A machining method for aeroengine blisks

Abstract

The present invention provides a method for machining an aero-engine blisk, which can meet the high-precision requirements of blade profiles in the machining of integral blisks and improve the yield rate of products. In the technical solution of the present invention, first, individual blades and hubs are machined separately, and bosses for connecting the blades are made at the rim of the hub. Then, the blades are tightly pressed on the bosses at the rim of the wheel disc, and linear friction welding is used for bonding. A relatively large-sized boss needs to be reserved in the lower 1 / 3 part of the blade. Based on numerical control machining, the actual shape and position of each blade are quickly obtained through three-coordinate measurement, and the blade digital model of the transition zone is reconstructed; using the reconstructed three-coordinate model, a unique personalized NC program is generated for each blade, and program segments with different allowances are designed for each blade; during the machining process, on-machine inspection is carried out through the machine tool, measurement is carried out according to the theoretical value, the measurement error of the machine tool is determined, and the blade is appropriately machined.

Description

Technical Field

[0001] The present invention relates to the technical field of aero-engine blisk machining, and specifically to a method for machining an aero-engine blisk. Background Art

[0002] There are multiple blades on the blisk of an aero-engine. When machining the blisk of an aero-engine, linear friction welding is usually used to machine the integral blisk. Among them, when performing the linear friction welding process, it is necessary to clamp the root of the blade. Therefore, a boss needs to be set for each blade, and the blade is pressed tightly on the boss of the rim of the disk, and they are combined by linear friction welding. Then, the redundant material is removed by numerical control machining.

[0003] However, after linear friction welding, due to reasons such as welding deformation and clamping, the position and torsional angle of each blade relative to the workpiece machining reference are inconsistent, and during the machining process, deformation occurs due to the release of machining stress caused by the removal of the lower half of the material at the upper half of the blade. Eventually, the profile shape of the blade changes. At the same time, due to the limitation of the existing numerical control machining system, on-line three-coordinate measurement during the machining process cannot be realized, that is, automatic on-line detection of the machined part cannot be realized. And if the initial design theoretical value of the blade is still used for machining during the numerical control machining process, precise machining of the blade cannot be achieved. In the prior art, it is mostly through manual adjustment by technicians according to the actual situation during the machining process, but it cannot be ensured that the error can be compensated, resulting in a low yield rate of the product. Summary of the Invention

[0004] In order to solve the problem that the machining accuracy of the blades on the blisk after linear friction welding in the prior art is uncontrollable, the present invention provides a method for machining an aero-engine blisk, which can meet the high-precision requirements of the blade profile in the integral blisk machining and improve the yield rate of the product.

[0005] The technical solution of the present invention is as follows: A method for machining an aero-engine blisk, characterized in that it includes the following steps:

[0006] S1: Based on numerical control machining technology, construct a theoretical model of the whole blisk;

[0007] Based on the theoretical model, use numerical control machining equipment to machine all the individual blades and the blisk respectively, and make bosses for connecting the blades at the rim of the blisk hub;

[0008] When machining the blade, after the upper 2 / 3 part of the blade is finished by precision machining, the blade is denoted as: the blade to be processed;

[0009] S2: Press the lower part of each blade to be processed tightly against the convex seat on the rim of the disk, and bond them by linear friction welding;

[0010] S3: Denote the upper 2 / 3 part of the blade to be processed that has been finish-machined as: reference area;

[0011] Obtain the number of measurement gear points corresponding to the reference area in the theoretical model, and evenly add gear points on the basis of the original gear points. The original gear points and the newly added gear points are collectively referred to as: reference area measurement gear points;

[0012] Among them, the number of newly added gear points is at least 1 time the number of the original gear points;

[0013] S4: Use a coordinate measuring machine to conduct physical measurement on the blade to be processed;

[0014] The measurement content includes the blade profile information and position tolerance corresponding to each reference area measurement gear point in the reference area. After measurement, the blade stacking point located at the center point of the blade profile position is denoted as: basic stacking point;

[0015] S5: Measure the offset position and blade profile twist angle of the basic stacking point, denoted as: basic parameters;

[0016] S6: Denote the area to be machined in the lower 1 / 3 half section of the blade to be processed as: area to be machined;

