A processing method for large-size aircraft engine precision retaining ring

Abstract

The present invention discloses a method for processing large-sized precision retaining rings for aircraft engines, comprising the steps of blanking, rolling, polishing and welding, vacuum heat setting, wire cutting, pickling, machining contouring, magnetic flaw detection, and chemical passivation. Rectangular sheet materials are used for blanking, vacuum heat setting is performed to obtain the required hardness of the precision retaining ring and to calibrate the roundness, wire cutting is performed to obtain a precision retaining ring intermediate piece that meets the flatness and parallelism requirements, pickling is performed to obtain the required thickness and surface roughness, machining is performed to obtain the final contour dimensions, and finally flaw detection and surface passivation treatment are performed. The processing method of the present invention can not only significantly reduce the loss of raw materials, but also ensure the dimensional accuracy of the precision retaining ring, and has a wide range of applications.

Description

Technical Field

[0001] The invention belongs to the field of mechanical processing, and in particular relates to a processing method for a large-size precision clamping ring. Background Art

[0002] A snap ring is a device used to fix mechanical parts in an aircraft engine. Its structure is as follows: Figure 1 As shown, it is a precision annular part with an outer diameter of The width is B, the flatness is 0.3mm, the parallelism is 0.03mm, the material thickness is C, the surface roughness is Ra0.8, and the hardness must also be guaranteed.

[0003] At present, there are three main processing solutions for this type of precision retaining ring:

[0004] The first method uses a plate with a thickness of C to cut and process to obtain a circular precision clamping ring, but the flatness size after cutting is difficult to guarantee, and a large amount of raw material in the middle of the ring material is wasted during the cutting process.

[0005] The second method is to use bar processing, cut the bar into sheets, and then remove the middle circular part to obtain the ring part, but this method also has the problem of a large amount of raw materials being wasted.

[0006] The third method is to use pipe processing. However, because there are no thin-walled pipes of such large sizes on the current market, they need to be customized, resulting in high material procurement costs.

[0007] After searching, apart from the three processing ideas mentioned above, no public literature has been found on other processing methods for this type of large-sized aircraft engine precision retaining rings. Summary of the Invention

[0008] The present invention aims to provide a method for processing a large-sized aircraft engine precision retaining ring, which can reduce the waste of raw materials and ensure the processing accuracy of the part size.

[0009] To achieve the above object, the present invention adopts the following technical solutions:

[0010] A method for processing a large-sized aircraft engine precision retaining ring comprises the following steps:

[0011] S1, blanking, using rectangular plate, the thickness of the plate is greater than the width of the precision clamping ring, and the width of the plate is greater than the thickness of the precision clamping ring;

[0012] S2, rolling, rolling the rectangular plate in S1 along the length direction;

[0013] S3, polishing and welding, polishing the two ends of the rectangular plate in the length direction after being rolled in S2, and then splicing and welding them into a ring-shaped part;

[0014] S4, vacuum heat setting, heating the ring part in S3 under vacuum environment, expanding the ring part from the inner ring surface outward, ensuring the hardness of the ring part while aligning the ring part;

[0015] S5, wire cutting, cutting the ring in S4 along a plane perpendicular to the axis of the ring to obtain at least one precision clamping ring intermediate part while ensuring the flatness and parallelism of the two axial end faces of the ring;

[0016] S6, pickling, pickling the precision clamping ring intermediate obtained in S5 to remove the ablation layer on its surface and ensure that its surface roughness meets the requirements;

[0017] S7, machining the shape, machining the precision clamping ring intermediate piece after pickling in S6 according to the requirements of the precision clamping ring part drawing, and obtaining a precision clamping ring with the shape dimensions and characteristic structure in the part drawing;

[0018] S8, magnetic flaw detection, checks whether the precision retaining ring in S7 has defects;

[0019] S9, chemical passivation, performs surface chemical passivation treatment on the precision clamping ring that does not have defects in S8.

[0020] As an option, in S2, a roller bed is used to roll the rectangular sheet material in S1.

[0021] As an option, in S4, a heat setting mold is used for heating under a vacuum environment. The heat setting mold includes a cylindrical surface for inserting the inner ring of the annular part in S3, and the thermal expansion linear velocity of the material of the heat setting mold is greater than the thermal expansion linear velocity of the rectangular sheet in S1.

[0022] As an option, in S6, the middle of the precision snap ring is pickled to obtain the thickness required by the precision snap ring part drawing.

[0023] As an option, in S7, the inner and outer surfaces of the precision snap ring intermediate part after pickling in S6 are machined according to the requirements of the precision snap ring part drawing to ensure that the outer diameter and width required by the precision snap ring part drawing are obtained, and the notch required by the precision snap ring part drawing is machined along the weld position in S3.

[0024] Compared with the existing technology, the processing method provided by the present invention greatly reduces the waste of raw materials compared to parts processed by traditional solutions (such as circular cutting on sheet materials and processing using rods), while ensuring the processing accuracy of the precision retaining ring size.

[0025] Compared with the prior art, the processing method provided by the present invention is more reliable, and the processed precision clamping rings have better consistency and higher quality. BRIEF DESCRIPTION OF THE DRAWINGS

[0026] Figure 1 This is a schematic diagram of the parts structure of a large-sized aircraft engine precision retaining ring;

[0027] Figure 2 Schematic diagram of the wool material;

[0028] Figure 3 This is a schematic diagram of coil welding;

[0029] Figure 4 Schematic diagram of heat setting;

[0030] Figure 5 This is a schematic diagram of wire cutting;

[0031] Figure 6 This is a schematic diagram of the machined appearance. DETAILED DESCRIPTION

[0032] The present invention is further described below with reference to specific embodiments. However, it should not be understood that the scope of the subject matter described in the present invention is limited to the following embodiments. Without departing from the above technical ideas of the present invention, various modifications, substitutions and changes made according to common technical knowledge and customary means in the field are included in the scope of the present invention.

