CN110064897B - Machining method for blank of spinning part of aviation part - Google Patents
Machining method for blank of spinning part of aviation part Download PDFInfo
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Abstract
The invention discloses a machining method for blank of spinning part of aviation part, when the blank of spinning part of aviation part is machined, when it is determined that the outer profile is not completely machined, the first machining allowance is determined by calculation, in the subsequent rough machining, semi-finish machining and finish machining processes, the cutter is normally adjusted in the X direction, the cutter compensation is kept unchanged, the first machining allowance of the cutter compensation or withdrawal in the Z direction is adjusted and machined, the method is named as an X-fixed Z-adjustable method, under the condition that the outer profile allowance is preliminarily determined, the obtained X-direction allowance is uniformly converted into the allowance needing to be adjusted in the Z direction by utilizing a trigonometric function relation according to the part profile taper, only radial point positions need to be kept unchanged during machining, the allowance is adjusted in the Z direction, so that the size control in the machining process is facilitated, the allowance can be accurately calculated without the assistance of a measuring tool, and the phenomenon that the machined size deviates from the theoretical required size is avoided.
Description
Technical Field
The invention relates to the technical field of aero-engines, in particular to a machining method for a blank of a spinning part of an aero-component.
Background
After the machining blank is changed from a forging piece to a spinning piece, the machining allowance is greatly reduced, the machining time is shortened for subsequent machining, and the machining efficiency is improved. But the spinning part blank is limited by the forming process, the axial and radial blank reference is unsteady, the size fluctuation is large, and the allowance is uneven. How to determine the machining allowance efficiently becomes the key point for machining the parts.
The traditional processing method comprises the steps of repeatedly turning the inner and outer molded surfaces of the part by adopting a plurality of common lathe processes, measuring and calculating the machining allowance by using an auxiliary clamp, finely turning the inner and outer molded surfaces and cutting the mounting edge.
This method has several problems:
(1) the repeated turning of the common lathe increases the process content, prolongs the processing period and does not meet the requirement of high-speed cutting processing;
(2) the common lathe is used for repeatedly turning, the machining quality is manually controlled, and the allowance of the inner and outer molded surfaces of the machined part cannot be ensured to be uniform enough;
(3) the difference between the part profile and the theoretical size causes the incomplete matching between the auxiliary measuring tool and the part profile, the calculated point position size is inaccurate, the calculated allowance is inaccurate, and the part is often scrapped due to the fact that the part cannot be machined.
Disclosure of Invention
The invention provides a machining method for a spinning part blank of an aviation part, and aims to solve the technical problems of uneven allowance and low machining efficiency of the spinning part blank in the machining process.
According to one aspect of the invention, a machining method for an aviation part spinning part blank is provided, a theoretical single-side allowance A of an inner profile and an outer profile of the aviation part spinning part is calculated according to theoretical sizes of the aviation part spinning part blank and the aviation part spinning part, and numerical control programming machining is carried out according to the theoretical size of the aviation part spinning part, and the machining method comprises the following steps:
s1, aligning and clamping the blank of the aviation part spinning piece, performing first-step rough machining on the outer profile of the blank of the aviation part spinning piece, removing rough machining allowance, judging whether to perform second-step rough machining on the outer profile of the blank of the aviation part spinning piece, if so, entering a step S2, and if not, directly entering a step S3;
s2, performing second-step rough machining on the outer profile of the blank of the aviation part spinning piece, keeping the X-direction normal tool setting, and supplementing a first machining allowance Z in the Z-direction, wherein the X-direction is the radial direction of the aviation part spinning piece, and the Z-direction is the axial direction of the aviation part spinning piece;
s3, roughly machining the inner profile of the blank of the spinning part of the aviation part, removing rough machining allowance, if the outer profile has a part which is not machined in place, withdrawing the cutter in the Z direction, machining the first machining allowance Z, and normally setting the cutter in the X direction to finish rough machining;
s4, performing semi-finishing on the outer profile of the blank of the spinning part of the aviation part, removing the allowance of the semi-finishing, if the outer profile has a part which is not processed in place, supplementing the first machining allowance Z in the Z direction, and normally setting the tool in the X direction to finish the semi-finishing;
and S5, performing finish machining on the inner profile and the outer profile of the blank of the spinning part of the aviation part respectively, and removing the residual finish machining allowance.
