CN104028782A - Lathe machining method for end face deep narrow groove in aerial engine crankcase - Google Patents
Lathe machining method for end face deep narrow groove in aerial engine crankcase Download PDFInfo
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- CN104028782A CN104028782A CN201410249686.8A CN201410249686A CN104028782A CN 104028782 A CN104028782 A CN 104028782A CN 201410249686 A CN201410249686 A CN 201410249686A CN 104028782 A CN104028782 A CN 104028782A
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
- B23B—TURNING; BORING
- B23B1/00—Methods for turning or working essentially requiring the use of turning-machines; Use of auxiliary equipment in connection with such methods
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Abstract
The invention provides a lathe machining method for an end face deep narrow groove in an aerial engine crankcase. The method comprises the following machining steps: 1, using a groove cutter to carry out the first machining step to form a transition end face deep narrow groove, wherein the width of a blade of the groove cutter is less than that of the end face deep narrow groove to be machined, and at least two opposite groove walls of the transition end face deep narrow groove have machining allowances; 2, removing the machining allowances of the transition end face deep narrow groove to form the actually machined end face deep narrow groove. According to the lathe machining method, the machined end face deep narrow groove is higher in machining precision.
Description
Technical field
The present invention relates to aero-engine casing processing technique field, in particular to the method for turning of the dark narrow groove of a kind of aero-engine casing end face.
Background technology
At present, in aero-engine, titanium alloy casing, high temperature alloy casing are applied to respectively compressor part and turbine part, as shown in Figure 1, on casing, all there is the narrow groove structure of the annular precise being processed to form through turning, for stator guide vane is installed, guide the dark narrow groove 1 of end face of air-flow.The process of the dark narrow groove 1 of above-mentioned end face is mainly to adopt blade width and estimate the groove cutter that the dark narrow well width of processing end face is identical and carry out a feed to form the dark narrow groove 1 of end face, but, adopting said method to carry out turning processing exists cutting force large, chip removal is difficult, the problem of easily forging a knife, as shown in Figure 2, the dark narrow groove 3 of actual processing end face (solid line region in figure) and the expectation processing dark narrow groove 4 of end face (dashed region in figure) after 2 processing of groove cutter are not identical, during grooving, can not guarantee that the feed of groove cutter straight line parallel causes skew, and cutting fluid is difficult to enter cutting zone, easily produce thermal deformation, flexural deformation, groove width size and cell wall are difficult to guarantee to the size at casing center.Above-mentioned situation all can reduce the machining accuracy of the dark narrow groove 1 of the end face machining.
Summary of the invention
The present invention aims to provide a kind of dark narrow groove of end face machining that makes and has the more method for turning of the dark narrow groove of aero-engine casing end face of high manufacturing accuracy.
To achieve these goals, the invention provides the method for turning of the dark narrow groove of a kind of aero-engine casing end face, comprise: the first procedure of processing, adopt blade width to be less than and estimate that the groove cutter of the dark narrow well width of processing end face carries out the first procedure of processing to form the dark narrow groove of transition end face, at least two relative cell walls of the dark narrow groove of transition end face all have allowance; The second procedure of processing, the allowance on the dark narrow groove of removal transition end face is to form the dark narrow groove of actual processing end face.
Further, the first procedure of processing comprises: groove cutter carries out repeatedly feed, and has withdrawing No. one time between adjacent twice feed.
Further, adopt above-mentioned blade width to be less than and estimate that the groove cutter of the dark narrow well width of processing end face carries out the second procedure of processing, the second procedure of processing comprises processing in the 3rd minute and processing in the 4th minute, processing in the 3rd minute comprises the allowance of removing a cell wall in two cell walls, and processing in the 4th minute comprises the allowance of removing another cell wall in two cell walls.
Further, the bottom land of the dark narrow groove of transition end face has allowance, adopt above-mentioned blade width to be less than and estimate that the groove cutter of the dark narrow well width of processing end face carries out the second procedure of processing, the second procedure of processing comprises processing in the 3rd minute and processing in the 4th minute, processing in the 3rd minute comprises the allowance of a cell wall removed in two cell walls and the allowance of the branch position of bottom land, and processing in the 4th minute comprises the allowance of another cell wall removed in two cell walls and the allowance of the rest position of bottom land.
Further, processing in the 3rd minute and processing in the 4th minute include: groove cutter carries out repeatedly feed, and has withdrawing No. one time between adjacent twice feed.
Further, the allowance of each cell wall account for estimate the dark narrow groove of processing end face width 5% to 7%.
