A method of machining a compressor blade

Abstract

The application belongs to the technical field of compressor blade processing, and discloses a compressor blade processing method, which comprises the following steps: obtaining a compressor blade blank precision forging; based on the compressor blade blank precision forging, sequentially performing the following processes: milling an air inlet edge and an exhaust edge, rough milling a tenon, fine milling the tenon, polishing the air inlet edge and the exhaust edge, linear cutting a blade tip, and milling the blade tip, so as to finally obtain a processed compressor blade; wherein, in each processing procedure, when positioning and clamping are performed based on a blade axial reference point and a blade body position reference point, the selected tooling and the blade axial reference point and the blade body position reference point are all surface contact with a preset area. The technical scheme disclosed by the application solves the technical problems existing in the prior art, such as large consumption of alloy auxiliary materials, long processing period, low qualified rate of blade body surface position degree, complex process, low material utilization rate, and high production cost.

Description

Technical Field

[0001] This invention belongs to the field of compressor blade processing technology, and specifically relates to a compressor blade processing method. Background Technology

[0002] In power equipment such as aero engines and gas turbines, the compressor is one of the key components, and its performance directly affects the efficiency and reliability of the entire power equipment. As the core working element of the compressor, the structural design and manufacturing quality of the blades play a decisive role in the performance of the compressor.

[0003] In the prior art, a certain type of compressor blade structure has a specific configuration, such as... Figure 1 As shown, the blade is specifically composed of a tenon, mounting plate, inlet edge, exhaust edge, blade body, and blade tip. The tenon is designed as a dovetail-shaped straight tooth, a structure that ensures a stable connection and transmission between the blade and the compressor rotor. The mounting plate has a conical surface shape, which helps in the precise installation and positioning of the blade in the compressor. The inlet and exhaust edges have varying profiles; this unique design optimizes the gas flow path and improves the compressor's compression efficiency. The blade body features a high-order curved surface; its complex surface shape is carefully designed to meet gas dynamics requirements and achieve efficient gas compression. The blade tip is designed as a cone, which effectively reduces gas leakage at the tip, further improving the compressor's operating efficiency.

[0004] Currently, there are two main methods for processing the blades with the above-mentioned structure: Firstly, precision forging blanks are used for machining. The specific process mainly involves: firstly, machining the inlet and exhaust edges using CNC milling; then, casting alloy into a mold to encase the blade; subsequently, clamping the alloy block and machining the tenon; then melting the alloy to remove the blade; next, polishing the inlet and exhaust edges; finally, clamping the tenon, cutting off the blade tip, and milling it to the required blade tip shape. However, this method has several drawbacks: on the one hand, it consumes a large amount of alloy auxiliary materials during machining, which not only increases production costs but also wastes resources; on the other hand, the entire machining cycle is long, affecting production efficiency; more importantly, because the blade is encased in alloy during machining, it cannot be inspected in real time, resulting in a low pass rate for the blade's surface position accuracy, thus affecting the overall quality and performance of the blade.

[0005] Secondly, it uses die-forged blanks for machining. This method requires machining all blade surfaces, including the blade body, making the process extremely complex. This not only places high demands on machining equipment and technicians but also significantly extends the machining cycle. In addition, this method has low material utilization and generates a lot of waste during machining, leading to a substantial increase in production costs.

[0006] In summary, both existing processing methods for the compressor blades described above have certain shortcomings, and there is an urgent need to develop a new processing method suitable for the compressor blade structure. Summary of the Invention

[0007] The purpose of this invention is to provide a compressor blade processing method to solve the technical problems existing in the prior art, such as high consumption of alloy auxiliary materials, long processing cycle, low blade profile position accuracy qualification rate, complex process, low material utilization rate and high production cost.

