A processing method for laser additive manufacturing of integral blade disk

Abstract

This application provides a laser additive manufacturing method for an integral blade disk, belonging to the field of aero-engine technology. The method includes setting reflective marking points on an integral blade disk blank; scanning the integral blade disk blank using optical scanning technology based on the reflective marking points to obtain an optical scanning model; comparing the optical scanning model with a theoretical model of the integral blade disk to obtain a first allowance distribution; fitting the first allowance distribution to obtain a uniform second allowance distribution; determining the machining angle of the integral blade disk; judging the rigidity of the blade and determining the milling strategy; based on the second allowance distribution, the machining angle and the milling strategy, using the optical scanning model to perform cutting simulation and milling the integral blade disk blank; and inspecting and compensating the allowance of the integral blade disk blade obtained after milling. The processing solution of this application improves the processing efficiency of parts and the blade qualification rate.

Description

Technical Field

[0001] The present application relates to the field of aero-engine technology, and in particular to a method for processing an integral blade disk by laser additive manufacturing. Background Art

[0002] The integral blade disk is a new type of structural component designed to meet the needs of high-performance aircraft engines. Its structural model is shown in the attached figure. Figure 1 As shown, the engine rotor blades and disc are integrated, eliminating the tenons, grooves, and locking devices typically found in traditional connections. This reduces structural weight and part count, avoids airflow loss from the tenons, improves aerodynamic efficiency, and significantly simplifies the engine structure. The blisk is primarily manufactured using CNC machining, electrolytic machining, electrochemical machining, and linear friction welding. CNC machining technology is the preferred choice for blisk production during the development phase of new products due to its advantages, including rapid response, simplified tooling, and relatively high process maturity.

[0003] The current industry-leading "die forging + machining" manufacturing process suffers from low material utilization, long production cycles, and poor microstructure and performance consistency. It also struggles to meet future manufacturing demands for high-performance metal matrix composite blisks and gradient blisks, becoming a significant bottleneck hindering the development of advanced aeroengines. Laser additive manufacturing (AM), with its outstanding manufacturing advantages, offers an effective approach for cost-effective, short-cycle manufacturing of large, complex, and critical titanium alloy components. However, a deep understanding of fundamental morphological control issues, such as precision and defect control, and microstructure and performance regulation, remains lacking. Unlike forged blanks, AM blisk blanks present several machining challenges: 1. The stock distribution of AM blanks is uneven. 2. The blades are already preliminarily formed, requiring the determination of their angular coordinate system before machining. 3. Unlike forged blanks, blade milling cannot utilize the current "simultaneous roughing and finishing, one-to-two" process. Therefore, conducting fundamental research on AM manufacturing technology for high-performance titanium alloy blisks is crucial for advancing my country's high-thrust-to-weight ratio aeroengine manufacturing capabilities. Summary of the Invention

[0004] In view of this, an embodiment of the present application provides a processing method for laser additive manufacturing of an integral blade disk, which at least partially solves the processing difficulties of laser additive manufacturing of an integral blade disk in the prior art.

[0005] The present application provides a method for laser additive manufacturing of an integral blade disk, comprising:

[0006] Set reflective marking points on the blisk blank;

[0007] Scanning the blisk blank using optical scanning technology based on the reflective marking points to obtain an optical scanning model;

[0008] Comparing the optical scanning model with a theoretical model of the blisk to obtain a first margin distribution of the blisk blank;

[0009] Fitting the first margin distribution to obtain a uniform second margin distribution;

[0010] Determine the machining angle of the blisk blades;

[0011] determining the rigidity of the blade and determining a milling strategy based on the rigidity of the blade;

[0012] Based on the second stock distribution, the machining angle, and the milling strategy, performing cutting simulation using the optical scanning model, and milling the blisk blank;

[0013] The blisk blades obtained after milling are inspected and the allowances are compensated.

[0014] According to a specific implementation method of an embodiment of the present application, the reflective marking points are randomly distributed, the spacing between each two reflective marking points ranges from 30mm to 250mm, and the distance between the reflective marking points and the edge of the integral blade disk blank is greater than 2mm.

