Device and method for polishing and repairing blisk of aero-engine by using composite laser

Abstract

The invention provides a device and a method for polishing and repairing a blisk of an aero-engine by using composite laser aiming at the common problems of cracks and surface roughness in the machining process of the blisk of the aero-engine, and the device comprises a five-axis moving platform system, a 1064nm infrared laser generator system and an optical ranging system; according to the method, a six-axis composite laser polishing and repairing device is utilized, a high-precision multi-wavelength and multi-frequency-band laser scanning device is carried, continuous polishing and repairing serve as a main body, and a five-axis moving platform system, a 1064nm infrared laser generator system, an optical distance measuring device and an ultrasonic scanning and surface analysis technology are combined. Honeycomb-shaped cracks left on the surface of the blade of the blade disc through milling are successfully repaired, and the surface quality of the blade disc is remarkably improved. According to the device and method, the repairing effect is excellent, the polishing efficiency is remarkably improved, and the time needed by traditional manual polishing can be greatly shortened. In addition, the surface roughness of the bladed disc repaired through the composite laser polishing repairing method is remarkably reduced, and the influence on the flowing property of working fluid is effectively controlled. Therefore, the method has important engineering application prospects and is expected to bring remarkable method progress and economic benefits in the field of aero-engine manufacturing.

Description

Technical Field

[0001] The invention belongs to the technical field of aero-engine manufacturing and surface processing, and in particular relates to a device and a method for polishing and repairing an integral blade disk of an aero-engine by using a composite laser. Background Art

[0002] As a key component in the field of aero-engines, the integral blade disk of an aero-engine directly affects the performance and reliability of the engine. However, due to factors such as wear and corrosion, the integral blade disk often needs to be repaired to extend its service life. The polishing and repair method of aero-engine blades currently used in China is complicated and includes the following steps: first, measuring the blade damage parameters to ensure that they meet the maintenance requirements of the original equipment manufacturer. Subsequently, impurities are treated by chemical methods, and visual inspection is performed to confirm the scope of work, including polishing of the leading edge of the blade and repair of large blade patches. Next, non-destructive monitoring is performed using X-rays, and precise milling and trimming of the blades is performed using CNC machine tools. After manual polishing is completed, a second non-destructive inspection is performed, and finally, anti-wear coating and dry film lubricant are sprayed on the blade interface to complete the repair.

[0003] However, this traditional method has some challenges and shortcomings. The main problems include reliance on a lot of manual operations, such as manual polishing, which may lead to unstable repair results and consistency. The lack of application of automation technology leads to low repair efficiency and increases the risk of human error. Although X-ray non-destructive monitoring and secondary inspection are adopted, there is still room for improvement, especially the introduction of more advanced automated detection technology can help improve the quality and safety of repairs. Summary of the invention

[0004] In order to solve the problems existing in the above-mentioned prior art, the purpose of the present invention is to provide a device and method for polishing and repairing the integral blade disk of an aircraft engine using a composite laser. The device and method not only have excellent repair effects, but also significantly improve the polishing efficiency, which can greatly reduce the time required for traditional manual polishing.

[0005] In order to achieve the above purpose, the present invention adopts the following technical solution:

[0006] A device for polishing and repairing the integral blade disk of an aero-engine using a composite laser ,include Five-axis mobile platform system, 1064nm infrared laser generator system and optical ranging system;

[0007] The five-axis mobile platform system includes a first x-axis translation guide rail X1 and a second x-axis translation guide rail X2 arranged in parallel, an x-axis guide rail driving motor 3 fixed on the first x-axis translation guide rail X1 and the second x-axis translation guide rail X2, a y-axis translation guide rail 4 fixed on the first x-axis translation guide rail X1 and the second x-axis translation guide rail X2, a z-axis translation guide rail 8 fixed on the y-axis translation guide rail 4, an A-axis rotation device 9 fixed on the z-axis translation guide rail 8, a C-axis workpiece turntable 10 fixed on the A-axis rotation device 9, and a workpiece fixture 11 installed on the C-axis workpiece turntable 10;