[0008] To achieve the above objectives, the present invention adopts the following technical solution: The present invention provides a method for processing compressor blades. The processed compressor blades are composed of tenons, mounting plates, inlet edges, exhaust edges, blade bodies, and blade tips. The tenons are dovetail-shaped straight teeth, the mounting plates are conical surfaces, the inlet and exhaust edges are variable profiles, the blade bodies are high-order curved surfaces, and the blade tips are conical. The steps of the compressor blade processing method include: A compressor blade blank forging is obtained, which is composed of a tenon, a mounting plate, an exhaust edge, an intake edge, a blade body, and a blade tip; wherein, the tenon is connected to a first process boss, the blade tip is connected to a second process boss, the blade body and the mounting plate have no allowance, and the intake edge and the exhaust edge have a preset machining allowance; the surface of the mounting plate is provided with a blade axial reference point, and the surface of the blade body is provided with a blade position reference point; Based on the compressor blade blank precision forging, the inlet edge and exhaust edge are milled sequentially, the tenon is rough milled, the tenon is fine milled, the inlet edge and exhaust edge are polished, the blade tip is wire cut, and the blade tip is milled to finally obtain the processed compressor blade; in each processing step, when positioning and clamping based on the blade axial reference point and the blade body position reference point, the selected tooling and the blade axial reference point and the blade body position reference point are in surface contact with a preset area.

[0009] A further improvement to the technical solution of this invention lies in the specific steps of milling the inlet and outlet sides, which include: Using tooling, the compressor blade blank precision forging is positioned and clamped on a CNC milling machine based on the first process boss, the second process boss, the blade axial reference point and the circumferential reference point among the blade position reference points, and the inlet edge and the exhaust edge are milled to obtain the machined inlet edge and exhaust edge. Both the intake and exhaust sides are left with allowance after processing.

[0010] A further improvement to the technical solution of the present invention lies in that the specific steps of rough milling the tenon include: Using tooling, the compressor blades after milling the inlet and exhaust sides are positioned and clamped on a CNC milling machine with the inlet side, mounting plate and second process boss as positioning and clamping. The tenons are then rough milled to obtain the processed tenons. The tenons are left with some allowance after processing.

[0011] A further improvement to the technical solution of the present invention lies in that the specific steps of precision milling the tenon include: Using tooling, the compressor blade after rough milling tenon treatment is positioned and clamped on a CNC milling machine with the blade axial reference point set on the air intake edge and the mounting plate surface, and the blade position reference point set on the blade surface. The tenon is then finely milled to the finished size to obtain the compressor blade after fine milling tenon treatment.

[0012] A further improvement to the technical solution of this invention lies in the specific steps of polishing the air intake edge and the air exhaust edge, which include: After the compressor blades have been precision milled and the tenons have been processed, the inlet and outlet edges are polished on a polishing machine. The dimensions and shapes of the inlet and outlet edges are then processed to the finished product dimensions to obtain the compressor blades with polished inlet and outlet edges.

[0013] A further improvement of the technical solution of the present invention is that, when polishing the air intake and exhaust sides on the polishing machine, a felt wheel and a nylon wheel are used for polishing the air intake and exhaust sides.

[0014] A further improvement to the technical solution of this invention lies in the fact that the specific steps of wire cutting blade tip treatment include: Using tooling, the compressor blades after polishing the intake and exhaust sides are positioned and clamped on a CNC wire EDM machine with tenons, and the blade tips are wire-cut to remove the second process boss, thus obtaining the wire-cut blade tips. The blade tips, after wire cutting, have a margin remaining.

[0015] A further improvement to the technical solution of the present invention lies in that the specific steps of the blade tip milling process include: Using tooling, the compressor blades after wire cutting and tip processing are positioned and clamped on a CNC milling machine with tenons. The blade tips are then milled to process the size and shape of the blade tips to the finished size, and finally the processed compressor blades are obtained.

[0016] A further improvement of the technical solution of the present invention is that the intake side and the exhaust side have a preset size of machining allowance, and the preset size ranges from 2mm to 4mm.

[0017] A further improvement of the technical solution of the present invention is that the selected tooling, the axial reference point of the blade, and the position reference point of the blade body all adopt a surface contact with a preset area, wherein the surface contact with the preset area has a size of 4×4mm. 2 ~10×10mm 2 Square face or φ 4mm~ φ A 10mm circular contact surface; wherein, the circular contact surface is designed to conform to the shape.

