CN101363327B - Method for processing TC11 material blade - Google Patents
Method for processing TC11 material blade Download PDFInfo
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- CN101363327B CN101363327B CN2008101560293A CN200810156029A CN101363327B CN 101363327 B CN101363327 B CN 101363327B CN 2008101560293 A CN2008101560293 A CN 2008101560293A CN 200810156029 A CN200810156029 A CN 200810156029A CN 101363327 B CN101363327 B CN 101363327B
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Abstract
The present invention relates to a method for processing a TC11 material vane. The method can conveniently machine out a TC11 material aviation vane which has large torsional angle, large string width, large rough blank profile margin and uneven margins at all positions and is easy to machine. The method comprises the steps as follows: retesting a central forging hole, processing the back of a middle body, a technical reference of the air outlet side and a vane top axial reference face, rough machining a vane root and a vane root bottom surface technical button, processing for reverse adjustment, finish milling the profile, polishing the profile, processing the total length, removing a vane top central hole and removing the vane root bottom surface button. The present invention is characterized in that the vane top central hole during swaging processing is always kept until the total length is cut; a forging vane top central hole is considered as the reference; after the distressing treatment, the reverse adjustment is conducted, and the vane root and the surface of the vane root bottom surface technical button is fine finished; a vane root positioning area is increased, so the technical button is reserved at the vane root bottom surface, a vane root molding knife is used for processing the vane root and the surface of the vane root bottom surface technical button to ensure that the surface of the vane root bottom surface technical button is consistent with the vane root; and when milling comprehensively, the vane root and the surface of the vane root bottom surface technical button are used for positioning, and the vane profile is rough milled and fine milled.
Description
(1) technical field
The present invention relates to the processing of leaves technical field, be specially a kind of processing method of TC11 material blade.
(2) background technique
Progress along with the domestic air mail motor, blade of aviation engine strong mechanical performance, lightweight requirement have been proposed, so the Design trend at blade of aviation engine are: select the contour performance material of difficult machining of TC11 titanium alloy for use, and in the blade shape design, continuous attenuate vane thickness, the torsional angle chord that increases blade is wide.This has brought big problem with regard to the manufacturing of giving blade.Because titanium alloy cold straightening meeting resilience just is difficult to satisfy the Blade Design requirement in case machining deformation takes place.So do not adopt the method for profile milling in traditional TC11 material blade processing scheme, but with the profile chemistry milling method that does not almost have machining deformation.Traditional TC11 material blade processing scheme step is: blade finish forge → thick, finish-milling blade technological datum face → broaching processing blade root → profile chemistry mill.But along with the wide increase of twist angle of blade chord in the Blade Design, the difficulty of the finish forge of blade constantly increases, and has to take die forging.And die forging precision deficiency causes the blade blank profile surplus constantly to increase, and surplus is inhomogeneous everywhere, makes blade profile the profile chemistry miller process processing of surplus such as can't use.
(3) summary of the invention
At the problems referred to above, the invention provides a kind of processing method of TC11 material blade, it can process easily, and torsional angle is big, and the string width is big, and the blank profile surplus is big, and the uneven TC11 material of surplus aerial blade everywhere, and processing is convenient.
Its technological scheme is such:
It may further comprise the steps:
(1) repetition measurement forges center hole;
(2) with three center holes location, axially to good blade line, the processing intermediate back side, the side of giving vent to anger technological datum and leaf apical axis are to reference level;
(3) be benchmark with the intermediate back side, the side of giving vent to anger technological datum and leaf top center hole, axial reference level, surplus of roughing blade root and blade root bottom surface technology, blade root and surplus single face of blade root bottom surface technology stay the 1mm surplus;
(4) rough mill the profile single face and stay the 1.5mm surplus with blade root, leaf top center hole location;
(5) destressing;
(6) repair center lapping, the center hole surface reaches Ra0.4
(7) carrying out reverse adjustment, is primary standard with leaf top center hole, and with the intermediate back side, the side of giving vent to anger technological datum location, fine finishing blade root and surplus surface of blade root bottom surface technology;
(8) with blade root, leaf top center hole location finish-milling profile;
(9) profile is repaiied in throwing;
(10) leaf top center hole is removed in length overall processing, removes surplus of blade root bottom surface;
It is characterized in that: keep die forging and add the leaf top center hole in man-hour, after stress removing, carry out reverse adjustment, fine finishing blade root and surplus surface of blade root bottom surface technology until the cutting length overall is a benchmark to forge leaf top center hole; Increase the blade root locating area, so stay surplus of technology in the blade root bottom surface,, guarantee that surplus surface of technology, blade root bottom surface is consistent with blade root with blade root moulding cutter processing blade root and surplus surface of blade root bottom surface technology, when comprehensively milling with blade root and surplus surface alignment of blade root bottom surface technology, thick, finish-milling blade profile.
