A method for machining a shaft rotor of an aviation turbine engine transmission part

Abstract

The present invention relates to the technical field of shaft rotor processing, and specifically to a method for processing a shaft rotor of an aviation turbine engine transmission part, comprising the following steps: first, preparing materials and preparing an alloy forging blank; second, rough turning the overall contour of the blank: using a common lathe to rough turn the contour of the axle rotor, specifically including turning the end face, turning the outer circle of the long axis end of the axle rotor, turning the outer circle of the step shaft at the long axis end, turning the end face on the other side, and turning the outer circle of the short axis of the axle rotor while taking into account the total length; third, semi-finishing turning the overall contour and drilling the top hole of the shaft rotor: turning the two end faces of the axle rotor to ensure the total length, drilling the top holes at both ends of the shaft rotor, turning the outer circle of the step shaft at the long axis end of the axle rotor, the outer circle of the axle rotor wheel disc, the axle rotor wheel disc step, and the outer circle of the short axis of the axle rotor; and fifth, electric spark grooving, using an electric spark cutting machine to pre-process electrodes as required, so as to be able to process shaft rotors with slender rod structures and small blade gaps, ensure the shape and position tolerances of the blades, have no chatter marks on the blade surface, and reduce the product scrap rate.

Description

Technical Field

[0001] The present invention relates to the technical field of shaft and rotor processing, and in particular to a method for processing a shaft and rotor of a transmission part of an aviation turbine engine. Background Art

[0002] Currently, the various key components of domestic aviation turbine engines vary in material, shape, and processing precision, which results in a wide range of processing methods. The shaft rotor, the primary transmission component of the turbine pump of an aviation turbine engine, is made of high-temperature alloy Class II forgings. It operates at a maximum speed of 50,000 r / min and has a slender rod structure with an aspect ratio of 18:1. It is equipped with 30 blades with small gaps between the blades and a surface roughness of Ra0.8. High dynamic balance requirements are required at high speeds. Due to its slender rod structure and small gaps between the blades, the workpiece support strength of the tooling is weakened during machining. Furthermore, the high hardness of the high-temperature alloy forgings places high demands on the machining tools. This leads to severe tool retraction during machining, unstable blade dimensions, and the formation of vibration marks on the blade surface, which affects machining quality. Summary of the Invention

[0003] Therefore, the technical problem to be solved by the present invention is to overcome the problems in the prior art of serious tool slippage during shaft rotor processing, unstable blade processing dimensions, and easy formation of vibration marks on the blade surface, which affect the processing quality, thereby providing a method for processing shaft rotors of transmission parts of aviation turbine engines.

[0004] In order to solve the above technical problems, the present invention provides a method for processing the shaft rotor of an aviation turbine engine transmission part, comprising the following steps: Step 1, material preparation, the blank is an alloy forging; Step 2, rough turning the overall contour of the blank: using an ordinary lathe to rough turn the contour of the axle rotor, specifically including turning the end face, turning the outer circle of the long axis end of the axle rotor, turning the outer circle of the step shaft at the long axis end, turning the other side end face, and turning the outer circle of the short axis of the axle rotor taking into account the total length; Step 3, semi-finishing the overall contour, drilling the top hole of the shaft rotor: turning the two end faces of the axle rotor to ensure the total length, drilling the top holes at both ends of the shaft rotor, turning the outer circle of the step shaft at the long axis end of the axle rotor, the outer circle of the axle rotor wheel disc, and the outer circle of the short axis of the axle rotor; Step 4 , engrave the sequence number, engrave the flow sequence number at the fixed place, so that the inspection records correspond one to one; Step 5, EDM grooving, use the EDM cutting machine, pre-process the electrode as required, use the auxiliary alignment tool to align, and cut 30 grooves on the outer circle of the shaft rotor disc to form the blade; Step 6, rough and fine milling of the blade profile, use the five-axis CNC machining center to rough and fine mill the blades on the shaft rotor until they are qualified, use the auxiliary alignment tool to align before machining, the specific steps are: A, trial cutting, during the trial cutting, cut a blade with a radial depth of 0.2mm at the outer edge end face of the blade profile, and according to the relative position of the blade profile in the rough milling blade profile after the trial cutting, rotate the shaft rotor for fine adjustment to ensure Each blade profile can be completely processed; B, rough milling wall, C, semi-finishing milling inner back arc, D, finishing milling inner back arc, E, finishing milling wall, F, bottom sweeping; step seven, clamp repair, remove burrs, clamp repair blade profile, polish surface; step eight, rough grinding shaft rotor disc outer circle; step nine, finish turning shaft rotor disc outer circle contour; step ten, rough grinding shaft rotor long shaft end outer circle, double center hole positioning; step eleven, CNC milling shaft rotor long shaft end keyway; step twelve, grinding shaft rotor long shaft end thread; step thirteen, finish grinding shaft rotor long shaft end, short shaft end and disc outer circle size; step fourteen, turning the outer circle of the long shaft close to the disc and the shaft rotor disc transition arc, and polishing the turned part The surface roughness of the outer circle and the surface of the transition arc of the shaft rotor disc is Ra0.1; Step 15, use the laser method to engrave the mark, batch number-product serial number; Step 16, wire cutting to cut off the process head part of the long axis end face of the shaft rotor to ensure the size is qualified; Step 17, turn the tapered surface of the long axis end of the axle rotor, pay attention to protecting the processed surface; Step 18, wire cutting the short axis end of the shaft rotor, find the correct direction, cut it flat, and ensure the size; Step 19, pliers repair, sharp edges blunt; Step 20, fluorescent inspection, perform fluorescent inspection on the shaft rotor, no cracks are allowed on the surface; Step 21, final inspection, check all dimensions according to the drawing and check the appearance quality; Step 22, put into storage after passing the inspection.