[0018] Compared with the prior art, the present invention has the following beneficial effects: This invention specifically discloses a new method for processing compressor blades, which is a new and improved compressor blade processing scheme that can improve the pass rate of blade profile position accuracy, shorten the processing cycle, and reduce resource consumption and production costs. Specifically, addressing the technical problems of high alloy material consumption in existing solutions, this invention employs a fixture-based method for directly clamping parts. This method eliminates the need for alloy materials, completely avoiding their consumption. Furthermore, addressing the technical problems of complex processes and long processing cycles in existing solutions, this invention omits the casting and melting steps from the existing precision forging blank casting process, further shortening the process flow and reducing complexity and processing cycle. Moreover, addressing the low pass rate of blade profile position accuracy, this invention uses a fixture-based method for directly clamping parts with precise clamping and positioning. This method allows for direct measurement of part dimensions after processing, enabling timely adjustments to prevent further defects and avoiding batch defects caused by the inability to detect alloy coating in existing technologies. Finally, addressing the low material utilization rate, this invention uses precision forging blanks for production, resulting in no excess material on the blade profile and eliminating the need for material removal during processing. This method offers higher material utilization compared to using die-forged blanks. It should be emphasized that the technical solution of the present invention adopts a small-surface contact technique, which solves the technical difficulty of poor rigidity of parts in existing positioning methods. Attached Figure Description

[0019] To more clearly illustrate the technical solutions in this invention or the prior art, the drawings used in the description of the embodiments or the prior art will be briefly introduced below. Obviously, the drawings described below are some embodiments of this invention. For those skilled in the art, other drawings can be obtained from these drawings without creative effort.

[0020] Figure 1 This is a schematic flowchart of a compressor blade processing method in an embodiment of the present invention; Figure 2 This is a schematic diagram of the structure of a compressor blade blank precision forging in an embodiment of the present invention; Figure 3 Is with Figure 2 Correspondingly, a schematic diagram of the processed compressor blade structure; Figure 4 This is a schematic diagram comparing the process flow of the present invention with that of the prior art in an embodiment of the present invention; The explanations of the reference numerals in the figure are as follows: 1. Tenon; 2. Mounting plate; 3. Exhaust edge; 4. Intake edge; 5. Blade body; 6. Blade tip; 7. First process boss; 8. Blade axial reference point; 9. First blade body position reference point; 10. Second blade body position reference point; 11. Third blade body position reference point; 12. Second process boss. Detailed Implementation

[0021] To make the objectives, technical solutions, and advantages of the present invention clearer, the technical solutions of the present invention will be clearly and completely described below with reference to the accompanying drawings of the embodiments of the present invention; obviously, the described embodiments are only some embodiments of the present invention, and not all embodiments.

[0022] Based on the technical solutions disclosed in the embodiments of this invention, all other embodiments obtained by those skilled in the art without inventive effort are within the scope of protection of this invention. Furthermore, the terms "comprising" and "having," and any variations thereof, are intended to cover non-exclusive inclusion. For example, a process, method, system, product, or device that includes a series of steps or units is not necessarily limited to those steps or units explicitly listed, but may include other steps or units not explicitly listed or inherent to these processes, methods, products, or devices.

[0023] Please see Figure 1 This invention provides a method for machining compressor blades. The machined compressor blade consists of a tenon 1, a mounting plate 2, an inlet edge 4, an exhaust edge 3, a blade body 5, and a blade tip 6. The tenon 1 is a dovetail-shaped straight tooth, the mounting plate 2 is a conical surface, the inlet edge 4 and the exhaust edge 3 are variable profiles, the blade body 5 is a high-order curved surface, and the blade tip 6 is conical. Figure 3 As shown.

[0024] In this embodiment of the invention, the steps of the compressor blade processing method include: Step S1: Obtain a precision forged compressor blade blank, which consists of a tenon 1, a mounting plate 2, an exhaust edge 3, an intake edge 4, a blade body 5, and a blade tip 6. The tenon 1 is connected to a first process boss 7, and the blade tip 6 is connected to a second process boss 12. The blade body 5 and mounting plate 2 have no allowance, while the intake edge 4 and exhaust edge 3 have a pre-defined machining allowance. The surface of the mounting plate 2 is provided with a blade axial reference point 8, and the surface of the blade body 5 is provided with a blade body position reference point. More specifically, the blade body position reference point includes a circumferential reference point and an axial reference point. The circumferential reference point includes a first blade body position reference point 9 and a second blade body position reference point 10, and the axial reference point includes a third blade body position reference point 11.