[0015] According to a specific implementation of an embodiment of the present application, determining the machining angle of the blisk blades includes:

[0016] Use the machine tool online measurement system to measure the allowance of the basin at the tip of the blade and the back of the blade at the tip of the blade. By analyzing the allowance distribution of the basin at the tip of the blade and the back of the blade at the tip of the blade, the processing angle of the integral blade disc blade is determined.

[0017] According to a specific implementation of the embodiment of the present application, the blade margin deviation is obtained by analyzing the margin distribution of the basin at the tip of the blade and the back at the tip of the blade.

[0018] When the optical scanning model is used for cutting simulation, a minimum collision clearance between the tool and the part is set based on the blade allowance deviation.

[0019] According to a specific implementation method of an embodiment of the present application, the rigidity of the blade is judged by the ratio of the total length of the integral blade of the impeller to the blade thickness. When the ratio of the total length of the integral blade of the impeller to the blade thickness is greater than 30, the milling strategy of rough and fine synchronous milling is adopted; when the ratio of the total length of the integral blade of the impeller to the blade thickness is less than 30, the milling strategy of spiral milling is adopted.

[0020] According to a specific implementation of the embodiment of the present application, the testing of the blisk blades obtained after milling includes:

[0021] The contour of the first piece of the blisk blade is detected using a machine tool online measurement system, and the contour detection is performed by a point fitting method.

[0022] According to a specific implementation method of an embodiment of the present application, in the contour detection, the sampling point intervals at the leading edge and the trailing edge of the blade are less than or equal to 0.2 mm, the sampling point intervals at the back of the blade are less than or equal to 2 mm, and the detection section intervals of each blade range from 5 mm to 10 mm.

[0023] According to a specific implementation method of the embodiment of the present application, in the contour detection, the number of points sampled at the back of the blade is greater than or equal to 20, and the number of points sampled at the leading edge and the trailing edge of the blade is greater than or equal to 5.

[0024] According to a specific implementation of the embodiment of the present application, the margin compensation includes:

[0025] When the contour degree at the blade tip is greater than that at the blade root, machining allowance compensation is performed from the blade tip to the blade root;

[0026] When the profile at the tip of the blade is smaller than the profile at the root, machining allowance compensation is performed from the root to the tip.

[0027] Beneficial effects

[0028] The laser additive manufacturing (AM) blisk machining method disclosed in the embodiments of the present application includes performing stock analysis on the AM blisk, performing blade angular fitting on the AM blisk, using a novel blade milling strategy for rough and finish machining of the AM blisk blades, and using blade machining allowance compensation technology to compensate for the blade finish contour. Optical scanning technology is used to determine the AM blisk blank model, which is then compared with a theoretical model. After fitting, the allowance distribution is accurately determined, preventing overcutting of parts, reducing on-site commissioning time, and improving part machining efficiency. Furthermore, applying the optical scanning model to blade cutting simulation allows for more accurate determination of the blade cutting state, preventing overcutting and tool interference. Furthermore, based on the blade inspection results, allowance compensation is performed on the blades to improve the blade qualification rate. Advances in AM blisk machining technology have significantly reduced on-site commissioning and machining time, indirectly improving production efficiency and reducing production costs. BRIEF DESCRIPTION OF THE DRAWINGS

[0029] In order to more clearly illustrate the technical solutions of the embodiments of the present application, the following briefly introduces the drawings required for use in the embodiments. Obviously, the drawings described below are only some embodiments of the present application. For ordinary technicians in this field, other drawings can be obtained based on these drawings without any creative work.