[0005] Furthermore, in step six, the tool for semi-finishing milling of the inner back arc and finishing milling of the inner back arc is a cone-shaped ball milling cutter with a diameter of 2.4 mm based on the distribution of the 30 blades.

[0006] Furthermore, the taper of the cone-ball milling cutter is 4°.

[0007] Furthermore, in step three, the overall contour is semi-finished and a top hole is drilled. Top holes are drilled at both ends of the shaft rotor, one end of the shaft rotor is retained, and the other end is the process top hole; wherein, the process top hole is cut off in step sixteen.

[0008] Furthermore, the auxiliary alignment tooling of step five and step six is the same tooling. The auxiliary alignment tooling and the shaft rotor are assembled before step five. After step six is completed and inspected to be qualified, the auxiliary alignment tooling is removed.

[0009] Furthermore, in step thirteen, when fine-grinding the long shaft end, short shaft end, and outer diameter of the wheel disc, the temperature of the workshop processing site is 20±2℃, the abnormal clearance of the machine tool is reduced, the rigidity of the machine tool is increased, the grinding wheel is ground frequently to keep it sharp, and care is taken not to scratch the surface of the workpiece during measurement. After processing, the workpiece is placed in a special turnover box.

[0010] Furthermore, in step seven, the roughness of the polished surface is Ra1.6.

[0011] Furthermore, in step eighteen, the short shaft end of the shaft rotor is cut by wire, the axis of the shaft rotor is aligned to be parallel to the wire cutting direction, and the short shaft end is cut flat to ensure the size.

[0012] Furthermore, in step nineteen, the radius of the sharp edge is rounded to R0.2~R0.3.

[0013] Furthermore, there is a corresponding workpiece inspection process after each processing sequence is completed.

[0014] The technical solution of the present invention has the following advantages:

[0015] The invention provides a method for machining the shaft rotor of an aviation turbine engine transmission part, comprising the following steps: Step 1, material preparation, the blank is an alloy forging; Step 2, rough turning the overall contour of the blank: using a common lathe to rough turn the contour of the axle rotor, specifically including turning the end face, turning the outer circle of the long axis end of the axle rotor, turning the outer circle of the step shaft at the long axis end, turning the end face on the other side, and turning the outer circle of the short axis of the axle rotor while taking into account the total length; Step 3, semi-finishing the overall contour, drilling the top hole of the shaft rotor: turning the two end faces of the axle rotor to ensure the total length, drilling the top holes at both ends of the shaft rotor, turning the outer circle of the step shaft at the long axis end of the axle rotor, the outer circle of the axle rotor wheel disc, and the outer circle of the short axis of the axle rotor; Step 4, engraving the sequence number, and engraving it at the fixed position. The flow sequence number is used to ensure that the inspection records are one-to-one corresponding; Step 5, EDM grooving, using an EDM cutting machine, pre-process the electrode as required, use the auxiliary alignment tool to align, and cut 30 grooves on the outer circle of the shaft rotor disc to form the blade; Step 6, rough and fine milling of the blade profile, using a five-axis CNC machining center to rough and fine mill the blade on the shaft rotor until it is qualified, and use the auxiliary alignment tool to align before processing. The specific steps are: A, trial cutting, during the trial cutting, a blade (5) with a radial depth of 0.2mm is cut out at the outer edge end face of the blade (5), and the shaft rotor is rotated and fine-tuned according to the relative position of the blade profile in the rough-milled blade profile after the trial cutting, so as to ensure that each The blade profile can be completely processed; B, rough milling wall, C, semi-finishing milling inner back arc, D, fine milling inner back arc, E, fine milling wall, F, bottom sweeping; step seven, clamp repair, remove burrs, clamp repair blade profile, polish surface; step eight, rough grinding shaft rotor disc outer circle; step nine, fine turning shaft rotor disc outer circle contour; step ten, rough grinding shaft rotor long shaft end outer circle, double center hole positioning; step eleven, CNC milling shaft rotor long shaft end keyway; step twelve, grinding shaft rotor long shaft end thread; step thirteen, fine grinding shaft rotor long shaft end, short shaft end and disc outer circle size; step fourteen, turning the transition arc between the outer circle of the long shaft close to the disc and the shaft rotor disc, and polishing the turned part outer circle The surface of the shaft rotor and the surface of the transition arc of the shaft rotor disc have a surface roughness of Ra0.1; Step 15, use the laser method to engrave the mark, batch number-product serial number; Step 16, wire cutting to cut off the process head part of the shaft rotor long axis end face to ensure that the size is qualified; Step 17, the conical surface of the long axis end of the axle rotor, pay attention to protecting the processed surface; Step 18, wire cutting the short axis end of the shaft rotor, find the correct direction, cut flat, and ensure the size; Step 19, pliers repair, sharp edges blunt; Step 20, fluorescent inspection, perform fluorescent inspection on the shaft rotor, no cracks are allowed on the surface; Step 21, final inspection, check all dimensions according to the drawing and check the appearance quality; Step 22, put into storage after passing the inspection.

[0016] This method for machining a shaft rotor, a transmission component for an aviation turbine engine, includes a verification step involving trial cutting a 0.2mm-deep groove on the blade end. This step is added because, in actual machining, blade profile defects often occur after blade machining, resulting in scrap. After the trial cut, the position of the cut profile within the end face blade profile is observed. Ideally, the position should be centered. If the deviation is too large, the zero offset of the rotary axis is rotated a certain angle to correct the resulting scrap. This also ensures uniform margins around the shaft rotor blade during machining, reduces tool deflection, and ensures a uniform blade profile after machining, ensuring dimensional accuracy and blade profile that meet technical requirements. This measure significantly reduces the scrap rate. Because the blade disc profile retains a process margin, the portion removed during the trial cut is ultimately removed without affecting quality. In step six, the tool selection for the semi-finishing inner back arc (C) and the finishing inner back arc (D) is based on the distribution of the 30 blades, ensuring both machining accuracy requirements and the relative positional relationships between the blades. Therefore, after the above steps, the method for processing the shaft rotor of the transmission parts of the aviation turbine engine can process the shaft rotor with a slender rod structure and a small blade gap. The blade shape and position tolerances are guaranteed, there are no chatter marks on the blade surface, and the product scrap rate is greatly reduced.

[0017] This Summary is provided to introduce a selection of concepts in a simplified form that are further described below in the Detailed Description. This Summary is not intended to identify key features or essential features of the disclosure, nor is it intended to limit the scope of the disclosure. BRIEF DESCRIPTION OF THE DRAWINGS

[0018] In order to more clearly illustrate the specific embodiments of the present invention or the technical solutions in the prior art, the following briefly introduces the drawings required for use in the specific embodiments or the description of the prior art. Obviously, the drawings described below are some embodiments of the present invention. For ordinary technicians in this field, other drawings can be obtained based on these drawings without paying any creative work.

[0019] Figure 1 The present invention provides a flow chart of the method for machining the shaft rotor of an aviation turbine engine transmission part.

