An eddy current detection device and damage location method for aircraft engine blades

Abstract

The present invention discloses an eddy current detection device and damage location method for aircraft engine blades, which relate to the field of non-destructive testing technology and include a positioning assembly, wherein the positioning assembly includes a detection plate, on which four pulleys are rotatably mounted, the four pulleys being connected by a movable belt transmission, and the detection plate being provided with a slide rail. The present invention can locate the damage position and test the dynamic balance of the engine blades through a single clamping operation, thereby reducing the risk of the engine blades being damaged by slipping during clamping; by providing a positioning assembly, the damage to the engine blades is located in a linear and rotational manner, making it easier to determine the cause and location of the fault when a fault occurs; by using a variable transmission ratio in the clamping assembly, the starting load of the rotary drive motor can be reduced when the dynamic balance test of the engine blades is performed, thereby extending the service life of the rotary drive motor.

Description

Technical Field

[0001] The present invention relates to the technical field of non-destructive testing, and in particular to an eddy current detection device for an aero-engine blade and a damage locating method. Background Art

[0002] Aircraft engines are highly complex and sophisticated thermodynamic machines. As the heart of an aircraft, they not only power its flight but also serve as a vital driving force for the development of aviation. Every significant revolution in human aviation history is closely linked to technological advancements in aircraft engines. To ensure stable operation, the blades must be inspected before assembly. To ensure that the blades do not develop defects during inspection, most non-destructive testing methods are employed, with eddy current testing being the most widely used. However, current inspections for aircraft engine blades cannot simultaneously detect surface defects and perform dynamic balance tests, requiring separate inspections. This increases the risk of blade scratches when replacing the positioning fixture.

[0003] Prior art, patent application CN110243926A discloses an in-situ eddy current testing system for fan blades, comprising a comparison specimen, an eddy current testing coil, a probe push rod, and an eddy current detector, wherein the eddy current testing coil is connected to the eddy current detector. The comparison specimen is provided with artificial grooves disposed around a damping platform, comprising a first artificial groove, a second artificial groove, and a third artificial groove. The probe push rod is a foldable push rod comprising a probe mounting section, a connecting section, and a handheld section. The foldable push rod has two states: a straight state; and a state in which the probe mounting section and the connecting section have a bending angle α, and the connecting section and the handheld section have a bending angle β. The eddy current testing coil is mounted on the probe mounting section of the probe push rod. A testing method is also disclosed, which effectively implements in-situ eddy current testing of blades without requiring blade disassembly, enabling effective crack detection, and enabling targeted measures to be taken to improve the safety and reliability of equipment operation. However, the technical solution adopted by this prior art fails to resolve the aforementioned technical problems. Summary of the Invention

[0004] In order to overcome the defects of the above-mentioned prior art, the present invention provides the following technical solutions: an eddy current detection device for aircraft engine blades, comprising a positioning assembly, the positioning assembly comprising a detection plate, four pulleys rotatably mounted on the detection plate, the four pulleys being connected by a moving belt transmission, a slide rail being provided on the detection plate, a slide rod bracket being slidably mounted in the slide rail, a slide rod being slidably mounted on the slide rod bracket, a movable seat being fixedly mounted on the slide rod, the movable seat being rotatably mounted on the moving belt, and a probe being fixedly mounted on the slide rod; further comprising a clamping assembly, the clamping assembly comprising a clamping table, three clamping columns being provided on the clamping table for sliding The movable bracket is provided with a plurality of movable brackets, each of which is provided with a plurality of movable brackets, and the movable bracket has a plurality of movable brackets, each of which is provided with a plurality of movable brackets.

[0005] Preferably, one of the pulleys is fixedly mounted on the output shaft of the positioning motor, the positioning motor is fixedly mounted on the detection plate, and a visual sensor is also fixedly mounted on the detection plate.