By above-mentioned processes TC11 material blade, can save the leaf topping material, can save the time and the expense of beating again center hole again, the more important thing is to guarantee all the time that back of the body arc surplus is even in the leaf top, reduce the distortion in the processing.
(4) description of drawings
Fig. 1 increases the false boss schematic representation for blade root;
Fig. 2 is to be benchmark with leaf top center hole, adjusts the schematic representation of fine finishing blade root.
(5) embodiment
Below in conjunction with accompanying drawing course of working of the present invention is described
(1) repetition measurement forges center hole;
(2) with three center holes location, axially to good blade line, the processing intermediate back side, the side of giving vent to anger technological datum and leaf apical axis are to reference level;
(3) with the intermediate back side, the side of giving vent to anger technological datum and leaf top center hole 4, axially reference level is a benchmark, in time processing, roughing simultaneously goes out surplus of blade root and blade root bottom surface technology; Increase surplus surface of technology, blade root bottom surface as the blade root locating area, because blade root locating area axial direction is shorter, be difficult for locating the distortion that also easily causes in the processing, stay surplus of technology in the blade root bottom surface, with the thick moulding cutter of blade root, in time processing, processing blade root and surplus surface of blade root bottom surface technology, guarantee that blade root bottom surface technical face is consistent with blade root, when comprehensively milling with blade root and surplus surface alignment of blade root bottom surface technology;
(4) rough mill the profile single face and stay the 1.5mm surplus with blade root, leaf top center hole location;
(5) destressing;
(6) repair center lapping, the center hole surface reaches Ra0.4
(7) carry out reverse adjustment, with leaf top center hole is primary standard, and with the intermediate back side, the side of giving vent to anger technological datum location, the blade root procedure is adjusted in position according to the relative blade root of leaf top center hole, in time processing, go out blade root and surplus surface of blade root bottom surface technology with the fine finishing of blade root precisive shaped cutter;
(8) with blade root, leaf top center hole location finish-milling profile;
(9) profile is repaiied in throwing;
(10) three center holes are removed in length overall processing, remove surplus of blade root bottom surface;
In above-mentioned technology, keep die forging and add the leaf top center hole in man-hour until the cutting length overall, to forge leaf top center hole is benchmark, after stress removing, carry out reverse adjustment, fine finishing blade root and surplus surface of blade root bottom surface technology have been improved the usability of processing technology and have been helped to improve machining accuracy; Increase the blade root locating area, because blade root locating area axial direction is shorter, be not easy for location and control deformable blade, so stay surplus of technology in the blade root bottom surface, with blade root moulding cutter processing blade root and surplus surface of blade root bottom surface technology, guarantee that surplus surface of technology, blade root bottom surface is consistent with blade root, when comprehensively milling with blade root and surplus surface alignment of blade root bottom surface technology, slightly, the finish-milling blade profile, effectively suppress machining deformation.The main points of this technology are: hold out against leaf top center hole all the time when thick, finish-milling blade root, be used for the location; And the blade root procedure is adjusted in the position according to the relative blade root of leaf top center hole when the finish-milling blade root; Increase surplus in the blade root bottom surface, provide the technology locating face also to suppress distortion and produce, 1 false boss among the figure for increase, 2 is the root center line, and 3 is the molded lines center line, and A, B, C are respectively blade root and eat size.