[0025] Step S2: Based on the compressor blade blank precision forging, the inlet edge and exhaust edge are milled sequentially, the tenon is rough milled, the tenon is fine milled, the inlet edge and exhaust edge are polished, the blade tip is wire cut, and the blade tip is milled to finally obtain the processed compressor blade; wherein, in each processing step, when positioning and clamping based on the blade axial reference point and the blade body position reference point, the selected tooling and the blade axial reference point and the blade body position reference point are in surface contact with a preset area.

[0026] In a specific exemplary technical solution of the present invention, the specific processing steps include: Step 1, blank preparation, includes: obtaining the compressor blade blank precision forging, the structure of which is as follows: Figure 2 As shown; the compressor blade blank precision forging is composed of a tenon 1, a mounting plate 2, an exhaust edge 3, an intake edge 4, a blade body 5, and a blade tip 6; wherein, the tenon 1 is connected to a first process boss 7, the blade tip 6 is connected to a second process boss 12, the blade body 5 and the mounting plate 2 have no allowance, the intake edge 4 and the exhaust edge 3 have a preset size (in the specific exemplary technical solution, the allowance is generally in the range of 2mm~4mm, such as 2.5mm) machining allowance; the surface of the mounting plate 2 is provided with a blade axial reference point 8 (in the specific exemplary technical solution, such as... Figure 2 As shown, based on existing technical solutions, the surface of the blade 5 is provided with a blade position reference (in a specific exemplary technical solution, a first blade position reference point 9, a second blade position reference point 10, and a third blade position reference point 11 are respectively provided on the surface of the blade, which can be determined based on existing technical solutions).

[0027] The compressor blade blank precision forging structure design in this embodiment of the invention lays the foundation for subsequent precise machining. The presence of the process boss facilitates clamping during machining, ensuring the stability of the blade during processing. The zero-margin design of the blade body and mounting plate reduces unnecessary material removal and improves material utilization. The pre-reserved machining allowances on the inlet and exhaust sides take into account factors such as deformation during machining while ensuring the accuracy of the final machined dimensions. Further, the reference points are determined using existing technical solutions. To ensure consistency in reference transfer, they are consistent with the reference points used for existing blank inspection, generally referred to as the 6-point positioning method. However, in the technical solution of this invention, these 6 points are not used for point contact but for small-area contact. Furthermore, the subsequent steps generate machining dimensions using a CNC program, and the machined dimensions are confirmed by dedicated inspection fixtures and equipment.

[0028] Step 2, milling the inlet and outlet sides, includes: using tooling, positioning and clamping the compressor blade blank precision forging on a CNC milling machine based on the first process boss, the second process boss, the blade axial reference point, and the blade position reference.

[0029] Explained, the tooling can be designed according to the shape and processing requirements of the blade to ensure that the blade is accurately positioned and firmly fixed during processing. In this embodiment of the invention, positioning and clamping at specific points can ensure the processing accuracy of the intake and exhaust sides. The processed intake and exhaust sides have a margin to allow for further processing and adjustment, in order to cope with possible processing errors and deformations.

[0030] Step 3, rough milling of the tenon, including: using tooling, positioning and clamping the blade processed in step 2 on a CNC milling machine with the air intake edge, mounting plate and second process boss.

[0031] In this embodiment of the invention, the air intake edge, mounting plate, and process boss serve as positioning references, accurately determining the machining position of the tenon. When machining the tenon, a allowance is left after machining. Rough milling of the tenon primarily involves quickly removing most of the excess material, preparing for subsequent finish milling. Leaving an allowance prevents the tenon dimensions from exceeding tolerances due to excessive cutting forces during rough machining, ensuring the smooth progress of subsequent finish machining.

[0032] Step 4, precision milling of the tenon, including: using a fixture, positioning and clamping the blade on a CNC milling machine using the air intake edge (the air intake edge machined in step 2), the blade axial reference point on the mounting plate surface, and three blade position reference points on the blade surface, and using auxiliary support pins on the fixture to provide auxiliary support to the mounting plate surface.