Further, the judging whether to perform the second-step rough machining of the outer profile on the blank of the rotary pressing piece of the aviation part comprises the following steps:
if the outer profile is completely processed in place, jumping to step S3 according to theoretical single-side allowance, and then, all processing steps do not need to carry out cutter feeding compensation or cutter retracting compensation;
if the outer profile has a part which is not processed in place, the process proceeds to step S2, and the depth Δ d of the region which is not processed in place is determined, and the depth Δ d is converted into a first machining allowance Z in the Z direction, which is Δ d/tan α, where α is the taper of the outer profile of the aircraft component spinning part.
Further, the determining the depth Δ d of the unprocessed-in-place region comprises the following steps:
selecting n position points uniformly distributed in an unprocessed in-place area on an outer molded surface along the axial direction of the blank of the spinning part of the aviation part, checking the whole circle run-out values of the n position points by a machine tool, recording the values as B1, B2, … and Bn respectively, and determining
Further, the determining the depth Δ d of the unprocessed-in-place region comprises the following steps:
selecting 3 position points uniformly distributed in an unmachined area on an outer molded surface along the axial direction of the blank of the spinning part of the aviation part, checking the whole-circle run-out values of the 3 position points by a machine tool, recording the values as B1, B2 and B3 respectively, and determining
Further, the theoretical unilateral margin A is not more than 3 mm.
Further, in step S1 and step S3, the rough machining allowance is
Further, in step S4, the semi-finishing allowance is
Where d is the remaining finishing allowance.
Further, the residual finishing allowance d is 0.05-0.15 mm.
Further, the specific steps of aligning and clamping the blank of the rotary pressing piece of the aviation part are as follows: clamping the blank of the spinning part of the aviation part on a numerical control machine tool, performing dial indicator operation for alignment, and measuring the reference circle full-circle run-out of the blank of the spinning part of the aviation part by using the dial indicator operation, wherein the run-out value is not more than
And enabling the center of the blank of the spinning part of the aviation part to be consistent with the rotation center of the numerical control machine tool.
Further, the aviation part spinning part comprises a spinning part with a regular shape and a spinning part with an irregular shape.
The invention has the following beneficial effects:
when the blank of the rotary pressing piece for the aviation parts is machined, when the outer molded surface is determined not to be completely machined, a first machining allowance is determined through calculation, the X-direction normal tool setting is carried out in the subsequent rough machining, semi-finishing machining and finishing machining processes, the tool compensation is kept unchanged, and the Z-direction tool compensation or tool withdrawal first machining allowance is maintained. The machining method of the blank of the spinning part of the aviation part cancels the machining of the blank of the rotary spinning part by the traditional general lathe, effectively shortens the machining period, reduces the degree of human intervention and improves the numerical control rate; the rough machining, the semi-finish machining and the finish machining are completed by utilizing a fixed X-Z adjusting method, the machining allowance is accurately measured, the use of a traditional auxiliary measuring tool is eliminated, the problems that the auxiliary measuring tool is not matched with the part profile, the measured point position size is inaccurate, and the calculated allowance is inaccurate are solved, and the problems of uneven allowance and low efficiency in the machining process are reduced, so that the machining quality of parts is ensured, and the machining efficiency is improved.
In addition to the objects, features and advantages described above, other objects, features and advantages of the present invention are also provided. The present invention will be described in further detail below with reference to the drawings.
