaft lead hole 12.

[0037] Optionally, the mating surface of the rear mounting edge of the high-pressure turbine disk and the labyrinth ring needs to be grooved for the routing of the fiberglass wires. During the routing of the fiberglass wires in the groove, skin spot welding is required for fixation. Therefore, the grooving size of the rear mounting edge of the high-pressure turbine is relatively important. If one fiberglass wire is routed in each groove, the groove width is 5 mm and the depth is 2 mm. If more than two fiberglass wires are routed in each groove, to ensure the routing of the lead wires and the skin can be spot welded, while placing the 1.6-mm-diameter fiberglass wires in the groove width, at least 2 - 3 mm of space should be left on each side for placing the spot welding skin for spot welding and fixing the fiberglass wires. Taking the example of routing three fiberglass wires in the groove, the grooving size of the rear mounting edge of the high-pressure turbine is 11 mm wide and 2 mm deep.

[0038] Optionally, to ensure the lead wires pass through and to strengthen the protection and fixation of the lead wires. At the radial end of the rear mounting edge of the high-pressure turbine disk, the corresponding position is the uppermost edge of the opening, and a lead hole is opened on the labyrinth ring. Also, a lead hole is opened at the corresponding position on the rear shaft mounting edge of the high-pressure turbine. If only one fiberglass wire passes through each lead hole, the opening can be a through hole with a diameter of 2.5 mm. If more than two fiberglass wires need to pass through each lead hole, to prevent interference between the lead wires, kidney-shaped holes need to be opened, that is, each lead wire can be arranged separately and the lead wires will not move in the holes. When three fiberglass wires pass through each hole, the lead holes on the labyrinth ring and the rear shaft mounting edge of the high-pressure turbine are both kidney-shaped holes with a length of 5.5 mm and a width of 2.6 mm.

[0039] During specific implementation, the slotting dimensions of the mating surface between the rear mounting flange of the turbine disk and the labyrinth ring are 11 mm in width and 2 mm in depth. 2 - 3 glass fiber lines can be routed along each slot. The uppermost edge of the opening corresponds to the radial end of the rear mounting flange of the turbine disk. 8 lead holes are drilled in the labyrinth ring. Also, 8 lead holes are drilled at the corresponding positions on the rear mounting flange of the low-pressure turbine rear shaft, and all are waist-shaped holes with a length of 5.5 mm and a width of 2.6 mm.

[0040] The glass fiber lines are routed along the rear shaft of the high-pressure turbine by means of skin spot welding. Since the telemetry system is installed at the rear end of the telemetry system lead shaft. The glass fiber lines need to be routed along the rear shaft of the high-pressure turbine to the prefabricated lead hole (high-pressure turbine rear shaft lead hole 12), penetrate into the interior of the rear shaft of the high-pressure turbine, and then pass through the prefabricated radial lead hole (high-pressure turbine rear shaft radial lead hole 13) on the telemetry system lead shaft to penetrate into the interior of the telemetry system lead shaft. Finally, it is led out backward through the prefabricated axial lead hole (telemetry system lead shaft lead hole 15) on the telemetry system lead shaft 14. The glass fiber lines are connected to the telemetry system located at the rear side to ensure the reliable fixation of the glass fiber lines and complete the pasting and routing of the high-temperature strain gauges.

[0041] Optionally, since it is not easy to operate during the process of the glass fiber lines passing through the rear shaft of the high-pressure turbine and the telemetry system lead shaft, it is best to pass only one glass fiber line through each hole. Then the opening diameter of the high-pressure turbine rear shaft lead hole is 2 mm. In order to ensure the effective passing of the glass fiber lines, the diameter of the radial lead hole of the telemetry system lead shaft is 3 mm, and the center line needs to be aligned with the center line of the high-pressure turbine rear shaft lead hole. And the axial lead hole of the telemetry system lead shaft has a size of 3 mm. The above three types of holes need to be symmetrical to maintain the balance of the entire shafting system.

[0042] During specific implementation, the glass fiber lines can withstand a temperature of 800 °C, have a diameter of 1.6 mm, and can be connected to the telemetry module; the metal skin used for the transfer between the strain gauge grid wire and the glass fiber line is a titanium alloy metal sheet; the high temperature of the high-temperature strain gauge refers to 250 °C - 1200 °C.

[0043] A high-temperature strain gauge routing method for a high-pressure turbine rotor blade according to an embodiment of the present invention uses a flame spraying process to paste a high-temperature strain gauge on the high-pressure turbine rotor blade, leads the strain gauge grid wire to the chamfer position at the leading edge of the blade root, and then leads the strain gauge grid wire into the lower side of the blade basin side edge plate along the prefabricated groove on the side edge plate of the blade tenon. Then, lead the glass fiber wire along the lead wire groove prefabricated at the position of the rim bump of the disk to the high-pressure turbine disk. Lead the glass fiber wire along the way to the inner side position of the rear baffle, and lead it out of the disk through the lead wire hole prefabricated in the rear baffle in advance. Route along the way to the rear section of the high-pressure turbine disk and fix it along the way. The glass fiber wire enters the labyrinth ring lead wire hole along the lead wire groove on the rear mounting edge of the high-pressure turbine disk and passes through the lead wire hole of the high-pressure turbine rear shaft. Route along the high-pressure turbine rear shaft to the prefabricated lead wire groove, penetrate into the inner side of the high-pressure turbine rear shaft, and then penetrate into the interior of the telemetry system lead wire shaft through the radially prefabricated lead wire hole on the telemetry system lead wire shaft. Finally, pass through the axially prefabricated lead wire hole on the telemetry system lead wire shaft and lead it out backward from the telemetry system lead wire shaft, and connect the glass fiber wire to the telemetry system located at the rear side to complete the pasting and routing of the high-temperature strain gauge. The embodiment of the present invention realizes the dynamic stress test and analysis of the turbine rotor blade under the core engine conditions, and lays a technical foundation for life prediction.

