A method of machining an air engine air swirler

Abstract

The application relates to a machining method of an aero-engine air swirler, and specifically comprises the following steps: determining a machining device, adopting a turning method to machine an outer surface of a part and an outer circle of a blade, including a ball head part, adopting a milling method to machine a blade part; determining a process route: turning the outer circle-drilling an axial hole-accurately turning the outer circle-accurately boring the hole-turning a half ball head-milling a blade type-turning another half ball head-cutting-off-inspecting; determining a machining strategy and a tool path: setting four ball milling cutters with different diameters to respectively perform rough milling of the blade type, accurate milling of the blade type, accurate milling of a side surface of the blade and root cleaning machining; determining a machining tool and a margin distribution; determining a programming method: adopting a macro program based on a trigonometric function to compile a numerical control machining program; determining a numerical control program and a parameterized variable; and determining process parameters and machining verification. By adopting the machining method, the air swirler with high programming efficiency, short machining period, size precision and surface roughness meeting the design drawing requirements can be obtained.

Description

Technical Field

[0001] The invention belongs to the technical field of aero-engines, and in particular relates to a method for processing an aero-engine air cyclone with a complex structure. Background Art

[0002] The air swirler plays the role of swirling air in the main fuel nozzle assembly of an aircraft engine. Its structure is similar to that of an integral blisk, consisting of a rotating part and a blade part. Its processing accuracy and surface roughness directly affect the flow and direction of the swirling air, and may even affect the oil-air mixture ratio, resulting in problems such as reduced engine thrust.

[0003] The air cyclone has a complex structure. The blade part and the rotating part intersect to form a flow channel. The flow channel area varies with the diameter. The intersection line of the blade and the shaft is a curve, which cannot be processed using the conventional spiral milling flow channel method. The tool path and milling strategy need to be replanned according to the structure, which makes programming difficult. At the same time, due to the thin wall thickness and large overhang of the blade, the dimensional accuracy and surface roughness requirements are high, which are difficult to guarantee and the processing time is long. At the same time, the material is the difficult-to-process nickel-based high-temperature alloy GH536, and the tool wear is severe during processing. Ordinary milling strategies and process parameters cannot meet the design requirements. Summary of the Invention

[0004] In view of the shortcomings of the existing technology, the present invention provides a method for processing an aircraft engine air cyclone, which can obtain an air cyclone with high programming efficiency, short processing cycle, and dimensional accuracy and surface roughness that meet the requirements of the design drawings.

[0005] A method for processing an aero-engine air swirler comprises the following steps:

[0006] Step 1: Determine the processing equipment;

[0007] Step 2: Determine the process route;

[0008] Step 3: Determine the processing strategy and tool path;

[0009] Step 4: Determine the machining tool and allowance allocation;

[0010] Step 5: Determine the programming method;

[0011] Step 6: Determine the NC program and parameterized variables;

[0012] Step 7: Determine process parameters and process verification.

[0013] In the step 1, a turning-milling composite machining center is selected to complete all the turning, milling and drilling processes through one clamping. The outer surface of the part and the outer circle of the blade, including the ball head part, are machined by turning, and the blade part is machined by milling.

[0014] The processing route in the step 2 is: turning the outer circle → drilling the axial hole → fine turning the outer circle → fine boring → turning the hemispherical head → milling the blade shape → turning the other hemispherical head → cutting → inspection.