[0006] Preferably, the detection plate is rotatably mounted on a workbench, the workbench is fixedly mounted on a pillar, a protective connecting rod is also fixedly mounted on the detection plate, one end of the protective connecting rod is movably connected to the telescopic rod of the protective telescopic electric cylinder, the telescopic cylinder of the protective telescopic electric cylinder is movably connected to the workbench, and a limit column for limiting the rotation angle of the protective connecting rod is also fixedly mounted on the workbench, and the limit column is in contact and cooperation with the protective connecting rod.

[0007] Preferably, the limiting slide support plate is provided with a tooth shape, the fixed barrel is fixedly mounted with a clamping drive motor, the output shaft of the clamping drive motor is fixedly mounted with a clamping drive gear, the clamping drive gear is engaged with the limiting slide support plate, and the fixed barrel is provided with a tooth shape.

[0008] Preferably, a rotation spring is wound around the rotation pull rod, and two ends of the rotation spring are respectively fixed to the centrifugal friction transmission block and the rotation pull rod.

[0009] Preferably, a rotating gear is rotatably mounted on the fixed barrel rotating seat, the rotating gear is engaged with the fixed barrel, and the eight centrifugal friction transmission blocks are connected to the rotating gear via a transmission belt.

[0010] Preferably, a rotary drive motor is slidably mounted on the fixed bracket via a floating reset rod, the output shaft of the rotary drive motor is fixed to the floating rotating shaft, a floating reset spring is surrounded by the floating reset rod, and the two ends of the floating reset spring are fixedly connected to the rotary drive motor and the fixed bracket respectively.

[0011] Preferably, the output shaft of the rotary drive motor is slidably fitted with the movable groove, the clamping table and the fixed barrel are slidably fitted in the working cover, the working cover is fixedly mounted on the working table, and an air inlet hole is provided on the working cover, a lifting electric cylinder is fixedly mounted on the working table, and the telescopic rod of the lifting electric cylinder is fixed to the fixed bracket.

[0012] Among them, a damage locating method for an aircraft engine blade includes the following steps: S1, constructing and recording the moving trajectory coordinates of the probe, and moving the probe above the engine blade; S2, moving the probe from the edge of the engine blade along the radial direction of the engine blade to the center; S3, rotating the engine blade 2 to 5 degrees; S4, moving the probe from the center of the engine blade along the radial direction of the engine blade to the edge; S5, repeating S2-S4 until the engine blade rotates to 360 degrees, and then stopping the rotation of the engine blade; S6, whether the voltage and impedance of the probe change in S2-S5; S7, marking the trajectory coordinates when the voltage and impedance of the probe change.

[0013] Compared with the prior art, the present invention has the following advantages: (1) The present invention can locate the damaged position and test the dynamic balance of the engine blades through one clamping, thereby reducing the risk of slipping of the engine blades during clamping; (2) The present invention uses a positioning component to locate the damage of the engine blades in a linear and rotational manner, making it easier to determine the cause and location of the fault when a fault occurs; (3) The present invention uses a variable transmission ratio in the clamping component, which can reduce the starting load of the rotary drive motor when performing a dynamic balance test on the engine blades, thereby extending the service life of the rotary drive motor. BRIEF DESCRIPTION OF THE DRAWINGS

[0014] Figure 1 It is a schematic diagram of the overall structure of the present invention.

[0015] Figure 2 This is a structural diagram of the visual sensor of the present invention.

[0016] Figure 3 It is a structural schematic diagram of the movable seat of the present invention.

[0017] Figure 4 It is a front view of the overall structure of the present invention.

[0018] Figure 5 It is a structural schematic diagram of the limiting column of the present invention.

[0019] Figure 6 This is a cross-sectional view of the working cover structure of the present invention.

[0020] Figure 7 It is a structural schematic diagram of the clamping column of the present invention.

[0021] Figure 8 This is a structural diagram of the sliding groove of the clamping column of the present invention.

[0022] Figure 9 It is a structural schematic diagram of the limiting slide of the present invention.

