CN101518835A - Method for controlling machining distortion of titanium alloy large-size fan blade of large aircraft - Google Patents
Method for controlling machining distortion of titanium alloy large-size fan blade of large aircraft Download PDFInfo
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- CN101518835A CN101518835A CN200910026263A CN200910026263A CN101518835A CN 101518835 A CN101518835 A CN 101518835A CN 200910026263 A CN200910026263 A CN 200910026263A CN 200910026263 A CN200910026263 A CN 200910026263A CN 101518835 A CN101518835 A CN 101518835A
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- titanium alloy
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Abstract
The invention relates to a method for controlling machining distortion of titanium alloy large-size fan blade of a large aircraft, which belongs to the field of manufacturing process for blades of aviation engine. The method can reduce machining errors, effectively control the machining distortion of the blades, and can save raw materials, reduce the cost and improve the machining ratio simultaneously; and the method is characterized in that in the process of machining the blades, a rough part central hole is preserved.
Description
Technical field
The invention belongs to blade of aviation engine manufacturing process field, relate to big aircraft engine fan rotor blade machined development, concrete method for controlling machining distortion of titanium alloy large-size fan blade of large aircraft.
Background technology
Country is carrying out big aircraft manufacturing, and aero-engine is the heart component of big aircraft, and blade is again the vitals of engine.At present the domestic air mail engine is small dimension with titanium alloy blade, blade molded lines torsional angle is little, string is wide little, general finish forge+broaching tenon+profile the chemistry that adopts mills, because its profile of large titanium alloy fan blade is long, the profile tolerance is higher, band damping platform in profile middle part is so machining distortion is wayward greatly.In the past during such blade processing, be positioned at the fabrication hole that drills and reams on the back of the body direction in the leaf top with the blade technological datum, with blade technological datum and fabrication hole location processing leaf top centre bore, with blade technological datum and fabrication hole location processing tenon, put in place with the direct broaching of broaching tool, this method has better effects to vanelets, because the blade blade is short, good rigidly, but for titanium alloy large-sized fan blade because roughing distortion is big, after the heat treatment destressing, the relative position of tenon and centre bore is difficult to guarantee, must be by the benchmark after distortion centre of location hole again, the method is thinner for blade profile, the relatively poor blade of rigidity is more prone to produce problem of unstable, and punching has also increased processing cost again, and working (machining) efficiency is low.
Summary of the invention
At the problems referred to above, the invention provides method for controlling machining distortion of titanium alloy large-size fan blade of large aircraft, it can reduce mismachining tolerance, effectively controls the vane machine machining deformation, can save material, reduce cost, improve simultaneously working (machining) efficiency.
Its technical scheme is such, it is characterized in that: when the processing blade, keep the blank centre bore.
It is further characterized in that: when the processing blade profile, adopt close serrated knife; In the profile process,, adjust the pressure correction profile of zones of different, and adopt the polishing of band cooling fluid according to the surperficial surplus situation of measuring.
Use the inventive method processing titanium alloy large-size fan blade of large aircraft, it can reduce the vane machine machining deformation effectively, and reduces production costs, and improves working (machining) efficiency.
The specific embodiment
The inventive method keeps the blank centre bore when the processing blade; When the processing blade profile, adopt close serrated knife; In the profile process,, adjust the pressure correction profile of zones of different, and adopt the polishing of band cooling fluid according to the surperficial surplus situation of measuring.
Keep the blank centre bore in the inventive method, and do not beat again centre bore, avoided like this that blade profile is thin, the relatively poor blade of rigidity is beaten again the issuable problem of unstable of centre bore, simultaneously can also effectively reduce blank length, save raw material, can save the time and the expense of beating again centre bore again, the more important thing is and to guarantee effectively that back of the body arc surplus is even in the leaf top, reduce the distortion in the processing, with former centre bore location, proportion centering position error is littler like this during thick, finish-milling blade root; When the processing profile, adopt close serrated knife, its cutting force can effectively reduce distortion; In the inventive method, according to the surperficial surplus situation of measuring, adjust the pressure correction profile of zones of different, and adopt the polishing of band cooling fluid, the defective in the time of can reducing the profile etching detection reduces the burn point, and used cooling fluid is the market universal product among the present invention.
Claims (3)
1, method for controlling machining distortion of titanium alloy large-size fan blade of large aircraft is characterized in that: when the processing blade, keep the blank centre bore.
2, method for controlling machining distortion of titanium alloy large-size fan blade of large aircraft according to claim 1 is characterized in that: when the processing blade profile, adopt close serrated knife.
3, method for controlling machining distortion of titanium alloy large-size fan blade of large aircraft according to claim 2, it is characterized in that: in the profile process, according to the surperficial surplus situation of measuring, adjust the pressure correction profile of zones of different, and adopt the polishing of band cooling fluid.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN200910026263A CN101518835A (en) | 2009-03-19 | 2009-03-19 | Method for controlling machining distortion of titanium alloy large-size fan blade of large aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN200910026263A CN101518835A (en) | 2009-03-19 | 2009-03-19 | Method for controlling machining distortion of titanium alloy large-size fan blade of large aircraft |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN101518835A true CN101518835A (en) | 2009-09-02 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN200910026263A Pending CN101518835A (en) | 2009-03-19 | 2009-03-19 | Method for controlling machining distortion of titanium alloy large-size fan blade of large aircraft |
Country Status (1)
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| CN (1) | CN101518835A (en) |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102950316A (en) * | 2012-11-26 | 2013-03-06 | 哈尔滨汽轮机厂有限责任公司 | Processing method of sub-last stage blade with good blade profile stability of large turbine |
| CN103537741A (en) * | 2012-07-13 | 2014-01-29 | 北汽福田汽车股份有限公司 | Evanescent mode processing method for casting automobile stamping die |
| CN105290475A (en) * | 2015-11-05 | 2016-02-03 | 西安航空动力股份有限公司 | Method for milling titanium alloy fan blade profiles |
| CN108687370A (en) * | 2017-04-12 | 2018-10-23 | 通用电气公司 | It drills to the superalloy turbine blades of flexible deformation |
-
2009
- 2009-03-19 CN CN200910026263A patent/CN101518835A/en active Pending
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103537741A (en) * | 2012-07-13 | 2014-01-29 | 北汽福田汽车股份有限公司 | Evanescent mode processing method for casting automobile stamping die |
| CN103537741B (en) * | 2012-07-13 | 2015-09-09 | 北汽福田汽车股份有限公司 | A kind of Press Tools for Automobiles vanish mould for casting processing method |
| CN102950316A (en) * | 2012-11-26 | 2013-03-06 | 哈尔滨汽轮机厂有限责任公司 | Processing method of sub-last stage blade with good blade profile stability of large turbine |
| CN105290475A (en) * | 2015-11-05 | 2016-02-03 | 西安航空动力股份有限公司 | Method for milling titanium alloy fan blade profiles |
| CN105290475B (en) * | 2015-11-05 | 2018-05-29 | 西安航空动力股份有限公司 | A kind of titanium alloy fan blade profile milling method |
| CN108687370A (en) * | 2017-04-12 | 2018-10-23 | 通用电气公司 | It drills to the superalloy turbine blades of flexible deformation |
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| C12 | Rejection of a patent application after its publication | ||
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Open date: 20090902 |