CN114011940A - Engine shell spinning method for eliminating surface cutter-receiving marks - Google Patents
Engine shell spinning method for eliminating surface cutter-receiving marks Download PDFInfo
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- CN114011940A CN114011940A CN202111316419.4A CN202111316419A CN114011940A CN 114011940 A CN114011940 A CN 114011940A CN 202111316419 A CN202111316419 A CN 202111316419A CN 114011940 A CN114011940 A CN 114011940A
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- 238000009987 spinning Methods 0.000 title claims abstract description 109
- 238000000034 method Methods 0.000 title claims abstract description 19
- 238000007514 turning Methods 0.000 claims description 10
- 101100134058 Caenorhabditis elegans nth-1 gene Proteins 0.000 claims description 4
- 238000005520 cutting process Methods 0.000 claims description 3
- 230000007704 transition Effects 0.000 claims description 2
- 208000012886 Vertigo Diseases 0.000 description 77
- 239000002184 metal Substances 0.000 description 4
- 238000010586 diagram Methods 0.000 description 3
- 238000003754 machining Methods 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- 238000003466 welding Methods 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000010276 construction Methods 0.000 description 1
- 230000007123 defense Effects 0.000 description 1
- 238000011161 development Methods 0.000 description 1
- 238000006073 displacement reaction Methods 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 238000004519 manufacturing process Methods 0.000 description 1
- 239000000463 material Substances 0.000 description 1
- 238000012545 processing Methods 0.000 description 1
- 238000003672 processing method Methods 0.000 description 1
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B21—MECHANICAL METAL-WORKING WITHOUT ESSENTIALLY REMOVING MATERIAL; PUNCHING METAL
- B21D—WORKING OR PROCESSING OF SHEET METAL OR METAL TUBES, RODS OR PROFILES WITHOUT ESSENTIALLY REMOVING MATERIAL; PUNCHING METAL
- B21D22/00—Shaping without cutting, by stamping, spinning, or deep-drawing
- B21D22/14—Spinning
- B21D22/16—Spinning over shaping mandrels or formers
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B21—MECHANICAL METAL-WORKING WITHOUT ESSENTIALLY REMOVING MATERIAL; PUNCHING METAL
- B21D—WORKING OR PROCESSING OF SHEET METAL OR METAL TUBES, RODS OR PROFILES WITHOUT ESSENTIALLY REMOVING MATERIAL; PUNCHING METAL
- B21D53/00—Making other particular articles
- B21D53/84—Making other particular articles other parts for engines, e.g. connecting-rods
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Shaping Metal By Deep-Drawing, Or The Like (AREA)
Abstract
The invention provides an engine shell spinning method for eliminating surface cutter mark connection, which comprises the steps of carrying out effective offset distance on inflection points of a next straight line thin-wall section and a slope section and an upper turn inflection point along the axial direction of a shell in the spinning process, and reasonably distributing the degree of an inclination angle of the slope section in each turn of spinning to obtain the engine shell without the surface cutter mark connection. The tool receiving mark on the spinning surface of the engine shell is completely eliminated, the forming quality of the straight line thin-wall section and the slope section of the shell is better, the forming precision is higher, the tool receiving mark on the spinning surface of the engine shell is completely eliminated, the surface quality of the shell after spinning is better, the shell meets the pneumatic requirement during working, and the service performance is greatly improved.
Description
Technical Field
The invention belongs to the technical field of metal part machining, and particularly relates to a spinning method of an engine shell for eliminating surface tool catching marks, which is suitable for spinning forming machining of metal stepped cylinder parts, and particularly aims at solving the problem that tool catching marks are easy to appear on parts in the spinning process.
Background
With the development of spinning forming technology, spinning forming becomes an extremely important forming processing method for metal thin-wall cylinder parts, and the spinning forming method has the process characteristics of high forming precision, good surface quality, high processing efficiency, excellent performance and the like, and is widely applied to the key fields of aerospace, national defense and military industry, automobile manufacturing and the like. As a typical metal thin-wall cylinder part, the engine shell structurally comprises a linear thin-wall section 1, a slope section 2 and a centering part 3 as shown in figure 1, wherein the centering part is often a welding part of the shell, and plays a role in reinforcing the welding of the shell, so that the shell meets the designed mechanical property requirement.