[0023] Figure 10 This is a diagram showing the installation position of the clamping drive motor of the present invention.

[0024] Figure 11 It is a schematic diagram of the transmission belt structure of the present invention.

[0025] Figure 12 For the present invention Figure 11 Schematic diagram of the structure at point A in the middle.

[0026] Figure 13 It is a structural schematic diagram of the fixing bracket of the present invention.

[0027] Figure 14 This is a structural diagram of the rotary drive motor of the present invention.

[0028] In the figure: 101-working cover; 1011-air inlet; 102-working table; 103-pillar; 104-detection plate; 1041-slide rail; 105-slide rod bracket; 106-pulley; 107-moving belt; 108-slide rod; 109-probe; 110-positioning motor; 111-visual sensor; 112-movable seat; 113-protective telescopic cylinder; 114-protective connecting rod; 115-limiting column; 201-clamping table; 2011-clamping column sliding groove; 202-fixed barrel; 203-clamping column; 204 -limiting slide; 205-limiting slide support plate; 206-clamping drive gear; 207-clamping drive motor; 208-fixed barrel rotating seat; 2081-moving slide; 209-rotating gear; 210-transmission belt; 211-floating rotating shaft; 212-rotating pull rod; 213-rotating spring; 214-centrifugal friction transmission block; 215-fixed bracket; 2151-moving slot; 216-rotating drive motor; 217-floating return spring; 218-floating return rod; 219-lifting electric cylinder; 3-engine blades. DETAILED DESCRIPTION

[0029] The technical solution of the present invention will be further described below with reference to the accompanying drawings and through specific implementation methods.

[0030] like Figures 1-6As shown, the present invention provides a technical solution: an eddy current detection device for an aircraft engine blade, including a positioning component, the positioning component including a detection plate 104, four pulleys 106 are rotatably mounted on the detection plate 104, the four pulleys 106 are connected by a moving belt 107, a slide rail 1041 is provided on the detection plate 104, a slide rod bracket 105 is slidably mounted in the slide rail 1041, a slide rod 108 is slidably mounted on the slide rod bracket 105, a movable seat 112 is fixedly mounted on the slide rod 108, the movable seat 112 is rotatably mounted on the moving belt 107, a probe 109 is fixedly mounted on the slide rod 108, one of the pulleys 106 is fixedly mounted on the positioning motor 1 10, the positioning motor 110 is fixedly mounted on the detection plate 104, the detection plate 104 is also fixedly mounted with a visual sensor 111, the detection plate 104 is rotatably mounted on the workbench 102, the workbench 102 is fixedly mounted on the pillar 103, the detection plate 104 is also fixedly mounted with a protective link 114, one end of the protective link 114 is movably connected to the telescopic rod of the protective telescopic electric cylinder 113, the telescopic cylinder of the protective telescopic electric cylinder 113 is movably connected to the workbench 102, and a limit column 115 for limiting the rotation angle of the protective link 114 is also fixedly mounted on the workbench 102, and the limit column 115 is in contact with the protective link 114.