Further, the allowance of bottom land account for estimate the dark narrow groove of processing end face the degree of depth 0.2% to 0.5%.
Further, in the first procedure of processing, each depth of cut of groove cutter account for estimate the dark narrow groove of processing end face the degree of depth 14% to 25%, each withdrawing amount accounts for 20% to 25% of the depth of cut.
Further, the aero-engine casing that adopts method for turning to process is to be made by titanium alloy or nickel base superalloy.
Further, the turning rotating speed of the turning rotating ratio of aero-engine casing when the first procedure of processing when the second procedure of processing is slow, and the feed velocity of groove cutter when the first procedure of processing is slower than the feed velocity when the second procedure of processing.
Apply technical scheme of the present invention, owing to first carrying out the first procedure of processing to form the dark narrow groove of transition end face, and two cell walls of the dark narrow groove of transition end face all have allowance, therefore when carrying out the second procedure of processing when by allowance removal on two cell walls, the suffered resistance of groove cutter is little, causes cutting force to diminish, groove cutter is more easily along projected path feed, reduce side-play amount, and reduced thermal deformation and flexural deformation, and then made the dark narrow groove of actual processing end face more meet standard.As the above analysis, method for turning of the present invention makes the dark narrow groove of end face machining have higher machining accuracy.
Accompanying drawing explanation
The Figure of description that forms the application's a part is used to provide a further understanding of the present invention, and schematic description and description of the present invention is used for explaining the present invention, does not form inappropriate limitation of the present invention.In the accompanying drawings:
Fig. 1 shows the partial schematic sectional view of aero-engine casing in prior art;
The partial schematic sectional view (hatching of not shown groove cutter) of the aero-engine casing that Fig. 2 shows Fig. 1 after the processing of groove cutter;
Fig. 3 shows according to the schematic flow sheet of the embodiment of the method for turning of the dark narrow groove of aero-engine casing end face of the present invention.
The specific embodiment
It should be noted that, in the situation that not conflicting, embodiment and the feature in embodiment in the application can combine mutually.Describe below with reference to the accompanying drawings and in conjunction with the embodiments the present invention in detail.
As shown in Figure 3, the method for turning of the dark narrow groove of aero-engine casing end face of the present embodiment comprises the first procedure of processing and the second procedure of processing, adopt blade width to be less than and estimate that the groove cutter of the dark narrow well width of processing end face carries out the first procedure of processing to form the dark narrow groove of transition end face, the dark narrow groove of transition end face is carried out to the second procedure of processing, allowance on the dark narrow groove of removal transition end face is to form the dark narrow groove of actual processing end face, and two cell walls of the dark narrow groove of transition end face all have allowance.
The method for turning of the dark narrow groove of aero-engine casing end face of application the present embodiment, owing to first carrying out the first procedure of processing to form the dark narrow groove of transition end face, and two cell walls of the dark narrow groove of transition end face all have allowance, therefore when carrying out the second procedure of processing when by allowance removal on two cell walls, the suffered resistance of groove cutter is little, cause cutting force to diminish, groove cutter is more easily along projected path feed, reduced side-play amount, and reduced thermal deformation and flexural deformation, and then made the dark narrow groove of actual processing end face more meet standard.As the above analysis, the method for turning of the present embodiment makes the dark narrow groove of end face machining have higher machining accuracy.In addition, why will make two cell walls all have allowance, be that the side-play amount that groove cutter produces causes certain cell wall to the off size standard at aero-engine casing center, and cannot make up in order to prevent when the first procedure of processing.In addition, owing to estimating that the groove width of the dark narrow groove of processing end face is narrow, therefore, the blade width of the groove cutter of selecting is also just narrow, and the narrower rigidity of groove blade width is poorer, and machining accuracy is poorer, because the method for turning of the present embodiment is divided into two steps, the dark narrow groove of transition end face forming through the first procedure of processing leaves allowance, therefore, can make up the defect of the first procedure of processing so that the dark narrow groove of end face machining has higher machining accuracy by the second procedure of processing.
In the present embodiment, the first procedure of processing comprises that groove cutter carries out repeatedly feed, and has withdrawing No. one time between adjacent twice feed.Owing to having No. one time withdrawing between adjacent twice feed, so groove cutter stressing conditions improves, and guarantees that iron filings can be able to discharge smoothly, reduces the risk of forging a knife, the service life of the groove cutter of prolongation.