[0033] Explained, the combined use of these positioning points in this step of the present invention enables more precise determination of the tenon's position and size. The auxiliary support pin provides greater clamping rigidity, and the tenon is machined to the finished size through the cooperation of a high-precision CNC milling machine and tooling. Precision milling of the tenon is a key process to ensure a precise connection and reliable transmission between the tenon and the compressor rotor, and its machining accuracy directly affects the installation quality and performance of the blades.

[0034] In a specific exemplary preferred technical solution, the tooling fixture and these positioning points are not in theoretical point contact, but are designed with a width of 4×4mm. 2 ~10×10mm 2 Square face or φ 4mm~ φ The 10mm circular contact surface is designed to increase the contact area (which is beneficial for clamping rigidity), but the contact surface cannot be too large, otherwise it will reduce the clamping accuracy.

[0035] Step 5, polishing the inlet and exhaust edges, includes polishing the inlet and exhaust edges on a polishing machine using felt wheels and nylon wheels. Felt wheels and nylon wheels have different polishing properties. Felt wheels are soft and can remove minor imperfections and burrs from the surface of the inlet and exhaust edges, making the surface smoother; nylon wheels can improve the surface finish to a certain extent. Through a proper polishing process, the size and shape of the inlet and exhaust edges are processed to the finished dimensions, reducing airflow resistance at the inlet and outlet of the blades and improving compressor efficiency.

[0036] Step 6, wire cutting the blade tip, includes: using tooling, clamping and machining the blade tip on a CNC wire cutting machine with a tenon for positioning. The CNC wire cutting machine is characterized by high precision and high efficiency, enabling it to accurately cut the blade tip according to design requirements. Using the tenon as a positioning reference ensures the relative positional accuracy of the blade tip and the overall blade. After removing the second process boss, the blade tip has sufficient allowance to provide machining space for the subsequent blade tip milling process.

[0037] Step 7, milling the blade tip, includes: using tooling, clamping and machining the blade tip on a CNC milling machine with a tenon for positioning; through the precise control of the CNC milling machine, machining the size and shape of the blade tip to the finished size. The blade tip milling process can further improve the accuracy and surface quality of the blade tip, ensure that the clearance between the blade tip and the compressor casing meets the design requirements, reduce gas leakage, and improve the working efficiency of the compressor.

[0038] Compared to traditional processing methods using precision forged blanks, the method of this invention eliminates the need for alloy cladding on the blade during processing. This allows for continuous monitoring of the blade's position during machining, enabling timely detection and correction of errors. Through precise positioning, clamping, and process control, the blade's position accuracy pass rate is significantly improved, effectively ensuring blade quality and reducing blade scrap and rework due to positional defects. This method avoids the casting and melting of low-melting-point alloys, reducing cumbersome procedures. Furthermore, the close integration of processing steps, coupled with efficient equipment and a well-planned process, greatly shortens the overall processing cycle. This allows compressor blades to be put into use more quickly, improving production efficiency and meeting the demands of rapid research and development and production. Additionally, the elimination of casting and melting of low-melting-point alloys avoids the consumption of alloy auxiliary materials, reducing raw material costs. Moreover, the simple processing flow of this method reduces investment in processing equipment and time, while high material utilization reduces waste, further lowering production costs.

[0039] Compared with the existing processing method using die forging blanks, the processing flow of the method provided by the embodiments of the present invention is simpler. It does not require complex processing of all surfaces such as the blade body, reducing processing steps and operational difficulty. This not only reduces the requirements for processing equipment and the technical level of operators, but also improves the stability and reliability of production, which is conducive to achieving large-scale, standardized production.

[0040] In a specific exemplary technical solution of the present invention, the specific process of the compressor blade processing method is as follows: Equipment and material preparation includes: preparing processing equipment such as CNC milling machines, polishing machines, and CNC wire cutting machines, and ensuring that the equipment accuracy meets the processing requirements; selecting qualified blade precision forging blanks, as well as polishing materials such as felt wheels and nylon wheels. In addition, tooling should be designed and manufactured according to the shape and processing requirements of the blade. The tooling should have sufficient strength and precision to ensure the stable positioning of the blade during the processing.