For the spinning forming of the engine shell, a multi-pass powerful spinning mode is generally adopted, a cutter connecting mark 7 is easily generated on a slope section of the shell after spinning, as shown in fig. 2, the existence of the cutter connecting mark 7 enables the shell not to meet the pneumatic requirement in working, and a large negative effect is generated on the performance of the shell. Therefore, the problem of tool contact marks of the engine shell in the spinning process is a key ring for ensuring the spinning forming surface quality and good working performance of the engine shell.
The reason for forming the cutter mark on the spinning surface of the engine shell is mainly that the inflection points of the straight thin-wall section and the slope section of the spinning pass are not effectively offset from the inflection points of the straight thin-wall section and the slope section formed by the previous pass, so that the overlapping part of the trajectory line of the spinning slope of the next pass and the slope surface formed by the previous pass is reduced, namely the rolling part of the slope section is less, the axial component force is reduced, and the whole spinning piece moves reversely, so that the indirect cutter mark of the pass of the spinning slope of the part is formed.
At present, an effective solution is not disclosed for the problem that the surface of the engine shell is easy to have tool-catching marks in the spinning process. Therefore, the research on a method for eliminating the cutter mark on the spinning surface of the engine shell is a technical problem which needs to be solved urgently by the technical personnel in the field.
Disclosure of Invention
In view of the above problems, an object of the present invention is to provide a method for spinning an engine case that eliminates surface contact marks.
In order to achieve the above purpose, the invention adopts the technical scheme that: a spinning method for eliminating surface cutter marks of an engine shell comprises the following steps:
s1, mounting the spinning blank on a spinning machine, and presetting to obtain the engine shell meeting the requirements through N-pass spinning;
the engine shell comprises a linear thin-wall section, a slope section and a centering part which are sequentially arranged, wherein the transition part of the linear thin-wall section and the slope section is an inflection point, the inclination angle degree of the slope section and the thickness of the linear thin-wall section after each pass of spinning of the engine shell are determined, and the inclination angle degree of the slope section after nth pass of spinning is set to be betanThickness t of straight thin-walled segmentn，n＝1、2、3、...、N；
S2, determining coordinate values of turning points of each pass of spinning of the engine shell, staggering the theoretical turning points of the next pass of spinning and the actual turning points of the previous pass of spinning, and after the n-1 pass of spinning forming, staggering S along the axial direction of the shell by the turning points of the n-1 pass of spinning relative to the turning points of the n-1 pass of spinningZMeasuring the length Ln-1 of the straight thin-wall section formed after the spinning of the nth-1 pass, calculating the coordinate value of the inflection point of the spinning track of the nth pass, and determining the inclination angle degree beta of the slope section after the spinning of the nth pass by combining the step S1nAnd (3) compiling a numerical control program, executing the program to carry out nth-pass spinning forming, and repeating the operation until the engine shell without the cutter mark on the surface is obtained after the required N-pass spinning.
After the origin and the coordinate system are set, the coordinate value of the inflection point can be determined according to the spinning of each pass of the engine shell, so that the offset S can be calculatedZEven if the coordinate system determined by different origin points is different, so that the coordinate of the inflection point is different, the offset S representing the relative displacement value of the inflection pointZThe same is true.
Specifically, the inclination angle alpha of the engine shell slope section is not more than 15 degrees, namely the inclination angle alpha of the engine shell slope section meeting the requirement is not more than 15 degrees after N times of spinning, and the inclination angle alpha of the engine shell slope section to be processed is obtained through spinning.