[0017] Obtain the measurement gear points corresponding to the area to be machined in the theoretical model, denoted as: measurement gear points for area to be machined; Obtain the blade profile stacking points corresponding to each measurement gear point for area to be machined in the theoretical model, denoted as: blade profile stacking points for area to be machined;

[0018] S7: Reconfigure the blade to be processed to obtain: machining model;

[0019] Based on the basic parameters, according to the principle of linear interpolation, use the theoretical model to correct the blade profile position coordinates with the basic stacking point and the blade profile stacking points for area to be machined as the centers respectively at the positions of the reference area measurement gear points in the machined area and the measurement gear points for area to be machined in the area to be machined, so as to obtain the machining model;

[0020] Among them, the correction principle is: first translation and then rotation;

[0021] S8: Based on the coordinate measuring machine, conduct physical measurement on the blade to be processed again to obtain the offset position and blade profile twist angle of the basic stacking point, denoted as: calibration parameters;

[0022] Meanwhile, compare the processed model with the physical object of the blade to be processed, and calculate the deflection amounts of X, Y, and R corresponding to all the measurement gear points in the reference area, denoted as: calibration deflection amount;

[0023] S9: Confirm all the calibration deflection amounts;

[0024] If any of the calibration deflection amounts is greater than 0.05, use the calibration parameters as the basic parameters and loop through steps S7 - S9;

[0025] Otherwise, implement step S10;

[0026] S10: Based on the blade model corresponding to each blade in the processed model, generate a unique personalized NC program for each blade;

[0027] S11: Clamp the entire blisk onto the numerical control processing equipment, and use an on - line measuring tool to measure and correct the clamping error;

[0028] S12: Process the area to be machined for each blade based on the NC program corresponding to each blade, specifically including the following steps:

[0029] a1: Arbitrarily select a blade and set it as the first - processed blade;

[0030] Set three machining stop points within the 3 - mm area near the weld of the first - processed blade;

[0031] The machining allowances for the three machining stop points are respectively set as: 1 mm, 0.5 mm, and 0.2 mm;

[0032] Set a calibration threshold for each machining stop point;

[0033] a2: Machine the area to be machined of the first - processed blade. After machining, perform on - line measurement on the measurement values at the machining stop points to obtain: machining measurement values;

[0034] a3: Randomly select calibration detection points in the reference area of the first - processed blade, and physically measure the measurement values corresponding to the calibration detection points, denoted as: machining target values;

[0035] The calibration detection points are set within 1 mm of the weld in the reference area, and a total of six points are taken at the inner back arc, including the inlet, middle, and outlet;

[0036] a4: Confirm the difference between each machining measurement value and the corresponding machining target value, denoted as: calibration difference;

[0037] When any one of the calibration differences is greater than its corresponding calibration threshold, step a5 is implemented;

[0038] Otherwise, step a6 is implemented;

[0039] a5: Adjust the machining angle of the numerically controlled machining equipment according to the calibration difference, and loop to implement steps a2 - a4;

[0040] a6: Sequentially obtain the unprocessed blades other than the first - processed blade, denoted as: to - be - processed blades;

[0041] For the to - be - processed blades, within a 3 - mm area near the weld, set a machining stop point with a 0.5 - mm allowance; meanwhile, set a calibration threshold for the machining stop point;

[0042] a7: Machine the to - be - processed blades. After machining each blade, perform an on - line measurement on the machining stop point to obtain the corresponding machining measurement value;

[0043] a8: Randomly select calibration detection points in the reference area of the to - be - processed blades, and physically measure to obtain the machining target value;

[0044] a9: Confirm the difference between each machining measurement value and the corresponding machining target value to obtain the calibration difference;

[0045] Compare the calibration difference with the preset calibration threshold. When the calibration difference is greater than the calibration threshold, execute step a10;

[0046] Otherwise, execute step a11;

[0047] a10: Adjust the machining angle of the numerically controlled machining equipment according to the calibration difference, and for the to - be - processed blades with calibration differences greater than the calibration threshold, loop to implement steps a7 - a9;

[0048] a11: Loop to implement steps a6 - a9 until all unprocessed blades are machined.