Drawings
The accompanying drawings, which are incorporated in and constitute a part of this application, illustrate embodiments of the invention and, together with the description, serve to explain the invention and not to limit the invention. In the drawings:
FIG. 1 is a processing flow chart of a blank processing method of a spinning part of an aviation part according to a preferred embodiment of the invention;
fig. 2 is a schematic view of machining a blank of a spinning part of an aerospace component according to a preferred embodiment of the invention.
Detailed Description
The embodiments of the invention will be described in detail below with reference to the accompanying drawings, but the invention can be embodied in many different forms, which are defined and covered by the following description.
Fig. 1 is a processing flow chart of a blank processing method of a spinning part of an aviation part according to a preferred embodiment of the invention.
As shown in fig. 1, the aviation part spinning part blank processing method of this embodiment calculates the theoretical single-sided allowance a of the inner profile and the outer profile of the aviation part spinning part according to the theoretical sizes of the aviation part spinning part blank and the aviation part spinning part, where the theoretical single-sided allowance a is the size difference between the spinning part blank and the spinning part, and a numerical control program is programmed according to the theoretical size of the aviation part spinning part, including the following steps:
s1, aligning and clamping an aviation part spinning blank, performing first-step rough machining on the outer profile of the aviation part spinning blank, removing rough machining allowance, judging whether to perform second-step outer profile rough machining on the aviation part spinning blank, if so, entering step S2, and if not, directly entering step S3;
s2, performing second-step rough machining on the outer profile of the blank of the aviation part spinning piece, keeping the X-direction normal tool setting, and supplementing a first machining allowance Z in the Z-direction, wherein the X-direction is the radial direction of the aviation part spinning piece, and the Z-direction is the axial direction of the aviation part spinning piece;
s3, roughly machining the inner profile of the blank of the spinning part of the aviation part, removing rough machining allowance, if the outer profile has a part which is not machined in place, machining by withdrawing a first machining allowance Z in the Z direction, and normally setting a tool in the X direction to finish rough machining;
s4, performing semi-finishing on the outer profile of the blank of the spinning part of the aviation part, removing the semi-finishing allowance, if the outer profile has a part which is not processed in place, supplementing a first machining allowance Z in the Z direction, and normally setting a tool in the X direction to finish the semi-finishing;
and S5, performing finish machining on the inner profile and the outer profile of the blank of the spinning part of the aviation part respectively, and removing the residual finish machining allowance.
In the machining of the blank of the spinning part of the aviation part of the embodiment, whether the blank of the spinning part of the aviation part is subjected to the second-step rough machining of the outer profile is judged, when the fact that the outer profile is not completely machined in place is determined, a first machining allowance is determined through calculation, in the subsequent rough machining, semi-finish machining and finish machining processes, the X-direction is normally adjusted in tool setting, the tool compensation is kept unchanged, and the Z-direction is supplemented or withdrawn with the first machining allowance, the method is named as an X-fixed and Z-adjustable method, under the condition that the outer profile allowance is primarily determined, the obtained X-direction allowance is uniformly converted into the allowance needing to be adjusted in the Z direction by utilizing the trigonometric function relation according to the part profile taper, the machining allowance is uniformly converted into the allowance needing to be adjusted in the Z direction, the point position in the X direction (radial direction) is kept unchanged during machining, the allowance adjustment in the Z direction, the phenomenon that the processed size deviates from the theoretical required size can not occur.
The blank processing method of the spinning part of the aviation part cancels the processing of the rotating spinning part blank by the traditional common lathe process, effectively shortens the processing period, reduces the human intervention degree and improves the numerical control rate; the rough machining, the semi-finish machining and the finish machining are completed by using a fixed X and Z adjusting method, the use of a traditional auxiliary measuring tool is eliminated, the machining allowance is accurately measured and calculated, and the problems of uneven allowance and low efficiency in the machining process are solved, so that the machining quality of parts is ensured, and the machining efficiency is improved.
