Self-adaptive machining method for micro notch edge fillets on outer wall face of aero-engine supporting plate

Abstract

The aero-engine supporting plate outer wall surface micro notch edge fillet self-adaptive machining method comprises the steps that a theoretical three-dimensional model of a supporting plate single piece and a notch is established, and a plurality of notch theoretical size parameters are obtained; a machining program is programmed according to the theoretical three-dimensional model of the support plate single piece and the notch, and machining of the support plate single piece and the notch in the outer wall of the support plate is completed; the symmetrical support plate single pieces are welded to form a support plate main piece; measuring actual size parameters of a plurality of notches on the outer wall surface of the support plate on line, and calculating a deviation value between the actual position and the theoretical position of the center of each notch; on the basis of the theoretical three-dimensional model, modeling is conducted on each notch edge fillet again, and a subprogram for notch edge fillet machining is compiled; according to theoretical parameters and actual measurement parameters of the notch, programmable shape proportion parameters and programmable zero offset parameters are set, and a notch edge fillet self-adaptive machining main program is compiled; and repeating the previous step to compile the self-adaptive machining main program of each notch edge fillet to finish numerical control machining of each notch edge fillet.

Description

Technical Field

[0001] The invention belongs to the technical field of aircraft engine support plate manufacturing, and relates to a method for adaptively processing tiny notch edge fillets on the outer wall surface of an aircraft engine support plate. Background Art

[0002] The manufacturing technology of aircraft engine blades is one of the most complex technologies in the turbine machinery manufacturing industry, and it is also a manufacturing technology that involves a wide range of professional fields in the machinery manufacturing industry. Therefore, the level of blade manufacturing technology reflects the level of engine manufacturing technology to a certain extent.

[0003] The support plate usually adopts a welded structure. Affected by the requirements of the welding process, the edges of the outer wall of the anti-icing groove are processed and exposed along with the outer wall after the welding assembly is formed. Because the narrow groove undergoes irregular deformation to varying degrees during the welding process, the process first adopts the process of manual clamping and polishing to complete the technical requirements of edge rounding. Generally, there are as many as dozens of anti-icing grooves on a support plate. The manual clamping speed is slow, and the groove width is 0.9 to 1.2 mm. The rigidity of the tools used is seriously affected, especially at the intersection of the arcs at both ends of the runway type. Because the tool cannot form a moving trajectory, processing defects are easily formed there. During subsequent use, fatigue cracks appeared in this area several times, and the origin of the cracks was closely related to the processing defects. Summary of the invention

[0004] In order to solve the above technical problems, the purpose of the present invention is to provide a method for adaptively processing the rounded edges of tiny notches on the outer wall of an aircraft engine support plate.

[0005] The present invention provides a method for adaptively processing the rounded corners of tiny notches on the outer wall of an aircraft engine support plate, comprising:

[0006] Step 1: Establish a theoretical three-dimensional model of the support plate and the notch, and obtain multiple theoretical positions of the notch center, theoretical lengths of the notch, and theoretical widths of the notch;

[0007] Step 2: Prepare a processing program based on the theoretical three-dimensional model of the support plate and the notch to complete the processing of the support plate and the notch on the outer wall of the support plate;

[0008] Step 3: Weld the symmetrical support plate pieces to form the support plate main part;

[0009] Step 4: Online measure the actual center positions, actual lengths and actual widths of multiple slots on the outer wall of the support plate, and calculate the deviation between the actual center position of the slot and the theoretical position;

[0010] Step 5: Based on the theoretical three-dimensional model of the support plate and the notch, the rounded corners of each notch are remodeled, and a subroutine for processing the rounded corners of each notch is compiled;

[0011] Step 6: According to the theoretical parameters and measured parameters of the notch, set the programmable shape ratio parameters and programmable zero offset parameters in the notch edge rounding processing subroutine to compile the notch edge rounding adaptive processing main program;

[0012] Step 7: Repeat step 6 to calculate the shape ratio parameters and zero offset parameters of each slot in turn, compile the main program for adaptive processing of the rounded edges of each slot, and complete the CNC processing of the rounded edges of each slot.

