Wiring method for high-temperature strain gauges of high-pressure turbine rotor blade

Abstract

The invention provides a high-temperature strain gauge routing method for a high-pressure turbine rotor blade, and relates to the field of aero-engine high-pressure turbine rotor blade testing.The method comprises the steps that a strain gauge is pasted on a rotor blade, and a strain gauge grid wire is led to the root of the front edge of the blade; the grid silk threads enter the lower portion of the blade basin side edge plate along the blade tenon edge plate to conduct switching between the grid silk threads and the glass silk fiber threads; the glass fiber wires are led to the turbine disc along the position of the wheel flange protruding block, led to the inner side of a rear baffle of the turbine disc along the way, enter the outer side of the rear baffle and then are routed to the rear section of the turbine disc along the way; a glass fiber wire enters a labyrinth ring lead hole along a turbine disc rear installation edge, penetrates out of a turbine rear shaft lead hole, penetrates into the inner side of a turbine rear shaft and then penetrates into a telemetering system lead shaft, finally the telemetering system lead shaft is led out, and the glass fiber wire is connected into a telemetering system. According to the invention, the lead of the high-temperature strain gauge can be led out under the condition that the bottom of the blade tenon has cracks and cannot be holed, and a foundation is laid for 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, contact high-temperature strain gauges are usually pasted by high-temperature spraying, 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 gauges to the high-temperature wires 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. This is mainly because the structure of the engine limits the telemetry module to be installed only 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, the routing of high-temperature strain gauges on high-pressure turbine rotor blades is very difficult, and there is no unified standard and specification at present. Summary of the Invention

[0005] In view of this, the embodiments of the present application provide 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, and proposes a routing method for the convex blocks on the rim of the turbine disk, realizing the lead-out of the high-temperature strain gauge under the condition that there are cracks at the bottom of the blade tenon and it is impossible to open holes, laying a foundation for realizing the high-temperature dynamic stress testing of high-pressure turbine rotor blades.

[0006] The embodiments of the present application provide the following technical solutions: A method for routing high-temperature strain gauges on high-pressure turbine rotor blades, comprising: Adopting a flame spraying process to paste a high-temperature strain gauge on a 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 side plate of the blade basin along the prefabricated lead groove on the flange plate of the blade tenon for the transfer of the grid wires of the strain gauge and the glass fiber wire; 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 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; Feed the glass fiber wire 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 high-pressure turbine rear shaft lead hole, then route the glass fiber wire along the high-pressure turbine rear shaft to the prefabricated lead groove and penetrate into the inner side of the high-pressure turbine rear shaft, then penetrate into the internal telemetry system lead shaft through the prefabricated radial lead hole on the telemetry system lead shaft, and finally lead out of the telemetry system lead shaft backward through the prefabricated axial lead hole on the telemetry system lead shaft, and connect the glass fiber wire to the telemetry system at the rear side to complete the pasting and routing of the high-temperature strain gauge.

[0007] 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, chamfer the blade leading edge blade concave side, and fix the strain gauge grid wire to the chamfered position of the blade leading edge blade concave side by flame spraying.

[0008] According to an embodiment of the present application, the chamfer size of the blade leading edge blade concave side is 2*2 mm.

[0009] 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.

[0010] 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 ground and cut off by 0.1 mm.

[0011] 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 wire is routed in the lead groove, the slotting width is 5 mm and the depth is 2 mm; if 2 or more glass fiber wires are routed in the lead groove, the slotting width is 11 mm and the depth is 2 mm.

[0012] 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 wire out of the high-pressure turbine rear shaft lead hole; wherein, if 1 glass fiber wire is routed in the lead hole, the aperture of the opening is 2.5 mm; 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 5.5 mm and a width of 2.6 mm.

[0013] According to an embodiment of the present application, the opening diameter of the high-pressure turbine rear shaft lead hole 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.

[0014] 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 reserved glass fiber wires on the blade and the disk to the glass fiber wires respectively to form two non-contact welding heads, covering insulating felts at the two welding heads, and fixing the insulating felts with a metal skin.

[0015] According to an embodiment of the present application, the metal skin is made of a titanium alloy metal sheet.