The aero-engine casing that the method for turning of employing the present embodiment is processed is to be made by titanium alloy or nickel base superalloy, because above-mentioned bi-material all belongs to difficult to machine material, difficult to machine material is more easily forged a knife, the precision of processing is more inaccurate, and the effect that the method for turning of employing the present embodiment is processed the aero-engine casing of above-mentioned material is more obvious.
The method for turning of the present embodiment for the groove degree of the dark narrow groove of expectation processing end face be 4 to 7mm, groove width is 1.5 to 2mm, " depth-to-width ratio " is 2 to 4.7.The precision of the dark narrow groove of expectation processing end face with above-mentioned " depth-to-width ratio " in reality processing is not high, also just more difficult processing, and the effect that adopts the method for turning of the present embodiment to process is more obvious.
In the present embodiment, adopt above-mentioned blade width to be less than and estimate that the groove cutter of the dark narrow well width of processing end face carries out the second procedure of processing, the second procedure of processing comprises processing in the 3rd minute and processing in the 4th minute, processing in the 3rd minute comprises the allowance of removing a cell wall in two cell walls, and processing in the 4th minute comprises the allowance of removing another cell wall in two cell walls.Adopt and to carry out the second procedure of processing with groove cutter identical in the first procedure of processing, can avoid the Efficiency Decreasing that brings due to replacing groove cutter, and when the method for turning of Digit Control Machine Tool application the present embodiment, can realize the continuity of processing.As feasible embodiment, also can adopt blade width to equal to estimate that the groove cutter of the dark narrow well width of processing end face carries out the second procedure of processing.
In the present embodiment, the bottom land of the dark narrow groove of transition end face has allowance, adopt above-mentioned blade width to be less than and estimate that the groove cutter of the dark narrow well width of processing end face carries out the second procedure of processing, processing in the 3rd minute comprises the allowance of a cell wall removed in two cell walls and the allowance of the branch position of bottom land, and processing in the 4th minute comprises the allowance of another cell wall removed in two cell walls and the allowance of the rest position of bottom land.Because bottom land has allowance, therefore, in the time of can preventing the second procedure of processing, bottom land produces and connects tool marks, reduces the surface quality of the bottom land of estimating the dark narrow groove of processing end face.Because the precision of Digit Control Machine Tool is very high, therefore, if adopt blade width to equal to estimate that the groove cutter of the dark narrow well width of processing end face carries out the second procedure of processing, without making the bottom land of the dark narrow groove of transition end face there is allowance.
In the present embodiment, processing in the 3rd minute and processing in the 4th minute include groove cutter and carry out repeatedly feed, and have withdrawing No. one time between adjacent twice feed.Owing to having No. one time withdrawing between adjacent twice feed, so groove cutter stressing conditions improves, and guarantees that iron filings can be able to discharge smoothly, reduce the risk of forging a knife, in the service life of the groove cutter extending, be conducive to cutting fluid simultaneously and enter cutting zone, and what process can obtain good surface quality.The method that the method for turning of the present embodiment adopts is " in the middle of first turning, rear turning both sides, and the cutter of repeatedly advancing and retreat during turning ", each step of said method is fitted to each other, and makes to estimate that the dark narrow groove of processing end face has higher machining accuracy.
By inventor according to iron filings chip breaking situation, cutter actual wear, the turning ability analysis of the aero-engine casing that the factors such as working (machining) efficiency are made titanium alloy, high-temperature alloy material, draw the optimum cutting parameter when the dark narrow groove of processing end face, in the present embodiment, the allowance of each cell wall account for estimate the dark narrow groove of processing end face width 5% to 7%.Why adopt above-mentioned number range to be because if two side surplus very little, easy cutter relieving when carrying out the second procedure of processing, machining accuracy is difficult for guaranteeing, if surplus is too many, on the one hand, it is large that the cutting force in the second procedure of processing becomes, on the other hand, groove cutter width requirement in the first procedure of processing is narrower, more easily causes and forges a knife, and inventor just determines above-mentioned numerical value by many experiments.Preferably, the allowance of each cell wall account for estimate the dark narrow groove of processing end face width 5%, for the width of estimating the dark narrow groove of processing end face, be that 2mm is example, the allowance of each cell wall is 0.1mm.