[0015] In the step 3, a fixed cutter axis milling strategy is adopted, the cutter axis direction is always in the Z direction, and four milling cutters of different diameters are set to perform rough milling of the blade profile, fine milling of the blade profile, fine milling of the blade side, and root cleaning respectively;

[0016] The rough milling blade profile trajectory is as follows: on the cylinder with a diameter of 21.3mm in the rotating part of the part, the blade profile on both sides is a closed curve formed by two curves with the radius of the milling cutter and the connecting curve of the two curves;

[0017] The tool path for fine milling the blade profile is: on the cylinder with a diameter of 16.61mm on the rotating part of the part, there are two curves with the radius of the milling cutter at the distance from the blade profile on both sides, and a closed curve formed by the connecting curve of the two curves;

[0018] The tool path for fine milling the blade side is: on the cylinder with a diameter of 10.61mm in the rotating part of the part, the blade body profile on both sides is a closed curve formed by two curves with the radius of the milling cutter and the connecting curve of the two curves;

[0019] The root cleaning tool trajectory is: on the cylinder with a diameter of 10.61mm in the rotating part of the part, the blade surfaces on both sides are two curves with the radius distance of the milling cutter tool and a closed curve formed by the connecting curve of the two.

[0020] In the step 4, the specific processing scheme is:

[0021] ① Rough milling of blade profile: Use 3mm ball cutter to rough open the flow channel, that is, the diameter of the flow channel is milled from 21.3mm to 16.5mm, and the milling is divided into 3 layers along the diameter direction, with a milling depth of 0.8mm per layer;

[0022] ② Fine milling of blade profile: Use 1.6mm ball cutter to further remove the allowance, that is, the diameter of the milling flow channel is milled from 16.61mm to 10.61mm, and the milling is divided into 10 layers along the diameter direction, with a milling depth of 0.3mm per layer;

[0023] ③ Fine milling of blade side: Use the side edge of a 1.5mm end cutter to fine mill the blade side to ensure the blade thickness accuracy and surface roughness;

[0024] ④ Root cleaning: Use Φ1mm ball cutter to clean the root to Φ10.61mm, and mill the side path in 5 layers perpendicular to the blade body. The milling depth of each layer is 0.1mm to ensure the designed fillet size requirements.

[0025] In the step 5, a macro program based on trigonometric functions is used to compile a CNC machining program, and a parametric program is compiled with the X coordinate of the cutting position as the independent variable and the Y and Z coordinates as the dependent variables. At the same time, the number of C-axis rotations and the number of milling layers are set as variables.

[0026] In step six, the IF[LT]GOTO statement is used to compile a single-layer interpolation program, and the Y and Z coordinates move as the X coordinate moves; the IF[GE]GOTO statement is used to compile an angle rotation and layer number control program to perform layered milling at each diameter position; the blade width, thickness and rotary axis angle, tool diameter, flow channel bottom diameter, outer diameter basic dimensions, as well as the number of blades and the number of milling layers are set as parameterized variables.

[0027] In the step seven, the process parameters for milling the blade and the flow channel surface, namely, the spindle speed, feed speed, and cutting depth, are determined. Specifically, the rough milling blade process is: spindle speed 3000-3600r / min, feed speed 35-40mm / min, and cutting depth 0.8mm; the fine milling blade process is: spindle speed 5500-6500r / min, feed speed 45-50mm / min, and cutting depth 0.3mm; the fine milling blade side process is: spindle speed 4000-4800r / min, feed speed 30-35mm / min; the root cleaning process is: spindle speed 4500-5500r / min, feed speed 20-25mm / min, and cutting depth 0.1mm.

[0028] The present invention has the following beneficial effects: air swirlers are widely used in aircraft engine combustion chambers. By combining the structural characteristics of the part with the required precision, this method plans the tool path, formulates a machining strategy, provides a CNC programming method, and optimizes process parameters, significantly reducing CNC programming time and iterative optimization time. The application of the proposed new method and high-quality machining process parameters can meet the requirements for part dimensional accuracy and surface roughness. This method has broad application prospects in the machining of complex structural parts, including air swirlers in aircraft engines and gas turbines. BRIEF DESCRIPTION OF THE DRAWINGS

[0029] Figure 1 is a schematic diagram of an air cyclone;

[0030] Figure 2 It is a schematic projection diagram of the blade part of the air cyclone;

[0031] Figure 3 for Figure 2BB view in the figure;

[0032] Figure 4 A schematic diagram of the blade spacing at the outer circumference of the air cyclone provided in this embodiment;

