CN102962694A - Clamping positioning device for finish machining aero-engine turbine blade - Google Patents
Clamping positioning device for finish machining aero-engine turbine blade Download PDFInfo
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- CN102962694A CN102962694A CN2012104744011A CN201210474401A CN102962694A CN 102962694 A CN102962694 A CN 102962694A CN 2012104744011 A CN2012104744011 A CN 2012104744011A CN 201210474401 A CN201210474401 A CN 201210474401A CN 102962694 A CN102962694 A CN 102962694A
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- cover plate
- position housing
- positioning device
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Abstract
The invention discloses a clamping positioning device for finish machining an aero-engine turbine blade, and the clamping positioning device comprises a framework consisting of a front cover plate, a rear cover plate, a left cover plate, a right cover plate, an upper cover plate and a lower cover plate through screws, a back surface positioning compression block which is arranged inside the framework and matched with the back molded surface of a blade body, a pelvic surface positioning compression block which is matched with a pelvic molded surface of the blade body, a positioning compression block which is matched with the blade body or an exhaust edge molded surface and a compression component which is used for compressing the other edge of the blade body, wherein one of the back surface positioning compression block and the pelvic surface positioning compression block is adjustably arranged on the front cover plate or the rear cover plate in the compression direction, the right cover plate or the left cover plate is provided with a blade body placing opening, and the cover plate is provided with a blade axial positioning component. Compared with the prior art, a fixing way for utilizing low-melting-point alloy to position the blade is adopted, so that the blade machining cost is greatly reduced, and problems caused by removing the low-melting-point alloy on the blade body can be avoided.
Description
Technical field
The present invention relates to the processing of aero engine turbine blades tenon, more specifically, relate to a kind of for the accurately machined clamping and positioning device of aero engine turbine blades tenon.
Background technology
Turbo blade in the aero-engine adopts smart type casting moulding, and wherein blade is one-shot forming, does not have allowance for finish, need not carry out machined, but the integral shroud of blade and tenon also need carry out further fine finishining by machined, to satisfy the matching requirements of blade.Because the free form surface that the blade surface forms for space coordinates point, conventional anchor clamps scheme are difficult to realize its location is clamped.The fine finishining location of traditional engine turbine blade is that employing cast low-melting alloy in square chest is fixed the blade blade, although this mode can realize the location to blade, and positioning accuracy and clamping force aspect existing problems and hidden danger.This is that bad to the positioning accuracy retentivity of blade, the clamping force that provides is less, is subjected to cutting force to affect easy distortion in the fine finishining process, and then affects machining accuracy because low-melting alloy has preferably ductility.In addition, because low-melting alloy directly contacts with the blade surface, the molten square chest that moves back after fine finishining is finished, inevitably can be at blade remained on surface low-melting alloy, some model engine turbine blade is hollow blade besides, molten moving back in the process of square chest after cast low-melting alloy fixed blade and the blade fine finishining in square chest, when misoperation molten state alloy can pour into the blade cavity inside, very difficult for the low-melting alloy removal process that remains in blade surface and pour into cavity inside, and have no idea to get rid of fully for the alloy that pours into cavity inside at all, the alloy that left behind is in the turbine running, under the hot environment of turbine work, can be penetrated into blade crystalline phase organization internal, with blade material component generation chemical reaction, cause the blade material performance to change, directly have influence on blade working performance and life-span.
In order to eliminate the low-melting alloy that remains on the blade surface and to enter low-melting alloy in the blade cavity to the impact of blade; tradition is removed the method for low-melting alloy; adopt first high temperature bath to dissolve for the low-melting alloy that remains in blade surface; but this measure can not guarantee to get rid of the low-melting alloy that remains in the blade surface fully, usually also needs to polish the alloy of blade remained on surface after high temperature bath.Blade remained on surface low-melting alloy is removed in polishing need to be very careful, slightly do not note having influence on blade surface profile degree, and then affect the blade fluid mechanical property, and extremely waste time and energy.For the low-melting alloy that pours into the blade cavity inside, only have at present the method that adopts high temperature bath to add pickling technique to remove.Removing the residual alloy of cavity inside for high temperature bath also is to guarantee thorough removal, for acid cleaning process, although acid cleaning process carries out for removing residual alloy, can not guarantee the composition matrix of blade material is not produced corrosion impact.