[0030] Figure 1 A structural model of an aero-engine blisk according to an embodiment of the present invention;

[0031] Figure 2 Schematic diagram of simultaneous rough and fine milling of blisk blades according to an embodiment of the present invention;

[0032] Figure 3 is a schematic diagram of spiral milling of a blisk blade according to an embodiment of the present invention;

[0033] Figure 4 is a margin compensation direction when the profile at the blade tip is greater than the profile at the blade root according to an embodiment of the present invention;

[0034] Figure 5 is a margin compensation direction when the profile at the blade tip is smaller than the profile at the blade root according to an embodiment of the present invention;

[0035] Figure 6 is a schematic structural diagram of a blisk blade according to an embodiment of the present invention;

[0036] Figure 7 An optical scanning model of an additively manufactured blisk blank according to an embodiment of the present invention;

[0037] Figure 8 A model comparison model of an additively manufactured blisk blank according to an embodiment of the present invention;

[0038] Figure 9 is a second margin distribution diagram after fitting according to an embodiment of the present invention;

[0039] Figure 10 is a diagram of angular measurement results according to an embodiment of the present invention;

[0040] Figure 11 2. FIG. 1 is a diagram showing a tip detection result of a blisk blade according to an embodiment of the present invention;

[0041] Figure 12 FIG. 1 is a diagram showing the blade root detection result of a blisk blade according to an embodiment of the present invention. DETAILED DESCRIPTION

[0042] The embodiments of the present application are described in detail below with reference to the accompanying drawings.

[0043] The following describes the embodiments of the present application through specific examples, and those skilled in the art can easily understand other advantages and effects of the present application from the contents disclosed in this specification. Obviously, the described embodiments are only a part of the embodiments of the present application, rather than all the embodiments. The present application can also be implemented or applied through other different specific embodiments, and the details in this specification can also be modified or changed in various ways based on different viewpoints and applications without departing from the spirit of the present application. It should be noted that, in the absence of conflict, the features in the following embodiments and embodiments can be combined with each other. Based on the embodiments in the present application, all other embodiments obtained by those of ordinary skill in the art without making creative work are within the scope of protection of this application.

[0044] It should be noted that various aspects of the embodiments within the scope of the appended claims are described below. It should be apparent that the aspects described herein can be embodied in a wide variety of forms, and any specific structure and / or function described herein is merely illustrative. Based on this application, it should be understood by those skilled in the art that an aspect described herein can be implemented independently of any other aspect, and two or more of these aspects can be combined in various ways. For example, any number of aspects described herein can be used to implement an apparatus and / or practice a method. In addition, other structures and / or functionalities other than one or more of the aspects described herein can be used to implement this apparatus and / or practice this method.

[0045] It should also be noted that the illustrations provided in the following embodiments are only schematic illustrations of the basic concept of the present application. The illustrations only show components related to the present application and are not drawn according to the number, shape and size of components in actual implementation. In actual implementation, the type, quantity and proportion of each component can be changed at will, and the component layout type may also be more complicated.

[0046] Additionally, in the following description, specific details are provided to provide a thorough understanding of the examples. However, one skilled in the art will appreciate that the aspects described can be practiced without these specific details.

[0047] An embodiment of the present application provides a method for processing an integral blade disk by laser additive manufacturing, which is described in detail below with reference to the accompanying drawings.

[0048] In one embodiment, a laser additive manufacturing method for a blisk includes the following steps:

[0049] Step S11, setting reflective marking points on the blisk blank;

[0050] Step S12: Scanning the blisk blank using optical scanning technology based on the reflective marking points to obtain an optical scanning model;

[0051] Step S13: comparing the optical scanning model with a theoretical model of the blisk to obtain a first margin distribution of the blisk blank;

[0052] Step S14: fitting the first margin distribution to obtain a uniform second margin distribution;

[0053] Step S15, determining the machining angle of the blisk blades;

[0054] Step S16: judging the rigidity of the blade, and determining the milling strategy according to the rigidity of the blade;

[0055] Step S17: Based on the second allowance distribution, the machining angle, and the milling strategy, performing cutting simulation using the optical scanning model, and milling the blisk blank;

[0056] Step S18: inspecting and compensating for the milled blisk blades.

[0057] In one embodiment, the reflective marking dots are randomly distributed, avoiding a regular pattern. The spacing between any two reflective marking dots ranges from 30mm to 250mm, and the distance between a reflective marking dot and the edge of the blisk blank is greater than 2mm. For workpieces with fewer features and less curvature variation, the distance between reflective marking dots can be increased, with a maximum of 250mm. For workpieces with more features and greater curvature variation, the distance between reflective marking dots can be decreased, with a minimum of 30mm.

