CN105312643A - Machining method for aero-engine part sealing coating - Google Patents
Machining method for aero-engine part sealing coating Download PDFInfo
- Publication number
- CN105312643A CN105312643A CN201510767465.4A CN201510767465A CN105312643A CN 105312643 A CN105312643 A CN 105312643A CN 201510767465 A CN201510767465 A CN 201510767465A CN 105312643 A CN105312643 A CN 105312643A
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- China
- Prior art keywords
- cutting
- machine tool
- coating
- processing method
- aircraft engine
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Classifications
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
- B23C—MILLING
- B23C3/00—Milling particular work; Special milling operations; Machines therefor
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
- B23C—MILLING
- B23C2215/00—Details of workpieces
- B23C2215/04—Aircraft components
Abstract
The invention discloses a machining method for an aero-engine part sealing coating. The machining method comprises the steps that a part to be machined is fixed to a numerical control machine tool after spraying is completed; then a hard alloy milling cutter is selected, and parameters of the numerical control machine tool are set; climb milling is conducted through the side edge of the hard alloy milling cutter; the cutting anterior angle and the relief angle are greater than three degrees, and the coating surface of the part to be machined is subjected to milling machining. Due to the fact that climb milling is conducted through the side edge of the hard alloy milling cutter and the cutting anterior angle and the relief angle are greater than three degrees, cutter cutting is in a shearing state and the coating is machined, the cutting force is reduced, and coating particles are prevented from falling down. Meanwhile, the relative grinding efficiency of the same milling mode is greatly improved, coating chip-falling can be avoided and the machining efficiency can be improved.
Description
Technical field
The present invention relates to aero-engine manufacturing technology field, particularly relate to a kind of processing method of aircraft engine parts seal coating.
Background technology
In aircraft engine parts, rotational parts and stationary components need to obturage, position of obturaging contacts realization by rotational parts comb tooth with stationary components small―gap suture, one end, contact site is the comb tooth of part, the other end is the surface of band coating, the surface of band coating is generally realized by spraying on part base solid, through analyzing the structure and characteristics of coating material, conventional nickel aluminium coating adds that the aluminium powder of 30% sprays to the surface of part through special spraying equipment by the nickel powder of 70%, the structure formed is the lepidiod porous organization of multilayer, there is a large amount of holes, mechanics surface is anisotropy.Therefore, it is different from the metal material of forging, is also different from composite, and coating does not dissolve completely, forms through repeatedly piling up.Because sprayed surface size and roughness cannot meet the demands, usually need to carry out machining, to reach surface size and roughness requirements.
Common machining process adopts Vehicle Processing or grinding, the advantage of Vehicle Processing is convenient, but in Vehicle Processing process, Lathe tool tip is vertical with piece surface slips over, because cutting force is comparatively large, there is very strong stripping effect for loose coating, the defect such as block, surface chromatic aberration is fallen in easy generation, when coating finished surface can not meet final part requirements, need, by coating removal, again to spray, expensive owing to dusting, significantly increase part manufacturing cost.And grinding is processed by very little cutting data, processing mode is grinding, because cutting data is little, cutting force is little, and therefore grinding is effective, not easily produce block and surface chromatic aberration, but the working (machining) efficiency of grinding is very low, cannot meet Production requirement.
Therefore, the processing method designing a kind of better aircraft engine parts seal coating is necessary, to solve the problem.
Summary of the invention
For prior art Problems existing, the invention provides one and prevent coating from falling block, and the processing method of the high aircraft engine parts seal coating of working (machining) efficiency.
To achieve these goals, the present invention adopts following technical scheme:
A kind of processing method of aircraft engine parts seal coating, comprise and first the part to be processed completing spraying is fixed on Digit Control Machine Tool, then carbide-tipped milling cutter is selected, set the parameter of described Digit Control Machine Tool, the side edge of described carbide-tipped milling cutter is used to carry out climb cutting, the forward and backward angle of cutting is greater than 3 °, to carry out Milling Process to the coating surface of described part to be processed.
Further, described Digit Control Machine Tool is selectable according to work surface is vertical four-coordinates machine tool or horizontal four-coordinates machine tool.
Further, Milling Process is divided into roughing and fine finishining, and cutting linear velocity is 30 ~ 50m/min, roughing cutting depth is 0.5mm ~ 1.2mm, per tooth feeding is 0.05mm ~ 0.15mm, and fine finishining cutting depth is 0.05mm ~ 0.15mm, and per tooth feeding is 0.005mm ~ 0.015mm.
Further, in roughing, cutter rotating speed is 1061 turns/min, and the amount of feeding is 424mm/min, and in fine finishining, cutter rotating speed is 1061 turns/min, and the amount of feeding is 42mm/min.
Further, the four tooth screw-on cutters of described carbide-tipped milling cutter to be diameter be 10mm ~ 16mm.