[0008] The 1064nm infrared laser generator system includes a laser generator z-axis translation guide rail 6 fixed on a working plane, a laser platform 5 horizontally mounted on the laser generator z-axis translation guide rail 6, a 1064nm infrared laser generator 7 placed on the laser platform 5, a first 3D galvanometer module 1201 fixed on the 1064nm infrared laser generator 7, and a reflection laser detector 13 fixed on the first 3D galvanometer module 1201; the light outlet axis of the first 3D galvanometer module 1201 is aligned with the center of the C-axis workpiece turntable 10;

[0009] The optical distance measuring system includes an optical distance measuring device base 1, an optical distance measuring device 2 fixed on the optical distance measuring device base 1, and a second 3D galvanometer module 1202 connected to the optical distance measuring device 2, wherein the axis of the light outlet of the second 3D galvanometer module 1202 is aligned with the center of the C-axis workpiece turntable 10.

[0010] Preferably, the The axis of the light outlet of the second 3D galvanometer module 1202 is at an angle of 45° with the z-axis and is aligned with the center of the C-axis workpiece turntable 11, so as to accurately measure the relative coordinates of the workpiece.

[0011] Preferably, the The reflected laser detector 13 is fixed to the outside of the first 3D galvanometer module 1201 by bolts and is aligned to receive the infrared laser reflected by the workpiece, so as to accurately adjust the processing surface to the focal plane of the 1064nm infrared laser.

[0012] Preferably, the The first 3D galvanometer module 1201 is fixed to the 1064nm infrared laser generator 7 by a clamp, and the upper surface is parallel to the horizontal plane; the rest of the fixings are fixed by bolts, which is conducive to rapid positioning and improved positioning accuracy.

[0013] A method for polishing and repairing an integral blade disk of an aero-engine using a composite laser , using the above device Now, it includes the following steps:

[0014] Step 1: Scan and analyze the thin-walled areas of the intake and exhaust edges on both sides of the blades of the aircraft engine integral blade disk and the middle area of ​​the blade to clarify the damage and repair scope of the uneven surface, scratches and cracks of the integral blade disk;

[0015] Step 2: Determine the polishing range and mesh the thin-walled areas on both sides of the blade and the middle area of ​​the blade: Use a digital scanner or CAD software to convert the geometric shapes of the thin-walled areas on both sides of the blade and the middle area of ​​the blade of the integral blade disk into a three-dimensional model, and convert the surface of the three-dimensional model into discrete grid points. Determine the laser focal depth based on the grid division and adjust the grid density and accuracy, and perform grid continuity division of the surface within the laser focal depth range;

[0016] Step 3: Set the scanning path: According to the damaged sampling of the blisk surface in step 1 and the meshing in step 2, select the best laser scanning path through the laser polishing software simulation;

[0017] Step 4: Determine laser polishing repair parameters;

[0018] Step 5: Set the defocus range according to the inherent focal length parameters of the device to ensure that the vertical height error between the area to be repaired and the laser focus is within the defocus range; use the reflected laser detector 13 to measure the height of the lower surface of the first 3D galvanometer module 1201 from the surface of the workpiece to be repaired, and then control the translation of the z-axis translation guide 6 of the laser generator through the servo motor to adjust the first 3D galvanometer module 1201 to a predetermined height;

[0019] Step 6: convert the laser scanning path selected in step 3 into a digital signal, and control the first 3D galvanometer module 1201 through the DB15 interface to adjust the laser well depth;

[0020] Step 7: Adjust the z-axis translation guide rail 8 so that the surfaces to be repaired in the thin-walled areas of the inlet and outlet edges on both sides of the blade and the middle area of ​​the blade are located at the focal plane of the 1064nm infrared laser generator 7, and adjust the position of the area to be repaired through the red light preview frame outline;

[0021] Step 8: Continuous laser polishing under argon protection environment;

[0022] Step 9: Using the laser repair parameters of step 4, the 1064nm infrared laser generator system of the six-axis composite laser polishing and repair device is used to scan and polish the divided grids one by one; the 1064nm infrared laser generator system is used to repair the surface cracks in the thin-walled areas of the intake and exhaust edges on both sides of the blade and the middle area of ​​the blade, and a continuous laser beam is used, and its energy density distribution is a Gaussian-like distribution, so that the metal in the crack part and the surrounding area is melted, and the generated Marannig effect causes a fluid flow cycle from the edge of the molten pool to the center, and flows into the crack to fill the crack;

[0023] Step 10: After the first polishing repair, the thin-walled areas of the inlet and exhaust edges on both sides of the blade and the middle area of ​​the blade after the initial polishing repair are re-scanned and analyzed, and the laser repeated polishing repair parameters and polishing repair area are re-determined, and steps 1 to 9 are repeated;

[0024] Step 11: Inspection and acceptance: Conduct a comprehensive inspection on the integral blade disk after multiple laser polishing repairs to ensure that the repair effect meets the requirements.