[0033] Figure 5 A schematic diagram of the blade spacing on the bottom surface of the flow channel of the air cyclone provided in this embodiment;

[0034] Figure 6 Schematic diagram of tool path;

[0035] Figure 7 This is a schematic diagram of the cutting trajectory of the Φ3 ball cutter;

[0036] Figure 8 This is a schematic diagram of the cutting trajectory of a Φ1.6 ball cutter;

[0037] Figure 9 This is a schematic diagram of the tool path of a Φ1.5R0.2 milling cutter;

[0038] Figure 10 This is a schematic diagram of the cutting trajectory of the Φ1 ball cutter;

[0039] in,

[0040] 1-blade part, 2-rotating part, 3-tool path. DETAILED DESCRIPTION

[0041] In order to better explain the present invention and facilitate understanding, the technical solutions and effects of the present invention are described in detail below with reference to the accompanying drawings through specific implementation methods.

[0042] The material grade of the air cyclone is nickel-based high-temperature alloy GH3536, and its structural diagram is as follows Figure 1 As shown, it consists of a blade part 1 and a rotating part 2. The outer diameter of the blade is Φ21.3mm, the bottom surface of the flow channel is Φ10.6mm, the number of blades is 10, the narrowest distance of the bottom surface of the flow channel is 1.5mm, and the blade cross section is a projection surface with an angle of 35° to the rotating axis. Figure 2-3 As shown, the blade thickness is 1.0 mm. The present application provides a method for processing an aero-engine air swirler, which specifically includes the following steps:

[0043] Step 1: Determine the processing equipment

[0044] Analyze the part structure and dimensional accuracy, use turning to machine the part's outer surface and the outer circle of the blade, including the ball head, and use milling to machine the blade part 1. If ordinary equipment is used, the process route should be: Turning the outer shape: Turning to the stepped shaft state, with the ball head as a cylinder; drilling radial holes; milling the blade; turning the ball head. Using ordinary equipment, turning and milling require secondary alignment, and when milling the blade, special or combined tooling is required for indexing. Taking into account processing efficiency and cost, combined with the structural characteristics of the part and the equipment capabilities, a turning and milling composite machining center is selected, which can complete all turning, milling, and drilling processes in one clamping. Specifically, considering the basic size of the part of Φ25mm, it was determined to use the Baomei S192 turning and milling composite machining center, which can complete all turning and milling processes in one clamping, improve part clamping and processing accuracy, improve processing efficiency, and save tooling costs.

[0045] Step 2: Determine the process route

[0046] Analysis of the part's structure revealed that the main challenges in machining the blades were milling the blade profile and controlling the surface quality. The distances between the two ends of the part and the blade were different, with the ball-end closer to the blade and also larger. To reduce the part's overhang and improve the machining system's rigidity, the ball-end was chosen as the clamping end, and the following basic process route was developed:

[0047] Turn the outer circle → drill the axial hole → fine turn the outer circle → fine boring → turn the hemisphere → mill the blade shape → turn the other hemisphere → cut off → inspect.

[0048] Step 3: Determine the machining strategy and tool path 3

[0049] The primary difficulty in turning and milling air cyclones lies in the design of the program for milling the blades. The swirl groove is a typical structure in nozzle parts. The dimensions and angles of the swirl groove are guaranteed by the linkage between the Z and C axes of the machine and a milling cutter of qualified size. However, the angle of the swirl groove is a developed surface dimension, and the thickness of the profile formed by the swirl groove decreases with decreasing diameter. In contrast, the angle of the air cyclone blades is a projected surface dimension, and the blade thickness remains constant. The flow channel area decreases with decreasing diameter, and the flow channel bottom forms a complex curve, not a spiral. Therefore, the same approach as milling the swirl groove cannot be used to design the machining program for air cyclone blades.