[0049] It is further characterized in that:

[0050] In step S11, it specifically includes the following steps:

[0051] b1: Clamp the entire blisk onto the numerically controlled machining equipment. Apply an on - line measurement tool to take 2 points each for the inlet, middle, and outlet of the inner back arc of the blade in the to - be - processed area, a total of 6 points, denoted as: clamping detection points;

[0052] Online measurement is performed on the clamping detection points to obtain measurement values, denoted as: clamping measurement values;

[0053] The measurement values include: the deflection amounts of X, Y, and R corresponding to each detection point;

[0054] b2: On the processing model, find the measurement values corresponding to the clamping detection points, denoted as: target values;

[0055] b3: Confirm the difference between each clamping measurement value and the corresponding target value, denoted as: clamping error;

[0056] When any one of the clamping errors is greater than 0.05 mm, steps b1 to b3 are repeatedly implemented;

[0057] Otherwise, step S12 is executed;

[0058] Step S12 further includes the following steps:

[0059] c1: Obtain the actual machining allowance of the reference area of each blade;

[0060] c2: When programming the NC program, set the target machining allowance for the area to be machined;

[0061] Target machining allowance = actual machining allowance + 0.05;

[0062] In step a1, the three calibration thresholds corresponding to the first machined blade are respectively set to: 0.2 mm, 0.1 mm, and 0.05 mm;

[0063] In step a6, the calibration threshold corresponding to the blades other than the first machined blade is set to 0.1 mm.

[0064] A method for machining an aeroengine blisk provided by the present invention, after linear friction welding the integral blisk disk body and the blades, the blades are then finish-machined to eliminate the weld seam and the surplus; during the machining process, for each blade, the upper 2 / 3 part is first completed by finish machining to ensure compliance with the machining accuracy requirements, and then the part completed by precision machining is used as the reference area, and the actual shape and position of each blade are quickly obtained by three-coordinate measurement. The integral blisk after linear friction welding is re-simulated and configured to obtain a new machining model, ensuring that the reconfigured model is closer to the actual situation of the blisk compared with the original model, and ensuring that the accuracy of subsequent machining can be improved. During the machining process of a single blade, only the area to be machined in the lower 1 / 3 half section is used as the area to be machined. During the machining process, the machining model and the physical object are compared based on the three-coordinate model, and all measurements and machining inspections are carried out based on the area adjacent to the weld seam, ensuring that the measurement and monitoring are carried out for the affected area after linear friction welding, and thus ensuring the smooth transition between the blade and the blisk. A unique personalized NC program is generated for each independent blade in the machining model, and program segments with different allowances are set for each blade to ensure precise machining of each blade separately. By setting three machining stop points for the first machined blade, different allowances are set for each machining stop point, and one machining stop point is set for each of the other blades. For each machined blade, the physical object and the machining model are compared based on the machining stop point to obtain the calibration difference value, and then the calibration difference value is compared with the preset calibration threshold value. When the calibration difference value is greater than the calibration threshold value, the machining angle of the numerical control machining equipment is adjusted, and the actual analysis of the machining accuracy of the blade is carried out; at the same time, it is ensured that the adjustment of the equipment during the machining of the previous blade can be applied to the machining of the subsequent blades, and at the same time, with as few measurement and adjustment times as possible, it is ensured that the adjustment of the numerical control machining equipment can solve the problem of different degrees of deformation between each blade. Based on the technical solution of the present application, for an integral blisk with different degrees of deformation of each blade, high-precision machining of the blades of the integral blisk can be realized, and the yield rate of the product can be improved. Description of the Drawings

[0065] Figure 1 is the flowchart of the method for machining an aeroengine integral blisk of the present application;

[0066] Figure 2 is a schematic diagram of using a three-coordinate measuring machine to measure the physical object of the blade to be processed;

[0067] Figure 3 is an embodiment of the schematic diagram of the measurement gear line;

[0068] Figure 4 is an embodiment of the schematic diagram of the three-coordinate measurement result report and statistics;

[0069] Figure 5An embodiment of a schematic diagram for changing the position of the blade profile line centered on the blade stacking point;

[0070] Figure 6 A schematic diagram of on - line inspection of a machine tool;

[0071] Figure 7 A schematic diagram for setting the position of the stop point;

[0072] Figure 8 A schematic diagram of the milling machining area according to the program;

[0073] Figure 9 An embodiment of the parameters of the machining stop point of the first - processed blade. Specific implementation mode

[0074] As Figure 1 shown, the present invention includes a method for machining an aero - engine blisk, which comprises the following steps.

