Method for correcting deformation of multiple micro-regions of non-welding region of thin-wall rotating part of engine

Abstract

The invention discloses a multi-micro-area deformation correction method for a non-welding area of an engine thin-wall rotating member, and relates to the field of thin-wall member deformation correction, and the method comprises the steps: S1, scanning the thin-wall rotating member through optical scanning equipment, converting the thin-wall rotating member into a solid model, and comparing the solid model with a design model, a plurality of non-uniform micro-deformation areas on the entity model are obtained; s2, the solid model is imported into finite element simulation software, shot blasting parameters are set on the basis of an existing shot blasting strengthening process, and a shot blasting mode is determined by conducting shot blasting shape correction simulation on a micro-deformation area; and S3, a physical feature piece matched with the physical model is prepared, so that reference parameters of shot blasting shape correction treatment are determined. The invention provides a multi-micro-area deformation correction method for a non-welding area of an engine thin-wall rotating part, which meets the precision requirement for deformation fault repair of a welding area of a wall rotating part in the field of aviation repair by adopting a means of combining digital simulation with a test and iterative correction.

Description

Technical Field

[0001] The present invention relates to the field of deformation correction of thin-walled parts, and more specifically, to a method for correcting deformation of multiple micro-regions of a non-welding zone of an engine thin-walled rotating part by using information technology to guide the deformation correction of thin-walled parts. Background Art

[0002] Thin-walled rotating parts refer to parts with thin-wall structures and in the shape of a body of revolution. They are widely used in aerospace, machinery manufacturing and other fields. Such parts are prone to deformation during processing and heat treatment, especially during welding in the field of aviation repair. For example, when repairing a combustion chamber shell, the heat input at the welding point is large, and local stress causes plastic deformation in the area around the weld, which in turn causes non-uniform large curvature deformation in multiple micro-areas on the installation edge of the non-welding area, resulting in excessive roundness and failure to meet assembly technical requirements, resulting in product discontinuation and huge losses.

[0003] Deformation in the field of aviation repair mainly refers to the deformation caused by welding in multiple places during the welding process. Because the welding time at each place is different, the deformation at each place is uneven, and each weld produces a large heat input in a relatively small range, resulting in large curvature deformation in a small area.

[0004] As for the repair of deformation failure of thin-walled rotating parts, which are typical thin-walled structural parts, mechanical correction and thermal correction are commonly used to repair them. However, in the actual correction and maintenance process, due to the influence of large residual tensile stress in the deformed parts, mechanical correction cannot eliminate internal stress, and it is easy to cause material fatigue and strength reduction; while heat treatment correction can eliminate stress to a certain extent, it is difficult to correct deformation in smaller areas. Therefore, it can be seen that the commonly used correction methods are not applicable to the correction of large curvature deformation in micro-areas of thin-walled rotating parts.

[0005] In the prior art, there is also a method of correction by shot peening, but it is mainly used for macro deformation. As for the correction of micro deformation, no one has yet proposed a more reasonable solution. Summary of the invention

[0006] An object of the present invention is to solve at least the above problems and / or disadvantages and to provide at least the advantages which will be described hereinafter.

[0007] In order to achieve these purposes and other advantages of the present invention, a method for correcting deformation of multiple micro-regions in a non-welding area of ​​a thin-walled rotating part of an engine is provided, comprising: 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 inwardly contracted micro-deformation area, 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.

[0008] Preferably, 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.

[0009] Preferably, 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.

[0010] Preferably, it is characterized in that, in S4, the process of iterative calibration is: 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 parametersP 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.

[0011] 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.

[0012] Other advantages, objectives and features of the present invention will be embodied in part through the following description, and in part will be understood by those skilled in the art through study and practice of the present invention. BRIEF DESCRIPTION OF THE DRAWINGS

[0013] Figure 1 It is a processing flow diagram of the shot peening correction method of the present invention; Figure 2 This is a schematic diagram of the structure of the damaged combustion chamber outer shell; Figure 3A schematic diagram of a process simulation when the shot peening shaping simulation is performed using the method of the present invention; Figure 4 A schematic diagram of the local deformation distribution of the outer shell of the combustion chamber when the method of the present invention is adopted; Figure 5 A schematic diagram of the distribution of the shot peening area of ​​the combustion chamber shell when the method of the present invention is used for iterative shape correction. DETAILED DESCRIPTION

[0014] The present invention is further described in detail below in conjunction with the accompanying drawings so that those skilled in the art can implement the invention with reference to the description.

