Method for correcting multi-micro-region deformation of non-welded area of thin-walled rotating parts of engine

Abstract

The present invention discloses a method for correcting multiple micro-region deformations in the non-welded area of an engine thin-walled rotary part, which relates to the field of thin-walled part deformation correction and includes: S1. Using an optical scanning device to scan the thin-walled rotary part and convert it into a solid model, comparing the solid model with the design model to obtain multiple non-uniform micro-deformation regions on the solid model; S2. Importing the solid model into finite element simulation software, setting shot peening parameters based on the existing shot peening strengthening process, and determining the shot peening method by simulating shot peening correction of the micro-deformation regions; S3. Preparing a physical feature part adapted to the solid model to determine the reference parameters for shot peening correction. The present invention provides a method for correcting multiple micro-region deformations in the non-welded area of an engine thin-walled rotary part. By adopting the means of digital simulation combined with experiments and iterative correction, the accuracy requirements for repairing deformation faults in the welded area of the wall rotary part in the aviation repair field are met.

Description

Technical Field

[0001] The present invention relates to the field of deformation correction of thin-walled parts. More specifically, the present invention relates to a method for correcting multiple micro-region deformations in the non-welded area of a thin-walled rotating part of an engine, which uses information technology to guide the deformation correction of thin-walled parts. Background Art

[0002] A thin-walled rotating part refers to a part with a thin-walled structure and a rotating body shape, which is widely used in the fields of aerospace, mechanical manufacturing, etc. Such parts are prone to deformation during the processing and heat treatment processes, especially during the welding process in the field of aviation repair, where the deformation is particularly prominent. For example, during the repair of a certain combustion chamber shell, the heat input at the welding joint is relatively large, and the local stress causes plastic deformation in the area around the weld, which in turn causes non-uniform multiple micro-region large-curvature deformations in the mounting edge of the non-welded area, resulting in an out-of-roundness exceeding the tolerance and not meeting the assembly technical requirements, causing the product to be out of use and resulting in huge losses.

[0003] In the field of aviation repair, the deformation mainly refers to the multiple deformations caused by welding during the welding process. Since the welding time at each location is different, the deformations at each location are uneven, and each welding location generates a relatively large heat input within a relatively small range, resulting in large-curvature deformations in the micro-region.

[0004] For the repair deformation failure of such typical thin-walled structure parts as thin-walled rotating parts, common methods such as mechanical shaping and thermal shaping are used for repair. However, in the actual shaping and maintenance process, affected by the large residual tensile stress at the deformed part, the mechanical shaping method cannot eliminate the internal stress and is prone to causing material fatigue and strength reduction; while the thermal treatment shaping method can eliminate the stress to a certain extent, but it is difficult to correct the deformation in a small area. Therefore, it can be seen that the common shaping methods are not applicable to the shaping of the micro-region large-curvature deformation of thin-walled rotating parts.

[0005] In the prior art, there are also methods of shaping by shot peening, but it is mainly applied to macroscopic deformation, and no more reasonable scheme has been proposed for the shaping of microscopic deformation. Summary of the Invention

[0006] An object of the present invention is to solve at least the above problems and / or defects and provide at least the advantages described later.

[0007] To achieve these objects and other advantages of the present invention, a method for correcting multiple micro-region deformations in the non-welded area of a thin-walled rotating part of an engine is provided, including:

[0008] S1. Use an optical scanning device to scan the thin-walled rotary part and convert it into a solid model. Compare the solid model with the design model to obtain multiple non-uniform micro-deformation regions on the solid model, and obtain the maximum deformation amount of curvature in each micro-deformation region. D i , i = 1, 2… m , m is the number of micro-deformation regions;

[0009] S2. Import the solid model into finite element simulation software, set shot peening parameters based on the existing shot peening process, and determine the shot peening method by simulating shot peening and straightening for the micro-deformation regions.

[0010] S3. Prepare a physical feature part adapted to the solid model to determine the shot peening reference parameters.

[0011] S4. Based on the shot peening reference parameters, perform shot peening and straightening treatment on each micro-deformation region by means of iterative straightening.

[0012] Among them, in S1, the micro-deformation region refers to a non-macroscopic deformation region with a proportion less than 10% relative to the overall surface of the thin-walled rotary part;

[0013] In the shot peening and straightening of S4, for the micro-deformation region that shrinks inward, support the impact region with a support rod, and the support position of the support rod changes with the change of the shot peening impact position, so that the shot peening only produces positive straightening on the thin-walled rotary part.

