CN115740978A - Machining method for blade disc of aircraft engine - Google Patents
Machining method for blade disc of aircraft engine Download PDFInfo
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Abstract
The invention provides a machining method of an aircraft engine blade disc, which can meet the high-precision requirement of a blade profile of a blade in the machining of a blisk and improve the yield of products. In the technical scheme of the invention, firstly, the single blade and the hub are respectively processed, and the boss for connecting the blade is formed at the rim of the hub, then, the blade is tightly pressed on the boss of the rim of the wheel disc, and the blade and the hub are combined by adopting a linear friction welding mode. A boss with a larger size needs to be reserved on a 1/3 part below the blade, the actual shape and position of each blade are quickly obtained through three-coordinate measurement based on a numerical control machining mode, and a transition region blade digital-analog is reconstructed; generating a unique personalized NC program for each blade by using the reconstructed three-coordinate model, and designing program segments with different margins for each blade; and in the machining process, the machine tool is used for detecting on line, measuring is carried out according to a theoretical value, the measuring error of the machine tool is determined, and the blade is machined properly.
Description
Technical Field
The invention relates to the technical field of engine blade disc machining, in particular to a machining method of an aero-engine blade disc.
Background
A plurality of blades are arranged on a blade disc of an aircraft engine, and when the blade disc of the aircraft engine is machined, a Linear friction welding (Linear welding) is generally adopted to machine the integral blade disc. When the linear friction welding process is carried out, the root of each blade needs to be clamped, so that each blade needs to be provided with a boss, the blades are tightly pressed on the bosses of the rim of the wheel disc, and the linear friction welding mode is adopted for combination. And then, finishing the removal of the redundant materials in a numerical control machining mode.
However, after linear friction welding, the position and the torsion angle of each blade relative to the workpiece processing reference are inconsistent due to welding deformation, clamping and the like, and the deformation caused by the release of processing stress is generated due to the removal of the material of the lower half section at the upper half section of the blade in the processing process, so that the profile shape of the blade is changed finally, and meanwhile, due to the limitation of the existing numerical control processing system, the three-coordinate online measurement in the processing process cannot be realized, namely, the automatic online detection of the processed part cannot be realized. And if the initial design theoretical value of the blade is still used for continuous processing in the numerical control processing process, the blade cannot be accurately processed. In the prior art, manual adjustment is mostly performed by technicians in the processing process according to actual conditions, but errors cannot be made up, and the yield of products is low.
Disclosure of Invention
In order to solve the problem that the machining precision of blades on a blade disc subjected to linear friction welding in the prior art is uncontrollable, the invention provides a machining method of an aero-engine blade disc, which can meet the high-precision requirement of blade profiles of blades in the machining of a blisk and improve the yield of products.
The technical scheme of the invention is as follows: the machining method of the blade disc of the aircraft engine is characterized by comprising the following steps of:
s1: constructing a theoretical model of the integral blade disc based on a numerical control machining technology;
based on the theoretical model, respectively processing all single blades and blade discs by using numerical control processing equipment, and making convex seats for connecting the blades at the wheel edges of the hubs of the blade discs;
when the blade is machined, after the upper 2/3 part of the blade is finished by adopting a finish machining mode, the blade is recorded as follows: a blade to be treated;
s2: pressing the lower part of each blade to be processed on a boss of a rim of the wheel disc, and combining the blades in a linear friction welding mode;
s3: and recording the upper 2/3 part of the blade to be processed, which is finished in a finish machining mode, as: a reference region;
acquiring the number of measurement gear points corresponding to the reference area in the theoretical model, uniformly adding gear points on the basis of the original gear points, and collectively referring the original gear points and the newly added gear points as follows: a reference region measurement file site;
wherein, the number of the newly added gear positions is at least 1 time of the number of the original gear positions;
s4: using a three-coordinate measuring machine to carry out object measurement on the blade to be processed;
the measurement content comprises the profile information and the position degree of each blade corresponding to the measurement gear point of the reference area in the reference area, and the blade profile stacking point located at the center point of the blade profile position after measurement is recorded as: a base stacking point;