[0013] The method for adaptively processing the rounded corners of the edges of the micro-notches on the outer wall of the aero-engine support plate of the present invention has the following beneficial effects:

[0014] The present invention summarizes and establishes an adaptive processing method for the rounded corners of tiny slot edges, and completes the processing of a single slot edge original by using online scanning, adaptive programming, and customized CNC milling processing technology. The method can realize customized CNC processing of deformed irregular slots to replace manual pliers, which not only has high processing efficiency, but also reliably guarantees the consistency of the geometric shape and geometric size of the processed fillets. According to anatomical observation, the processed fillets form smooth joint marks with the two side surfaces, and no manual intervention is required after processing. The size, shape, and roughness can directly meet the design requirements, and the formed processing texture is more conducive to fatigue resistance. BRIEF DESCRIPTION OF THE DRAWINGS

[0015] Figure 1 The present invention is a flow chart of a method for adaptively processing the rounded edges of tiny notches on the outer wall of an aero-engine support plate. DETAILED DESCRIPTION

[0016] like Figure 1 As shown, the method for adaptively processing the rounded corners of the edges of the micro-notches on the outer wall of the aero-engine support plate of the present invention comprises:

[0017] Step 1: Establish a theoretical three-dimensional model of the support plate and the notch, and obtain multiple theoretical positions of the notch center, theoretical lengths of the notch, and theoretical widths of the notch, specifically:

[0018] Using UG software and according to the design drawings, a theoretical three-dimensional model of the support plate and the slot is established to obtain multiple theoretical positions of the slot center, theoretical lengths of the slot, and theoretical widths of the slot.

[0019] Step 2: Prepare a processing program based on the theoretical three-dimensional model of the support plate and the notch to complete the processing of the support plate and the notch on the outer wall of the support plate;

[0020] Step 3: Weld the symmetrical support plate pieces to form the support plate main part;

[0021] Step 4: Measure the actual center positions, actual lengths and actual widths of multiple slots on the outer wall of the support plate online, and calculate the deviation between the actual center position of the slot and the theoretical position; specifically, calculate the position deviation value according to the following formula:

[0022]

[0023] in, is the coordinate of the actual position of the center of the i-th slot; x i ,y i , z i is the coordinate of the theoretical center position of the i-th slot; Δx i , Δy i , Δz i is the position coordinate deviation value, i=1…n, n is the number of slots.

[0024] Step 5: Based on the theoretical three-dimensional model of the support plate and the notch, the rounded corners of each notch are remodeled, and a subroutine for processing the rounded corners of each notch is compiled;

[0025] Step 6: According to the theoretical parameters and measured parameters of the notch, set the programmable shape ratio parameters and programmable zero offset parameters in the notch edge rounding processing subroutine to compile the notch edge rounding adaptive processing main program, specifically:

[0026] Step 6.1: Calculate the X-axis contour magnification and the Y-axis contour magnification based on the theoretical length and actual length, theoretical width and actual width of the slot. The calculation formula is as follows:

[0027]

[0028]

[0029] Among them, a i is the X-axis contour magnification of the i-th slot, is the actual length of the i-th slot, L i is the theoretical length of the i-th slot; b i is the Y-axis contour magnification of the i-th slot, is the actual width of the i-th slot, W i is the theoretical width of the i-th slot; i and b i Set the shape scale parameter SCALE of the i-th slot;

[0030] Step 6.2: Set the position coordinate deviation value Δx i , Δy i , Δz iSet as zero offset parameter ATRANS of the i-th slot;

[0031] Step 6.3: Based on the subroutine for the rounding of the notch edges compiled in step 5, the actual notch position model and the rounding model are generated using UG software according to the shape scale parameter SCALE and the zero offset parameter ATRANS;

[0032] Step 6.4: Based on the fillet model, call the subroutine for the rounding of the slot edges in step 5, and automatically generate the corresponding slot edge rounding adaptive processing main program according to the set variables SCALE and ATRANS for each slot to complete the processing of the slot.

[0033] Step 7: Repeat step 6 to calculate the shape ratio parameters and zero offset parameters of each slot in turn, compile the main program for adaptive processing of the rounded edges of each slot, and complete the CNC processing of the rounded edges of each slot.