[0058] By using this method of affixing reflective marking points, the accuracy of the optical scanning model of the additively manufactured integral blade disk blank can be controlled within 0.2mm, which is sufficient to meet the subsequent allowance fitting distribution confirmation and cutting simulation accuracy requirements.

[0059] In one embodiment, Geomagic Control software was used to compare the optical scan model with the theoretical model of the blisk, and the blisk blank margins were fitted using Geomagic Control. This fitting process accurately determined the blisk blank margin distribution, preventing overcutting, reducing on-site commissioning time, and improving part processing efficiency.

[0060] In one embodiment, determining the machining angle of the blisk blades includes:

[0061] The machine tool's online measurement system measures the allowances of the blade tip basin and blade tip back. By analyzing the allowance distribution of these two areas, the machining angle of the blisk blade is determined. Furthermore, by analyzing the allowance distribution of these two areas, the deviation between the actual and theoretical blade shape—the blade allowance deviation—can be determined. This conclusion can be used in blisk milling simulations.

[0062] When forged blisk blanks are received, the blades are not yet formed, and the blade angular orientation can be arbitrary. Unlike forged blanks, additively manufactured blisks are already formed upon receipt, requiring the blade angular orientation to be determined before blade processing. In this embodiment, online measurement is used to analyze the allowances of the blade's base and back, accurately determining the blade's angular position and avoiding blank shorting or excessive milling removal deviations during blade milling.

[0063] In one embodiment, the rigidity of the blade is determined by the ratio of the total length of the blade of the integral blade disk to the blade thickness. When the ratio of the total length of the blade of the integral blade disk to the blade thickness is greater than 30, it is determined that the rigidity of the blade is poor, and the milling strategy of rough and fine synchronous milling is adopted. The milling route is referenced. Figure 2 As shown, rough milling is performed first and then fine milling; when the ratio of the total length of the blade of the integral blisk to the blade thickness is less than 30, it is judged that the rigidity of the blade is good, and the spiral milling strategy is adopted. The milling route is referenced Figure 3 As shown. In this embodiment, the milling strategies of "spiral milling" and "coarse and fine synchronization" are used to replace the "one-to-two" milling strategy widely used on forgings, and the "spiral milling" and "coarse and fine synchronization" milling strategies are used differently according to the rigidity of the blades to achieve efficient processing of the blades. The "one-to-two" processing method is a blade milling method specially developed for the integral blade disk of the forging blank. This method is to groove the blade spacers during the rough processing of the blades so that there is still a blank between every two blades. Then, during the blade finishing process, the blank between the blades and the blade finishing are milled and removed synchronously. In this way, the blank between the blades is used to provide rigidity for the blades, which can achieve the purpose of high-precision and high-efficiency milling. However, there is no blank between the blades of the additively manufactured integral blade disk, so the "one-to-two" process strategy cannot be used.

[0064] In one embodiment, the blades of an additively manufactured blisk have already been initially formed. The blade stock distribution is extremely uneven, and the blade shape is extremely irregular. Cutting simulation is performed using an ".STL" file outputted from optical scanning to obtain the most realistic cutting state and avoid blade overcutting and tool collision. Applying the optical scanning model to the blade cutting simulation allows for more accurate blade cutting state, avoiding blade overcutting and tool interference. After the cutting simulation, the blisk blank is milled.

[0065] Specifically, by analyzing the allowance distribution of the basin at the tip of the blade and the back at the tip of the blade, the blade allowance deviation is obtained. When the optical scanning model is used for cutting simulation, the minimum collision clearance between the tool and the part is set based on the blade allowance deviation. In other words, in the process of cutting simulation, sufficient safety margin (minimum collision clearance) must be reserved. The method for determining the safety margin is: blade allowance deviation + model accuracy + tool safety distance, where the blade allowance deviation can be obtained by online measurement of the machine tool; the model accuracy is related to the optical scanning accuracy. Through the above steps, the model accuracy of the optical scanning can be controlled at 0.2mm; the tool safety distance is the machining gap between the tool and the machined part during the milling process, which is generally 0.1mm. It should be noted that there is no special limitation on the model accuracy and tool safety distance here, and they can be adjusted to appropriate values ​​according to actual conditions.