s5: measuring the offset position and profile twist angle of the base stacking point, recorded as: a base parameter;
s6: recording the area to be processed of 1/3 half section below the blade to be processed as: a region to be processed;
obtaining a measurement file site corresponding to the region to be processed in the theoretical model, and recording as follows: a measurement file site to be processed; acquiring a leaf profile stacking point corresponding to each gear point to be processed and measured in the theoretical model, and recording as follows: stacking points of the leaf profiles to be processed;
s7: reconfiguring the blade to be treated to obtain: processing the model;
based on the basic parameters and according to a linear interpolation principle, using the theoretical model to correct the blade profile position coordinates on the positions of the reference region measurement gear positions of the machined region and the to-be-machined measurement gear positions of the to-be-machined region by respectively taking the basic stacking points and the to-be-machined blade profile stacking points as centers to obtain the machining model;
wherein, the correction principle is as follows: firstly, translating and then rotating;
s8: and based on a three-coordinate machine, carrying out real object measurement on the blade to be processed again to obtain the offset position and the blade profile torsion angle of the basic stacking point, and recording as follows: correcting parameters;
meanwhile, comparing the machining model with the real object of the blade to be processed, calculating to obtain the deflection amounts of X, Y and R corresponding to all the reference region measuring gear points, and recording as follows: correcting the deflection amount;
s9: confirming all of the corrected deflection amounts;
if any one of the corrected deflection amounts is larger than 0.05, using the correction parameter as a basic parameter, and circularly executing the steps S7-S9;
otherwise, implementing the step S10;
s10: generating a unique personalized NC program for each blade based on the blade model corresponding to each blade in the machining model;
s11: integrally clamping the blade disc on the numerical control machining equipment, and measuring and correcting a clamping error by using an online measuring tool;
s12: processing the area to be processed of each blade based on the NC program corresponding to each blade, specifically comprising the following steps:
a1: any one blade is set as follows: firstly, processing the blade;
setting three processing stop points in a 3mm area near a welding seam of the first processed blade;
the machining allowance of the three machining stopping points is respectively set as: 1mm, 0.5mm and 0.2mm;
setting a threshold value for calibration for each machining stop point;
a2: processing the area to be processed of the first processed blade, and after the processing is finished, performing online measurement on the measured value of the processing stop point to obtain: processing the measured value;
a3: randomly extracting detection points for calibration in the reference area of the first processed blade, and obtaining a measurement value corresponding to the detection points for calibration through real object measurement, and recording the measurement value as: processing the target value;
the detection points for calibration are arranged in the position of a welding line of the reference area within 1mm, and the inner back arc is respectively taken in, in and out at six positions in total;
a4: and confirming the difference value between each machining measured value and the corresponding machining target value, and recording the difference value as: a difference value for calibration;
when any one of the calibration difference values is larger than the corresponding calibration threshold value, implementing the step a5;
otherwise, implementing the step a6;
a5: adjusting the machining angle of the numerical control machining equipment according to the difference value for calibration, and circularly implementing the steps a 2-a 4;
a6: and acquiring unprocessed blades except the first processed blade one by one, and recording as follows: a blade to be processed;
setting a machining stop point with a margin of 0.5mm in a 3mm area near a welding seam for the blade to be machined; meanwhile, a threshold value for calibration is set for the machining stop point;
a7: processing the blade to be processed, and measuring the processing stop point on line to obtain the corresponding processing measured value when one blade is processed;
a8: randomly extracting the detection points for calibration in the reference area of the blade to be machined, and performing real object measurement to obtain the machining target value;
a9: confirming the difference value between each machining measured value and the corresponding machining target value to obtain the difference value for calibration;
comparing the difference value for calibration with a preset threshold value for calibration, and executing step a10 when the difference value for calibration is greater than the threshold value for calibration;
otherwise, executing step a11;
a10: adjusting the machining angle of the numerical control machining equipment according to the difference value for calibration, and circularly implementing the steps a 7-a 9 on the blade to be machined of which the difference value for calibration is larger than the threshold value for calibration;
a11: and c, circularly implementing the steps a 6-a 9 until all the unprocessed blades are processed.