[0025] Preferably, in step 4, according to the surface roughness information of the entire blade disk, the original crack distribution information and the polishing requirements, the laser scanning speed range is adjusted to 50mm / s-2000mm / s, the scanning interval range is 15μm-50μm, and the laser power range is 10W-300W; this can improve production efficiency and reduce processing time to obtain better surface finish and roughness.

[0026] The method for determining laser polishing repair parameters is as follows:

[0027] Energy density of continuous laser beam The distribution obeys the Gaussian distribution and satisfies the following relationship:

[0028]

[0029] Indicates the peak energy density at the center of the beam, J / cm 2 ;ω 0 is the beam waist radius, μm; r is the distance from a point in the beam to the center of the beam, μm; E p is the laser pulse energy, μJ;

[0030] At the same time, the peak energy density at the center of the beam Proportional to the pulse energy:

[0031]

[0032] Where P is the average laser power, W; f is the laser repetition frequency, kHz;

[0033] According to formula (1) and formula (3), we can get:

[0034]

[0035] When the molten pool diameter is 0 μm, let P th is the corresponding average laser power, W; is the corresponding incident laser energy density (J / cm 2 ), calculated using formula (5):

[0036]

[0037] Assuming that the diameter of the molten pool generated by the Marannier effect between the laser and the material surface is D, according to formula (1), formula (2), formula (3), formula (4) and formula (5), we can obtain:

[0038]

[0039] The crack width D' obtained by scanning in step 1 is approximately equal to the required molten pool diameter D, and is substituted into formula (6) to obtain the laser power parameter power range of 10W-300W;

[0040] Then, according to the relevant data, the viscosity of the molten metal of the blade disk sample and the gravity acceleration are obtained, and the molten metal flow rate is estimated by combining the following formula:

[0041]

[0042] v is the metal melt flow rate, g is the gravitational acceleration, r is the radius of the fluid, and η is the viscosity of the fluid; thus, the scanning speed range is determined to be 50mm / s-2000mm / s and the scanning interval range is 15μm-50μm.

[0043] Preferably, a high-precision ultrasonic three-dimensional scanner or a blue light three-dimensional detection system is used in step 1 and step 10, and combined with computer-aided design method scanning and analysis, which is conducive to more accurately determining the damage conditions and repair scope of the uneven surface, scratches, and cracks of the entire blade disk.

[0044] Preferably, in step 5, the defocus range is set to -4 mm to 4 mm according to the inherent focal length parameters of the device to ensure that the vertical height error between the area to be repaired and the laser focus is within the defocus range.

[0045] Preferably, the argon pressure in step 8 is 0.1 MPa-2 MPa, which can prevent the workpiece from being oxidized during the polishing process.

[0046] Preferably, in step 11, a comprehensive inspection is performed on the integral blade disk after multiple laser polishing repairs, including surface roughness inspection using equipment such as a lever dial indicator, and surface crack inspection using a surface analysis instrument, so as to determine whether the repair of the area to be repaired is complete.

[0047] Compared with the prior art, the present invention has the following advantages:

[0048] 1) The composite laser surface repair effect is excellent: Microscopic observation revealed that the residual honeycomb cracks from milling processing were basically completely repaired, and the crack grid was completely repaired after multiple polishing laser scanning.

[0049] 2) The six-axis composite laser polishing and repair device of the present invention is highly efficient and can improve the efficiency of traditional manual polishing by more than 4 times.

[0050] 3) Use composite laser polishing repair method: The surface quality and geometric accuracy of the entire blade disk can be improved by using continuous laser scanning polishing with different powers on the initial milling surface, so that it can be repaired to the state required by the design.