Specifically, the inclination angle degree of each pass of the spinning slope section of the engine shell meets the following relation: alpha ═ betan-△β，△β＝βn-1-βnThat is, the angle of inclination of the slope section is reduced by the angle of inclination of the nth pass compared with the angle of inclination of the slope section of the nth-1 pass, and the angle of inclination is 1.5-3 degrees.
Specifically, the number N of times of the spinning of the engine shell is more than or equal to 2.
Specifically, the offset S along the axial direction of the shellZAnd (5) 0.5t, wherein t is the theoretical value of the wall thickness of the linear thin-walled section after the current-pass spinning of the engine shell, namely the wall thickness of the linear thin-walled section obtained by the nth-pass spinning after the nth-1-pass spinning in S2.
More specifically, the wall thickness t of the straight thin-wall section of the engine shell is more than or equal to 1mm, and the wall thickness of the centering part is less than or equal to 2 t.
The invention has the beneficial effects that:
the forming quality is good: the invention not only completely eliminates the cutter-receiving mark on the spinning surface of the engine shell, but also has better forming quality of the straight thin-wall section and the slope section of the shell and higher forming precision.
The product performance is good: because the cutter receiving mark on the spinning surface of the engine shell is completely eliminated, the surface quality of the shell after spinning is better, and the shell further meets the pneumatic requirement during working.
The operation is simple: the method has simple operation and uncomplicated process, does not need special tools or equipment, and can be finished in the spinning process of the engine shell.
Drawings
FIG. 1 is a schematic diagram of an engine housing construction;
FIG. 2 is a schematic view of a ramp pass cutting mark of an engine housing;
FIG. 3 is a schematic view of a spin-forming structure;
FIG. 4 is a schematic diagram of a spinning right-side structure;
FIG. 5 is a schematic view of a first pass of spinning;
FIG. 6 is a schematic diagram of a second pass of spinning;
FIG. 7 is a schematic view of a third spinning pass;
FIG. 8 is a schematic view after spinning is completed;
wherein, the cutting tool comprises 1-a linear thin-wall section, 2-a slope section, 3-a centering part, 4-a main shaft, 5-a rotating wheel, 6-a core mold and 7-a tool connecting mark.
Detailed Description
The present invention will be described in further detail with reference to the accompanying drawings.
Selecting spinning blank of 30CrMnSiA as material, its inner diameter
A wall thickness of
Inner diameter of engine case after spinning forming
A wall thickness of
The inclination angle of the slope section is 10 degrees, and the spinning forming of the engine shell comprises 3 passes in total.
As shown in fig. 1, the present embodiment provides an engine case spinning method for eliminating surface contact tool marks, including the following steps:
s1, as shown in fig. 3 and 4, the spinning blank is mounted on the core mold 6, the core mold 6 is driven to rotate by the rotation of the spindle 4 of the spinning machine, and further the blank is driven to rotate, the rotation speed of the spindle 4 is 50 r/min; three spinning wheels 5 which are symmetrically arranged are adopted for spinning forming, the radial forces of the three spinning wheels 5 are mutually balanced, the forming quality is good, feeding is synchronously carried out along the axial direction and the radial direction, and the spinning adopts a reverse spinning mode; the three-pass spinning track of the engine shell is shown in fig. 5 to 8, the inclination angle degree of the first-pass spinning slope section is beta 1-16 degrees, the inclination angle degree of the second-pass spinning slope section is beta 2-14 degrees, and the inclination angle degree of the third-pass spinning slope section is beta 3-12 degrees;
s2, accurately measuring the lengths L of the straight thin-wall sections after the first-pass spinning and the second-pass spinning1＝498mm、L2852mm, performing offset Sz1 on the inflection point of the straight-line thin-wall section and the slope section of the second-pass spinning track relative to the inflection point formed after the first-pass spinning along the axial direction of the engine shell to be 2mm, similarly performing offset Sz2 on the inflection point of the third-pass spinning track relative to the inflection point formed after the second-pass spinning along the axial direction of the engine shell to be 1mm, further calculating the inflection point coordinate values of the second-pass spinning track and the third-pass spinning track, compiling a second-pass and third-pass spinning numerical control program by combining the inclination angle degrees of the slope section of the pass spinning determined in the step S1, and finally performing spinning by executing the program to obtain the engine shell which is free of surface joint cutter marks and has the inclination angle degrees of the slope section of 10 degrees, as shown in fig. 8.