[0066] Different from forgings, the blade allowance of additively manufactured blanks is unevenly distributed, and the consistency between blades is poor, so the blade allowance deviation is large. For example, when making blanks for additively manufactured integral blade disks, the blanks are made according to the allowance of 3mm. However, due to process limitations and part deformation, the actual allowance of the blank may be greater than 3mm. In this way, the distance between the blades (the space through which the tool passes) will be reduced. The amount of reduction is the blade allowance deviation, which is the actual detection allowance - theoretical allowance. In order to prevent the tool from colliding with the part during the processing and to achieve safe processing, the blade allowance deviation needs to be calculated into the safety margin.

[0067] In one embodiment, the testing of the blisk blades obtained after milling includes:

[0068] The contour of the first piece of the blisk blade is detected using a machine tool online measurement system, and the contour detection is performed by a point fitting method.

[0069] Specifically, in the contour detection, the intervals between sampling points at the leading edge and trailing edge of the blade are less than or equal to 0.2 mm, the intervals between sampling points at the back of the blade are less than or equal to 2 mm, and the intervals between the detection sections of each blade are in the range of 5 mm to 10 mm. Figure 6When testing the contour, the sampling point spacing is set mainly because the blade contour is evaluated by using software to draw lines at the measurement points. The smaller the spacing between points, the closer the line drawing accuracy is to the actual blade contour. In this embodiment, the sampling point spacing of the leading and trailing edges is much smaller than the spacing of the back of the basin. This is because the curvature of the back of the basin contour does not change significantly, while the curvature of the leading and trailing edge curved surface changes much more than that of the blade back. Therefore, in order to increase the accuracy of the contour evaluation, the sampling points on the leading and trailing edges should be denser than those on the back of the basin.

[0070] Specifically, in the contour detection, the number of sampling points at the back of the blade is greater than or equal to 20, and the number of sampling points at the leading edge and the trailing edge of the blade is greater than or equal to 5.

[0071] Before making allowance compensation for the blades based on the test results, the test results can be analyzed first. The blade profile test of the integral blade disk is prone to three types: the first is that the dimensions of the blades are evenly distributed, and the difference in the contour dimensions of the blade tip and the blade root is within 0.01mm; the second is that the dimension at the blade tip is larger than the dimension at the blade root; the third is that the dimension at the blade tip is smaller than the dimension at the blade root. The first situation is the test result under relatively ideal conditions; the second situation occurs when the blade is deflected under the action of cutting force, resulting in an increase in the blade profile. Because the rigidity of the blade tip is weaker than that of the blade bottom, the deflection at the blade tip is greater than that at the blade bottom; the third situation occurs because the tool wears during the blade processing process, which causes the blade profile at the blade root to be greater than the blade profile at the blade tip. The inconsistent blade dimensions during the actual processing process may be the result of the combined effect of the above-mentioned multiple situations.

[0072] In one embodiment, the margin compensation includes:

[0073] When the contour of the blade tip is greater than that of the blade root, the machining allowance compensation is performed from the blade tip to the blade root. Figure 4 As shown; when the contour degree at the tip of the blade is smaller than the contour degree at the root, the machining allowance compensation is performed from the root to the tip, referring to Figure 5 According to the inspection results of the blades, the blade margin compensation can be performed to improve the blade qualification rate.

[0074] The following example uses a certain type of aircraft engine integral blade blank as an example. The material is TC17, and the blank is an additively manufactured printed part. Its blade length is 92mm, the maximum blade thickness is about 4.5mm, and the minimum gap between blades is 22mm.

[0075] Step S21: Affix reflective markings to the additively manufactured blisk blank. Reflective markings are applied to the blisk blank's blades, spokes, drum, and other curved surfaces. The spacing between reflective markings is approximately 30 mm, and the spacing between markings on the blisk blank's end faces is 100 mm.

[0076] Step S22: Scan the additively manufactured blisk blank using optical scanning technology and output the model in “.STL” format. The scanned model is as follows: Figure 7 shown.