[0051] 4) Roughness after polishing and repair: The roughness of the middle area of ​​the blade perpendicular to the grain and parallel to the grain is controlled between 0.4 and 0.1 μm, and the roughness of the thin-walled areas on both sides of the blade edge is controlled between 0.4 and 0.2 μm. Compared with the initial milling blade surface roughness, it is reduced by about 9 times, which is much higher than the required roughness of the original polishing and grinding.

[0052] 5) Composite laser polishing uses the flexible effect of light and material, and basically no mechanical polishing force is generated. The thin-walled area of ​​the intake and exhaust edges is polished without deformation, eliminating burrs and uneven surfaces on the exhaust edges, reducing airflow resistance, increasing airflow speed and flow, reducing exhaust noise, and helping to increase the output power of the engine. At the same time, the mechanical polishing force acting on the thin-walled area of ​​the blade will make the thin-walled area more susceptible to factors such as vibration and stress, increasing the risk of fatigue damage of the material or affecting the flow performance of the airflow. Therefore, the use of composite laser polishing thickness has obvious advantages over the uncontrollable deformation under the action of mechanical polishing force. BRIEF DESCRIPTION OF THE DRAWINGS

[0053] Figure 1 Comparison of surface cracks on the integral blade before and after repair.

[0054] Figure 2 Schematic diagram of the object to be polished and repaired in the present invention: Schematic diagram of the overall blade disk of the polished and repaired sample.

[0055] Figure 3a and Figure 3b They are respectively a stereoscopic view and a front view of a device for polishing and repairing an integral blade disk of an aero-engine by using a composite laser according to the present invention.

[0056] Figure 4 The present invention is a flowchart of specific implementation steps. DETAILED DESCRIPTION

[0057] The present invention is further described in detail below in conjunction with the accompanying drawings and specific embodiments.

[0058] The present invention uses an aeroengine integral blade disk as an experimental object and uses a six-axis composite laser polishing and repair device to perform a polishing and repair experiment on the aeroengine integral blade disk blade. The material of the sample includes nickel-based high-temperature alloy and titanium alloy, and the surface of the sample is a milling surface. After scanning electron microscopy analysis, it was found that there were a large number of cracks on its surface (such as Figure 1 As shown, Figure 1 The left side is the scan result of the unrepaired part. It can be seen that there are many horizontal scratches and some vertical cracks on the surface. The surface cracks have the following characteristics: the crack width is 0.1μm-2μm, the crack characteristics are honeycomb distribution, and the surface cracks appear after the milling process of CNC machining. Figure 2 As shown, the integral blade disk includes a central blade disk and blades A loaded with its outer diameter, and the blade part is divided from the outside to the inside into blade tip B, thin-walled areas C on both sides of the blade intake and exhaust edges, and blade middle area D. After measurement by a roughness instrument, the surface roughness range is 0.8μm-6.4μm, and the roughness range of the sample blade middle area D is 0.8μm-1.6μm; the roughness range of the thin-walled areas C on both sides of the blade intake and exhaust edges is 1.6μm-6.4μm.

[0059] like Figure 3a and Figure 3b As shown, a device for polishing and repairing an integral blade disk of an aircraft engine using a composite laser has a working area on a horizontal plane, is provided with a five-axis mobile platform system consisting of a first x-axis translation guide X1, a second x-axis translation guide X2, a y-axis translation guide 4, a z-axis translation guide 8, an A-axis rotation device 9, a C-axis workpiece turntable 10 and a workpiece fixture 11, a 1064nm infrared laser generator system consisting of a 1064nm infrared laser generator 7, a laser generator z-axis translation guide 6, a laser platform 5, a first 3D galvanometer module 1201 and a reflection laser detector 13, and an optical ranging system: it includes an optical ranging device 2, an optical ranging device base 1 and a second 3D galvanometer module 1202.

[0060] First, the first x-axis translation guide X1 and the second x-axis translation guide X2 are fixed on the platform with bolts at a certain interval, and the x-axis guide drive motors 3 are fixed on the top of the two guide rails respectively.

[0061] Further, the y-axis translation guide rail 4 is fixed to the x-axis translation guide rails X1 and X2 by bolts, and the z-axis translation guide rail 8 is fixed to the y-axis translation guide rail 4 by bolts. Each part is driven by a servo motor.