[0016] 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 have realized the high-temperature strain gauge pasting and wire routing of the high-pressure turbine rotor blade, overcome the difficulty of wire routing under the condition of blade dovetail crack, and realized the method of the high-pressure turbine rotor blade under the complex high-pressure turbine disk structure. The dynamic stress data of the high-pressure turbine rotor blade 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 the high-pressure turbine rotor blade. BRIEF DESCRIPTION OF THE DRAWINGS

[0017] 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, other drawings can be obtained based on these drawings without creative efforts.

[0018] Figure 1 Schematic diagram of the high-temperature strain gauge wire routing method for the high-pressure turbine rotor blade in the embodiment of the present invention; 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 basin side flange; 7 - high-pressure turbine disk rim bump; 8 - blade-disk rim bump 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 DESCRIPTION OF THE EMBODIMENTS

[0019] The embodiments of the present application will be described in detail below with reference to the drawings.

[0020] The following describes the implementation methods 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 implementation methods, 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 following embodiments and the features in the embodiments can be combined with each other. Based on the embodiments in the present application, all other embodiments obtained by ordinary technicians in the field without making creative work belong to the scope of protection of the present application.

[0021] like Figure 1 As shown, an embodiment of the present invention provides a method for routing high-temperature strain gauges of high-pressure turbine rotor blades, comprising: pasting high-temperature strain gauges on high-pressure turbine rotor blades 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-in 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-in 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 rear baffle of the high-pressure turbine disk, and leading out of the high-pressure turbine through the prefabricated lead-in 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 comb ring lead hole along the prefabricated lead groove on the rear mounting edge of the high-pressure turbine disk and passes through the lead hole of the high-pressure turbine rear shaft, and then the glass fiber line is routed along the rear shaft of the high-pressure turbine to the prefabricated lead groove and penetrates into the inner side of the rear shaft of the high-pressure turbine, and then passes through the prefabricated radial lead hole on the lead shaft of the telemetry system and penetrates into the inside of the lead shaft of the telemetry system, and finally passes through the prefabricated axial lead hole on the lead shaft of the telemetry system to lead out of the lead shaft of the telemetry system backwards, and the glass fiber line is connected to the telemetry system located on the rear side to complete the pasting and routing of the high-temperature strain gauge.

[0022] When implementing it, 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 solution: First, use the high-temperature spraying process to paste high-temperature strain gauges 2 on the high-pressure turbine rotor blades 1, and lead the grid wires 3 of the strain gauges to the root position of the blade leading edge. In order to reduce the impact on the blade strength and protect the strain leads, chamfering treatment is carried out on the blade leading edge blade basin edge to form the blade leading edge chamfer position 4. Then, prefabricate a lead wire groove at the blade tenon flange position to form the blade tenon flange prefabricated groove 5. After fixing the grid wires 3 of the strain gauge to the chamfer position of the blade leading edge blade basin edge by flame spraying, it enters under the side flange 6 of the blade basin through the blade tenon flange prefabricated groove 5, and the grid wires are transferred to the glass fiber wires.

[0023] Optionally, the size of the glass fiber wire of the strain gauge is 1.6 mm in diameter. Therefore, chamfering treatment is carried out on the blade leading edge blade basin edge to form the blade leading edge chamfer position 4, and the chamfering size starts from the blade basin edge and is 2 * 2 mm.

[0024] Optionally, prefabricate a lead wire groove at the blade tenon flange position, and the groove size is 2.5 * 1.9 mm.

[0025] Specifically, the transfer steps of the grid wires 3 of the strain gauge and the glass fiber wires on the blade flange under the tenon include: sandblasting at the transfer position, coating 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 welding heads, and the two welding heads should not touch; after covering the two welding heads with insulating felt, fix the insulating felt with a metal skin.

[0026] Fix the transferred glass fiber wires to the tenon groove position by spot welding along the skin, and then lead the glass fiber wires along the prefabricated lead wire groove (blade disk rim lug lead wire groove 8) at the position of the high-pressure turbine disk rim lug 7 to the high-pressure turbine disk. After routing, fix it by spot welding with the skin. In order to reduce the suspended section of the glass fiber wires, 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.