[0050] According to the requirements of the cyclone design drawings, the blade features a projection surface stretched onto the rotating body. Therefore, the dimensions and positions of each section along the projection direction are the same, and the blade thickness remains unchanged at any diameter. Therefore, the fixed-axis milling processing strategy can ensure that the part size and surface quality meet the design requirements. That is: the part is clamped to the spindle of the turning and milling composite machining center, the milling position is fixed, and the part extension size is guaranteed to meet the processing requirements of the entire blade. The milling cutter axis is parallel to the blade surface, and the tool is milled around the blade surface. Since the flow channel area decreases with the reduction of the rotating shaft diameter, the width of the narrowest position at the bottom of the flow channel is approximately 1.5mm, and there is a certain spatial angle between the blade plane and the part's rotating axis. Therefore, four milling cutters of different diameters are set up for rough milling of the blade profile, fine milling of the blade profile, fine milling of the blade side, and root cleaning to ensure the part's dimensional accuracy and surface roughness requirements.

[0051] The milling strategy adopts a fixed tool axis, and the tool axis direction is always in the Z direction.

[0052] Tool path 3 Figure 6 As shown, specifically:

[0053] Rough milling blade profile: On the cylinder with a diameter of 21.3 mm in the rotating part 2 of the part, the blade profiles on both sides are two curves of the milling cutter tool radius distance and a closed curve formed by the connecting curve of the two.

[0054] Fine milling blade profile: On the cylinder with a diameter of 16.61 mm in the rotating part 2 of the part, the blade profiles on both sides are two curves of the milling cutter tool radius distance and a closed curve formed by the connecting curve of the two.

[0055] Fine milling of the blade side: On the cylinder with a diameter of 10.61 mm in the rotating part 2 of the part, the blade surfaces on both sides are two curves of the milling cutter tool radius distance and a closed curve formed by the connecting curve of the two.

[0056] Root cleaning: On the cylinder with a diameter of 10.61 mm in the rotating part 2 of the part, the blade surfaces on both sides are two curves of the milling cutter tool radius distance and a closed curve formed by the connecting curve of the two.

[0057] Step 4: Determine the machining tool and allowance allocation: Figure 4 As shown in the figure, the narrowest blade spacing at the outer circle is about 4.5 mm. Figure 5 As shown, the narrowest blade spacing on the bottom of the flow channel is about 1.5mm. Taking into account the size of the part and the rigidity of the tool, it is determined that four milling cutters with different diameters of Ф3R1.5, Ф1.6R0.8, Ф1.5R0.2, and Ф1R0.5 will be used to perform rough milling of the blade profile, fine milling of the blade profile, fine milling of the blade side, and root cleaning respectively. The specific processing plan is as follows:

[0058] ① Rough milling of blade profile: Use 3mm ball cutter to rough open the flow channel, that is, the diameter of the flow channel is milled from 21.3mm to 16.5mm, and the milling is divided into 3 layers along the diameter direction, with a milling depth of 0.8mm per layer;

[0059] ② Fine milling of blade profile: Use 1.6mm ball cutter to further remove the allowance, that is, the diameter of the milling flow channel is milled from 16.61mm to 10.61mm, and the milling is divided into 10 layers along the diameter direction, with a milling depth of 0.3mm per layer;

[0060] ③ Fine milling of blade side: Use the side edge of a 1.5mm end cutter to fine mill the blade side to ensure the blade thickness accuracy and surface roughness;

[0061] ④ Root cleaning: Use Φ1mm ball cutter to clean the root to Φ10.61mm, and mill the side path in 5 layers perpendicular to the blade body. The milling depth of each layer is 0.1mm to ensure the designed fillet size requirements.