Beneficial effect of the present invention:
The side edge of carbide-tipped milling cutter is used to carry out climb cutting, the coating surface treating processing parts carries out Milling Process, the forward and backward angle of cutting is greater than 3 °, Tool in Cutting is made to be in shearing condition processing coating, reduce cutting force, prevent coating granule from dropping, the relative grinding efficiency of mode of milling simultaneously improves greatly, both coating can have been avoided to fall block, can working (machining) efficiency have been improved again.
Accompanying drawing explanation
Fig. 1 is the machining sketch chart of aircraft engine parts seal coating of the present invention;
In figure, 1-part to be processed, 2-coating, 3-carbide-tipped milling cutter.
Detailed description of the invention
Below in conjunction with the accompanying drawing in the embodiment of the present invention, be clearly and completely described the technical scheme in the embodiment of the present invention, obviously, described embodiment is only a part of embodiment of the present invention, instead of whole embodiments.Based on the embodiment in the present invention, those of ordinary skill in the art, not making the every other embodiment obtained under creative work prerequisite, belong to the scope of protection of the invention.
As Fig. 1, the invention provides a kind of processing method of aircraft engine parts seal coating, first the part to be processed 1 completing spraying is fixed on Digit Control Machine Tool, Digit Control Machine Tool is selected according to work surface, if work surface is radial dimension, select vertical four-coordinates machine tool, if work surface is axial dimension, select horizontal four-coordinates machine tool.Then the carbide-tipped milling cutter 3 that diameter is suitable is selected, and set the parameter of Digit Control Machine Tool, the diameter of carbide-tipped milling cutter 3 is that 10mm ~ 16mm is for best, the side edge of milling cutter 3 is used to carry out climb cutting, the forward and backward angle of cutting is greater than 3 °, and Milling Process is carried out on coating 2 surface for the treatment of processing parts 1 with suitable cutter rotating speed, the amount of feeding and feed speed.
The Milling Process of coating 2 is divided into roughing and fine finishining, and cutting linear velocity is 30 ~ 50m/min, mainly determines according to the hardness of coating 2.Roughing cutting depth is 0.5mm ~ 1.2mm, per tooth feeding is 0.05mm ~ 0.15mm, cutting depth is large, feeding block, then can improve working (machining) efficiency, fine finishining cutting depth is 0.05mm ~ 0.15mm, and per tooth feeding is 0.005mm ~ 0.015mm, then can improve dimensional accuracy, reduce surface roughness.
Can be processed the part met the demands by above-mentioned processing method, reduce and fall block and surface chromatic aberration in process, surface luminous intensity is good, can reduce simultaneously and repeat to spray number of times, efficiency faster than grinding 30% ~ 50%.
Be below the process of processing parts roughness 1.6:
First select Digit Control Machine Tool, this example processing axial dimension, therefore select horizontal Four axis machining center, then part is fixed on platen, selection diameter is the four tooth screw-on cutters of 12mm, and use its side edge to process, the forward and backward angle of cutting is greater than 3 °, determine machined parameters: roughing cutting depth is 0.5mm, linear velocity is 40m/min, and per tooth feeding is 0.1mm, and cutter rotating speed is 1061 turns/min, the amount of feeding is 424mm/min, for the allowance of 0.1mm is stayed in fine finishining.Fine finishining cutting depth is 0.1mm, and linear velocity is 40m/min, and per tooth feeding is 0.005mm ~ 0.015mm, and cutter rotating speed is 1061 turns/min, and the amount of feeding is 42mm/min, thus ensures the requirement of part roughness 1.6.
Above embodiment is only in order to illustrate technical scheme of the present invention and unrestricted, although with reference to preferred embodiment to invention has been detailed description, those skilled in the art are to be understood that, can modify to technical scheme of the present invention or equivalent replacement, and not departing from aim and the scope of the technical program, it all should be encompassed in right of the present invention.
Claims (5)
1. the processing method of an aircraft engine parts seal coating, it is characterized in that, comprise: first the part to be processed completing spraying is fixed on Digit Control Machine Tool, then carbide-tipped milling cutter is selected, set the parameter of described Digit Control Machine Tool, use the side edge of described carbide-tipped milling cutter to carry out climb cutting, the forward and backward angle of cutting is greater than 3 °, to carry out Milling Process to the coating surface of described part to be processed.
2. the processing method of aircraft engine parts seal coating according to claim 1, is characterized in that: described Digit Control Machine Tool is selectable according to work surface is vertical four-coordinates machine tool or horizontal four-coordinates machine tool.
3. the processing method of aircraft engine parts seal coating according to claim 1, it is characterized in that: Milling Process is divided into roughing and fine finishining, cutting linear velocity is 30 ~ 50m/min, roughing cutting depth is 0.5mm ~ 1.2mm, per tooth feeding is 0.05mm ~ 0.15mm, fine finishining cutting depth is 0.05mm ~ 0.15mm, and per tooth feeding is 0.005mm ~ 0.015mm.