[0027] 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 wires 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.

[0028] After installing the rear baffle 9 on the high-pressure turbine disk, lead the glass fiber wires along the way to the inner side position of the rear baffle, lead out of the high-pressure turbine disk through the prefabricated lead wire hole and enter the outer side of the rear baffle, and then route along the way to the rear section of the high-pressure turbine disk and fix it along the way.

[0029] Optionally, to prevent the leads from being suspended, the hole opening position on 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 wire during the installation process. Therefore, the hole is opened 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 wire during the installation of the rear baffle and also reducing the suspended section of the lead during the routing of the fiberglass wire.

[0030] Optionally, the diameter of the fiberglass wire is 1.6 mm. One hole is opened for each lead of the strain gauge, and the hole opening size of the rear baffle 9 is 2 mm in diameter.

[0031] When the rear mounting edge of the high-pressure turbine disk, the labyrinth ring mounting edge, and the rear shaft of the high-pressure turbine are connected by bolts, the fiberglass wire needs to be routed. By means of skin spot welding, the fiberglass wire enters the labyrinth ring lead hole 11 along the lead groove 10 on the rear mounting edge of the turbine disk and passes through the lead hole 12 of the rear shaft of the high-pressure turbine.

[0032] Optionally, the mating surface between the rear mounting edge of the high-pressure turbine disk and the labyrinth ring needs to be grooved for the routing of the fiberglass wire. During the routing of the fiberglass wire in the groove, it needs to be fixed by means of skin spot welding. 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 leads and the ability to perform skin spot welding, while placing the fiberglass wire with a diameter of 1.6 mm in the groove width, at least 2 - 3 mm of space needs to be left on both the left and right for placing the spot welding skin to fix the fiberglass wire by spot welding. 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.

[0033] Optionally, to ensure the lead passes through and to strengthen the protection and fixation of the lead. At the radial end of the rear mounting edge of the high-pressure turbine disk, the corresponding position is the uppermost edge of the hole 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 hole 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 leads, a kidney-shaped hole needs to be opened, that is, to enable each lead to be arranged separately and to prevent the leads from moving in the hole. 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.

[0034] During specific implementation, the slotting dimensions on 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 wires 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 on 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.

[0035] Using the method of skin spot welding, route the glass fiber wires along the rear shaft of the high-pressure turbine. Since the telemetry system is installed at the rear end of the telemetry system lead shaft. The glass fiber wires 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, lead 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 wires are connected to the telemetry system located at the rear side to ensure the reliable fixation of the glass fiber wires and complete the pasting and routing of the high-temperature strain gauges.

[0036] Optionally, since it is not easy to operate during the process of the glass fiber wires 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 wire 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 wires, 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 size of the axial lead hole of the telemetry system lead shaft is 3 mm. The above three types of holes need to be symmetric to maintain the balance of the entire shafting system.

[0037] During specific implementation, the glass fiber wires 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 wires and the glass fiber wires is a titanium alloy metal sheet; the high temperature of the high-temperature strain gauge refers to 250 °C - 1200 °C.

[0038] A high-temperature strain gauge wiring 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 chamfered 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 flange along the prefabricated groove on the side flange 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. 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 wiring 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 condition, and lays a technical foundation for life prediction.

[0039] As described above, the above is only a specific embodiment 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 within the protection scope of the present application. Therefore, the protection scope of the present application should be subject to the protection scope of the claims.