[0075] S1: Based on numerical control machining technology, construct a theoretical model of the whole blisk;

[0076] Based on the theoretical model, use numerical control machining equipment to machine all individual blades and the blisk respectively, and make bosses for connecting the blades at the rim of the blisk hub;

[0077] When machining the blade, after the upper 2 / 3 part of the blade is finished by precision machining, the blade is denoted as: the blade to be processed.

[0078] S2: Press each blade to be processed tightly on the boss at the rim of the disk, and combine them by linear friction welding.

[0079] S3: Denote the already precision - machined upper 2 / 3 part of the blade to be processed as: the reference area;

[0080] Obtain the number of measurement gear points corresponding to the reference area in the theoretical model, uniformly increase the gear points on the basis of the original gear points, and collectively call the original gear points and the newly added gear points: the reference area measurement gear points;

[0081] Among them, the number of newly added gear points is at least 1 times the number of the original gear points.

[0082] In this embodiment, the gear line of a pair of the finally obtained reference area measurement gear points is as Figure 3 shown.

[0083] S4: As Figure 2 shown, use a coordinate measuring machine to conduct physical measurement on the blade to be processed;

[0084] The measurement content includes the blade profile information and positional tolerance corresponding to each measurement position point in the reference area. After measurement, the blade stacking point located at the center point of the blade position is denoted as: the basic stacking point.

[0085] In specific implementation, a coordinate measuring machine is used to detect the blade profile of the specified measurement positions. The blade profile information and positional tolerance corresponding to each measurement position in the reference area are obtained through the measurement method of sweeping (taking countless points) the blade. The center of the blade position is the blade stacking point. In this embodiment, the coordinate measuring result report and statistical schematic diagram are as Figure 4 shown. After measurement based on the blade contour line, the X, Y, R values and the corresponding position height in the "initial positional tolerance" are extracted from the measured data, which is the physical measurement result of the blade to be processed.

[0086] S5: Measure the offset position and blade twist angle of the basic stacking point, denoted as: basic parameters.

[0087] S6: Denote the area to be processed in the lower 1 / 3 half section of the blade to be processed as: the area to be processed;

[0088] Obtain the measurement position points corresponding to the area to be processed in the theoretical model, denoted as: the measurement position points to be processed; obtain the blade stacking points corresponding to each measurement position point to be processed in the theoretical model, denoted as: the blade stacking points to be processed. In specific implementation, the schematic diagram of changing the position of the blade contour line with the blade stacking point as the center is as Figure 5 shown.

[0089] In the technical solution of the present application, the upper 2 / 3 part of the blade is first completed by precision machining, and then the already precision-machined reference area and the area to be processed in the lower 1 / 3 half section of the blade to be processed are strictly separated for processing. Compared with the prior art method of processing the blade as a whole, in the technical solution of the present application, when processing the area to be processed, the tool will not cause any damage to the already precision-machined reference area, effectively avoiding the occurrence of accidental injury problems during the processing, and can effectively improve the yield rate of the product.

[0090] S7: Based on the basic parameters, according to the principle of linear interpolation, use the theoretical model in the 3D modeling software. At the positions of the measurement position points in the reference area of the processed area and the measurement position points to be processed in the area to be processed, respectively, with the basic stacking point and the blade stacking points to be processed as the centers, first translate and then rotate to reconfigure the blade to be processed, and obtain: the processing model.

[0091] S8: Based on the coordinate measuring machine, physically measure the blade to be processed again to obtain the offset positions of the basic stacking points and the blade profile twist angles, denoted as: calibration parameters; meanwhile, compare the processing model with the physical object of the blade to be processed, and calculate the deflection amounts of X (shift), Y (shift), and R (rotation) corresponding to all the measurement positions in the reference area, denoted as: calibration deflections. Among them, X (shift) and Y (shift) are the coordinates in the coordinate system of the processing model (or workpiece); R (rotation) is the blade profile twist angle.

[0092] S9: Confirm all the calibration deflections;

[0093] If any one of the calibration deflections is greater than 0.05, use the calibration parameters as the basic parameters and loop to execute steps S7 - S9;

[0094] Otherwise, implement step S10.