[0020] Figure 2 This is a schematic diagram of the outline of the semi-finished rear axle rotor;

[0021] Figure 3 This is a schematic diagram of the structure of the auxiliary alignment tool used for EDM and CNC rough and fine milling of blade profiles;

[0022] Figure 4 This is a schematic diagram of the shaft rotor structure of an aviation turbine engine transmission part using the shaft rotor processing method provided by the present invention;

[0023] Figure 5 The present invention provides a front view of a shaft rotor used in the method for machining the shaft rotor of an aviation turbine engine transmission part.

[0024] Description of reference numerals:

[0025] 1. Long axis end of the shaft rotor; 2. Step; 3. Disc; 4. Short axis end of the shaft rotor; 5. Blade. DETAILED DESCRIPTION

[0026] Hereinafter, only certain exemplary embodiments are briefly described. As will be appreciated by those skilled in the art, the described embodiments may be modified in various ways without departing from the spirit or scope of the present disclosure. Therefore, the drawings and description are to be considered as illustrative in nature and not restrictive.

[0027] In the description of the present disclosure, it should be understood that the terms "center," "longitudinal," "transverse," "length," "width," "thickness," "up," "down," "front," "back," "left," "right," "vertical," "horizontal," "top," "bottom," "inside," "outside," "clockwise," "counterclockwise," and the like, indicating positions or relationships, are based on the positions or relationships shown in the accompanying drawings and are intended solely for the purpose of facilitating the description of the present disclosure and simplifying the description. They do not indicate or imply that the devices or components referred to must have a specific orientation, be constructed, or operate in a specific orientation, and therefore should not be construed as limiting the present disclosure. Furthermore, the terms "first" and "second" are used for descriptive purposes only and should not be construed as indicating or implying relative importance or implicitly specifying the number of the technical features indicated. Thus, features defined as "first" or "second" may explicitly or implicitly include one or more of the described features. In the description of the present disclosure, "plurality" means two or more, unless otherwise expressly and specifically defined.

[0028] In the description of this disclosure, it should be noted that, unless otherwise expressly specified or limited, the terms "installed," "connected," and "connected" should be understood broadly. For example, they can refer to fixed, removable, or integral connections; mechanical, electrical, or intercommunication connections; direct or indirect connections through an intermediary; and internal communication between two components or interaction between two components. Those skilled in the art will understand the specific meanings of these terms in this disclosure based on specific circumstances.

[0029] In this disclosure, unless otherwise expressly specified or limited, a first feature being "above" or "below" a second feature may include the first and second features being in direct contact, or may include the first and second features not being in direct contact but being in contact via another feature between them. Furthermore, a first feature being "above," "above," and "above" a second feature may include the first feature being directly above or diagonally above the second feature, or may simply mean that the first feature is at a higher level than the second feature. A first feature being "below," "below," and "below" a second feature may include the first feature being directly above or diagonally above the second feature, or may simply mean that the first feature is at a lower level than the second feature.

[0030] The disclosure below provides many different embodiments or examples for realizing different structures of the present disclosure. In order to simplify the disclosure of the present disclosure, the components and settings of specific examples are described below. Of course, they are merely examples and are not intended to limit the present disclosure. In addition, the present disclosure may repeat reference numbers and / or reference letters in different examples, and such repetition is for the purpose of simplicity and clarity and does not in itself indicate the relationship between the various embodiments and / or settings discussed. In addition, the present disclosure provides examples of various specific processes and materials, but those of ordinary skill in the art will appreciate the application of other processes and / or the use of other materials.

[0031] The preferred embodiments of the present disclosure are described below in conjunction with the accompanying drawings. It should be understood that the preferred embodiments described herein are only used to illustrate and explain the present disclosure, and are not used to limit the present disclosure.