It is further characterized in that:
in step S11, the following steps are included in detail:
b1: integrally clamping a blade disc on the numerical control machining equipment, applying an online measuring tool, respectively taking in, taking out and taking out the inner and back arcs of the blade in the area to be machined, wherein 2 points of each type count 6 points, and recording the points as follows: clamping the detection points;
and carrying out on-line measurement on the clamping detection points to obtain a measured value, and recording as follows: clamping the measured value;
the measured values include: the deflection of X, Y and R corresponding to each detection point;
b2: and finding the measured value corresponding to the clamping detection point on the machining model, and recording the measured value as: a target value;
b3: and confirming the difference value between each clamping measured value and the corresponding target value, and recording the difference value as: clamping errors;
when any one clamping error is larger than 0.05mm, circularly implementing the steps b 1-b 3;
otherwise, executing step S12;
the step S12 further includes the steps of:
c1: acquiring the actual machining allowance of the reference area of each blade;
c2: when the NC program is programmed, setting a target machining allowance for the area to be machined;
target machining allowance = actual machining allowance +0.05;
in step a1, the three calibration thresholds corresponding to the first machined blade are respectively set as: 0.2mm, 0.1mm and 0.05mm;
in step a6, the calibration threshold value corresponding to the blade other than the first processed blade is set to 0.1mm.
According to the machining method of the aero-engine blade disc, after the integral blade disc body and the blades are subjected to linear friction welding, the blades are subjected to finish machining, and welding seams and allowance are eliminated; in the machining process, the last 2/3 part of each blade is finished by adopting a finish machining mode, the machining precision requirement is ensured to be met, then the part finished by finish machining is used as a reference area, the actual shape and position of each blade are quickly obtained by three-coordinate measurement, the integral blade disc subjected to linear friction welding after the linear friction welding is re-simulated and configured, a new machining model is obtained, the reconstructed model is ensured to be closer to the actual condition of the blade disc compared with the original model, and the accuracy of subsequent machining is ensured to be improved. In the machining process of a single blade, only the area needing to be machined in the next 1/3 half section is used as an area to be machined, in the machining process, the machining model and a real object are compared based on a three-coordinate model, all measurement and machining detection are carried out based on the adjacent area of a welding seam, the measurement and monitoring are ensured to be carried out on the affected area after linear friction welding, and then smooth switching of the blade and a blade disc is ensured to be realized. Generating a unique personalized NC program for each independent blade in the machining model, and setting and designing program segments with different margins for each blade to ensure that each blade is accurately machined. Setting three machining stopping points for the first machined blade, setting different margins for each machining stopping point, respectively setting one machining stopping point for other blades, comparing a real object with a machining model based on the machining stopping points to obtain a difference value for calibration when each blade is machined, comparing a preset threshold value for calibration of the difference value for calibration, adjusting the machining angle of the numerical control machining equipment when the difference value for calibration is greater than the threshold value for calibration, and actually analyzing the machining accuracy of the blade; meanwhile, the adjustment of the equipment in the processing of the front blade can be ensured along with the processing of the subsequent blade, and the problem that the deformation of each blade in different degrees exists can be solved by adjusting the numerical control processing equipment with the measurement and adjustment times as few as possible. Based on this application technical scheme, there is the blisk of the deformation of different degrees to every blade, can realize the high accuracy processing of blisk blade, improves the yields of product.
Drawings
FIG. 1 is a flow chart of an aircraft engine blisk processing method of the present application;
FIG. 2 is a schematic illustration of a physical measurement of a blade to be processed using a three coordinate measuring machine;
FIG. 3 is an embodiment of a measurement block line schematic;
FIG. 4 is an embodiment of a three-coordinate measurement report and statistics diagram;
FIG. 5 is an embodiment of a schematic representation of a profile contour line position change centered on a stacking point of a profile;
FIG. 6 is a schematic view of on-line detection of a machine tool;
FIG. 7 is a schematic view of a setting stop point position;
FIG. 8 is a schematic view of a programmed milling area;
FIG. 9 is an example of parameters for a machining dwell point for first machining a blade.
Detailed Description
As shown in fig. 1, the present invention includes a method of machining an aircraft engine blisk, comprising the following steps.
S1: constructing a theoretical model of the integral blade disc based on a numerical control machining technology;
based on a theoretical model, respectively processing all single blades and blade discs by using numerical control processing equipment, and making convex seats for connecting the blades at the wheel edges of the hubs of the blade discs;
when the blade is machined, after the upper 2/3 part of the blade is finished by adopting a finish machining mode, the blade is recorded as follows: and (4) treating the blade to be treated.
S2: and pressing the lower part of each blade to be processed on a boss of the rim of the wheel disc, and combining the blades by adopting a linear friction welding mode.