[0031] like Figure 5-Figure 14As shown, it also includes a clamping assembly, which includes a clamping platform 201, three clamping column sliding grooves 2011 are provided on the clamping platform 201, and clamping columns 203 are slidably installed in the three clamping column sliding grooves 2011. The clamping platform 201 is fixedly installed on the fixed barrel 202, and a limited slide support plate 205 is rotatably installed on the fixed barrel 202. Three limited slides 204 that slide with the clamping columns 203 are fixedly installed on the limited slide support plate 205. The fixed barrel 202 is rotatably installed on the fixed barrel rotating seat 208, and the fixed barrel rotating seat 208 is provided with a floating slide groove 2081. A floating shaft 211 is slidably installed in the movable slide groove 2081, and eight rotating pull rods 212 are fixedly installed on the floating shaft 211. A centrifugal friction transmission block 214 is slidably installed on each rotating pull rod 212. The fixed barrel rotating seat 208 is fixedly installed on the fixed bracket 215. The fixed bracket 215 is provided with a moving groove 2151. The limiting slide support plate 205 is provided with a tooth shape. The fixed barrel 202 is fixedly installed with a clamping drive motor 207. The output shaft of the clamping drive motor 207 is fixedly installed with a clamping drive gear 206. The clamping drive gear 206 and the limiting slide support plate 205 are engaged, a tooth shape is provided on the fixed barrel 202, a rotating spring 213 is surrounded on the rotating pull rod 212, and the two ends of the rotating spring 213 are respectively fixed to the centrifugal friction transmission block 214 and the rotating pull rod 212, a rotating gear 209 is rotatably installed on the fixed barrel rotating seat 208, the rotating gear 209 is engaged with the fixed barrel 202, the eight centrifugal friction transmission blocks 214 are connected to the rotating gear 209 through a transmission belt 210, a rotating drive motor 216 is slidably installed on the fixed bracket 215 through a floating reset rod 218, and the output shaft of the rotating drive motor 216 is connected to the floating rotary The shaft 211 is fixed, and a floating return spring 217 is wrapped around the floating return rod 218. The two ends of the floating return spring 217 are respectively fixedly connected to the rotary drive motor 216 and the fixed bracket 215. The output shaft of the rotary drive motor 216 slides with the movable groove 2151. The clamping table 201 and the fixed barrel 202 slide in the working cover 101. The working cover 101 is fixedly installed on the working table 102, and an air inlet hole 1011 is opened on the working cover 101. A lifting electric cylinder 219 is fixedly installed on the working table 102, and the telescopic rod of the lifting electric cylinder 219 is fixed to the fixed bracket 215.