[0033] like Figures 1 to 6 As shown in FIG. 1 , a method for processing a large-sized aircraft engine precision retaining ring provided in this embodiment includes the following steps:

[0034] (1) Cutting: Calculate the size of the rough material and use a rectangular sheet with a thickness of 7.5 mm for cutting, such as Figure 2 As shown. The size of the raw material after welding should be consistent with the size of the heat setting mold Match.

[0035] (2) Rolling: Use a rolling bed to roll the sheet metal. Figure 3 shown.

[0036] (3) Polishing welding: After polishing and rolling, the two ends of the spliced ​​parts are used as the welding place and the rounded sheet is welded. After welding, there is a weld seam on the ring. Figure 3 shown.

[0037] (4) Vacuum heat setting: Vacuum heat setting ring parts to ensure hardness. The thermal expansion linear speed of the heat setting mold and the precision clamping ring raw material is different (the thermal expansion linear speed of the precision clamping ring raw material is smaller than that of the heat setting mold). Through thermal expansion and contraction, the ring parts are rounded, such as Figure 4 Dimensions It should be ensured that the welded ring can be placed before thermal expansion, and the inner ring should have a margin for subsequent machining after thermal expansion. Vacuum heat setting is carried out in a vacuum furnace. The heating parameter of the vacuum furnace is the aging temperature, so the temperature window has been determined. The type of precision clamping ring material has also been determined. The expansion amount of the ring at this temperature can be determined. From this, the material and size of the heat setting mold can be determined to ensure that the ring is round.

[0038] (5) Slow wire cutting: Slow wire cutting parts, when cutting Figure 3 Based on the right picture, multiple rings are cut from left to right (or multiple rings with the same outer diameter and height are cut in the direction of the ring axis), ensuring a flatness of 0.3mm and a parallelism of 0.03mm. Figure 5 As shown. The thickness dimension leaves margin for subsequent pickling.

[0039] (6) Pickling: Pickle the parts and control the process parameters. Remove the surface ablation layer and ensure the surface roughness and part thickness dimension C. The pickling process ensures both surface roughness and thickness. In other words, the thickness of the intermediate part after wire cutting must be combined with the pickling process to ensure both the surface quality and thickness of the intermediate part after pickling.

[0040] (7) Machining shape: According to the requirements of the precision clamping ring parts drawing, the inner and outer circles of the ring are machined to ensure the size and B, the notch position is cut along the original weld position. Figure 6 shown.

[0041] (8) Magnetic testing: Magnetic testing is performed on precision retaining rings.

[0042] (9) Chemical passivation: surface treatment, chemical passivation of precision clamping rings.

[0043] Any matters not described in detail in the present specification are prior art known to those skilled in the art. Although the above description of the present invention is based on illustrative embodiments to facilitate understanding of the present invention by those skilled in the art, it should be understood that the present invention is not limited to the scope of the specific embodiments. As long as various modifications are within the spirit and scope of the present invention as defined and determined by the appended claims, such modifications will be obvious to those skilled in the art, and all inventions and creations utilizing the concepts of the present invention are protected.

Claims

1. A method for processing a large-size aircraft engine precision retaining ring, characterized in that: The following steps are involved: S1, blanking, using rectangular plate, the thickness of the plate is greater than the width of the precision clamping ring, and the width of the plate is greater than the thickness of the precision clamping ring; S2, rolling, rolling the rectangular plate in S1 along the length direction; S3, polishing and welding, polishing the two ends of the rectangular plate in the length direction after being rolled in S2, and then splicing and welding them into a ring-shaped part. The welded ring-shaped part has a weld seam; S4, vacuum heat setting, heating the ring part in S3 under vacuum environment, expanding the ring part from the inner ring surface outward, ensuring the hardness of the ring part while calibrating the ring part; S5, wire cutting, cutting the ring in S4 along a plane perpendicular to the axis of the ring to obtain at least one precision clamping ring intermediate part while ensuring the flatness and parallelism of the two axial end faces of the ring; S6, pickling, pickling the precision clamping ring intermediate obtained in S5 to remove the ablation layer on its surface and ensure that its surface roughness meets the requirements; S7, machining the outer shape, according to the requirements of the precision snap ring part drawing, the inner and outer surfaces of the precision snap ring intermediate piece after pickling in S6 are machined to ensure that the outer diameter and width required by the precision snap ring part drawing are obtained, and the notch required by the precision snap ring part drawing is machined along the weld position in S3 to obtain the precision snap ring with the outer dimensions and characteristic structure in the part drawing; S8, magnetic flaw detection, checks whether the precision retaining ring in S7 has defects; S9, chemical passivation, performs surface chemical passivation treatment on the precision clamping ring that does not have defects in S8.

2. The method for processing a large-sized aircraft engine precision retaining ring according to claim 1, characterized in that: In S2, the rectangular plate in S1 is rolled using a rolling bed.

3. The method for processing a large-sized aircraft engine precision retaining ring according to claim 1, characterized in that: In S4, a heat setting mold is used for heating in a vacuum environment. The heat setting mold includes a cylindrical surface for inserting the inner ring of the annular part in S3, and the thermal expansion linear velocity of the material of the heat setting mold is greater than the thermal expansion linear velocity of the rectangular plate in S1.

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