S3: the upper 2/3 part of the blade to be treated, which has been finished, is recorded as: a reference region;
acquiring the number of measurement gear points corresponding to a reference area in a theoretical model, uniformly adding gear points on the basis of original gear points, and collectively referring the original gear points and the newly added gear points as follows: a reference region measurement file site;
wherein, the number of the newly added gear positions is at least 1 time of the number of the original gear positions.
In this embodiment, the obtained reference region measures the shift position line of one shift position point pair, as shown in fig. 3.
S4: as shown in fig. 2, a three-coordinate measuring machine is used for measuring the object of the blade to be processed;
the measurement content comprises leaf profile information and position degree corresponding to each reference region measurement gear point in the reference region, and the leaf profile stacking point located at the central point of the leaf profile position after measurement is recorded as: a base stacking point.
In the specific implementation, a three-coordinate measuring machine is used for detecting the blade profile of a specified measuring gear, and blade profile information and position degree corresponding to each measuring gear in a reference region are obtained in a blade scanning (taking countless points) measuring mode, wherein the center of the blade profile position is a blade profile stacking point. In this embodiment, a three-coordinate measurement result report and a statistical diagram are shown in fig. 4. After measurement is carried out based on the blade profile, values of X, Y and R in the initial position degree and corresponding gear height are extracted based on data obtained through measurement, and the values are the result of real object measurement of the blade to be processed.
S5: the offset position and profile twist angle of the base stacking point are measured and recorded as: and (4) basic parameters.
S6: and recording the area to be processed in 1/3 half section below the blade to be processed as follows: a region to be processed;
obtaining a measurement file site corresponding to a region to be processed in the theoretical model, and recording as follows: measuring file sites to be processed; acquiring a blade profile stacking point corresponding to each gear point to be processed and measured in the theoretical model, and recording as follows: and (5) stacking points of the leaf profiles to be processed. In specific implementation, a schematic diagram of changing the position of the profile contour line by taking the profile stacking point as a center is shown in fig. 5.
According to the technical scheme, the finish machining mode is firstly adopted for the upper 2/3 part of the blade, and then the finish machined reference area and the area to be machined of the lower 1/3 half section of the blade to be machined are strictly separated for machining. Compared with the prior art, the method for machining the blade as a whole has the advantages that according to the technical scheme, when the to-be-machined area is processed, the cutter cannot damage the finish-machined reference area, the problem of accidental injury in the machining process is effectively avoided, and the yield of products can be effectively improved.
S7: based on basic parameters and according to a linear interpolation principle, a theoretical model is used in three-dimensional modeling software, a basic stacking point and a to-be-processed blade profile stacking point are respectively taken as centers on a measuring gear point position of a reference area of a processed area and a to-be-processed measuring gear point of a to-be-processed area, translation and rotation are carried out, and a to-be-processed blade is reconfigured to obtain: and (6) processing the model.
S8: based on the three-coordinate machine, the object measurement is carried out on the blade to be processed again, the offset position and the blade profile torsion angle of the basic stacking point are obtained, and the values are recorded as follows: correcting parameters; meanwhile, comparing the machining model with the real object of the blade to be processed, calculating and obtaining the deflection quantity of X (shift), Y (shift) and R (rotation) corresponding to all the reference region measuring gear points, and recording the deflection quantity as follows: the amount of deflection is corrected. Wherein, X (shift) and Y (shift) are coordinates in a coordinate system of the processing model (or the workpiece); r (rotation) is the leaf-shaped torsion angle.
S9: confirming all corrected deflection amounts;
if any one correction deflection amount is larger than 0.05, using the correction parameter as a basic parameter, and circularly executing the steps S7-S9;
otherwise, step S10 is implemented.
S10: a unique, personalized NC (Numerical Control) program is generated for each leaf based on the leaf model corresponding to each leaf in the machining model.
S11: and integrally clamping the blade disc on a numerical control machining device, and measuring and correcting a clamping error by using an online measuring tool. Fig. 6 is a schematic diagram of on-line detection of a machine tool.