The method of the embodiment not only completely eliminates the cutter receiving mark on the spinning surface of the engine shell, but also has better forming quality and higher forming precision of the straight line thin-wall section and the slope section of the shell, and the cutter receiving mark on the spinning surface of the engine shell is completely eliminated, so that the surface quality of the shell after spinning is better, and the shell further meets the pneumatic requirement during working.
The above examples of the present invention are merely illustrative of the present invention and are not intended to limit the embodiments of the present invention. Variations and modifications in other variations will occur to those skilled in the art upon reading the foregoing description. Not all embodiments are exhaustive. All obvious changes and modifications of the present invention are within the scope of the present invention.
Claims (6)
1. A spinning method for eliminating surface cutter marks of an engine shell is characterized by comprising the following steps:
s1, the engine shell to be processed comprises a straight line thin-wall section, a slope section and a centering part which are sequentially arranged, wherein the transition position of the straight line thin-wall section and the slope section is an inflection point, and the spinning slope section of each pass of the engine shell is determinedThe degree of the inclination angle is set as beta in the first slope section1The inclination angle degree of the slope section of the nth pass is betanFinally obtaining the inclination angle degree alpha of the slope section required by the shell after the required n-pass spinning;
s2, determining coordinate values of turning points of each pass of spinning of the engine shell, staggering the turning points between the passes and the tracks, and on the basis of the turning points after the n-1 pass of spinning forming, staggering S along the axial direction of the shell for the turning points of the straight-line thin-wall section and the slope section of the nth pass of spinning track relative to the turning points after the n-1 pass of spinning formingZMeasuring the length Ln-1 of the straight thin-wall section formed after the spinning of the nth-1 pass, calculating the coordinate value of the inflection point of the spinning track of the nth pass, compiling a numerical control program by combining the inclination angle degree of the slope section of the nth pass determined in the step S1, finally executing the program to perform the spinning forming of the nth pass, and obtaining the engine shell without the cutter mark on the surface after the spinning of the required n passes.
2. The method for spinning the engine shell to eliminate the surface cutter marks according to claim 1, wherein the inclination angle degree of each spinning slope section of the engine shell satisfies the following relation: alpha ═ betan-△β，△β＝βn-1-βnThat is, the angle of inclination of the slope section is reduced by the angle of inclination of the nth pass compared with the angle of inclination of the slope section of the nth-1 pass, and the angle of inclination is 1.5-3 degrees.
3. The method for spinning the engine housing with the surface cutting marks eliminated according to claim 1 or 2, wherein the inclination angle degree alpha of the slope section of the engine housing is less than or equal to 15 degrees.
4. The engine shell spinning method for eliminating the surface cutter marks according to claim 1, characterized in that the number n of spinning channels of the engine shell is more than or equal to 2.
5. The method for spinning the engine shell for eliminating the surface cutter mark according to claim 1, wherein the offset Sz along the axial direction of the shell is obtained according to an empirical formula SZAnd calculating 0.5t, wherein t is a theoretical value of the wall thickness of the straight thin-wall section of the engine shell after the current-pass spinning.
6. The engine housing spinning method for eliminating the surface cutter mark according to claim 5, characterized in that the wall thickness t of the straight thin-walled section of the engine housing is more than or equal to 1mm, and the wall thickness of the centering part is less than or equal to 2 t.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111316419.4A CN114011940A (en) | 2021-11-08 | 2021-11-08 | Engine shell spinning method for eliminating surface cutter-receiving marks |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111316419.4A CN114011940A (en) | 2021-11-08 | 2021-11-08 | Engine shell spinning method for eliminating surface cutter-receiving marks |
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2021
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Application publication date: 20220208 |