[0062] The A-axis rotating device 9 is further fixed to the z-axis translation guide rail 8 by bolts, and the A-axis rotating device 9 is controlled to rotate by the servo motor. The C-axis workpiece turntable 10 is fixed to the A-axis rotating device 9 by bolts, and the level is adjusted. The workpiece fixture 11 is installed on the C-axis workpiece turntable 10 and is fixedly connected to the C-axis workpiece turntable 10 by bolts.

[0063] Further installation of the 1064nm infrared laser generator system: first fix the laser generator z-axis translation guide rail 6 on the working plane, install the laser platform 5 on the laser generator z-axis translation guide rail 6 and adjust it to be horizontal.

[0064] Further, the 1064nm infrared laser generator 7 is horizontally placed on the laser platform 5 and fixed by bolts. The first 3D galvanometer module 1201 and the reflected laser detector 13 are installed. The first 3D galvanometer module 1201 is fixed to the 1064nm infrared laser generator 7 by a clamp, and the upper surface is parallel to the horizontal plane. The axis of the light outlet of the first 3D galvanometer module 1201 is aligned with the center of the C-axis workpiece turntable 10. At the same time, the reflected laser detector 13 is fixed to the outside of the first 3D galvanometer module 1201 by bolts, and is aligned to receive the infrared laser reflected by the workpiece.

[0065] The optical distance measuring system is further installed: including the optical distance measuring device 2, the optical distance measuring device base 1 and the 3D galvanometer module 1202. The optical distance measuring device base 1 is first fixed on a horizontal plane with bolts, and then the optical distance measuring device 2 is mounted on the optical distance measuring device base 1 and fixed with bolts.

[0066] The second 3D galvanometer module 1202 is further connected to the optical distance measuring device 2 , and is tightened by a clamp so that the angle between the axis of the light outlet of the second 3D galvanometer module 1202 and the z-axis is adjusted to 45° and aligned with the center of the C-axis workpiece turntable 11 .

[0067] In order to repair the cracks of the above-mentioned sample and reduce the surface roughness of the sample, the present invention provides a device for polishing and repairing the integral blade disk of an aeroengine using a composite laser, and a method for composite polishing and repairing the integral blade disk of an aeroengine using a composite laser (the schematic diagram of the blade disk sample is shown in FIG. Figure 2 , the schematic diagram of the device is shown in Figure 3), such as Figure 4 As shown, it includes the following main steps:

[0068] Step 1: Scan and analyze the thin-walled area C on the intake and exhaust edges and the middle area D of the aero-engine integral blade disk: Use high-precision ultrasonic 3D scanners or blue light 3D detection systems and other equipment and combine computer-aided design technology to scan and analyze the thin-walled area C on the intake and exhaust edges and the middle area D of the blade to be repaired on both sides of the blade to be repaired, and clarify the damage conditions and repair scope of the surface unevenness, scratches, and cracks of the integral blade disk.

[0069] Step 2: Determine the polishing range and mesh the thin-walled area C on both sides of the blade intake and exhaust edges and the middle area D of the blade: Use a digital scanner or CAD software to convert the geometric shapes of the thin-walled area C on both sides of the blade intake and exhaust edges and the middle area D of the blade of the integral blade disk into a three-dimensional model, and convert the three-dimensional model surface into discrete grid points and store it in .stp format. Determine the laser focal depth based on the grid division and adjust the grid density and accuracy, and perform 3mm×3mm grid continuity division of the surface within the focal depth range.

[0070] Step 3: Set the scanning path: According to the damaged sampling of the entire blade surface in step 1 and the meshing in step 2, the best laser scanning path is selected through the laser polishing software simulation.

[0071] Step 4: Determine the laser polishing repair parameter configuration: According to the surface roughness information of the integral blade disk, the original crack distribution information and the polishing requirements, adjust the laser scanning speed range to 50mm / s-2000mm / s, the scanning interval range to 15μm-50μm, and the laser power range to 10W-300W. The method for determining the laser polishing repair parameters is as follows:

[0072] Energy density of continuous laser beam The distribution obeys the Gaussian distribution and satisfies the following relationship:

[0073]

[0074]

[0075] Indicates the peak energy density at the center of the beam, J / cm 2 ;ω 0 is the beam waist radius, μm; r is the distance from a point in the beam to the center of the beam, μm; E p is the laser pulse energy, μJ;