In the present embodiment, the allowance of bottom land account for estimate the dark narrow groove of processing end face the degree of depth 0.2% to 0.5%, preferably, the allowance of bottom land account for estimate the dark narrow groove of processing end face the degree of depth 0.5%.Why adopt above-mentioned number range to be because if surplus very little, adds easy cutter relieving in man-hour, still may exist and connect tool marks, if surplus is too many, groove cutter bottom is stressed large, and bottom land and cell wall add the precision that trade union affects groove sidewall simultaneously, and inventor just determines above-mentioned numerical value by many experiments.For the degree of depth of estimating the dark narrow groove of processing end face, be that 4mm is example, the allowance of bottom land is 0.02mm.
In the present embodiment, in the first procedure of processing, each depth of cut of groove cutter account for estimate the dark narrow groove of processing end face the degree of depth 14% to 25%, each withdrawing amount accounts for 20% to 25% of the depth of cut.Why adopt above-mentioned number range to be because if feed very little, the second procedure of processing adds the iron filings that produce man-hour and is difficult for chip breaking to cut efficiency low, if feed is too many, it is large that cutting force becomes, reduce cutter life, easily forge a knife, inventor just determines above-mentioned numerical value by many experiments.Preferably, each depth of cut of groove cutter account for estimate the dark narrow groove of processing end face the degree of depth 25%, each withdrawing amount accounts for 20% of the depth of cut.For the degree of depth of estimating the dark narrow groove of processing end face, be that 4mm is example, each withdrawing amount is 1mm, and each withdrawing amount is 0.2mm.
In the present embodiment, in processing in the 3rd minute and processing in the 4th minute, each depth of cut of groove cutter account for estimate the dark narrow groove of the processing dark narrow groove end face of end face the degree of depth 14% to 25%, each withdrawing amount accounts for 20% to 25% of the depth of cut, preferably, each depth of cut of groove cutter account for estimate the dark narrow groove of processing end face the degree of depth 25%, each withdrawing amount accounts for 20% of the depth of cut.For the degree of depth of estimating the dark narrow groove of processing end face, be that 4mm is example, each withdrawing amount is 1mm, and each withdrawing amount is 0.2mm.
In the present embodiment, the turning rotating speed of the turning rotating ratio of aero-engine casing when the first procedure of processing when the second procedure of processing is slow, and the feed velocity of groove cutter when the first procedure of processing is slower than the feed velocity when the second procedure of processing.During feed velocity feed velocity the first procedure of processing, the turning rotating speed of aero-engine casing is 20m/min to 35m/min, also can say, the rotating speed of aero-engine casing is 20m/min to 35m/min, and the feed velocity of groove cutter is 0.01mm/r to 0.03mm/r.During the second procedure of processing, the turning rotating speed of aero-engine casing is 22m/min to 40m/min, also can say, the rotating speed of aero-engine casing is 25m/min to 40m/min, and the feed velocity of groove cutter is 0.04mm/r to 0.08mm/r.
For nickel base superalloy, make aero-engine casing, during the first procedure of processing, the turning rotating speed of aero-engine casing is 30m/min, and the feed velocity of groove cutter is 0.02mm/r; During the second procedure of processing, the turning rotating speed of aero-engine casing is 35m/min, and the feed velocity of groove cutter is 0.06mm/r.For cast superalloy, make aero-engine casing, during the first procedure of processing, the turning rotating speed of aero-engine casing is 20m/min, and the feed velocity of groove cutter is 0.01mm/r; During the second procedure of processing, the turning rotating speed of aero-engine casing is 25m/min, and the feed velocity of groove cutter is 0.04mm/r.For titanium alloy, make aero-engine casing, during the first procedure of processing, the turning rotating speed of aero-engine casing is 35m/min, and the feed velocity of groove cutter is 0.03mm/r; During the second procedure of processing, the turning rotating speed of aero-engine casing is 40m/min, and the feed velocity of groove cutter is 0.08mm/r.
The foregoing is only the preferred embodiments of the present invention, be not limited to the present invention, for a person skilled in the art, the present invention can have various modifications and variations.Within the spirit and principles in the present invention all, any modification of doing, be equal to replacement, improvement etc., within all should being included in protection scope of the present invention.
Claims (10)
1. a method for turning for the dark narrow groove of aero-engine casing end face, is characterized in that, comprising:
The first procedure of processing, adopts blade width to be less than and estimates that the groove cutter of the dark narrow well width of processing end face carries out described the first procedure of processing to form the dark narrow groove of transition end face, and at least two relative cell walls of the dark narrow groove of described transition end face all have allowance;
The second procedure of processing, removes allowance on the dark narrow groove of described transition end face to form the dark narrow groove of actual processing end face.