[0032] See also Figures 1 to 5As shown, the present invention provides a method for processing the shaft rotor of an aviation turbine engine transmission part, comprising the following steps: Step 1, material preparation, the blank is an alloy forging; Step 2, rough turning the overall contour of the blank: using a common lathe to rough turn the contour of the axle rotor, specifically including turning the end face, turning the outer circle 1 of the long axis end of the axle rotor, turning the outer circle of the step 2 of the long axis end, turning the end face on the other side, and turning the outer circle of the short axis of the axle rotor taking into account the total length; Step 3, semi-finishing the overall contour, drilling the top hole of the shaft rotor: turning the two end faces of the axle rotor to ensure the total length, drilling the top holes at both ends of the shaft rotor, turning the outer circle of the step 2 of the long axis end of the axle rotor, the outer circle of the axle rotor wheel disc, and the outer circle of the short axis of the axle rotor; Step 4, engraving the sequence number, in The flow sequence number is engraved at the fixed place so that the inspection records correspond one to one; Step 5, EDM grooving, use the EDM cutting machine to pre-process the electrode as required, use the auxiliary alignment tool to align, and cut 30 grooves on the outer circle of the shaft rotor disc to form blades 5; Step 6, rough and fine milling of the blade 5, use the five-axis CNC machining center to rough and fine mill the blade 5 on the shaft rotor until it is qualified, use the auxiliary alignment tool to align before machining, the specific steps are: A, trial cutting, during the trial cutting, cut a blade 5 with a radial depth of 0.2mm at the outer edge end face of the blade 5, and according to the relative position of the blade shape after the trial cutting in the blade shape of the rough milled blade, rotate the shaft rotor for fine adjustment to ensure that each blade The shape can be completely processed; B, rough milling wall, C, semi-finishing milling inner back arc, D, fine milling inner back arc, E, fine milling wall, F, sweeping the bottom; Step 7, clamp repair, remove burrs, clamp repair blade shape, polish the surface; Step 8, rough grinding the outer circle of the shaft rotor disc; Step 9, fine turning the outer circle contour of the shaft on both sides of the shaft rotor disc; Step 10, rough grinding the outer circle of the long shaft end of the shaft rotor, double center hole positioning; Step 11, CNC milling of the long shaft end 1 keyway of the shaft rotor; Step 12, grinding the long shaft end 1 thread of the shaft rotor; Step 13, fine grinding the long shaft end 1 of the shaft rotor, the short shaft end and the outer circle size of the disc; Step 14, turning the transition arc between the outer circle of the long shaft close to the disc and the shaft rotor disc, and polishing the outer circle of the turned part The surface roughness of the circle and the surface of the transition arc of the shaft rotor disc is Ra0.1; Step 15, use the laser method to engrave the mark, batch number-product serial number; Step 16, wire cutting to cut off the process head part of the long axis end of the shaft rotor to ensure the size is qualified; Step 17, the conical surface of the long axis end of the axle rotor 1, pay attention to protect the processed surface; Step 18, wire cutting the short axis end of the shaft rotor 4, find the correct direction, cut flat, and ensure the size; Step 19, pliers repair, sharp edges blunt; Step 20, fluorescent inspection, perform fluorescent inspection on the shaft rotor, no cracks are allowed on the surface; Step 21, final inspection, check all dimensions according to the drawing and check the appearance quality; Step 22, put into storage after passing the inspection.

[0033] This method for machining a shaft rotor, a transmission component for an aviation turbine engine, includes a verification step of trial-cutting a 0.2mm-deep groove on the end face of the blade 5 to verify the cross-sectional profile of the blade 5. This step is added because, in actual machining, blade 5 often suffers from imperfections in its profile after machining, resulting in scrap. After the trial cut, the position of the cut profile within the end face blade profile is observed. Ideally, it should be centered. If the deviation is too large, the zero offset of the rotary axis is rotated by a certain angle to correct the resulting scrap. This also ensures uniform margins around the shaft rotor blade 5 during machining, reduces tool deflection, and ensures a uniform blade profile after machining, ensuring dimensional accuracy and blade 5 profile that meet technical requirements. This measure significantly reduces the scrap rate. Because the blade disc profile retains a process margin, any portions removed during the trial cut are ultimately removed without affecting quality. In step six, the tool selection for the semi-finishing milling of the inner back arc (C) and the finishing milling of the inner back arc (D) is based on the distribution of the 30 blades 5, ensuring both machining accuracy requirements and the relative positional relationships between the blades 5. Therefore, after the above steps, the method for processing the shaft rotor of the transmission parts of the aviation turbine engine can process the shaft rotor with a slender rod structure and a small gap between the blades 5. The shape and position tolerances of the blades 5 are guaranteed, there are no chatter marks on the surface of the blades 5, and the product scrap rate is greatly reduced.

[0034] The rotor blades produced using this machining method are evenly distributed around the circumference, with a distribution error of no more than ±10°. The impeller profile deviation of the centrifugal impeller produced using this machining method is no more than ±0.05mm, and the surface roughness of the blades is Ra1.6. This machining method can achieve extremely high dynamic balance, dimensional accuracy, and geometric tolerance requirements.