Claims

1. A method for routing high-temperature strain gauges for high-pressure turbine rotor blades, characterized in that: include: A high-temperature strain gauge is pasted on a high-pressure turbine rotor blade by a flame spraying process, and the strain gauge grid wire is led to the root position of the leading edge of the blade; the strain gauge grid wire is then led 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; Lead the transferred glass fiber wire along the prefabricated lead-in groove on the convex position of the high-pressure turbine disk rim to the high-pressure turbine disk, lead the glass fiber wire along the way to the inner side of the rear baffle of the high-pressure turbine disk, and lead out of the high-pressure turbine disk through the prefabricated lead-in hole on the rear baffle to the outside of the rear baffle, and then run along the way to the rear section of the high-pressure turbine disk, and fix the glass fiber wire along the way; The glass fiber wire is routed along the prefabricated lead groove on the rear mounting edge of the high-pressure turbine disk into the lead hole of the comb ring and passes through the lead hole of the high-pressure turbine rear shaft. The glass fiber wire is then routed along the rear shaft of the high-pressure turbine to the prefabricated lead groove and passed through the inner side of the rear shaft of the high-pressure turbine. The glass fiber wire is then passed through the prefabricated radial lead hole on the lead shaft of the telemetry system and into the interior of the lead shaft of the telemetry system. Finally, the glass fiber wire is passed through the prefabricated axial lead hole on the lead shaft of the telemetry system and led out of the lead shaft of the telemetry system backwards. The glass fiber wire is connected to the telemetry system located on the rear side to complete the pasting and routing of the high-temperature strain gauge.

2. The high-temperature strain gauge routing method for high-pressure turbine rotor blades according to claim 1 is characterized in that: The method further comprises: when the strain gauge wire is led to the root position of the leading edge of the blade, an angle treatment is performed on the blade leading edge basin edge, and the strain gauge wire is fixed to the angled position of the blade leading edge basin edge by flame spraying.

3. The high-pressure turbine rotor blade high-temperature strain gauge routing method according to claim 2 is characterized in that: The chamfer size of the blade leading edge and the blade basin edge is 2*2mm.

4. The high-pressure turbine rotor blade high-temperature strain gauge routing method according to claim 1, characterized in that: The slot size of the prefabricated lead groove on the blade tenon edge plate is 2.5*1.9mm.

5. The high-pressure turbine rotor blade high-temperature strain gauge routing method according to claim 1 is characterized in that: The prefabricated wire groove at the position of the high-pressure turbine disc rim protrusion has a slot size of 2 mm in width and 1.9 mm in depth, and the entire surface of the wire groove is ground off by 0.1 mm.

6. The high-pressure turbine rotor blade high-temperature strain gauge routing method according to claim 1, characterized in that: The slot dimensions of the prefabricated lead groove on the rear mounting edge of the high-pressure turbine disc are: if one glass fiber wire is routed in the lead groove, the slot width is 5 mm and the depth is 2 mm; if two or more glass fiber wires are routed in the lead groove, the slot width is 11 mm and the depth is 2 mm.

7. The high-pressure turbine rotor blade high-temperature strain gauge routing method according to claim 1, characterized in that: The corresponding position at the radial end of the rear mounting edge of the high-pressure turbine disc is the uppermost edge of the lead groove opening, a lead hole is opened on the comb tooth ring, and a lead hole is also opened at the corresponding position of the rear shaft mounting edge of the high-pressure turbine to pass the glass fiber wire through the lead hole of the rear shaft of the high-pressure turbine; wherein, if one glass fiber wire is routed in the lead hole, the aperture of the opening is 2.5mm; if two or more glass fiber wires are routed in the lead hole, the lead hole on the comb tooth ring and the lead hole 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.

8. The high-pressure turbine rotor blade high-temperature strain gauge routing method according to claim 6, characterized in that: The opening diameter of the lead hole of the high-pressure turbine rear shaft is 2mm, the opening diameter of the radial lead hole prefabricated on the lead shaft of the telemetry system is 3mm, and the opening diameter of the axial lead hole prefabricated on the lead shaft of the telemetry system is 3mm.

9. The high-temperature strain gauge routing method for high-pressure turbine rotor blades according to claim 1, characterized in that: The process of connecting the strain gauge grid wire and the glass fiber wire includes: Sand is blown at the transfer position, ceramic cement glue is coated on the sand blowing area, and the reserved glass fiber wires on the blades and the disk are spot welded to form two non-contact welding heads, and insulating felt is covered at the two welding heads, and the insulating felt is fixed with a metal skin.

10. The high-pressure turbine rotor blade high-temperature strain gauge routing method according to claim 9, characterized in that: The metal skin is made of titanium alloy metal sheet.

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