In the embodiment, the aviation part spinning part comprises a spinning part with a regular shape and a spinning part with an irregular shape. The method of the embodiment is not only suitable for spinning parts with regular shapes, but also suitable for spinning parts with irregular shapes, the axial and radial sizes of the spinning parts with irregular shapes fluctuate within a certain range, and the machining allowance is uneven.
In this embodiment, the concrete steps of aligning clamping aviation spare part spinning part blank are: clamping the blank of the spinning part of the aviation part on a numerical control machine tool, calibrating a dial indicator, and measuring the reference circle full-circle run-out of the blank of the spinning part of the aviation part by using the dial indicator to be not more than
The center of the blank of the spinning part of the aviation part is consistent with the rotation center of the numerical control machine tool. The purpose of alignment and clamping is to ensure that the center of a blank of a spinning part of an aviation part is consistent with the rotation center of a numerical control machine tool, so that the cutting allowance of each step is uniform, and the whole-circle run-out is not more than
(roughing allowance) can reduce the machining error in the subsequent rough machining of the outer profile.
In this embodiment, judging whether to carry out the rough machining of second step outer profile to aviation spare part spinning piece blank includes:
if the outer profile is completely processed in place, jumping to step S3 according to theoretical single-side allowance, and then, all processing steps do not need to carry out cutter feeding compensation or cutter retracting compensation;
if the outer profile has a part which is not processed in place, the process proceeds to step S2, the depth Δ d of the region which is not processed in place, i.e. the height difference between the high point and the low point of the surface of the aircraft part spinning member after processing, is determined, and the depth Δ d is converted into a first machining allowance Z in the Z direction, which is Δ d/tan α, according to a trigonometric function formula, where α is the taper of the outer profile of the aircraft part spinning member.
After all the rough machining allowance of the outer molded surface of the spinning part of the aviation part is completely removed, the integrity of the machined surface is good, no oxide skin part in a blank state exists, and after the rough machining allowance of the outer molded surface of the spinning part of the aviation part is not completely removed, local low-point areas exist on the machined surface, and the local low-point areas belong to the oxide skin part in the blank state. If it is determined in step S1 that all the outer mold surfaces are processed in place, the process proceeds directly to step S3, and steps S3, S4, and S5 all adopt normal processing, and no tool feeding or tool retracting is needed in the X direction and the Z direction, which is an ideal situation, but generally, a portion of the outer mold surface that is not processed in place is easy to occur during processing, and at this time, if the processing is performed as usual, the processed dimension deviates from the theoretically required dimension.
In this embodiment, determining the depth Δ d of the unprocessed in-place region includes the following steps:
selecting n position points uniformly distributed in an unprocessed in-place area on an outer molded surface along the axial direction of a blank of a spinning part of the aviation part, checking the whole circle of jumping values of the n position points by a watch on a machine tool, respectively recording the values as B1, B2, … and Bn, and determining
Preferably, 3 position points uniformly distributed in the unprocessed in-place area on the outer molded surface are selected along the axial direction of the blank of the spinning part of the aviation part,checking the full circle run-out values of 3 position points on the machine tool by drawing a table, recording the values as B1, B2 and B3 respectively, and determining
Δ d is a height difference between a high point and a low point on the surface of the machined spinning part of the aviation part, in this embodiment, preferably, 3 position points axially and uniformly distributed on the outer profile of the blank of the spinning part of the aviation part are used to obtain a height difference average value of the 3 position points, which is more favorable for reducing errors, and certainly, more position points can be selected to measure Δ d, so that the error is smaller, and the selection needs to be performed by comprehensively considering the working efficiency.
In this embodiment, the theoretical single-sided margin a is not greater than 3 mm. The larger the theoretical allowance is, the more the machining allowance needs to be removed during part machining, the longer the machining time is, and in the machining process of the spinning piece, the theoretical allowance is generally smaller than 3mm, so that the machining time can be shortened, and the machining efficiency can be improved.