The method for correcting the clamping error of the machine tool comprises the following steps in detail:
b1: clamping the whole blade disc on a numerical control machining device, applying an online measuring tool, respectively taking in, centering and out the inner and back arcs of the blade in a region to be machined, wherein 2 points of each type are counted as 6 points, and recording the points as follows: clamping the detection points;
and (3) carrying out online measurement on the clamping detection points to obtain a measured value, and recording the measured value as: clamping a measured value;
the measured values include: deflection amounts of X, Y and R corresponding to each detection point;
b2: on the machining model, finding a measured value corresponding to the clamping detection point, and recording as follows: a target value;
b3: and (3) determining the difference value between each clamping measured value and the corresponding target value, and recording as follows: clamping errors;
when any clamping error is larger than 0.05mm, circularly implementing the steps b 1-b 3;
otherwise, step S12 is executed.
S12: and machining the area to be machined of each blade based on the NC program corresponding to each blade.
a1: any one blade is set as follows: firstly, processing a blade;
setting three processing stop points in a 3mm area near a welding seam of a first processed blade; the machining allowance of the three machining stopping points is respectively set as: 1mm, 0.5mm and 0.2mm; setting a threshold value for calibration for each machining stop point respectively: 0.2mm, 0.1mm and 0.05mm. As shown in fig. 7, the schematic diagram is for setting the stop point position.
a2: processing the area to be processed of the first processed blade, and after the processing is finished, performing online measurement on the measured value of the processing stop point to obtain: processing the measured value; fig. 8 is a schematic diagram illustrating the milling of the machining area according to the NC program.
a3: in the reference area of the first processed blade, randomly extracting detection points for calibration, and obtaining a measurement value corresponding to the detection points for calibration through real object measurement, and recording the measurement value as: processing the target value;
the detection points for calibration are arranged in 1mm of the welding seam of the reference area, and the inner back arc is respectively taken in, in and out of six positions;
in the present embodiment, the parameters of the machining stop point of the first machined blade are detailed in the table shown in fig. 9.
a4: the difference between each machining measurement and the corresponding machining target is determined and recorded as: a difference value for calibration;
when any one of the calibration difference values is larger than the corresponding calibration threshold value, implementing the step a5;
otherwise, implementing the step a6;
a5: adjusting the machining angle of the numerical control machining equipment according to the difference value for calibration, and circularly implementing the steps a 2-a 4;
a6: obtaining unprocessed blades except the first processed blade one by one, and recording as follows: a blade to be processed;
in step a6, the calibration threshold value corresponding to the blade other than the first processed blade is set to 0.1mm.
Setting a machining stop point with a margin of 0.5mm in a 3mm area near a welding seam of a blade to be machined; meanwhile, a threshold value for calibration is set for the machining stop point;
a7: processing the blade to be processed, and performing online measurement on a processing stop point to obtain a corresponding processing measured value when one blade is processed;
a8: randomly extracting detection points for calibration in a reference area of the blade to be processed, and carrying out real object measurement to obtain a processing target value;
a9: confirming the difference value between each processing measured value and the corresponding processing target value to obtain a difference value for calibration;
comparing the difference value for calibration with a preset threshold value for calibration, and executing the step a10 when the difference value for calibration is larger than the threshold value for calibration;
otherwise, executing step a11;
and for each blade to be processed except for the first processed blade, the detection point for calibration is respectively taken in, in and out of six positions in total in the inner and back arcs, and during comparison, the height difference between the processing stop point and the detection point for calibration is not allowed to exceed 0.1mm.
a10: adjusting the machining angle of the numerical control machining equipment according to the difference value for calibration, and circularly implementing the steps a 7-a 9 on the blade to be machined of which the difference value for calibration is greater than the threshold value for calibration;
a11: and c, circularly implementing the steps a 6-a 9 until all the unprocessed blades are processed.
The step S12 further includes the steps of:
c1: acquiring the actual machining allowance of the reference area of each blade;
c2: when an NC program is compiled, setting target machining allowance for a region to be machined;
target machining allowance = actual machining allowance +0.05.
And setting a target machining allowance for the to-be-machined area by taking the reference area as a standard, and ensuring that the to-be-machined area is more natural to transition from the reference area after machining is finished.