[0041] Please see Figure 4 Currently, the main method for processing the aforementioned blade structure is as follows: using a precision forged blank, first CNC milling the inlet and outlet edges, then casting an alloy to cover the blade body using a mold, then clamping the alloy block to machine the tenon, then melting the alloy to remove the blade, polishing the inlet and outlet edges, and finally clamping the tenon to cut off the blade tip and milling the blade tip. This method consumes a large amount of alloy auxiliary materials and has a long processing cycle. During the processing, the blade body cannot be inspected because it is covered by the alloy, resulting in a low pass rate for the blade body surface position accuracy. Using a die-forged blank, this method requires processing all blade surfaces, including the blade body, which is complex, has a long processing cycle, low material utilization, and high production costs. Unlike the existing technical solutions, the specific processing process of this invention includes: sequentially performing milling of the inlet and outlet edges, rough milling of the tenon, finish milling of the tenon, polishing of the inlet and outlet edges, wire cutting of the blade tip, and milling of the blade tip according to the steps of the above technical solution of this invention; before each processing step, the condition of the equipment and tooling is carefully checked to ensure normal operation; during the processing, the process parameters, such as cutting speed, feed rate, and depth of cut, are strictly followed to ensure processing quality. In addition, after each processing step is completed, the dimensions and surface quality of the blades are inspected to ensure that all dimensions and shapes of the blades meet the design requirements. If any defects are found, the causes are analyzed promptly and corresponding adjustment measures are taken, such as re-clamping or adjusting processing parameters, until qualified blades are produced.

[0042] In a specific exemplary technical solution of the present invention, a method for processing compressor blades is implemented through the following steps. The compressor blade blank is a precision forging; the blank structure is described below. Figure 3Tenon 1 connects to the first process boss 7, blade tip 6 connects to the second process boss 12, blade body 5 and mounting plate 2 have no allowance, air intake edge 4 and exhaust edge 3 have a machining allowance of 2.5mm, the preset V point on the surface of mounting plate 2 is the axial reference of the blade, and the preset K1, K2 and K3 points on the surface of blade body 5 are the blade position reference points (K1 and K3 are circumferential reference points, K2 is the axial reference point). The machining steps are as follows: (1) Milling the inlet and outlet edges: Using tooling, the blade blank is positioned and clamped on a CNC milling machine with the first process boss, the second process boss, the V point and the K1 and K3 points on the blade body, and the inlet and outlet edges are machined. The machined inlet and outlet edges have a margin.

[0043] (2) Rough milling of tenons: Using tooling, the blades are positioned and clamped on a CNC milling machine with the air intake edge, mounting plate and second process boss, and the tenons are machined. The machined tenons have a allowance.

[0044] (3) Precision milling of tenons: Using tooling, the blades are positioned and clamped on a CNC milling machine using the V point on the air intake edge, the mounting plate surface, and the K1, K2, and K3 points on the blade body, and the tenons are machined to the finished size.

[0045] (4) Polishing the air intake and exhaust edges: Polish the air intake and exhaust edges on a polishing machine using felt wheels and nylon wheels, and process the size and shape of the air intake and exhaust edges to the finished product size.

[0046] (5) Wire EDM blade tip: Using tooling, the blade tip is machined on a CNC wire EDM machine with tenon positioning and clamping. The second process boss is removed, and the blade tip is left with a margin.

[0047] (6) Milling blade tip: Using special tooling, the blade tip is machined on a CNC milling machine with tenon positioning and clamping, and the size and shape of the blade tip are machined to the finished size.

[0048] Compared with the existing traditional processing method using precision forged blanks, the method of this invention does not involve alloy coating on the blade during processing, and the blade position accuracy can be detected, thus improving the pass rate of blade position accuracy processing. It also reduces the processing steps of casting and melting low-melting-point alloys, shortens the processing cycle, avoids the consumption of low-melting-point alloy auxiliary materials, and reduces production costs. Compared with the processing method using die forged blanks, the method of this invention has a simple processing flow, high material utilization rate, and the advantages of lower cost and shorter production cycle.