[0034] By using the invented adaptive processing method for rounding the edges of tiny notches on the outer wall of an aircraft engine support plate, the processing accuracy of the rounded corners of the anti-icing grooves of the support plate is greatly improved, the efficiency is also improved to a certain extent, the geometric shape and geometric dimensions are reliably guaranteed, the quality risks of manual repairs with pliers are eliminated, and the safety of use is guaranteed.

[0035] Through the above method, the risk of scrapping the air intake casing can be avoided every year, and the loss of scrap can be reduced by hundreds of millions of yuan, which has achieved good results. With the increase of the company's production capacity and the promotion and application of this technology, the economic benefits will be greatly improved.

[0036] The above description is only a preferred embodiment of the present invention and is not intended to limit the concept of the present invention. Any modifications, equivalent substitutions, improvements, etc. made within the spirit and principle of the present invention should be included in the protection scope of the present invention.

Claims

1. An adaptive processing method for rounding the edges of tiny notches on the outer wall of an aircraft engine support plate, characterized in that: include: Step 1: Establish a theoretical three-dimensional model of the support plate and the notch, and obtain multiple theoretical positions of the notch center, theoretical lengths of the notch, and theoretical widths of the notch; Step 2: Prepare a processing program based on the theoretical three-dimensional model of the support plate and the notch to complete the processing of the support plate and the notch on the outer wall of the support plate; Step 3: Weld the symmetrical support plate pieces to form the support plate main part; Step 4: Online measure the actual center positions, actual lengths and actual widths of multiple slots on the outer wall of the support plate, and calculate the deviation between the actual center position of the slot and the theoretical position; Step 5: Based on the theoretical three-dimensional model of the support plate and the notch, the rounded corners of each notch are remodeled, and a subroutine for processing the rounded corners of each notch is compiled; Step 6: According to the theoretical parameters and measured parameters of the notch, set the programmable shape ratio parameters and programmable zero offset parameters in the notch edge rounding processing subroutine to compile the notch edge rounding adaptive processing main program; Step 7: Repeat step 6 to calculate the shape ratio parameters and zero offset parameters of each slot in turn, compile the main program for adaptive processing of the rounded edges of each slot, and complete the CNC processing of the rounded edges of each slot.

2. The method for adaptively processing the edge rounding of a micro-notch on the outer wall of an aircraft engine support plate according to claim 1, characterized in that: The step 1 is specifically as follows: Using UG software and according to the design drawings, a theoretical three-dimensional model of the support plate and the slot is established to obtain multiple theoretical positions of the slot center, theoretical lengths of the slot, and theoretical widths of the slot.

3. The method for adaptively processing the rounded edges of micro-notches on the outer wall of an aircraft engine support plate according to claim 1, characterized in that: In step 4, the position deviation value is calculated according to the following formula: in, is the coordinate of the actual position of the center of the i-th slot; x i ,y i , z i is the coordinate of the theoretical center position of the i-th slot; Δx i , Δy i , Δz i is the position coordinate deviation value, i=1…n, n is the number of slots.

4. The method for adaptively processing the edge rounding of a micro-notch on the outer wall of an aircraft engine support plate according to claim 1, characterized in that: The step 6 is specifically as follows: Step 6.1: Calculate the X-axis contour magnification and the Y-axis contour magnification based on the theoretical length and actual length, theoretical width and actual width of the slot. The calculation formula is as follows: Among them, a i is the X-axis contour magnification of the i-th slot, is the actual length of the i-th slot, L i is the theoretical length of the i-th slot; b i is the Y-axis contour magnification of the i-th slot, is the actual width of the i-th slot, W i is the theoretical width of the i-th slot; i and b i Set the shape scale parameter SCALE of the i-th slot; Step 6.2: Set the position coordinate deviation value Δx i , Δy i , Δz i Set as zero offset parameter ATRANS of the i-th slot; Step 6.3: Based on the subroutine for the rounding of the notch edges compiled in step 5, the actual notch position model and the rounding model are generated using UG software according to the shape scale parameter SCALE and the zero offset parameter ATRANS; Step 6.4: Based on the fillet model, call the subroutine for the rounding of the slot edges in step 5, and automatically generate the corresponding slot edge rounding adaptive processing main program according to the set variables SCALE and ATRANS for each slot to complete the processing of the slot.

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