[0015] In order to correct the deformation of non-welding areas of thin-walled rotating parts of aircraft engines after welding, which cannot be repaired by mechanical correction or thermal correction, a shot peening correction method for large curvature deformation of multiple non-uniform micro-areas in non-welding areas of thin-walled rotating parts of aircraft engines after welding was proposed based on the principle of shot peening deformation and combined with rigid support rods, which provides a technical means for green manufacturing and cost reduction and efficiency improvement.

[0016] Furthermore, after welding, the thin-walled rotating parts face the large curvature deformation of multiple non-uniform micro-regions in the non-welding area, such as Figure 1 As shown, the present invention provides a method for correcting deformation of multiple micro-regions in non-welding areas of thin-walled rotating parts of an engine, and the specific processing flow is as follows: Step 1: Deformation test: Use optical scanning equipment such as blue light 3D scanner to scan the thin-walled rotating parts, convert the scan data into a solid model, and test the thin-walled rotating parts based on the design model. It is found that there are multiple (N 1 ,N 2 ,…,N m ) Non-uniform and large curvature micro-deformation area D i (D 1 ,D 2 ,…,D m ) (Micro deformation area refers to the non-macro deformation of the local area with a proportion of less than 10% relative to the overall surface of the part), measure the deformation amount and trend of the micro deformation area, and re-measure with a high-precision caliper to determine the reliability of the deformation test.

[0017] Step 2: Shot peening simulation to determine the shot peening method: convert the scan data into a solid model and import it into the finite element simulation software, define the material and related material performance parameters of the solid model, set the shot peening parameters according to the existing shot peening strengthening process, simulate the shot peening shape correction of the deformation area, and determine the corresponding shot peening direction of the specific deformation area, that is, the inward contraction area of ​​the shell should be shot peened on the outside, and the outward expansion area of ​​the shell should be shot peened on the inside.

[0018] Step 3: Determine the shot peening parameters: According to the solid model converted from the scan data, manufacture the physical feature parts with corresponding deformation characteristics to correct the minimum deformation {min (D 1 ,D 2 ,…,D m The shot peening parameters at the position of b , whose 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.

[0019] Step 4. Determine the tooling: Since welding is performed on the outside of the thin-walled rotating part, the deformation is mostly the inward contraction of the shell. Therefore, a follower support rod is used to support the inner wall of the thin-walled rotating part during shot peening. That is, its support position changes with the shot peening impact position, and the support position corresponds to the shell in the impact area, which increases the shell stiffness while offsetting the impact of the shot, so that the shot peening only has a positive shaping effect on the outer shell of the combustion chamber.

[0020] Step 5. Determine the iterative shaping method: For deformations of multiple non-uniform micro-regions with large curvature, different shaping effects can be achieved by controlling different shot peening times and corresponding areas while keeping the shot peening intensity (i.e., the reference shaping parameter) fixed.

[0021] In step 5, since the degree of deformation in many other places changes due to the correction of one place, this step adopts the following iterative correction: First, according to the maximum deformation {max(D 1 ,D 2 ,…,D m )} relative to the minimum deformation in step 3 (i.e. {min(D 1 ,D 2 ,…,D m )}) multiples of B 1 , determine the reference correction parameter P b , the calibration time is t 1 (t 1 =B 1 × P b ), for the maximum deformation point Ⅰ (i.e. {max (D 1 ,D 2 ,…,D m )}) Shot peening and correction are carried out at 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 ,…,D2m ); Again, according to the maximum deformation II (i.e. {max (D 21 ,D 22 ,…,D 2m )}) relative to the minimum deformation in step 3 {min (D 1 ,D 2 ,…,D m )} multiple B 2 , determine the reference correction parameter P b , time t 2 (t 2 =B 2 × P b ), shot peening is performed on the maximum deformation part II; 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.

[0022] 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; 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; 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.

[0023] 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).

[0024] 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.

[0025] 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.

[0026] 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.

[0027] The above solution is only an illustration of a preferred embodiment, but is not limited thereto. When implementing the present invention, appropriate replacement and / or modification can be performed according to user needs.

[0028] Although the embodiments of the present invention have been disclosed above, they are not limited to the applications listed in the specification and the embodiments. It can be fully applied to various fields suitable for the present invention. For those familiar with the art, additional modifications can be easily realized. Therefore, without departing from the general concept defined by the claims and equivalent scope, the present invention is not limited to the specific details and the illustrations shown and described here.

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 inwardly contracted micro-deformation area, 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.

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 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.

4. 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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