In this embodiment, in steps S1 and S3, the rough machining allowance is
The roughing operation is performed by cutting away a substantial portion of the stock of the preform so that the shape and size of the preform is close to the finished product, with the remainder generally close to 2/3 of the total stock, thereby defining a roughing stock
In the present embodiment, in step S4, the semi-finishing allowance is set
Where d is the remaining finishing allowance. The semi-finishing process is to remove a certain margin to prepare for finishing the main surface of the spinning part, and the rest is to subtract the finishing margin from the rest margin.
In the embodiment, the remaining finishing allowance d is 0.05-0.15 mm. And the finish machining process is used for ensuring that the surface quality and the size of the main surface of the spinning part meet the requirements of a drawing, and the rest amount is generally between 0.05 and 0.15 mm.
Example 1
Taking a certain type of engine combustion casing machining as an example, the engine combustion casing is a typical spinning piece, and as shown in fig. 2, the taper α of the outer profile is known to be 16 °.
According to the theoretical sizes of the blank of the combustion chamber casing part and the part, calculating the theoretical single-side allowance A of the inner and outer molded surfaces of the part to be 3mm, and taking the residual finish machining allowance to be 0.15mm, wherein the machining steps are as follows:
s1, aligning and clamping the parts, performing the first step of rough machining on the outer molded surface, and removing the rough machining allowance LCoarse＝2mm；
And judging whether the part continues to perform the rough machining of the second step of the outer molded surface:
(1) if the outer profile is completely processed in place, jumping to the third step for downward processing according to theoretical single-side allowance, and performing backward processing without tool feeding and tool retracting compensation;
(2) if the outer profile has a part which is not processed in place, determining the depth delta d of the region which is not processed in place, selecting 3 points which are uniformly distributed in the axial direction (Z direction) of the region which is not processed in place of the outer profile of the part, drawing a table on a machine tool to check the full-circle run-out value of the position at 3, respectively recording the values as 0.8mm, 1mm and 0.9mm, determining that the delta d is 0.9mm, converting the delta d into a first machining allowance Z in the Z direction as 3.14mm,
s2, performing second-step rough machining on the outer molded surface, keeping the cutter compensation in the X direction (namely radial direction) unchanged, and machining by using a cutter compensation in the Z direction for 3.14 mm;
s3, roughly machining the inner molded surface and removing the rough machining allowance LCoarseIf the outer molded surface has a part which is not processed in place, the outer molded surface needs to be processed in the Z direction (axial direction) with a tool withdrawal compensation value Z of 3.14mm, and the tool is normally set in the X direction to finish rough machining;
s4, performing semi-finishing on the outer molded surface, and removing a semi-finishing allowance LSemi-extractIf the outer molded surface has an unprocessed part, the cutter compensation value Z in the Z direction needs to be processed to be 3.14mm, and the cutter is normally adjusted in the X direction;
s5, finish machining the inner and outer mold surfaces respectively according to the above-mentioned Z-3.14 mm compensation value, and removing the remaining finish allowance of 0.15 mm. The part is qualified this time.
The above description is only a preferred embodiment of the present invention and is not intended to limit the present invention, and various modifications and changes may be made by those skilled in the art. Any modification, equivalent replacement, or improvement made within the spirit and principle of the present invention should be included in the protection scope of the present invention.