[0077] Step S23: Use Geomagic Control software to compare the optical scanning model and the theoretical model of the part to determine the first margin distribution of each part of the additively manufactured blisk blank. The comparison results are as follows: Figure 8 shown.

[0078] Step S24: Use Geomagic Control software to fit the first allowance distribution of the part blank to obtain a uniform second allowance distribution. The fitting result is as follows: Figure 9 As shown in the figure, it can be seen that after fitting, the maximum and minimum allowances are both located at the tip of the blade, which are 0.9mm and -1.55mm respectively, and are distributed in a point-to-point manner. For the surface where the machining reference is located, the maximum allowance is +0.5mm and the minimum is -0.8mm, which is also distributed in a point-to-point manner.

[0079] Step S25, determine the machining angle of the blade of the integral blade disk. Use the machine tool on-machine measurement system to measure the blade angle. The measurement results are as follows: Figure 10 As shown, the measured minimum blade profile is 3.2847mm and the maximum is 8.2731mm. After coordinate system correction, the minimum blade profile is 4.7874mm and the maximum is 6.5597mm. The coordinate system correction amount is X0.494314mm, Y-1.886041mm, and the angular correction is -3.8388E-6mm. The theoretical blade margin is 4.5mm, so the blade margin deviation = 6.5597-4.5 = 2.597mm.

[0080] Step S26: Determine the blade rigidity and determine the milling strategy based on the blade rigidity. The total length of the blisk blade is 92 mm, and the thickest point is 4.5 mm. The total length / thickness ratio is 20.1, and 20.1 < 30, indicating that the blade rigidity of the blisk blade is poor. Due to the low blade rigidity, a simultaneous roughing and fine milling method is required.

[0081] Step S27, blade milling simulation. Import the ".STL" file obtained by optical scanning into the Vericut software for cutting simulation. Calculate the simulation safety margin: blade allowance deviation + model accuracy + tool safety distance = safety margin; from the above steps, it can be obtained that the blade allowance deviation is 2.597mm, the model accuracy is 0.2mm, and the tool safety distance is 0.1mm. Therefore, the safety margin = 2.597+0.2+0.1 = 2.897mm, and the integer is 2.9mm. Therefore, the simulation safety margin can be set to 2.9mm. The meaning of setting this parameter is that during the program running, when the distance between the tool and the blank is greater than 2.9mm, it is considered that the tool used in the program will not collide with the part, and it is safe and feasible.

[0082] Step S28: Inspect the first blade and perform margin compensation. Use the machine tool online inspection system to inspect the first blade. In order to meet the requirement that the interval between sampling points at the leading and trailing edges shall not be greater than 0.2mm, and the interval between sampling points at the back of the basin shall not be greater than 2mm, for this integral blade, the number of sampling points at the back of the basin shall not be less than 20, and the number of sampling points at the leading and trailing edges shall not be less than 5; the inspection section spacing is 10mm, and the number of inspection sections is 10. The inspection results of the integral blade are as follows: Figure 11 and Figure 12 As shown, the contour degree at the blade tip is 0.0645mm, and the contour degree at the blade root is 0.0799mm. The contour degree at the blade root is greater than the contour degree at the blade tip, so the margin compensation should be performed from the blade root to the blade tip, and the compensation amount is about 0.015mm.

[0083] The above are the processing steps for additive manufacturing of an integral blade disk for an aero-engine in this embodiment. During the processing, the allowances are evenly distributed at various locations, and the blade milling is efficient and safe.

[0084] The laser additive manufacturing method for the blisk of this application has the following characteristics:

[0085] 1. Optical scanning technology is used to determine the blank model of the additively manufactured integral blade disk, and it is compared with the theoretical model. After fitting, the allowance distribution can be accurately obtained, which avoids overcutting of parts, reduces on-site debugging time, and improves the processing efficiency of parts.

[0086] 2. Applying the optical scanning model to blade cutting simulation can more accurately obtain the cutting state of the blade, avoiding blade overcutting and tool interference.

[0087] 3. Use online measurement to analyze the allowance of the blade's basin and back, which can accurately obtain the angular position of the blade, avoiding blank material shortage or excessive deviation in milling removal during blade milling.