[0049] Finally, it should be noted that the above embodiments are only used to illustrate the technical solutions of the present invention and not to limit it. Although the present invention has been described in detail with reference to the above embodiments, those skilled in the art should understand that modifications or equivalent substitutions can still be made to the specific implementation of the present invention. Any modifications or equivalent substitutions that do not depart from the spirit and scope of the present invention should be covered within the scope of protection of the claims of the present invention.

Claims

1. A method for processing compressor blades, characterized in that, The processed compressor blade consists of a tenon, mounting plate, inlet edge, exhaust edge, blade body, and blade tip; among which, the tenon is a dovetail straight tooth, the mounting plate is a conical surface, the inlet edge and exhaust edge are variable profiles, the blade body is a high-order curved surface, and the blade tip is conical. The steps of the compressor blade processing method include: A compressor blade blank forging is obtained, which is composed of a tenon, a mounting plate, an exhaust edge, an intake edge, a blade body, and a blade tip; wherein, the tenon is connected to a first process boss, the blade tip is connected to a second process boss, the blade body and the mounting plate have no allowance, and the intake edge and the exhaust edge have a preset machining allowance; the surface of the mounting plate is provided with a blade axial reference point, and the surface of the blade body is provided with a blade position reference point; Based on the compressor blade blank precision forging, the inlet edge and exhaust edge are milled sequentially, the tenon is rough milled, the tenon is fine milled, the inlet edge and exhaust edge are polished, the blade tip is wire cut and the blade tip is milled, and finally the processed compressor blade is obtained; wherein, in each processing step, when positioning and clamping based on the blade axial reference point and the blade body position reference point, the selected tooling and the blade axial reference point and the blade body position reference point are in surface contact with a preset area. in, The specific steps for milling the inlet and exhaust edges include: using tooling, positioning and clamping the compressor blade blank precision forging on a CNC milling machine based on the first process boss, the second process boss, the blade axial reference point, and the circumferential reference point among the blade position reference points; milling the inlet and exhaust edges to obtain the machined inlet and exhaust edges; wherein, the machined inlet and exhaust edges both have a allowance. The specific steps for rough milling tenons include: using tooling, positioning and clamping the compressor blades after milling the intake and exhaust edges on a CNC milling machine with the intake edge, mounting plate and second process boss as positioning and clamping, rough milling the tenons to obtain the machined tenons; wherein, the machined tenons have a allowance. The specific steps of precision milling tenon processing include: using tooling, positioning and clamping the compressor blade after rough milling tenon processing on a CNC milling machine with the blade axial reference point set on the air intake edge and the surface of the mounting plate, and the blade position reference point set on the blade surface; and fine milling the tenon to the finished size to obtain the compressor blade after precision milling tenon processing. The specific steps for polishing the intake and exhaust edges include: polishing the intake and exhaust edges of the compressor blades after precision milling the tenons on a polishing machine, and machining the size and shape of the intake and exhaust edges to the finished size to obtain the polished intake and exhaust edges of the compressor blades. The specific steps of wire EDM blade tip processing include: using tooling, clamping the polished compressor blade with the inlet and exhaust edges in a CNC wire EDM machine tool with tenons, and wire EDMing the blade tip to remove the second process boss, thereby obtaining the wire-cut blade tip; wherein, the wire-cut blade tip leaves a margin. The specific steps of milling blade tip processing include: using tooling, clamping the compressor blade after the blade tip processing with tenon positioning on a CNC milling machine, milling the blade tip, processing the size and shape of the blade tip to the finished size, and finally obtaining the processed compressor blade. The intake and exhaust edges have a pre-defined machining allowance, with the pre-defined size ranging from 2mm to 4mm. The selected tooling, blade axial reference point, and blade position reference point all use a pre-defined area of ​​surface contact, with the pre-defined area having a size of 4×4mm. 2 ~10×10mm 2 Square face or φ 4mm~ φ A 10mm circular contact surface; wherein, the circular contact surface is designed to conform to the shape.

2. The compressor blade processing method according to claim 1, characterized in that, When polishing the air intake and exhaust sides on a polishing machine, felt wheels and nylon wheels are used for polishing the air intake and exhaust sides.

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