[0076] At the same time, the peak energy density at the center of the beam Proportional to the pulse energy:

[0077]

[0078] Where P is the average laser power, W; f is the laser repetition frequency, kHz;

[0079] According to formula (1) and formula (3), we can get:

[0080]

[0081] When the molten pool diameter is 0 μm, let P th is the corresponding average laser power, W; is the corresponding incident laser energy density (J / cm 2 ), similarly we can get:

[0082]

[0083] Assuming that the diameter of the molten pool generated by the Marannier effect between the laser and the material surface is D, according to formula (1), formula (2), formula (3), formula (4) and formula (5), we can obtain:

[0084]

[0085] The crack width D' obtained by scanning in step 1 is approximately equal to the required molten pool diameter D, and is substituted into formula (6) to obtain the laser power parameter power range of 10W-300W;

[0086] Then, according to the relevant data, the viscosity of the molten metal of the blade disk sample and the gravity acceleration are obtained, and the molten metal flow rate is estimated by combining the following formula:

[0087]

[0088] v is the metal melt flow rate, g is the gravitational acceleration, r is the radius of the fluid, and η is the viscosity of the fluid; thus, the scanning speed range is determined to be 50mm / s-2000mm / s and the scanning interval range is 15μm-50μm.

[0089] Step 5: According to the inherent focal length parameters of the device, the defocus range is set to -4mm to 4mm, ensuring that the vertical height error between the area to be repaired and the laser focus is within the defocus range. The height of the lower surface of the first 3D galvanometer module 1201 from the surface of the workpiece to be repaired is measured by the reflected laser detector 13, and then the translation of the z-axis translation guide rail 6 of the laser generator is controlled by the servo motor to adjust the first 3D galvanometer module 1201 to a predetermined height.

[0090] Step 6: Convert the laser scanning path selected in step 3 into a digital signal, and control the first 3D galvanometer module 1201 through the DB15 interface to adjust the laser well depth from the original 1-3 mm to different depths such as 10 mm, 20 mm, and 50 mm.

[0091] Step 7: Adjust the z-axis translation guide 8 so that the surfaces to be repaired in the thin-walled areas C on both sides of the blade and the middle area D of the blade are located at the focal plane of the 1064nm infrared laser generator 7, and adjust the position of the area to be repaired through the red light preview frame outline.

[0092] Step 8: Perform continuous laser polishing in an argon protection environment with an argon pressure of 0.1MPa-2MPa.

[0093] Step 9: Using the process parameters of step 4, the 1064nm infrared laser generator system of the six-axis composite laser polishing and repair device is used to scan and polish the divided grids one by one. The 1064nm infrared laser generator system is used to repair the surface cracks in the thin-walled area C on the intake and exhaust edges on both sides of the blade and the middle area B of the blade. A continuous laser beam is used, and its energy density distribution is a Gaussian distribution, so that the metal in the crack part and the surrounding area is melted, and the Marannig effect produced causes a fluid flow cycle from the edge of the molten pool to the center, flowing into the crack to fill the crack.

[0094] Step 10: After the first polishing repair, it is necessary to use high-precision ultrasonic 3D scanners or blue light 3D detection systems and other equipment again, and combine computer-aided design methods to scan and analyze the thin-walled areas C on the intake and exhaust edges of the blades and the middle area B of the blades after the initial polishing repair. Re-determine the laser repeated polishing repair parameter configuration and polishing repair area, and repeat steps 1 to 9.

[0095] Step 11: Inspection and acceptance: Conduct a comprehensive inspection on the integral blade disk after multiple laser polishing repairs, including using equipment such as a lever dial indicator to detect surface roughness, and using surface analysis instruments to detect surface cracks to ensure that the repair effect meets the requirements.

[0096] The scanning results after polishing and repair by the method of the present invention are as follows: Figure 1 As shown in the middle right part, it can be seen that after the laser polishing scan, the impurities, scratches and other defects on the original surface disappear and are repaired to the state required by the design. The service life of the entire blade disk is extended and the performance of the engine is improved, thereby improving the safety and reliability of the entire aviation field.