4. the processing method of aircraft engine parts seal coating according to claim 3, it is characterized in that: in roughing, cutter rotating speed is 1061 turns/min, the amount of feeding is 424mm/min, and in fine finishining, cutter rotating speed is 1061 turns/min, and the amount of feeding is 42mm/min.
5. the processing method of aircraft engine parts seal coating according to claim 1, is characterized in that: the four tooth screw-on cutters of described carbide-tipped milling cutter to be diameter be 10mm ~ 16mm.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510767465.4A CN105312643A (en) | 2015-11-11 | 2015-11-11 | Machining method for aero-engine part sealing coating |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510767465.4A CN105312643A (en) | 2015-11-11 | 2015-11-11 | Machining method for aero-engine part sealing coating |
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| Publication Number | Publication Date |
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| CN105312643A true CN105312643A (en) | 2016-02-10 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN201510767465.4A Pending CN105312643A (en) | 2015-11-11 | 2015-11-11 | Machining method for aero-engine part sealing coating |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108405996A (en) * | 2018-03-20 | 2018-08-17 | 深圳市守正航空工业有限公司 | The processing technology of Thin-walled Workpiece |
| CN109158677A (en) * | 2018-09-29 | 2019-01-08 | 芜湖通潮精密机械股份有限公司 | A kind of dry etching lower electrode surface covering Milling Process Cutting tool and its processing method |
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| CN1827862A (en) * | 2006-04-10 | 2006-09-06 | 南京航空航天大学 | Layered microstructure electroforming method and apparatus |
| DE102006022572A1 (en) * | 2006-05-15 | 2007-11-22 | Gühring Ohg | Milling tool for machining e.g. sandwich-like designed material composite board, has peripheral blades, whose cutting geometry changes in peripheral direction from one blade to another blade with same cutting direction in opposite direction |
| CN102676970A (en) * | 2012-05-29 | 2012-09-19 | 青铜峡铝业股份有限公司 | In-situ spraying reparation method of horizontal aluminum busbar in electrolytic plant |
| CN102862108A (en) * | 2012-09-12 | 2013-01-09 | 沈阳黎明航空发动机(集团)有限责任公司 | Grinding method for processing cobalt-chromium-tungsten coating by diamond grinding wheel |
| CN103588469A (en) * | 2013-11-05 | 2014-02-19 | 中国航空工业集团公司北京航空材料研究院 | Method for preparing ceramic-based high temperature abradable seal coating layer based on sol-gel |
| US20140227055A1 (en) * | 2013-02-13 | 2014-08-14 | Airbus Operations Sas | Method For Machining A Through-Hole In A Component And Machining Device For Implementing The Said Method |
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2015
- 2015-11-11 CN CN201510767465.4A patent/CN105312643A/en active Pending
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN1827862A (en) * | 2006-04-10 | 2006-09-06 | 南京航空航天大学 | Layered microstructure electroforming method and apparatus |
| DE102006022572A1 (en) * | 2006-05-15 | 2007-11-22 | Gühring Ohg | Milling tool for machining e.g. sandwich-like designed material composite board, has peripheral blades, whose cutting geometry changes in peripheral direction from one blade to another blade with same cutting direction in opposite direction |
| CN102676970A (en) * | 2012-05-29 | 2012-09-19 | 青铜峡铝业股份有限公司 | In-situ spraying reparation method of horizontal aluminum busbar in electrolytic plant |
| CN102862108A (en) * | 2012-09-12 | 2013-01-09 | 沈阳黎明航空发动机(集团)有限责任公司 | Grinding method for processing cobalt-chromium-tungsten coating by diamond grinding wheel |
| US20140227055A1 (en) * | 2013-02-13 | 2014-08-14 | Airbus Operations Sas | Method For Machining A Through-Hole In A Component And Machining Device For Implementing The Said Method |
| CN103588469A (en) * | 2013-11-05 | 2014-02-19 | 中国航空工业集团公司北京航空材料研究院 | Method for preparing ceramic-based high temperature abradable seal coating layer based on sol-gel |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108405996A (en) * | 2018-03-20 | 2018-08-17 | 深圳市守正航空工业有限公司 | The processing technology of Thin-walled Workpiece |
| CN108405996B (en) * | 2018-03-20 | 2019-03-19 | 深圳市守正航空工业有限公司 | The processing technology of Thin-walled Workpiece |
| CN109158677A (en) * | 2018-09-29 | 2019-01-08 | 芜湖通潮精密机械股份有限公司 | A kind of dry etching lower electrode surface covering Milling Process Cutting tool and its processing method |
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Application publication date: 20160210 |
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