[0062] The specific tool path is:

[0063] The rough milling blade profile path 3 is: on the cylinder with a diameter of 21.3mm on the rotating part 2, there are two curves with a distance of 1.5mm (Φ3R1.5 milling cutter tool radius) from the blade profile on both sides, and a closed curve formed by the connecting curve between the two. The rough milling blade profile path 3 has three layers, each layer is offset 0.8mm downward along the tool axis direction (Z axis direction), see the attached Figure 7 ;

[0064] The blade profile finishing tool path 3 is: on the cylinder with a diameter of 16.61mm on the rotating part 2, there are two curves with a distance of 0.8mm (Φ1.6R0.8 milling cutter tool radius) from the blade profile on both sides, and a closed curve formed by the connecting curve between the two curves. The blade profile finishing tool path 3 has a total of 10 layers, and each layer is offset 0.3mm downward along the tool axis direction (Z axis direction), see the attached Figure 8 ;

[0065] The tool path 3 for fine milling the blade side is: on the cylinder with a diameter of 10.61mm on the rotating part 2, there are two curves with a distance of 0.75mm (Φ1.5R0.2 milling cutter tool radius) from the blade body surface on both sides and a closed curve formed by the connecting curves of the two curves. The tool path 3 for fine milling the blade side is 1 layer, see the attached Figure 9 ;

[0066] The root cleaning tool path 3 is: on the cylinder with a diameter of 10.61mm on the rotating part 2, there are two curves with a distance of 0.5mm (Φ1R0.5 milling cutter tool radius) from the blade surface on both sides, and a closed curve formed by the connecting curve of the two. The root cleaning tool path 3 has 5 layers, each layer is offset 0.1mm inward along the tool axis direction (Z axis direction), see the attached Figure 10 .

[0067] Step 5: Determine the programming method

[0068] When milling the blades, the NC machining program was compiled using UG-CAM software and machine tool macro program respectively.

[0069] Programming with UG-CAM software is relatively simple. By selecting a suitable programming template, setting the processing area and drive method, and setting reasonable processing allowances and processing parameters for the four tools used, a NC program can be generated.

[0070] Using machine tool macros to create CNC programs is complex and requires defining multiple independent and dependent variables. For example, as the X coordinate of the tool's cutting position changes, the Y and Z coordinates change synchronously, so X is the independent variable and Y and Z are the dependent variables. As the tool's side edge mills along the blade profile, the tool's bottom edge mills along the outer diameter of the flow channel. Given the X coordinate, the Y and Z coordinates of the tool center at any position can be calculated. Since the part has 10 blades along the circumference, the CNC machining program can be simplified by creating a loop program and setting the C-axis angle variable.

[0071] Comparing the NC programs compiled by the two methods, the program compiled by UG-CAM software is point coordinates, and the correctness of the tool path depends on the model, but it is inconvenient to modify and change the tool midway. The program and parameter debugging require multiple model modifications, post-processing, and importing into DNC. In addition, the program text is relatively long, and it is inconvenient to find and modify problems that arise during the processing. If there is a problem, the entire program segment needs to be rerun. The NC program is compiled using a machine tool macro program. The program contains more complex trigonometric function calculations. After the program framework is correct, it is convenient to modify specific process parameters and change tools midway. The program and parameter debugging can directly modify the parameterized variables. If there is a problem, only the processing position needs to be set locally, saving programming and processing time. Therefore, the present invention finally chooses to use a machine tool macro program based on trigonometric functions to process the air cyclone blade part 1.

[0072] To improve programming efficiency, shorten program statements, and provide parametric programs for similar parts of varying sizes, we decided to use macro programs based on trigonometric functions to create CNC machining programs. This parametric program uses the X coordinate of the cutting position as the independent variable and the Y and Z coordinates as dependent variables. The number of C-axis rotations and the number of milling layers are also set as variables to achieve parametric programming.

[0073] Step 6: Determine the NC program and parameterized variables

[0074] Use the IF[LT]GOTO statement to compile a single-layer interpolation program, and the Y and Z coordinates move as the X coordinate moves; use the IF[GE]GOTO statement to compile an angle rotation and layer number control program to perform layered milling at each diameter position.