[0095] S10: Based on the blade model corresponding to each blade in the processing model, generate a unique personalized NC (Numerical Control) program for each blade.

[0096] S11: Clamp the entire blisk onto the CNC machining equipment, and use the on - line measuring tool to measure and correct the clamping error. As Figure 6 shown, it is a schematic diagram of on - line inspection of the machine tool.

[0097] Regarding the method for correcting the clamping error of the machine tool, it specifically includes the following steps:

[0098] b1: Clamp the entire blisk onto the CNC machining equipment, and use the on - line measuring tool to take 2 points each for the inlet, middle, and outlet of the inner and back arcs of the blade in the area to be processed, with a total of 6 points, denoted as: clamping inspection points;

[0099] Conduct on - line measurement on the clamping inspection points to obtain the measured values, denoted as: clamping measured values;

[0100] The measured values include: the deflection amounts of X, Y, and R corresponding to each inspection point;

[0101] b2: On the processing model, find the measured values corresponding to the clamping inspection points, denoted as: target values;

[0102] b3: Confirm the difference between each clamping measured value and the corresponding target value, denoted as: clamping error;

[0103] When any one of the clamping errors is greater than 0.05 mm, loop to implement steps b1 - b3;

[0104] Otherwise, execute step S12.

[0105] S12: Machine the to-be-machined areas of each blade based on the NC program corresponding to each blade, specifically including the following steps.

[0106] a1: Arbitrarily select a blade and set it as the first-machined blade.

[0107] Within the area of 3 mm near the weld of the first-machined blade, set three machining stop points; the machining allowances of the three machining stop points are respectively set as: 1 mm, 0.5 mm, and 0.2 mm; set a calibration threshold for each machining stop point: 0.2 mm, 0.1 mm, and 0.05 mm. As Figure 7 shown, it is a schematic diagram of setting the stop point positions.

[0108] a2: Machine the to-be-machined area of the first-machined blade. After machining, conduct on-line measurement of the measured values of the machining stop points to obtain: machining measured values; as Figure 8 shown, it is a schematic diagram of the milling machining area according to the NC program.

[0109] a3: Randomly select calibration inspection points in the reference area of the first-machined blade, and physically measure the measured values corresponding to the calibration inspection points, denoted as: machining target values;

[0110] The calibration inspection points are set within 1 mm of the weld in the reference area, and a total of six points are taken at the inlet, middle, and outlet of the inner and back arcs respectively;

[0111] In this embodiment, the parameters of the machining stop points of the first-machined blade are detailed as shown in the table in Figure 9 .

[0112] a4: Confirm the difference between each machining measured value and the corresponding machining target value, denoted as: calibration difference;

[0113] When there is any calibration difference greater than its corresponding calibration threshold, implement step a5;

[0114] Otherwise, implement step a6;

[0115] a5: Adjust the machining angle of the numerical control machining equipment according to the calibration difference, and repeatedly implement steps a2 - a4;

[0116] a6: Obtain one by one the un-machined blades other than the first-machined blade, denoted as: to-be-machined blades;

[0117] In step a6, the calibration threshold corresponding to the blades other than the first-machined blade is set as 0.1 mm.

[0118] For the to-be-machined blades, within the area of 3 mm near the weld, set a machining stop point with a 0.5 mm allowance; at the same time, set a calibration threshold for the machining stop point;

[0119] a7: Process the blade to be processed. For each processed blade, conduct an on-line measurement of the processing stop point to obtain the corresponding processing measurement value.

[0120] a8: Randomly select calibration detection points in the reference area of the blade to be processed, and physically measure to obtain the processing target value.

[0121] a9: Confirm the difference between each processing measurement value and the corresponding processing target value to obtain the calibration difference.

[0122] Compare the calibration difference with the preset calibration threshold. When the calibration difference is greater than the calibration threshold, execute step a10.

[0123] Otherwise, execute step a11.

[0124] For each blade to be processed other than the first processed blade, a total of six points, namely the inlet, middle, and outlet points, are taken on the inner back arc for the calibration detection points. When comparing, the height difference between the processing stop point and the calibration detection point is not allowed to exceed 0.1 mm.

[0125] a10: Adjust the processing angle of the numerical control processing equipment according to the calibration difference, and for the blades to be processed with the calibration difference greater than the calibration threshold, repeatedly execute steps a7 - a9.