2. method for turning according to claim 1, is characterized in that, described the first procedure of processing comprises:
Described groove cutter carries out repeatedly feed, and described in adjacent twice, has No. one time between feed withdrawing.
3. method for turning according to claim 1, it is characterized in that, adopt above-mentioned blade width to be less than and estimate that the groove cutter of the dark narrow well width of processing end face carries out described the second procedure of processing, described the second procedure of processing comprises processing in the 3rd minute and processing in the 4th minute, processing in described the 3rd minute comprises the allowance of removing a described cell wall in described two cell walls, and processing in described the 4th minute comprises the allowance of removing cell wall described in another in described two cell walls.
4. method for turning according to claim 1, it is characterized in that, the bottom land of the dark narrow groove of described transition end face has allowance, adopt above-mentioned blade width to be less than and estimate that the groove cutter of the dark narrow well width of processing end face carries out described the second procedure of processing, described the second procedure of processing comprises processing in the 3rd minute and processing in the 4th minute, processing in described the 3rd minute comprises the allowance of a described cell wall removed in described two cell walls and the allowance of the branch position of described bottom land, processing in described the 4th minute comprises the allowance of removing the allowance of cell wall described in another in described two cell walls and the rest position of described bottom land.
5. according to the method for turning described in claim 3 or 4, it is characterized in that, processing in described the 3rd minute and processing in described the 4th minute include:
Described groove cutter carries out repeatedly feed, and described in adjacent twice, has No. one time between feed withdrawing.
6. method for turning according to claim 1, is characterized in that, described in each allowance of cell wall account for the dark narrow groove of described expectation processing end face width 5% to 7%.
7. method for turning according to claim 4, is characterized in that, the allowance of described bottom land account for the dark narrow groove of described expectation processing end face the degree of depth 0.2% to 0.5%.
8. method for turning according to claim 2, it is characterized in that, in described the first procedure of processing, each depth of cut of described groove cutter account for the dark narrow groove of described expectation processing end face the degree of depth 14% to 25%, each described withdrawing amount accounts for 20% to 25% of the described depth of cut.
9. method for turning according to claim 1, is characterized in that, the aero-engine casing that adopts described method for turning to process is to be made by titanium alloy or nickel base superalloy.
10. method for turning according to claim 1, it is characterized in that, the turning rotating speed of the turning rotating ratio of aero-engine casing when described the first procedure of processing when described the second procedure of processing is slow, and the feed velocity of described groove cutter when described the first procedure of processing is slower than the feed velocity when described the second procedure of processing.
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Cited By (11)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104483892A (en) * | 2014-10-28 | 2015-04-01 | 沈阳黎明航空发动机(集团)有限责任公司 | Receiver part complex surface numerical control machining method |
| CN104475843A (en) * | 2014-11-07 | 2015-04-01 | 沈阳黎明航空发动机(集团)有限责任公司 | Processing method for annular type engine-case radial narrow groove |
| CN106623987A (en) * | 2016-12-27 | 2017-05-10 | 中国南方航空工业(集团)有限公司 | Precision machining method for deep and narrow groove of flame tube thin-walled part |
| CN107175470A (en) * | 2017-06-02 | 2017-09-19 | 中国航发南方工业有限公司 | The special-shaped deep groove processing method of titanium alloy component |
| CN107876843A (en) * | 2017-11-24 | 2018-04-06 | 中国航发沈阳黎明航空发动机有限责任公司 | A kind of titanium alloy inlet casing branch wrench space deep narrow groove processing method |