[0088] 4. The milling strategies of "spiral milling" and "simultaneous roughing and fine-finishing" are adopted to replace the "one-support-two" milling strategy widely used in forgings. According to the rigidity of the blades, the milling strategies of "spiral milling" and "simultaneous roughing and fine-finishing" are used differently to achieve efficient processing of the blades.

[0089] 5. According to the inspection results of the blades, the blades are compensated for the margin to improve the qualified rate of the blades.

[0090] The above description is merely a specific embodiment of the present application, but the scope of protection of the present application is not limited thereto. Any changes or substitutions that can be easily conceived by a person skilled in the art within the technical scope disclosed in the present application should be included in the scope of protection of the present application. Therefore, the scope of protection of the present application should be based on the scope of protection of the claims.

Claims

1. A laser additive manufacturing method for an integral blade disk, characterized in that: include: Set reflective marking points on the blisk blank; Scanning the blisk blank using optical scanning technology based on the reflective marking points to obtain an optical scanning model; Comparing the optical scanning model with a theoretical model of the blisk to obtain a first margin distribution of the blisk blank; Fitting the first margin distribution to obtain a uniform second margin distribution; Determine the machining angle of the blisk blades; determining the rigidity of the blade and determining a milling strategy based on the rigidity of the blade; Based on the second stock distribution, the machining angle, and the milling strategy, performing cutting simulation using the optical scanning model, and milling the blisk blank; The blisk blades obtained after milling are inspected and the allowances are compensated.

2. The laser additive manufacturing method for an integral blade disk according to claim 1, characterized in that: The reflective marking points are randomly distributed, the spacing between each two reflective marking points ranges from 30 mm to 250 mm, and the distance between the reflective marking points and the edge of the integral blade disk blank is greater than 2 mm.

3. The laser additive manufacturing method for an integral blade disk according to claim 1, characterized in that: Determining the machining angle of the blisk blades includes: Use the machine tool online measurement system to measure the allowance of the basin at the tip of the blade and the back of the blade at the tip of the blade. By analyzing the allowance distribution of the basin at the tip of the blade and the back of the blade at the tip of the blade, the processing angle of the integral blade disc blade is determined.

4. The laser additive manufacturing method for an integral blade disk according to claim 3, characterized in that: By analyzing the margin distribution of the basin at the tip of the blade and the back at the tip of the blade, the blade margin deviation is obtained. When the optical scanning model is used for cutting simulation, a minimum collision clearance between the tool and the part is set based on the blade allowance deviation.

5. The laser additive manufacturing method for an integral blade disk according to claim 1, characterized in that: The rigidity of the blade is judged by the ratio of the total length of the integral blade disc to the blade thickness. When the ratio of the total length of the integral blade disc to the blade thickness is greater than 30, the milling strategy of rough and fine synchronous milling is adopted; when the ratio of the total length of the integral blade disc to the blade thickness is less than 30, the milling strategy of spiral milling is adopted.

6. The laser additive manufacturing method for an integral blade disk according to claim 1, characterized in that: The testing of the blisk blades obtained after milling includes: The contour of the first piece of the blisk blade is detected using a machine tool online measurement system, and the contour detection is performed by a point fitting method.

7. The laser additive manufacturing method for an integral blade disk according to claim 6, characterized in that: In the contour detection, the sampling point intervals at the leading and trailing edges of the blade are less than or equal to 0.2 mm, the sampling point intervals at the back of the blade are less than or equal to 2 mm, and the detection section intervals of each blade range from 5 mm to 10 mm.

8. The laser additive manufacturing method for an integral blade disk according to claim 6, characterized in that: In the contour detection, the number of sampling points at the back of the blade is greater than or equal to 20, and the number of sampling points at the leading edge and the trailing edge of the blade is greater than or equal to 5.

9. The laser additive manufacturing method for an integral blade disk according to claim 1, characterized in that: The margin compensation includes: When the contour degree at the blade tip is greater than that at the blade root, machining allowance compensation is performed from the blade tip to the blade root; When the profile at the tip of the blade is smaller than the profile at the root, machining allowance compensation is performed from the root to the tip.

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