[0126] a11: Repeatedly execute steps a6 - a9 until all unprocessed blades are processed.

[0127] The following steps are further included in step S12:

[0128] c1: Obtain the actual processing allowance of the reference area of each blade.

[0129] c2: Set the target processing allowance for the area to be processed during NC program preparation.

[0130] Target processing allowance = actual processing allowance + 0.05.

[0131] Taking the reference area as the standard, set the target processing allowance for the area to be processed to ensure a more natural transition between the area to be processed and the reference area after processing.

[0132] After adopting the technical solution of the present invention, first, the single blade and the hub are processed separately, and the convex seats for connecting the blades have been made at the rim of the hub. Then, the blade is pressed tightly on the convex seat at the rim of the wheel disc, and linear friction welding is used for combination. In order to ensure that the blade parts can be welded to the disc body within the range of rigid support, a convex platform with a relatively large size needs to be reserved in the lower 1 / 3 part of the blade; then, based on the numerical control machining method, the actual shape and position of each blade are quickly obtained through three-coordinate measurement; according to the measurement data, the blade digital model in the transition zone is reconstructed; using the reconstructed three-coordinate model, a dedicated programming method is designed to generate a unique personalized NC program for each blade, and program segments with different allowances are designed for each blade; during the machining process, online inspection of the machine tool is carried out, measurement is carried out according to the theoretical value, and the measurement error of the machine tool is determined; the blade is appropriately machined, multiple machining stop points are set according to the program segments with different allowances, and the accuracy of the blade is actually analyzed to eliminate the weld seam and the allowance, and finally the smooth transition of the blade profile is realized. At the same time, the problem of accidental damage to the machined part by the tool is avoided, and the yield rate of the product is greatly improved. The technical solution of this application is particularly applicable to application scenarios with limited adaptability and the ability to process blades.