| CN109277584A (en) * | 2018-11-09 | 2019-01-29 | 中国航发沈阳黎明航空发动机有限责任公司 | A kind of efficient method for turning of high temperature alloy integral wheel |
| CN109290592A (en) * | 2018-11-14 | 2019-02-01 | 中国航发动力股份有限公司 | A kind of deeply narrow annular groove tool in resilient bearing seat end face and processing method |
| CN110744070A (en) * | 2019-11-18 | 2020-02-04 | 中国航发贵州黎阳航空动力有限公司 | Method for machining molded surface of flame tube of ultrathin-wall aircraft engine |
| CN110744071A (en) * | 2019-11-18 | 2020-02-04 | 中国航发贵州黎阳航空动力有限公司 | Method for machining deep and narrow groove with angle |
| CN111001825A (en) * | 2019-12-26 | 2020-04-14 | 保定市东利机械制造股份有限公司 | Deep groove rough turning process |
| CN115351305A (en) * | 2022-08-24 | 2022-11-18 | 西安万威机械制造股份有限公司 | Numerical control machining method for air film groove of thin-walled part |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPH03170231A (en) * | 1989-11-30 | 1991-07-23 | Mitsubishi Heavy Ind Ltd | Super precision processing method |
| CN101530966A (en) * | 2009-04-13 | 2009-09-16 | 吴淼东 | Manufacturing method of turning tool of small inner bore grooving tool |
| CN102489719A (en) * | 2011-11-16 | 2012-06-13 | 中国南方航空工业(集团)有限公司 | NC (Numerical Control) machining method for oblique end slot of thin-wall workpiece |
| CN103447833A (en) * | 2013-08-12 | 2013-12-18 | 重庆江增船舶重工有限公司 | PTFE (polytetrafluoroethylene) plastic rotating sleeve machining method |
| CN104162683A (en) * | 2014-05-06 | 2014-11-26 | 哈尔滨汽轮机厂有限责任公司 | Numerical control machining method of steam turbine rotor sawtooth groove |
-
2014
- 2014-06-06 CN CN201410249686.8A patent/CN104028782A/en active Pending
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPH03170231A (en) * | 1989-11-30 | 1991-07-23 | Mitsubishi Heavy Ind Ltd | Super precision processing method |
| CN101530966A (en) * | 2009-04-13 | 2009-09-16 | 吴淼东 | Manufacturing method of turning tool of small inner bore grooving tool |
| CN102489719A (en) * | 2011-11-16 | 2012-06-13 | 中国南方航空工业(集团)有限公司 | NC (Numerical Control) machining method for oblique end slot of thin-wall workpiece |
| CN103447833A (en) * | 2013-08-12 | 2013-12-18 | 重庆江增船舶重工有限公司 | PTFE (polytetrafluoroethylene) plastic rotating sleeve machining method |
| CN104162683A (en) * | 2014-05-06 | 2014-11-26 | 哈尔滨汽轮机厂有限责任公司 | Numerical control machining method of steam turbine rotor sawtooth groove |
Cited By (13)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104483892A (en) * | 2014-10-28 | 2015-04-01 | 沈阳黎明航空发动机(集团)有限责任公司 | Receiver part complex surface numerical control machining method |
| CN104475843A (en) * | 2014-11-07 | 2015-04-01 | 沈阳黎明航空发动机(集团)有限责任公司 | Processing method for annular type engine-case radial narrow groove |
| CN106623987A (en) * | 2016-12-27 | 2017-05-10 | 中国南方航空工业(集团)有限公司 | Precision machining method for deep and narrow groove of flame tube thin-walled part |
| CN107175470B (en) * | 2017-06-02 | 2019-03-05 | 中国航发南方工业有限公司 | The special-shaped deep groove processing method of titanium alloy component |
| CN107175470A (en) * | 2017-06-02 | 2017-09-19 | 中国航发南方工业有限公司 | The special-shaped deep groove processing method of titanium alloy component |
| CN107876843A (en) * | 2017-11-24 | 2018-04-06 | 中国航发沈阳黎明航空发动机有限责任公司 | A kind of titanium alloy inlet casing branch wrench space deep narrow groove processing method |
| CN109277584A (en) * | 2018-11-09 | 2019-01-29 | 中国航发沈阳黎明航空发动机有限责任公司 | A kind of efficient method for turning of high temperature alloy integral wheel |
| CN109290592A (en) * | 2018-11-14 | 2019-02-01 | 中国航发动力股份有限公司 | A kind of deeply narrow annular groove tool in resilient bearing seat end face and processing method |
| CN110744070A (en) * | 2019-11-18 | 2020-02-04 | 中国航发贵州黎阳航空动力有限公司 | Method for machining molded surface of flame tube of ultrathin-wall aircraft engine |
| CN110744071A (en) * | 2019-11-18 | 2020-02-04 | 中国航发贵州黎阳航空动力有限公司 | Method for machining deep and narrow groove with angle |
| CN111001825A (en) * | 2019-12-26 | 2020-04-14 | 保定市东利机械制造股份有限公司 | Deep groove rough turning process |
| CN115351305A (en) * | 2022-08-24 | 2022-11-18 | 西安万威机械制造股份有限公司 | Numerical control machining method for air film groove of thin-walled part |
| CN115351305B (en) * | 2022-08-24 | 2024-01-12 | 西安万威机械制造股份有限公司 | Numerical control machining method for thin-wall part air film groove |
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Application publication date: 20140910 |
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