After the technical scheme of the invention is used, firstly, the single blade and the hub are respectively processed, and the boss for connecting the blade is already made at the rim of the hub, then, the blade is tightly pressed on the boss at the rim of the wheel disc, and the combination is carried out by adopting a linear friction welding mode. In order to ensure that the blade part is welded with the disk body within the rigid supportable range, a boss with larger size needs to be reserved at 1/3 part below the blade; then, rapidly acquiring the actual shape and position of each blade through three-coordinate measurement based on a numerical control machining mode; reconstructing a blade digital model in a transition area according to the measured data; using the reconstructed three-coordinate model to design a special programming mode, generating a unique personalized NC program for each blade, and designing program segments with different margins for each blade; in the machining process, the machine tool is used for detecting on line, measuring is carried out according to a theoretical value, and the machine tool measuring error is determined; the method comprises the steps of carrying out appropriate processing on the blade, carrying out a plurality of processing stop points according to program segments with different margins, carrying out actual analysis on the accuracy of the blade, eliminating welding seams and margins, and finally realizing smooth transition of the profile of the blade. Meanwhile, the problem that the machined part is accidentally damaged by the cutter is avoided, and the yield of the product is greatly improved. The technical scheme is particularly suitable for application scenes with limited self-adaptive capacity and blade processing capacity.
Claims (5)
1. The machining method of the blade disc of the aircraft engine is characterized by comprising the following steps of:
s1: constructing a theoretical model of the integral blade disc based on a numerical control machining technology;
based on the theoretical model, respectively processing all single blades and blade discs by using numerical control processing equipment, and making convex seats for connecting the blades at the wheel edges of the hubs of the blade discs;
when the blade is machined, after the upper 2/3 part of the blade is finished by adopting a finish machining mode, the blade is recorded as follows: a leaf to be treated;
s2: pressing the lower part of each blade to be processed on a boss of a rim of the wheel disc, and combining the blades in a linear friction welding mode;
s3: and recording the upper 2/3 part of the blade to be processed, which is finished in a finish machining mode, as: a reference region;
acquiring the number of measurement gear points corresponding to the reference area in the theoretical model, uniformly adding gear points on the basis of the original gear points, and collectively referring the original gear points and the newly added gear points as follows: a reference region measurement file site;
wherein, the number of the newly added gear positions is at least 1 time of the number of the original gear positions;
s4: using a three-coordinate measuring machine to carry out object measurement on the blade to be processed;
the measurement content comprises the profile information and the position degree of the blade profile corresponding to each reference region measurement gear point in the reference region, and the blade profile stacking point located at the central point of the blade profile position after measurement is recorded as: a base stacking point;
s5: measuring the offset position and profile twist angle of the base stacking point, recorded as: a base parameter;
s6: recording the area to be processed of 1/3 half section below the blade to be processed as: a region to be processed;
obtaining a measurement file site corresponding to the region to be processed in the theoretical model, and recording as follows: a measurement file site to be processed; acquiring a leaf profile stacking point corresponding to each gear point to be processed and measured in the theoretical model, and recording as follows: stacking points of the leaf profiles to be processed;
s7: reconfiguring the blade to be processed to obtain: processing the model;
based on the basic parameters and according to a linear interpolation principle, using the theoretical model to correct the blade profile position coordinates on the positions of the reference region measurement gear positions of the machined region and the to-be-machined measurement gear positions of the to-be-machined region by respectively taking the basic stacking points and the to-be-machined blade profile stacking points as centers to obtain the machining model;
wherein, the correction principle is as follows: firstly, translating and then rotating;
s8: and based on a three-coordinate machine, carrying out real object measurement on the blade to be processed again to obtain the offset position and the blade profile torsion angle of the basic stacking point, and recording as follows: correcting parameters;
meanwhile, comparing the machining model with the real object of the blade to be processed, calculating the deflection of X, Y and R corresponding to all the reference region measuring gear points, and recording the deflection as follows: correcting the deflection amount;
s9: confirming all of the corrected deflection amounts;
if any one of the corrected deflection amounts is larger than 0.05, using the correction parameter as a basic parameter, and circularly executing the steps S7-S9;
otherwise, implementing the step S10;
s10: generating a unique personalized NC program for each blade based on the blade model corresponding to each blade in the machining model;
s11: clamping the whole blade disc on the numerical control machining equipment, and measuring and correcting a clamping error by using an online measuring tool;