[0014] Preferably, in S2, the shot peening method is:

[0015] For the micro-deformation region that shrinks inward, shot peening and straightening should be carried out on the outer side of the thin-walled rotary part;

[0016] For the micro-deformation region that expands outward, shot peening and straightening should be carried out on the inner side of the thin-walled rotary part.

[0017] Preferably, in S3, the shot peening reference parameters refer to: D i The shot peening correction parameters and time of the minimum value in P b during shot peening and straightening in the shot peening die are used as the reference straightening parameters T b , and the other regions achieve the straightening effect by increasing the number of shot peening reciprocating cycles.

[0018] Preferably, its characteristic lies in that in S4, the process of iterative straightening is:

[0019] S41. Based on D iThe maximum and minimum values ​​in the equation determine the deformation multiple. B ;

[0020] S42, Select D i The maximum value in is used as the current calibration area, based on the benchmark calibration parameters P b And initial calibration time t Shot peening is performed on the current calibration area, where: t = P b ×B ;

[0021] S43. Re-measure the overall part size of the thin-walled rotating part after shot peening to obtain the deformation amount D corresponding to each micro-deformation area. ij , j =1, 2… n , n is the number of iterations;

[0022] S44, to D ij It is determined whether the deformation amount at each location meets the requirements. If not, it goes to S45, otherwise the shape correction is completed;

[0023] S45, based on D ij The maximum value in D i The minimum value among them determines the deformation multiple B j ;

[0024] S46, Select D i The maximum value in is used as the current calibration area, based on the benchmark calibration parameters P b and iterative calibration time t j Shot peening is performed on the current calibration area, where: t j =P b ×B j ;

[0025] S47. Return to S43.

[0026] The present invention includes at least the following beneficial effects: the method of the present invention is mainly used in the correction of microscopic large curvature deformation, and by adopting digital simulation combined with experiments and iterative corrections, the accuracy requirements for repairing deformation faults in the welding area of ​​wall rotating parts in the aviation repair field are met.

[0027] Other advantages, objects and features of the present invention will be partly reflected by the following description, and partly will be understood by those skilled in the art through the research and practice of the present invention. Description of the Drawings

[0028] Figure 1 It is a schematic diagram of the processing flow of the shot peening correction method of the present invention;

[0029] Figure 2 It is a schematic structural diagram of a damaged combustion chamber outer casing;

[0030] Figure 3 It is a schematic diagram of the process simulation during the shot peening shape correction simulation using the method of the present invention;

[0031] Figure 4 It is a schematic diagram of the deformation distribution of a local part of the combustion chamber outer casing when using the method of the present invention;

[0032] Figure 5 It is a schematic diagram of the shot peening area distribution of the combustion chamber casing during iterative shape correction using the method of the present invention. Detailed Embodiment

[0033] The following further describes the present invention in detail with reference to the drawings, so that those skilled in the art can implement it according to the description in the specification.

[0034] In order to correct the deformation of the non-welded area after welding of thin-walled rotating parts of aero-engines that cannot be repaired by mechanical shape correction, thermal shape correction, etc., based on the shot peening deformation principle and combined with rigid support rods, a shot peening correction method for large-curvature deformation of multiple non-uniform micro-regions in the non-welded area after welding of thin-walled rotating parts of aero-engines is proposed, providing a technical means for green manufacturing, cost reduction and efficiency improvement.

[0035] Furthermore, for the large-curvature deformation of multiple non-uniform micro-regions in the non-welded area after welding of thin-walled rotating parts, as Figure 1 shown, the present invention provides a method for correcting the deformation of multiple micro-regions in the non-welded area of thin-walled rotating parts of an engine, and its specific processing flow is as follows:

[0036] Step 1, deformation testing: Use optical scanning equipment such as a blue light 3D scanner to scan the thin-walled rotating part, convert the scan data into a solid model, and test the thin-walled rotating part based on the design model. It is found that it has multiple (N1, N2,..., N m ) non-uniform and large-curvature micro-deformation regions D i (D1, D2,..., D m) (The micro-deformation area refers to the local area where the ratio to the overall part surface is less than 10% and is not macroscopically deformed). Measure the deformation amount and trend of the micro-deformation area, and at the same time re-measure with a high-precision caliper to determine the reliability of its deformation test.

[0037] Step 2: Shot peening simulation to determine the shot peening method: Convert the scanned data into a solid model and import it into the finite element simulation software. Define the material and related material property parameters of the solid model. Set the shot peening parameters according to the existing shot peening strengthening process, and perform shot peening correction simulation on the deformed area to determine the corresponding shot peening direction for a specific deformed area, that is, shot peening should be carried out on the outside for the area where the shell shrinks inward, and shot peening should be carried out on the inside for the area where the shell expands outward.