[0035] Specifically, in step six, the tools used for semi-finishing and finishing the inner back arc are 2.4mm diameter cone-shaped ball milling cutters with a taper of 4°, based on the distribution of the 30 blades 5. This configuration maximizes tool strength and minimizes tool breakage, tool breakage, and surface chatter marks on the blades 5, ensuring greater dimensional accuracy.

[0036] In some optional embodiments, in step three, the overall contour is semi-finished, and a top hole is drilled. Top holes are drilled at both ends of the shaft rotor, one end of the shaft rotor is retained, and the other end is the process top hole; wherein, the process top hole is cut off in step sixteen.

[0037] In some optional embodiments, the auxiliary alignment tooling of steps five and six is the same tooling, and the auxiliary alignment tooling and the shaft rotor are assembled before step five. After step six is completed and inspected and passed, the auxiliary alignment tooling is removed, and alignment is performed according to the auxiliary alignment tooling to ensure consistency in the relative positions of the cut grooves and the alignment tooling, and 30 grooves are cut.

[0038] In some optional embodiments, in step thirteen, when fine-grinding the long axis end 1, the short axis end, and the outer diameter of the wheel disc of the shaft rotor, the double center hole is positioned, the first piece is trial-cut to select a suitable grinding wheel, and the processing is strictly carried out in accordance with the processing sequence. The workshop processing site temperature is 20±2°C, the abnormal clearance of the machine tool is reduced, the rigidity of the machine tool is increased, the grinding wheel is ground frequently to keep it sharp, and care is taken not to scratch the surface of the workpiece during measurement. After processing, the workpiece is placed in a special turnover box.

[0039] Wherein, in step seven, the roughness of the polished surface is Ra1.6.

[0040] In some optional embodiments, in step seventeen, the long shaft end 1 of the axle rotor is tapered, threaded, the short shaft end is positioned with a top, and the long shaft end is clamped with soft claws, paying attention to protecting the processed surface.

[0041] In step eighteen, the short shaft end 4 of the shaft rotor is cut by wire, the axis of the shaft rotor is aligned to be parallel to the wire cutting direction, and the short shaft end 4 is cut flat to ensure the size.

[0042] In step 19, the radius of the sharp edge is rounded to R0.2~R0.3.

[0043] After each of the above processing sequences is completed, there is a corresponding workpiece inspection process. The key dimensions of key parts are measured using a three-coordinate machine, and key processes require 100% inspection.

[0044] Obviously, the above embodiments are merely examples for clarity of explanation and are not intended to limit the implementation methods. Those skilled in the art will readily appreciate that other variations or modifications based on the above descriptions are possible. It is not necessary and impossible to enumerate all implementation methods here. Obvious variations or modifications arising therefrom remain within the scope of protection of the present invention.