Claims

1. A device for polishing and repairing aircraft engine blades using composite laser , characterized in that: include Five-axis mobile platform system, 1064nm infrared laser generator system and optical ranging system; The five-axis mobile platform system comprises a first x-axis translation guide rail (X1) and a second x-axis translation guide rail (X2) arranged in parallel, an x-axis guide rail driving motor (3) respectively fixed on the first x-axis translation guide rail (X1) and the second x-axis translation guide rail (X2), a y-axis translation guide rail (4) fixed on the first x-axis translation guide rail (X1) and the second x-axis translation guide rail (X2), a z-axis translation guide rail (8) fixed on the y-axis translation guide rail (4), an A-axis rotation device (9) fixed on the z-axis translation guide rail (8), a C-axis workpiece turntable (10) fixed on the A-axis rotation device (9), and a workpiece fixture (11) installed on the C-axis workpiece turntable (10); The 1064nm infrared laser generator system comprises a laser generator z-axis translation guide rail (6) fixed on a working plane, a laser platform (5) horizontally mounted on the laser generator z-axis translation guide rail (6), a 1064nm infrared laser generator (7) placed on the laser platform (5), a first 3D galvanometer module (1201) fixed on the 1064nm infrared laser generator (7), and a reflection laser detector (13) fixed on the first 3D galvanometer module (1201); the light outlet axis of the first 3D galvanometer module (1201) is aligned with the center of the C-axis workpiece turntable (10); The optical distance measuring system comprises an optical distance measuring device base (1), an optical distance measuring device (2) fixed on the optical distance measuring device base (1), and a second 3D galvanometer module (1202) connected to the optical distance measuring device (2), wherein the axis of the light outlet of the second 3D galvanometer module (1202) is aligned with the center of the C-axis workpiece turntable (10).

2. A device for polishing and repairing an integral blade disk of an aero-engine using a composite laser according to claim 1 , characterized in that: Said The axis of the light outlet of the second 3D galvanometer module (1202) is at an angle of 45° with the z-axis and is aligned with the center of the C-axis workpiece turntable (11).

3. The device for polishing and repairing an integral blade disk of an aero-engine by using a composite laser according to claim 1 , characterized in that: Said The reflected laser detector (13) is fixed to the outside of the first 3D galvanometer module (1201) by means of bolts and is aligned to receive the infrared laser reflected by the workpiece.

4. The device for polishing and repairing an integral blade disk of an aero-engine by using a composite laser according to claim 1 , characterized in that: Said The first 3D galvanometer module (1201) is fixed to the 1064nm infrared laser generator (7) via a clamp, and the upper surface is parallel to the horizontal plane; the rest of the fixing is done by bolts.

5. A method for polishing and repairing an integral blade disk of an aero-engine using a composite laser , characterized in that: Right of adoption The device according to any one of claims 1 to 4 is implemented, comprising the following steps: Step 1: Scan and analyze the thin-walled areas of the intake and exhaust edges on both sides of the blades of the aircraft engine integral blade disk and the middle area of ​​the blade to clarify the damage and repair scope of the uneven surface, scratches and cracks of the integral blade disk; Step 2: Determine the polishing range and mesh the thin-walled areas on both sides of the blade and the middle area of ​​the blade: Use a digital scanner or CAD software to convert the geometric shapes of the thin-walled areas on both sides of the blade and the middle area of ​​the blade of the integral blade disk into a three-dimensional model, and convert the surface of the three-dimensional model into discrete grid points. Determine the laser focal depth based on the grid division and adjust the grid density and accuracy, and perform grid continuity division of the surface within the laser focal depth range; Step 3: Set the scanning path: According to the damaged sampling of the blisk surface in step 1 and the meshing in step 2, select the best laser scanning path through the laser polishing software simulation; Step 4: Determine laser polishing repair parameters: According to the surface roughness information of the integral blade disk, the original crack distribution information and the polishing requirements, adjust the laser scanning speed range to 50mm / s-2000mm / s, the scanning interval range to 15μm-50μm, and the laser power range to 10W-300W; Step 5: setting a defocus range according to the inherent focal length parameters of the device to ensure that the vertical height error between the area to be repaired and the laser focus is within the defocus range; using a reflected laser detector (13) to measure the height between the lower surface of the first 3D galvanometer module (1201) and the surface of the workpiece to be repaired, and then controlling the translation of the z-axis translation guide rail (6) of the laser generator through a servo motor to adjust the first 3D galvanometer module (1201) to a predetermined height; Step 6: convert the laser scanning path selected in step 3 into a digital signal, and control the first 3D galvanometer module (1201) through the DB15 interface to adjust the laser well depth; Step 7: Adjust the z-axis translation guide rail (8) so that the surfaces to be repaired in the thin-walled areas of the inlet and outlet edges on both sides of the blade and the middle area of ​​the blade are located at the focal plane of the 1064nm infrared laser generator (7), and adjust the position of the area to be repaired through the red light preview frame outline; Step 8: Continuous laser polishing under argon protection environment; Step 9: Using the laser repair parameters of step 4, the 1064nm infrared laser generator system of the six-axis composite laser polishing and repair device is used to scan and polish the divided grids one by one; the 1064nm infrared laser generator system is used to repair the surface cracks in the thin-walled areas of the intake and exhaust edges on both sides of the blade and the middle area of ​​the blade, and a continuous laser beam is used, and its energy density distribution is a Gaussian-like distribution, so that the metal in the crack part and the surrounding area is melted, and the generated Marannig effect causes a fluid flow cycle from the edge of the molten pool to the center, and flows into the crack to fill the crack; Step 10: After the first polishing repair, the thin-walled areas of the inlet and exhaust edges on both sides of the blade and the middle area of ​​the blade after the initial polishing repair are re-scanned and analyzed, and the laser repeated polishing repair parameters and polishing repair area are re-determined, and steps 1 to 9 are repeated; Step 11: Inspection and acceptance: Conduct a comprehensive inspection on the integral blade disk after multiple laser polishing repairs to ensure that the repair effect meets the requirements.