Claims (1)
1. the processing method of a TC11 material blade, it may further comprise the steps:
(1) repetition measurement forges center hole;
(2) with three center holes location, axially to good blade line, the processing intermediate back side, the side of giving vent to anger technological datum and leaf apical axis are to reference level;
(3) be benchmark with the intermediate back side, the side of giving vent to anger technological datum and leaf top center hole, axial reference level, surplus of roughing blade root and blade root bottom surface technology, blade root and surplus single face of blade root bottom surface technology stay the 1mm surplus;
(4) rough mill the profile single face and stay the 1.5mm surplus with blade root, leaf top center hole location;
(5) destressing;
(6) repair center lapping, the center hole surface reaches Ra0.4
(7) carrying out reverse adjustment, is primary standard with leaf top center hole, and with the intermediate back side, the side of giving vent to anger technological datum location, fine finishing blade root and surplus surface of blade root bottom surface technology;
(8) with blade root, leaf top center hole location finish-milling profile;
(9) profile is repaiied in throwing;
(10) leaf top center hole is removed in length overall processing, removes surplus of blade root bottom surface;
It is characterized in that: keep die forging and add the leaf top center hole in man-hour, after stress removing, carry out reverse adjustment, fine finishing blade root and surplus surface of blade root bottom surface technology until the cutting length overall is a benchmark to forge leaf top center hole; Increase the blade root locating area, so stay surplus of technology in the blade root bottom surface,, guarantee that surplus surface of technology, blade root bottom surface is consistent with blade root with blade root moulding cutter processing blade root and surplus surface of blade root bottom surface technology, when comprehensively milling with blade root and surplus surface alignment of blade root bottom surface technology, thick, finish-milling blade profile.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2008101560293A CN101363327B (en) | 2008-09-26 | 2008-09-26 | Method for processing TC11 material blade |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2008101560293A CN101363327B (en) | 2008-09-26 | 2008-09-26 | Method for processing TC11 material blade |
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| Publication Number | Publication Date |
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| CN101363327A CN101363327A (en) | 2009-02-11 |
| CN101363327B true CN101363327B (en) | 2011-08-24 |
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| CN2008101560293A Active CN101363327B (en) | 2008-09-26 | 2008-09-26 | Method for processing TC11 material blade |
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| CN102658459B (en) * | 2012-05-18 | 2014-05-21 | 重庆江增船舶重工有限公司 | Manufacturing method of blade for centrifugal aeration blower diffuser and positioning tool for same |
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| CN102794609A (en) * | 2012-08-24 | 2012-11-28 | 无锡透平叶片有限公司 | Method for re-drilling center holes of blades |
| CN102935582A (en) * | 2012-11-16 | 2013-02-20 | 哈尔滨汽轮机厂有限责任公司 | Processing method of large blade with tiepiece boss and bone type shroud ring structure of turbine |
| 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 |
| CN103240574B (en) * | 2013-05-10 | 2015-05-27 | 西安航空动力股份有限公司 | Processing method of journal guide vane of aero-engine |
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| CN104308481B (en) * | 2014-10-27 | 2017-01-11 | 西安航空动力股份有限公司 | Stator blade machining method of aeroengine compressor without mounting plate |
| CN105436838B (en) * | 2015-11-05 | 2018-02-23 | 西安航空动力股份有限公司 | A kind of moving turbine blade machining process |
| CN105252224B (en) * | 2015-11-19 | 2017-09-22 | 华中科技大学无锡研究院 | A kind of aero-engine outer duct outlet guide vanes processing method |
| CN111687269B (en) * | 2020-06-09 | 2021-04-27 | 安徽江淮汽车集团股份有限公司 | Rear door outer plate stamping process method and automobile rear door outer plate |
| CN112819206B (en) * | 2021-01-19 | 2023-08-22 | 无锡透平叶片有限公司 | Technological treatment method for blade mixing sequencing |
| CN114310203B (en) * | 2021-12-31 | 2024-05-24 | 无锡透平叶片有限公司 | Secondary processing method for assembling surface of blade shroud and boss of turbine blade |
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Address after: 214000 No. 1800, Huishan Avenue, Huishan Economic Development Zone, Wuxi City, Jiangsu Province Patentee after: WUXI TURBINE BLADE Co.,Ltd. Address before: 214023 No. 305 Yang Qing Road, Jiangsu, Wuxi Patentee before: WUXI TURBINE BLADE Co.,Ltd. |
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