Claims (5)
1. A machining method for blanks of spinning parts of aviation parts is characterized in that,
calculating theoretical single-side allowance A of an inner molded surface and an outer molded surface of the aviation part spinning and pressing piece according to the theoretical sizes of the aviation part spinning and pressing piece blank and the aviation part spinning and pressing piece, wherein the theoretical single-side allowance A is not more than 3mm, and carrying out numerical control programming processing according to the theoretical size of the aviation part spinning and pressing piece, and the method comprises the following steps:
s1, aligning and clamping the blank of the aviation part spinning part, performing first-step rough machining on the outer profile of the blank of the aviation part spinning part, removing rough machining allowance, judging whether to perform second-step outer profile rough machining on the blank of the aviation part spinning part, and judging whether to perform second-step outer profile rough machining on the blank of the aviation part spinning part comprises the following steps: if the outer profile is completely processed in place, jumping to step S3 according to theoretical single-side allowance, then all processing steps do not need to feed or withdraw, and if the outer profile has a part which is not processed in place, entering step S2;
s2, performing second-step rough machining on the outer profile of the blank of the aviation part spinning piece, keeping the X-direction normal tool setting, supplementing a first machining allowance Z in the Z-direction, determining the depth delta d of an area which is not machined in place, and converting the depth delta d into the first machining allowance Z = delta d/tan alpha in the Z-direction, wherein alpha is the taper of the outer profile of the aviation part spinning piece, the X-direction is the radial direction of the aviation part spinning piece, and the Z-direction is the axial direction of the aviation part spinning piece;
s3, roughly machining the inner profile of the blank of the spinning part of the aviation part, removing rough machining allowance, if the outer profile has a part which is not machined in place, withdrawing the cutter in the Z direction, machining the first machining allowance Z, and normally setting the cutter in the X direction to finish rough machining;
s4, performing semi-finishing on the outer profile of the blank of the spinning part of the aviation part, removing the allowance of the semi-finishing, if the outer profile has a part which is not processed in place, supplementing the first machining allowance Z in the Z direction, and normally setting the tool in the X direction to finish the semi-finishing;
s5, performing finish machining on the inner molded surface and the outer molded surface of the blank of the spinning part of the aviation part respectively, and removing the residual finish machining allowance;
in step S1 and step S3, the rough machining allowance is
；
In step S4, the semi-finishing allowance is
Wherein d is the remaining finishing allowance;
and the residual finishing allowance d is 0.05-0.15 mm.
2. The method for machining a blank of a spinning part of an aerospace part according to claim 1, wherein the blank is formed by machining a blank of a spinning part of an aerospace part,
the determining the depth deltad of the unprocessed-in-place area comprises the following steps:
selecting n position points uniformly distributed in an unprocessed in-place area on an outer molded surface along the axial direction of the blank of the spinning part of the aviation part, checking the whole circle run-out values of the n position points by a machine tool, recording the values as B1, B2, … and Bn respectively, and determining
。
3. The method for machining a blank of a spinning part of an aerospace part according to claim 2, wherein the blank is formed by machining a blank of a spinning part of an aerospace part,
the determining the depth deltad of the unprocessed-in-place area comprises the following steps:
selecting 3 position points uniformly distributed in an unmachined area on an outer molded surface along the axial direction of the blank of the spinning part of the aviation part, checking the whole-circle run-out values of the 3 position points by a machine tool, recording the values as B1, B2 and B3 respectively, and determining
。
4. The method for machining a blank of a spinning part for an aerospace part according to any one of claims 1 to 3, wherein the blank is formed by a die-cutting process,
the specific steps of aligning and clamping the aviation part spinning and pressing piece blank are as follows: clamping the blank of the spinning part of the aviation part on a numerical control machine tool, performing dial indicator operation for alignment, and measuring the reference circle full-circle run-out of the blank of the spinning part of the aviation part by using the dial indicator operation, wherein the run-out value is not more than
And the center of the blank of the spinning part of the aviation part is consistent with the rotation center of the numerical control machine tool.
5. The method for machining a blank of a spinning part for an aerospace part according to any one of claims 1 to 3, wherein the blank is formed by a die-cutting process,
the spinning part of the aviation part comprises a spinning part with a regular shape and a spinning part with an irregular shape.
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| CN115157007B (en) * | 2022-07-11 | 2023-05-05 | 一重集团(黑龙江)重工有限公司 | Machining allowance analysis method for large cylindrical forging |
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| CN103481044A (en) * | 2012-06-11 | 2014-01-01 | 沈阳黎明航空发动机(集团)有限责任公司 | Cutting and feeding path planning method applied to mechanical machining of metal components |
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