Claims

1. A method for machining a shaft rotor of an aviation turbine engine transmission part, characterized in that: The following steps are involved: Step 1: Prepare the material and the blank is an alloy forging; Step 2: Rough turning the overall outline of the blank: Use a common lathe to rough turn the axle rotor outline, specifically including turning the end face, turning the outer circle of the axle rotor's long axis end (1), turning the outer circle of the long axis end step (2), turning the other side end face, and turning the outer circle of the axle rotor's short axis taking into account the total length; Step 3: Semi-finish turning the overall contour, drilling the top hole of the shaft rotor: turning the two end faces of the shaft rotor to ensure the total length, drilling the top holes at both ends of the shaft rotor, the step (2) of the long shaft end of the shaft rotor, the outer circle of the axle rotor wheel, and the outer circle of the short shaft of the axle rotor; Step 4: Carve the sequence number. Carve the flow sequence number at a fixed location to ensure one-to-one correspondence between the inspection records. Step 5: Electric spark cutting: Use an electric spark cutting machine to pre-process the electrode as required, use an auxiliary alignment tool to align it, and cut 30 grooves on the outer circle of the shaft rotor disc to form blades (5); Step 6: Rough and fine milling of the blade (5) blade shape, using a five-axis CNC machining center to rough and fine mill the blade (5) on the rotor shaft until it is qualified, and before machining, use auxiliary alignment tooling to align it. The specific steps are as follows: A. Trial cutting: During the trial cutting, a blade (5) with a radial depth of 0.2 mm is cut out at the outer edge end surface of the blade (5). According to the relative position of the blade after the trial cutting in the blade profile of the rough milling blade, the shaft rotor is rotated and fine-tuned to ensure that each blade profile can be completely processed; B, rough milling wall, C, semi-finishing milling inner back arc, D, finishing milling inner back arc, E, finishing milling wall, F, bottom sweeping; Step 7: Clamp and trim, remove burrs, trim blade shape, and polish the surface; Step 8: Roughly grind the outer circle of the shaft rotor disc; Step 9: Fine turning the outer contours of the shafts on both sides of the axle rotor disc; Step 10: Roughly grind the outer circle of the long axis end of the shaft rotor and position the double center holes; Step 11, CNC milling spindle rotor long axis end (1) keyway; Step 12: Grind the threads of the long shaft end (1) of the rotor; Step 13: Finely grind the dimensions of the long axis end (1), the short axis end and the outer diameter of the wheel disc of the shaft rotor; Step 14: Turn the outer circle of the long shaft close to the wheel disc and the transition arc between the shaft rotor wheel disc, and polish the surface of the turned outer circle and the surface of the transition arc of the shaft rotor wheel disc, with the surface roughness being Ra0.1; Step 15: Use laser to engrave the batch number and product serial number; Step 16: Cut off the process head portion of the long axis end (1) of the shaft rotor by wire cutting to ensure the size is qualified; Step 17: Taper the long axis end (1) of the axle rotor, taking care to protect the machined surface; Step 18: Cut the short shaft end (4) of the shaft rotor by wire cutting, find the correct direction, cut flat, and ensure the size; Step 19: Pliers and trim the sharp edges; Step 20: Fluorescence inspection: perform fluorescence inspection on the shaft rotor. No cracks are allowed on the surface. Step 21: Final inspection: check all dimensions according to the drawings and inspect the appearance quality; Step 22: Put the goods into storage after inspection.

2. The method for machining the shaft and rotor of an aviation turbine engine transmission part according to claim 1, characterized in that: In step 6, the tool for semi-finishing milling of the inner back arc and finishing milling of the inner back arc is a cone ball milling cutter with a diameter of 2.4 mm according to the distribution of the 30 blades (5).

3. The method for machining the shaft and rotor of an aviation turbine engine transmission part according to claim 2, characterized in that: The taper of the cone ball milling cutter is 4°.

4. The method for machining a shaft rotor of an aviation turbine engine transmission part according to any one of claims 1 to 3, characterized in that: Step 3: Semi-finish turning the overall contour, drilling the top hole, drilling the top hole at both ends of the shaft rotor, retaining one end of the shaft rotor and the other end as the process top hole; wherein, the process top hole is cut off in step 16.

5. The method for machining the shaft and rotor of an aviation turbine engine transmission part according to claim 4, characterized in that: The auxiliary alignment tooling in steps five and six is the same tooling. Before step five, the auxiliary alignment tooling and the shaft rotor are assembled. After step six is completed and inspected to be qualified, the auxiliary alignment tooling is removed.

6. The method for machining the shaft and rotor of an aviation turbine engine transmission part according to claim 5, characterized in that: Step 13: When fine-grinding the long axis end (1) and short axis end of the shaft rotor and the outer diameter of the wheel, the workshop processing site temperature is 20±2℃, reduce the abnormal clearance of the machine tool, increase the rigidity of the machine tool, grind the grinding wheel frequently, keep the grinding wheel sharp, and be careful not to scratch the surface of the workpiece when measuring. After processing, the workpiece is placed in a special turnover box.

7. The method for machining the shaft and rotor of an aviation turbine engine transmission part according to claim 6, characterized in that: In step seven, the roughness of the polished surface is Ra1.

6.

8. The method for machining the shaft and rotor of an aviation turbine engine transmission part according to claim 6, characterized in that: In step eighteen, the short shaft end (4) of the shaft rotor is cut by wire, the axis of the shaft rotor is aligned to be parallel to the wire cutting direction, and the short shaft end (4) is cut flat to ensure the size.

9. The method for machining a shaft rotor of an aviation turbine engine transmission part according to any one of claims 5 to 8, characterized in that: In step 19, the radius of the sharp edge is rounded to R0.2~R0.

3.

10. The method for machining the shaft and rotor of an aviation turbine engine transmission part according to claim 9, characterized in that: After each processing sequence is completed, there is a corresponding workpiece inspection process.

Images