Claims

1. A method for machining an aeroengine blisk, characterized in that, It includes the following steps: S1: Based on numerical control machining technology, construct a theoretical model of the integral blisk; Based on the theoretical model, use numerical control machining equipment to machine all individual blades and the blisk respectively, and make convex seats for connecting the blades at the rim of the blisk hub; When machining the blades, after the upper 2 / 3 part of the blades is finished by precision machining, the blades are denoted as: blades to be processed; S2: Press each of the blades to be processed tightly on the convex seats at the rim of the disk, and bond them by linear friction welding; S3: Denote the already precision-machined upper 2 / 3 part of the blades to be processed as: reference area; Obtain the number of measurement gear points corresponding to the reference area in the theoretical model, and uniformly add gear points on the basis of the original gear points. The original gear points and the newly added gear points are collectively referred to as: reference area measurement gear points; Among them, the number of newly added gear points is at least 1 times the number of the original gear points; S4: Use a coordinate measuring machine to conduct physical measurement on the blades to be processed; The measurement content includes the blade profile information and position accuracy corresponding to each reference area measurement gear point in the reference area. After measurement, the blade stacking point located at the center point of the blade profile position is denoted as: basic stacking point; S5: Measure the offset position and blade profile twist angle of the basic stacking point, and denote them as: basic parameters; S6: Denote the area to be machined in the lower 1 / 3 half section of the blades to be processed as: area to be machined; Obtain the measurement gear points corresponding to the area to be machined in the theoretical model, and denote them as: measurement gear points to be machined; obtain the blade stacking points corresponding to each measurement gear point to be machined in the theoretical model, and denote them as: blade stacking points to be machined; S7: Reconfigure the blades to be processed to obtain: machining model; Based on the basic parameters, according to the principle of linear interpolation, use the theoretical model to correct the blade profile position coordinates respectively with the basic stacking point and the blade stacking points to be machined as the centers at the positions of the reference area measurement gear points in the already machined area and the measurement gear points to be machined in the area to be machined, so as to obtain the machining model; Among them, the correction principle is: first translation and then rotation; S8: Based on the coordinate measuring machine, conduct physical measurement on the blades to be processed again to obtain the offset position and blade profile twist angle of the basic stacking point, and denote them as: correction parameters; Meanwhile, compare the machining model with the physical object of the blades to be processed, and calculate the deflection amounts of X, Y, and R corresponding to all the reference area measurement gear points, and denote them as: correction deflection amounts; S9: Confirm all the correction deflection amounts; If any one of the correction deflection amounts is greater than 0.05, use the correction parameters as the basic parameters, and loop to execute steps S7 - S9; Otherwise, implement step S10; S10: Based on the blade models corresponding to each blade in the machining model, generate a unique personalized NC program for each blade; S11: Clamp the integral blisk on the numerical control machining equipment, and use an on-line measuring tool to measure and correct the clamping error; S12: Based on the NC program corresponding to each blade, the to-be-processed area of ​​each blade is processed, specifically comprising the following steps: a1: select any blade and set it as: first processing blade; Three processing stop points are set within a 3mm area near the weld of the first processed blade; The machining allowances of the three machining stop points are set to: 1 mm, 0.5 mm and 0.2 mm respectively; Setting a calibration threshold for each of the processing stop points; a2: Processing the to-be-processed area of ​​the first-processed blade, and after the processing is completed, online measuring the measured value of the processing stop point to obtain: processing measurement value; a3: randomly selecting calibration detection points in the reference area of ​​the first processed blade, and physically measuring to obtain the measurement values ​​corresponding to the calibration detection points, which are recorded as processing target values; The calibration detection points are set within 1 mm of the weld in the reference area, and the inner back arc is taken at the entry, middle and exit of a total of six points; a4: confirming the difference between each of the processing measurement values ​​and the corresponding processing target value, recorded as: calibration difference; When any of the calibration difference values ​​is greater than the corresponding calibration threshold value, performing step a5; Otherwise, implement step a6; a5: adjusting the machining angle of the numerical control machining equipment according to the calibration difference, and cyclically implementing steps a2 to a4; a6: Obtain unprocessed blades other than the first processed blade one by one, and record them as: blades to be processed; For the blade to be processed, a processing stop point with a margin of 0.5 mm is set in a 3 mm area near the weld; at the same time, a calibration threshold is set for the processing stop point; a7: Processing the blade to be processed, and after each blade is processed, online measuring the processing stop point to obtain the corresponding processing measurement value; a8: randomly selecting the calibration detection points in the reference area of ​​the blade to be processed, and obtaining the processing target value by actual measurement; a9: confirming the difference between each of the processing measurement values ​​and the corresponding processing target value to obtain the calibration difference; Compare the calibration difference with the preset calibration threshold, and when the calibration difference is greater than the calibration threshold, execute step a10; Otherwise, execute step a11; a10: adjusting the machining angle of the numerical control machining equipment according to the calibration difference, and cyclically implementing steps a7 to a9 for the blade to be machined whose calibration difference is greater than the calibration threshold; a11: Repeat steps a6 to a9 until all unprocessed blades are processed.

2. The aeroengine blisk machining method according to claim 1, characterized in that: In step S11, the details The following steps are involved: b1: Clamp the blade disk as a whole onto the CNC machining equipment, and use the online measurement tool to take two points at the in, middle and out of the inner back arc of the blade in the area to be machined, for a total of six points, which are recorded as clamping detection points; The clamping detection point is measured online to obtain a measurement value, which is recorded as: clamping measurement value; The measured values ​​include: the deflection amounts of X, Y, and R corresponding to each detection point; b2: On the machining model, find the measurement value corresponding to the clamping detection point, denoted as: target value; b3: Confirm the difference between each clamping measurement value and the corresponding target value, denoted as: clamping error; When there is any clamping error greater than 0.05 mm, loop through steps b1 - b3; Otherwise, execute step S12.

3. The aeroengine blisk machining method according to claim 1, characterized in that: Step S12 also includes the following steps: c1: Obtain the actual machining allowance of the reference area of each blade; c2: When programming the NC program, set the target machining allowance for the area to be machined; Target machining allowance = actual machining allowance + 0.

05.

4. The aero-engine blisk machining method according to claim 1, characterized in that: In step a1, the three calibration thresholds corresponding to the first machined blade are set to: 0.2 mm, 0.1 mm, and 0.05 mm respectively.

5. A method for machining an aeroengine blisk according to claim 1, characterized in that: In step a6, the calibration threshold corresponding to the blades other than the first machined blade is set to 0.1 mm.

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