[0038] Step 3: Determine the shot peening parameters: According to the solid model converted from the scanned data, manufacture a physical feature part with corresponding deformation characteristics to correct the shot peening parameters at the minimum deformation {min(D1, D2, …, D m )} as the reference correction parameter P b , and its time is T b . The correction work for other deformation degree areas is achieved by increasing the number of shot peening reciprocating cycles (i.e., time) to achieve the correction effect.

[0039] Step 4: Determine the tooling: Since the operation is on the outside of the thin-walled rotating part during welding and the deformation is mostly that the shell shrinks inward, a follower strut is used to support the inner wall of the thin-walled rotating part during shot peening correction, that is, its support position changes with the shot peening impact position, and the support position corresponds to the shell opposite to the impact area. While increasing the shell stiffness, it offsets the impact of the shot peening material, so that the shot peening only has a positive correction effect on the combustion chamber outer shell correction.

[0040] Step 5: Determine the iterative correction method: For the deformation of multiple non-uniform micro-regions with large curvature, when the shot peening intensity (i.e., the reference correction parameter) is fixed, different correction effects are achieved by controlling different shot peening times and corresponding regions.

[0041] In Step 5, in view of the fact that the deformation degree of other multiple places changes due to the correction of a certain place, the following iterative correction is adopted in this step:

[0042] First, according to the multiple B1 of the maximum deformation {max(D1, D2, …, D m )} relative to the minimum deformation place in Step 3 (i.e., {min(D1, D2, …, D m )}), determine the reference correction parameter P b , and the calibration time is t1 (t1 = B1 × P b ), and perform shot peening correction on the maximum deformation place Ⅰ (i.e., {max(D1, D2, …, D m )});

[0043] Then, after a shot peening correction, re-measure the overall part size after shot peening to determine the deformation area of ​​the part (N 21 , N 22 ,…,N 2m ) at the real-time deformation (D 21 ,D 22 ,…,D 2m );

[0044] Again, according to the maximum deformation II (i.e. {max (D 21 ,D 22 ,…,D 2m )}) relative to the minimum deformation point {min(D1,D2,…,D m )} multiple B2, determine the reference correction parameter P b , time t2(t2=B2 × P b ), shot peening is performed on the maximum deformation part II;

[0045] Further re-measure the overall part size after shot peening to determine the deformation area of ​​the part (N 31 ,N 32 ,…,N 3m ) Deformation (D 31 ,D 32 ,…,D 3m ), and use this method to iteratively correct the shape according to the deformation from large to small and the corresponding position, until each deformation size meets the technical requirements.

[0046] After welding thin-walled rotating parts, the shot peening correction method was verified for multiple non-uniform and large-curvature micro-deformation areas in non-welding areas;

[0047] like Figure 2 As shown, during the fluorescent flaw detection of the outer shell of the combustion chamber, it was found that Figure 2 There was a crack at point A (point A is the weld), so repair welding was performed;

[0048] After welding, the ØD dimension was checked and it was found that Figure 2 The difference between the maximum and minimum diameters at point B (point B is the deformation point) can reach as much as 1.80mm, that is, the roundness is 0.90mm, which exceeds the process requirement of 0.50mm. Further inspection found that the heat input at the repair welding point was large, and the local stress caused the mounting edge of the welding area to deform, and the ØD size was locally reduced.

[0049] Use a blue light 3D scanner to scan the faulty combustion chamber outer shell, convert the scan data into a solid model and import it into the ABAQUS finite element simulation software, define the material and related material performance parameters of the solid model of the combustion chamber outer shell, preliminarily set the shot peening parameters, and simulate the shot peening process. Figure 3 As shown ( Figure 3 The red circle C in the middle is the projectile, D is the shell, and the red circle E represents the stress in the impact area).

[0050] Under certain shot peening parameters, the local stress changes and deformation distribution of the combustion chamber outer shell were obtained, such as Figure 4 As shown ( Figure 4 The red circle F in the middle indicates the impact deformation area). The results of shot peening simulation show that the shot peening on the outside of the combustion chamber where the ØD size is small produces a small positive deformation under the action of the shot material. It can be considered that if the shot peening intensity continues to increase, the ØD size tends to increase, so shot peening correction has certain technical feasibility.