6. The method for polishing and repairing an integral blade disk of an aero-engine by using a composite laser according to claim 5 ,That Features include: The method for determining the laser polishing repair parameters in step 4 is as follows: Energy density of continuous laser beam The distribution obeys Gaussian distribution and satisfies the following relationship: Indicates the peak energy density at the center of the beam, J / cm 2 ; ω0 is the beam waist radius, μm; r is the distance from a point in the beam to the center of the beam, μm; E p is the laser pulse energy, μJ; At the same time, the peak energy density at the center of the beam Proportional to the pulse energy: Where P is the average laser power, W; f is the laser repetition frequency, kHz; According to formula (1) and formula (3), we can get: When the molten pool diameter is 0 μm, let P th is the corresponding average laser power, W; is the corresponding incident laser energy density, J / cm 2 , calculated using formula (5): Assuming that the diameter of the molten pool generated by the Marannier effect between the laser and the material surface is D, according to formula (1), formula (2), formula (3), formula (4) and formula (5), we can obtain: The crack width D' obtained by scanning in step 1 is approximately equal to the required molten pool diameter D, and is substituted into formula (6) to obtain the laser power parameter power range of 10W-300W; Then, according to the relevant data, the viscosity of the molten metal of the blade disk sample and the gravity acceleration are obtained, and the molten metal flow rate is estimated by combining the following formula: v is the metal melt flow rate, g is the gravitational acceleration, r is the radius of the fluid, and η is the viscosity of the fluid; thus, the scanning speed range is determined to be 50mm / s-2000mm / s and the scanning interval range is 15μm-50μm.

7. The method for polishing and repairing an aero-engine integral blade disk using a composite laser according to claim 5 ,That Features include: In step 1 and step 10, a high-precision ultrasonic 3D scanner or a blue light 3D detection system is used, and scanning and analysis are combined with a computer-aided design method.

8. The method for polishing and repairing an aero-engine integral blade disk using a composite laser according to claim 5 ,That Features include: In step 5, the defocus range is set to -4 mm to 4 mm according to the inherent focal length parameters of the device.

9. The method for polishing and repairing an integral blade disk of an aero-engine by using a composite laser according to claim 5 ,That Features include: In step 8, the argon pressure is 0.1 MPa-2 MPa.

10. The method for polishing and repairing an integral blade disk of an aero-engine by using a composite laser according to claim 5 ,That Features include: In step 11, a comprehensive inspection is performed on the integral blade disk after multiple laser polishing repairs, including surface roughness inspection using equipment such as a lever dial indicator, and surface crack inspection using a surface analysis instrument.

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