[0075] The basic dimensions of blade width, thickness, rotary axis angle, tool diameter, flow channel bottom diameter, outer diameter, number of blades, and number of milling layers are set as parametric variables, providing a NC program template for subsequent process parameter adjustment, design structure fine-tuning, and similar parts processing. The NC program is as follows:

[0076] ① Parameterized variables

[0077] #101=35 / / Blade angle

[0078] #102=1.06 / / Blade thickness

[0079] #103=3 / / Tool diameter

[0080] #104=21.3 / / Initial processing diameter

[0081] #105=7.6 / / Blade width

[0082] #106=[#103+#105] / 2

[0083] #107=0.5 / / Safety distance

[0084] #108=#106+#107 / / X initial processing position

[0085] #150=[#102+#103] / 2 / COS[#101]

[0086] #109=-#108*TAN[#101]+#150 / / Y initial processing position

[0087] #110=[#103+#104] / 2

[0088] #111=-#108

[0089] #112=-#109

[0090] #113=0

[0091] #114=16.5 / / The diameter of the last cut #140=#104-#114 / / Remove the remainder

[0092] #141=#140 / 3 / / Number of floors

[0093] #121=#121-0.1 / / X step 0.1

[0094] #122=-#121*TAN[#101]+#150 / / Y coordinate position #123=SQRT[[#110*#110]-[#122*#122]]

[0095] #125=#123-#103 / 2 / / Z coordinate position ② Main processing program

[0096] N30

[0097] G00 X#108Y#109Z15 C#113

[0098] N10 G01 X#121Y#122Z#125F100IF[#121GE#111]GOTO 10

[0099] G00 Z15

[0100] Y#112

[0101] #121=#111

[0102] #132=-#121*TAN[#101]-#150

[0103] #133=SQRT[[#110*#110]-[#132*#132]]

[0104] #135=#133-#103 / 2

[0105] N20 G01 X#121Y#132Z#135F100

[0106] #121=#121+0.1

[0107] #132=-#121*TAN[#101]-#150

[0108] #133=SQRT[[#110*#110]-[#132*#132]]

[0109] #135=#133-#103 / 2

[0110] IF[#121LE#108]GOTO 20

[0111] G00 Z15

[0112] #113=#113+36

[0113] G68 G19 X0 Y0 Z0 R-#113

[0114] IF[#113LT360]GOTO 30

[0115] #113=0

[0116] #104=#104-#141

[0117] #110=[#103+#104] / 2

[0118] IF[#104GE#114]GOTO 30

[0119] G00 X-10Y0 Z15

[0120] Step 7: Determine process parameters and process verification

[0121] Since the entire milling process is a cantilever structure and the material is the difficult-to-machine nickel-based high-temperature alloy GH3625, in order to prevent part vibration and tool deflection, the clamping amount should be increased as much as possible, and the cutting parameters should be strictly controlled. The process parameters for milling the blade and flow channel surface, such as spindle speed, feed rate, and cutting depth, are determined as shown in Table 1 below.

[0122] Table 1 Milling blade process parameters

[0123]

[0124] After determining the parameters, the part was machined. Final testing confirmed that the dimensional accuracy, positional precision, and surface roughness of the part manufactured using this air cyclone machining method met design requirements. By controlling the tool path and process parameters, manual polishing of blades and flow channels was eliminated, reducing machining time by 75% and ensuring consistent air flow.