[0051] The shot peening test was carried out on the scrapped combustion chamber shell using a shot peening device (equipped with Ø0.40mm steel shot). Before the test, the size of the combustion chamber shell ØD was measured and divided into Figure 5 The area shown (such as Figure 5 As shown, four groups of relative areas are divided, namely (0#, 0#-1), (1#, 1#-1), (2#, 2#-1), and (3#, 3#-1). The positions of the maximum and minimum values ​​are determined from the divided areas. The outer side of the area with smaller ØD (1#, 1#-1) and the inner side of the area with larger ØD (0#, 0#-1) are shot peened respectively. Before shot peening, a support rod is used to provide support for the inner side of the area with the smallest ØD size. Then, the diameters of each area of ​​the combustion chamber shell are re-measured, and the outer side of the area with smaller ØD size and the inner side of the area with larger ØD size are shot peened in turn (it should be noted that in actual operation, (2#, 2#-1) and (3#, 3#-1) may become the maximum and minimum values ​​in the iterative process and are shot peened). The final test results showed that the ØD size of the combustion chamber outer shell measured before the test was Ø355.96mm at the maximum and Ø354.33mm at the minimum. After the test, the size changed to Ø355.56 and Ø354.86, and the ØD roundness was 0.35mm, which was less than the technical requirement of 0.50mm, and the size was qualified.

[0052] This project is based on a shot peening correction method for large curvature deformation in multiple non-uniform micro-areas in non-welding areas of thin-walled rotating parts after welding. It can be used for the correction of other thin-walled parts, providing technical support for green manufacturing, cost reduction and efficiency improvement.

[0053] The above solution is only an illustration of a preferred example, but is not limited thereto. When implementing the present invention, appropriate substitutions and / or modifications can be made according to the needs of users.

[0054] Although the embodiments of the present invention have been disclosed as above, it is not limited to the applications listed in the specification and embodiments. It can be fully applied to various fields suitable for the present invention. For those familiar with the field, additional modifications can be easily achieved. Therefore, without departing from the general concept defined by the claims and the equivalent scope, the present invention is not limited to the specific details and the examples shown and described herein.

Claims

1. A method for correcting deformation of multiple micro-regions in non-welding areas of thin-walled rotating parts of an engine, characterized in that: include: S1. Use optical scanning equipment to scan the thin-walled rotating parts and convert them into a solid model. Compare the solid model with the design model to obtain multiple non-uniform micro-deformation areas on the solid model and obtain the deformation with the largest curvature in each micro-deformation area. D i , i =1, 2… m , m is the number of micro-deformation areas; S2. Import the solid model into the finite element simulation software, set the shot peening parameters based on the existing shot peening strengthening process, and determine the shot peening method by performing shot peening correction simulation on the micro-deformation area; S3. Prepare physical feature parts that are compatible with the physical model to determine the shot peening reference parameters; S4. Based on the shot peening reference parameters, each micro-deformation area is shot peened and shaped by an iterative shaping method; Wherein, in S1, the micro-deformation region refers to a non-macro-deformation region with a proportion of less than 10% relative to the overall profile of the thin-walled rotating part; In the shot peening correction of S4, for the micro-deformation area that shrinks inward, the impact area is supported by a support rod, and the support position of the support rod changes with the change of the shot peening impact position, so that the shot peening only produces positive correction on the thin-walled rotating parts; In S3, the shot peening reference parameter refers to: D i The minimum value in the shot peening correction mode is used as the shot peening correction parameter and time as the benchmark correction parameter. P b , benchmark calibration time T b For other areas, the correction effect is achieved by increasing the number of shot peening reciprocating cycles.

2. The method for correcting deformation of multiple micro-regions in non-welding areas of thin-walled rotating parts of an engine as claimed in claim 1, characterized in that: In S2, the shot peening method is: For the micro-deformation area that shrinks inward, shot peening should be performed on the outside of the thin-walled rotating part; For micro-deformation areas that expand outward, shot peening should be performed on the inner side of thin-walled rotating parts.

3. The method for correcting deformation of multiple micro-regions in non-welding areas of thin-walled rotating parts of an engine as claimed in claim 1, characterized in that: In S4, the iterative calibration process is as follows: S41, based on D i The maximum and minimum values ​​in the equation determine the deformation multiple. B ; S42, Select D i The maximum value in is used as the current calibration area, based on the benchmark calibration parameters P b And initial calibration time t Shot peening is performed on the current calibration area, where: t=P b ×B ; S43. Re-measure the overall part size of the thin-walled rotating part after shot peening to obtain the deformation amount D corresponding to each micro-deformation area. ij , j =1, 2… n , n is the number of iterations; S44, to D ij It is determined whether the deformation amount at each location meets the requirements. If not, it goes to S45, otherwise the shape correction is completed; S45, based on D ij The maximum value in D i The minimum value among them determines the deformation multiple B j ; S46, Select D i The maximum value in is used as the current calibration area, based on the benchmark calibration parameters P b and iterative calibration time t j Shot peening is performed on the current calibration area, where: t j =P b ×B j ; S47. Return to S43.

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