[0032] The working principle of an eddy current detection device and damage location method for aircraft engine blades disclosed in the present invention is as follows: when in use, the engine blade 3 is placed in the middle of the working cover 101, and then the telescopic rod of the lifting electric cylinder 219 is controlled to extend. At this time, the telescopic rod of the lifting electric cylinder 219 will drive the fixed bracket 215 to move upward (through the fixed barrel rotating seat 208 and the fixed barrel 202). At this time, the clamping platform 201 will move upward so that the upper surface of the clamping platform 201 is flush with the upper surface of the working cover 101, and at the same time, the three clamping columns 203 are moved to the middle (according to the shape of the engine blade 3, appropriate clamps are installed on the clamping columns 203 so that the engine blade 3 can be stably clamped, such as Figure 7As shown, the center of the engine blade 3 is a circle), and then the clamping drive motor 207 is controlled to rotate, and the output shaft of the clamping drive motor 207 drives the clamping drive gear 206 to rotate, and the rotation of the clamping drive gear 206 drives the limit slide support plate 205 to rotate, and the rotation of the limit slide support plate 205 drives the limit slide 204 to rotate, and the rotation of the limit slide 204 drives the three clamping columns 203 to move away from or close to each other. At this time, they need to move away from each other so that the engine blade 3 can be fixed on the clamping column 203, and then Draw a mark on the engine blade 3 with a pen, and then start the rotary drive motor 216. The output shaft of the rotary drive motor 216 drives the floating shaft 211 to rotate. The floating shaft 211 drives the centrifugal friction transmission block 214 to rotate by rotating the pull rod 212. The centrifugal friction transmission block 214 drives the rotary gear 209 to rotate through the transmission belt 210. The rotation of the rotary gear 209 drives the fixed barrel 202 to rotate. The rotation of the fixed barrel 202 drives the clamping platform 201 to rotate. The rotation of the clamping platform 201 drives the engine blade through the clamping column 203. 3 rotates. When the engine blade 3 rotates, the mark on the engine blade 3 also rotates accordingly. The visual sensor 111 is used to observe whether the rotational motion path of the mark is eccentric, thereby determining the mass distribution of the engine blade 3. Specifically, when the rotary drive motor 216 is started, the output shaft of the rotary drive motor 216 drives the floating shaft 211 to rotate. The rotation of the floating shaft 211 drives the rotation of the rotating pull rod 212. The rotation of the rotating pull rod 212 drives the centrifugal friction transmission block 214 to rotate. When rotating at a low speed, the centrifugal force exerted on the centrifugal friction transmission block 214 does not compress the rotation spring 213. When rotating at a high speed, the centrifugal force exerted on the centrifugal friction transmission block 214 will compress the rotation spring 213. At this time, the centrifugal friction transmission block 214 will slide outward along the rotating pull rod 212. Therefore, the transmission ratio of the rotation of the rotating gear 209 caused by the rotation of the centrifugal friction transmission block 214 at a high speed is greater than the transmission ratio of the rotation of the rotating gear 209 caused by the rotation of the centrifugal friction transmission block 214 at a low speed, thereby realizing the function of an adaptive transmission ratio and improving the starting efficiency of the rotary drive motor 216. By controlling the extension and retraction of the protective telescopic electric cylinder 113, the swing of the detection plate 104 can be controlled through the protective connecting rod 114 to prevent the probe 109 from colliding with the engine blade 3 when installing the engine blade 3. By controlling the start of the positioning motor 110, the output shaft of the positioning motor 110 will drive one of the pulleys 106 to rotate, and then drive the moving belt 107 to rotate. The rotation of the moving belt 107 will drive the slide bar 108 to move along the path of the moving belt 107 (it is only necessary to make the moving path of the slide bar 108 L-shaped). The movement of the slide bar 108 will drive the probe 109 to move. When the probe 109 is working, an alternating current is passed through it, thereby establishing an alternating magnetic field. The alternating magnetic field passes through the engine blade 3 and generates electromagnetic induction with the engine blade 3, thereby establishing eddy currents in the engine blade 3.The eddy currents in the engine blade 3 also generate their own magnetic field. The eddy current magnetic field changes the strength of the original magnetic field (probe 109), which in turn causes changes in the voltage and impedance of probe 109. Therefore, when a defect appears in the engine blade 3 or the material of the engine blade 3 changes, it will affect the intensity and distribution of the eddy currents in the engine blade 3. The change in eddy currents will cause changes in the voltage and impedance of probe 109. Therefore, it is possible to determine whether there is a defect in the engine blade 3. By controlling the movement of probe 109 and the rotation of the engine blade 3, it is possible to locate the damage at various locations on the engine blade 3.