Claims

1. A method for processing an aircraft engine air cyclone, characterized in that: The specific steps include: Step 1: Determine the processing equipment; Step 2: Determine the process route; The processing route in step 2 is: turning the outer circle → drilling the axial hole → fine turning the outer circle → fine boring → turning the hemispherical head → milling the blade shape → turning the other hemispherical head → cutting → inspection; Step 3: Determine the processing strategy and tool path; In the step 3, a fixed cutter axis milling strategy is adopted, the cutter axis direction is always in the Z direction, and four milling cutters of different diameters are set to perform rough milling of the blade profile, fine milling of the blade profile, fine milling of the blade side, and root cleaning respectively; The rough milling blade profile trajectory is as follows: on the cylinder with a diameter of 21.3mm in the rotating part of the part, the blade profile on both sides is a closed curve formed by two curves with the radius of the milling cutter and the connecting curve of the two curves; The tool path for fine milling the blade profile is: on the cylinder with a diameter of 16.61mm on the rotating part of the part, there are two curves with the radius of the milling cutter at the distance from the blade profile on both sides, and a closed curve formed by the connecting curve of the two curves; The tool path for fine milling the blade side is: on the cylinder with a diameter of 10.61mm in the rotating part of the part, the blade body profile on both sides is a closed curve formed by two curves with the radius of the milling cutter and the connecting curve of the two curves; The root cleaning trajectory is: on the cylinder with a diameter of 10.61mm in the rotating part of the part, the blade surfaces on both sides are The closed curve formed by the two curves of the milling cutter radius distance and the connecting curve of the two; Step 4: Determine the machining tool and allowance allocation; In the step 4, the specific processing scheme is: ① Rough milling of blade profile: Use 3mm ball cutter to rough open the flow channel, that is, the diameter of the flow channel is milled from 21.3mm to 16.5mm, and the milling is divided into 3 layers along the diameter direction, with a milling depth of 0.8mm per layer; ② Fine milling of blade profile: Use 1.6mm ball cutter to further remove the allowance, that is, the diameter of the milling flow channel is milled from 16.61mm to 10.61mm, and the milling is divided into 10 layers along the diameter direction, with a milling depth of 0.3mm per layer; ③ Fine milling of blade side: Use the side edge of a 1.5mm end cutter to fine mill the blade side to ensure the blade thickness accuracy and surface roughness; ④ Root cleaning: Use Φ1mm ball cutter to clean the root to Φ10.61mm, and mill the side path in 5 layers perpendicular to the blade body. The milling depth of each layer is 0.1mm to ensure the design fillet size requirements; Step 5: Determine the programming method; Step 6: Determine the NC program and parameterized variables; Step 7: Determine process parameters and process verification.

2. The method for machining an aircraft engine air swirler according to claim 1, characterized in that: In the step 1, a turning-milling composite machining center is selected to complete all the turning, milling and drilling processes through one clamping. The outer surface of the part and the outer circle of the blade, including the ball head part, are machined by turning, and the blade part is machined by milling.

3. The method for machining an aircraft engine air swirler according to claim 1, characterized in that: In the step 5, a macro program based on trigonometric functions is used to compile a CNC machining program, and a parametric program is compiled with the X coordinate of the cutting position as the independent variable and the Y and Z coordinates as the dependent variables. At the same time, the number of C-axis rotations and the number of milling layers are set as variables.

4. The method for machining an aircraft engine air swirler according to claim 1, characterized in that: In step six, the IF[LT]GOTO statement is used to compile a single-layer interpolation program, and the Y and Z coordinates move as the X coordinate moves; the IF[GE]GOTO statement is used to compile an angle rotation and layer number control program to perform layered milling at each diameter position; the blade width, thickness and rotary axis angle, tool diameter, flow channel bottom diameter, outer diameter basic dimensions, as well as the number of blades and the number of milling layers are set as parameterized variables.

5. The method for machining an aircraft engine air swirler according to claim 1, characterized in that: In the step seven, the process parameters for milling the blade and the flow channel surface, namely, the spindle speed, feed speed, and cutting depth, are determined. Specifically, the rough milling blade process is: spindle speed 3000-3600 r / min, feed speed 35-40 mm / min, and cutting depth 0.8 mm; the fine milling blade process is: spindle speed 5500-6500 r / min, feed speed 45-50 mm / min, and cutting depth 0.3 mm; the fine milling blade side process is: spindle speed 4000-4800 r / min, feed speed 30-35 mm / min; the root cleaning process is: spindle speed 4500-5500 r / min, feed speed 20-25 mm / min, and cutting depth 0.1 mm.

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