s12: processing the area to be processed of each blade based on the NC program corresponding to each blade, specifically comprising the following steps:
a1: any one blade is set as follows: firstly, processing the blade;
setting three processing stop points in a 3mm area near a welding seam of the first processed blade;
the machining allowance of the three machining stopping points is respectively set as: 1mm, 0.5mm and 0.2mm;
setting a threshold value for calibration for each machining stop point;
a2: processing the area to be processed of the first processed blade, and after the processing is finished, performing online measurement on the measured value of the processing stop point to obtain: processing the measured value;
a3: randomly extracting detection points for calibration in the reference area of the first processed blade, and obtaining a measurement value corresponding to the detection points for calibration through real object measurement, and recording the measurement value as follows: processing the target value;
the detection points for calibration are arranged in the position of a welding line of the reference area within 1mm, and the inner back arc is respectively taken in, in and out at six positions in total;
a4: and confirming the difference value between each machining measured value and the corresponding machining target value, and recording the difference value as: a difference value for calibration;
when any one of the calibration difference values is larger than the corresponding calibration threshold value, implementing the step a5;
otherwise, implementing the step a6;
a5: adjusting the machining angle of the numerical control machining equipment according to the difference value for calibration, and circularly implementing the steps a 2-a 4;
a6: obtaining unprocessed blades except the first processed blade one by one, and recording as: a blade to be processed;
setting a machining stop point with a margin of 0.5mm for the blade to be machined in a region which is 3mm near a welding seam; meanwhile, a threshold value for calibration is set for the machining stop point;
a7: processing the blade to be processed, and performing online measurement on the processing stop point to obtain a corresponding processing measured value when one blade is processed;
a8: randomly extracting the detection points for calibration in the reference area of the blade to be processed, and obtaining the processing target value through real object measurement;
a9: confirming the difference value between each machining measured value and the corresponding machining target value to obtain the difference value for calibration;
comparing the difference value for calibration with a preset threshold value for calibration, and executing step a10 when the difference value for calibration is greater than the threshold value for calibration;
otherwise, executing step a11;
a10: adjusting the machining angle of the numerical control machining equipment according to the difference value for calibration, and circularly implementing the steps a 7-a 9 on the blade to be machined of which the difference value for calibration is larger than the threshold value for calibration;
a11: and c, circularly implementing the steps a 6-a 9 until all the unprocessed blades are processed.
2. The aircraft engine blisk machining method as recited in claim 1, characterized in that: in step S11, the method specifically includes the steps of:
b1: integrally clamping a blade disc on the numerical control machining equipment, applying an online measuring tool, respectively taking in, taking out and taking out the inner and back arcs of the blade in the area to be machined, wherein 2 points of each type are 6 points in total, and recording the points as follows: clamping the detection points;
and carrying out on-line measurement on the clamping detection points to obtain a measured value, and recording as follows: clamping the measured value;
the measured values include: deflection amounts of X, Y and R corresponding to each detection point;
b2: and finding the measured value corresponding to the clamping detection point on the machining model, and recording the measured value as: a target value;
b3: and confirming the difference value between each clamping measured value and the corresponding target value, and recording the difference value as: clamping errors;
when any one clamping error is larger than 0.05mm, the steps b 1-b 3 are carried out in a circulating mode;
otherwise, step S12 is executed.
3. The aircraft engine blisk machining method as recited in claim 1, characterized in that: the step S12 further includes the steps of:
c1: acquiring the actual machining allowance of the reference area of each blade;
c2: when the NC program is compiled, setting target machining allowance for the area to be machined;
target machining allowance = actual machining allowance +0.05.
4. The aircraft engine blisk machining method as claimed in claim 1, wherein: in step a1, the three calibration thresholds corresponding to the first machined blade are respectively set as: 0.2mm, 0.1mm and 0.05mm.
5. The aircraft engine blisk machining method as claimed in claim 1, wherein: in step a6, the calibration threshold value corresponding to the blade other than the first processed blade is set to 0.1mm.
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN116787300A (en) * | 2023-07-01 | 2023-09-22 | 广州中誉精密模具有限公司 | Polishing control method, device, equipment and storage medium for car lamp mold |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN116787300A (en) * | 2023-07-01 | 2023-09-22 | 广州中誉精密模具有限公司 | Polishing control method, device, equipment and storage medium for car lamp mold |
| CN116787300B (en) * | 2023-07-01 | 2024-04-02 | 广州中誉精密模具有限公司 | Polishing control method, device, equipment and storage medium for car lamp mold |
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