Claims

1. An eddy current detection device for aircraft engine blades, characterized by: The positioning assembly comprises a detection plate (104), four pulleys (106) are rotatably mounted on the detection plate (104), the four pulleys (106) are connected by a moving belt (107), a slide rail (1041) is provided on the detection plate (104), a slide rod bracket (105) is slidably mounted in the slide rail (1041), a slide rod (108) is slidably mounted on the slide rod bracket (105), a movable seat (112) is fixedly mounted on the slide rod (108), the movable seat (112) is rotatably mounted on the moving belt (107), and a probe (109) is fixedly mounted on the slide rod (108); One of the pulleys (106) is fixedly mounted on the output shaft of the positioning motor (110), the positioning motor (110) is fixedly mounted on the detection plate (104), and the detection plate (104) is also fixedly mounted with a visual sensor (111); the detection plate (104) is rotatably mounted on the workbench (102), the workbench (102) is fixedly mounted on the pillar (103), and a protective connecting rod (114) is also fixedly mounted on the detection plate (104), one end of the protective connecting rod (114) is movably connected to the telescopic rod of the protective telescopic electric cylinder (113), the telescopic cylinder of the protective telescopic electric cylinder (113) is movably connected to the workbench (102), and a limiting column (115) for limiting the rotation angle of the protective connecting rod (114) is also fixedly mounted on the workbench (102), and the limiting column (115) is in contact with the protective connecting rod (114); The clamping assembly further comprises a clamping platform (201), the clamping platform (201) is provided with three clamping column sliding grooves (2011), and the three clamping column sliding grooves (2011) are all slidably mounted with clamping columns (203), the clamping platform (201) is fixedly mounted on the fixed barrel (202), a limiting slide support plate (205) is rotatably mounted on the fixed barrel (202), and three limiting slides (204) that are slidably matched with the clamping columns (203) are fixedly mounted on the limiting slide support plate (205), the fixed barrel (202) is rotatably mounted on the fixed barrel rotating seat (208), and a floating slide groove (2081) is provided on the fixed barrel rotating seat (208), and a sliding slide groove (2081) is slidably mounted in the floating slide groove (2081). A floating rotating shaft (211) is provided, and eight rotating pull rods (212) are fixedly installed on the floating rotating shaft (211), and a centrifugal friction transmission block (214) is slidably installed on each rotating pull rod (212). The fixed barrel rotating seat (208) is fixedly installed on a fixed bracket (215), and a moving groove (2151) is provided on the fixed bracket (215); a tooth shape is provided on the limit slide support plate (205), a clamping drive motor (207) is fixedly installed on the fixed barrel (202), and a clamping drive gear (206) is fixedly installed on the output shaft of the clamping drive motor (207), and the clamping drive gear (206) is meshed with the limit slide support plate (205). The fixed barrel (202) is provided with a tooth shape.

2. The eddy current detection device for aircraft engine blades according to claim 1, characterized in that: A rotation spring (213) is wound around the rotation pull rod (212), and two ends of the rotation spring (213) are respectively fixed to the centrifugal friction transmission block (214) and the rotation pull rod (212).

3. The eddy current detection device for aircraft engine blades according to claim 2, characterized in that: A rotating gear (209) is rotatably mounted on the fixed barrel rotating seat (208), the rotating gear (209) is meshed with the fixed barrel (202), and the eight centrifugal friction transmission blocks (214) are connected to the rotating gear (209) via a transmission belt (210).

4. The eddy current detection device for aircraft engine blades according to claim 3, characterized in that: A rotation drive motor (216) is slidably mounted on the fixed bracket (215) via a floating reset rod (218); an output shaft of the rotation drive motor (216) is fixed to the floating shaft (211); a floating reset spring (217) is surrounded by the floating reset rod (218); and two ends of the floating reset spring (217) are fixedly connected to the rotation drive motor (216) and the fixed bracket (215), respectively.

5. The eddy current detection device for aircraft engine blades according to claim 4, characterized in that: The output shaft of the rotary drive motor (216) is slidably engaged with the movable groove (2151); the clamping platform (201) and the fixed barrel (202) are slidably engaged in the working cover (101); the working cover (101) is fixedly mounted on the working platform (102); and an air inlet (1011) is provided on the working cover (101); a lifting electric cylinder (219) is fixedly mounted on the working platform (102); and a telescopic rod of the lifting electric cylinder (219) is fixed to the fixed bracket (215).

6. A method for locating damage on an aero-engine blade using the eddy current detection device for an aero-engine blade according to claim 5, characterized in that: The following steps are involved: S1, constructing and recording the moving trajectory coordinates of the probe (109), and moving the probe (109) to above the engine blade (3); S2, moving the probe (109) from the edge of the engine blade (3) to the center along the radial direction of the engine blade (3); S3, rotating engine blades (3) 2-5°; S4, moving the probe (109) from the center of the engine blade (3) to the edge along the radial direction of the engine blade (3); S5, repeating S2-S4 until the engine blade (3) rotates to 360 degrees, and then stopping the rotation of the engine blade (3); S6. Whether the voltage and impedance of the probe (109) change in S2-S5; S7. Mark the trajectory coordinates when the voltage and impedance of the probe (109) change.

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