[0044] The above is only the specific implementation manner of the present application, but the protection scope of the present application is not limited thereto. Any changes or substitutions that can be easily thought of by those skilled in the art within the technical scope disclosed in the present application should be covered by the protection scope of the present application. Therefore, the protection scope of the present application shall be subject to the protection scope of the claims.

Claims

1. A high-temperature strain gauge wiring method for a high-pressure turbine rotor blade, characterized in that, Including: Adopt the flame spraying process to paste high-temperature strain gauges on the high-pressure turbine rotor blades, lead the strain gauge grid wires to the root position of the blade leading edge; then lead the strain gauge grid wires into the lower side of the blade basin side flange along the prefabricated lead grooves on the blade tenon flange, and perform the transfer of the strain gauge grid wires and glass fiber wires; Lead the transferred glass fiber wires to the high-pressure turbine disk along the prefabricated lead grooves at the positions of the high-pressure turbine disk rim bumps, lead the glass fiber wires along the way to the inner side of the rear baffle of the high-pressure turbine disk, and lead them out of the high-pressure turbine disk through the prefabricated lead holes on the rear baffle and into the outer side of the rear baffle, then route along the way to the rear section of the high-pressure turbine disk, and fix the glass fiber wires along the way; Lead the glass fiber wires into the labyrinth ring lead holes through the prefabricated lead grooves on the rear mounting edge of the high-pressure turbine disk and pass through the high-pressure turbine rear shaft lead holes, then lead the glass fiber wires along the high-pressure turbine rear shaft to the prefabricated lead grooves and penetrate into the inner side of the high-pressure turbine rear shaft, then penetrate into the interior of the telemetry system lead shaft through the prefabricated radial lead holes on the telemetry system lead shaft, and finally lead out of the telemetry system lead shaft backward through the prefabricated axial lead holes on the telemetry system lead shaft, and connect the glass fiber wires to the telemetry system located at the rear side to complete the pasting and routing of the high-temperature strain gauges; The slotting size of the prefabricated lead grooves on the blade tenon flange is 2.5*1.9mm; The slotting size of the prefabricated lead grooves at the positions of the high-pressure turbine disk rim bumps is 2mm in width and 1.9mm in depth, and 0.1mm is ground off the entire plane of the lead grooves; The slotting size of the prefabricated lead grooves on the rear mounting edge of the high-pressure turbine disk is: if 1 glass fiber wire is routed in the lead groove, the slotting width is 5mm and the depth is 2mm; if 2 or more glass fiber wires are routed in the lead groove, the slotting width is 11mm and the depth is 2mm; The corresponding position at the radial end of the rear mounting edge of the high-pressure turbine disk is the uppermost edge of the lead groove opening. The labyrinth ring is provided with lead holes, and lead holes are also opened at the corresponding positions on the rear shaft mounting edge of the high-pressure turbine to lead the glass fiber wires out of the high-pressure turbine rear shaft lead holes; among them, if 1 glass fiber wire is routed in the lead hole, the aperture of the opening is 2.5mm; if 2 or more glass fiber wires are routed in the lead hole, the lead holes on the labyrinth ring and the lead holes on the rear shaft mounting edge of the high-pressure turbine are both waist-shaped holes with a length of 5.5mm and a width of 2.6mm; The opening diameter of the high-pressure turbine rear shaft lead hole is 2mm, the opening diameter of the prefabricated radial lead holes on the telemetry system lead shaft is 3mm, and the opening diameter of the prefabricated axial lead holes on the telemetry system lead shaft is 3mm; The process of transferring the strain gauge grid wires and glass fiber wires includes: Blow sand at the transfer position, apply ceramic cement glue in the blow sand area, respectively spot-weld the reserved glass fiber wires on the blade and the disk with the glass fiber wires to form two non-contact welding heads, cover insulating felts at the two welding heads, and fix the insulating felts with metal skins.

2. The high-temperature strain gauge wiring method for a high-pressure turbine rotor blade according to claim 1, wherein The method further includes: when leading the strain gauge grid wire to the root position of the blade leading edge, chamfering the blade leading edge blade basin edge, and fixing the strain gauge grid wire to the chamfered position of the blade leading edge blade basin edge by flame spraying.

3. The high-temperature strain gauge routing method for a high-pressure turbine rotor blade according to claim 2, wherein The chamfer size of the blade leading edge blade basin edge is 2*2 mm.

4. The high-temperature strain gauge wiring method for a high-pressure turbine rotor blade according to claim 1, wherein The metal skin is made of a titanium alloy metal thin sheet.

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