In view of prior art adopts in square chest the cast low-melting alloy too many to the problem that blade is fixed existence, production practices are badly in need of finding a kind of not by pour into a mould the locate mode of low-melting alloy fixed blade in square chest, to avoid removing the problems that the alloy in blade remained on surface alloy and the blade cavity brings.This mode is preferably abandoned cast low-melting alloy technique fully, comes one to take away the firewood under the cauldron, put things right once and for all.
Summary of the invention
Blade is fixed the problem of existence for prior art employing cast low-melting alloy in square chest, purpose of the present invention aims to provide and a kind ofly realizes the device that the blade location clamps is finished the fine finishining of blade tenon with mechanical clamping type, removes variety of issue that the alloy in blade remained on surface alloy and the blade cavity exists with worried to realize fundamentally solving.
Provided by the invention for the accurately machined clamping and positioning device of aero engine turbine blades tenon, mainly comprise: by front shroud, back shroud, left cover, the right cover plate, the framework that upper cover plate and lower cover consist of by screw, be positioned at the back side position housing piece that framework and blade back side profile match, the pelvic surface of sacrum position housing piece that matches with blade pelvic surface of sacrum profile, the position housing piece that matches with blade air inlet or exhaust edge profile and be used for compressing the pressed component at another edge of blade, described back side position housing piece is separately positioned on relative two cover plates that consist of framework with the pelvic surface of sacrum position housing piece, and both arrange on the cover board adjustably in compaction direction one of at least, the pressed component that the position housing piece that matches with blade air inlet or exhaust edge profile and being used for compresses another edge of blade is separately positioned on another two relative cover plates that consist of framework, is designed with at right cover plate or left cover to make blade insert opening in the framework and the align member of axial location blade.
In order to solve better technical problem to be solved by this invention, the present invention also can further take following technical measures.Following every technical measures can be taked separately, also capable of being combined taking, even take in the lump.
In technique scheme, described back side position housing piece preferentially is separately positioned on two cover plates of relative front and back with the pelvic surface of sacrum position housing piece, and the pressed component that the position housing piece that matches with blade air inlet or exhaust edge profile and being used for compresses another edge of blade is separately positioned on relative up and down two cover plates.Described back side position housing piece and pelvic surface of sacrum position housing piece be preferred set-up mode further, be both one of be fixedly installed on front shroud or the back shroud, another is arranged on back shroud or the front shroud adjustably in compaction direction.Further preferred mode again, the pelvic surface of sacrum position housing piece is fixedly installed on the back shroud, and back side position housing piece is arranged on the front shroud adjustably in compaction direction.Back side position housing piece can be by being arranged on adjustment screw on the front shroud in the compaction direction adjustment.
In technique scheme, the side preferred design that described back side position housing piece and blade back side profile match is useful on the groove that reduces with the blade phase-contact surface; The side that described pelvic surface of sacrum position housing piece and blade pelvic surface of sacrum profile match preferably also is designed with for the groove of minimizing with the blade phase-contact surface, to improve chucking power, better clamping position blade.
In technique scheme, describedly be arranged on position housing piece that lower cover and blade edge profile match and pay the utmost attention to locating piece into location blade air inlet leading edge.
In technique scheme, described to be arranged on the upper cover plate pressed component that is used for compressing the blade edge be housing screw, and the blade edge that compresses is the exhaust back edge.
In technique scheme, the described member that is used for the blade axial location on right cover plate or the left cover that is arranged on is preferentially selected alignment pin, realizes the blade axial location by the listrium face that the alignment pin termination is supported between blade blade and the tenon.
Provided by the invention for the accurately machined clamping and positioning device of aero engine turbine blades tenon, be based on that the inventor finishes the profound understanding design of benchmark relation between the blade of engine turbine blade and the tenon.The engine turbine blade adopts smart type casting moulding, wherein blade is one-shot forming, the blade surface is without surplus, three basal plane design basises of turbo blade are all on tenon, tenon coordinate system and blade profile coordinate system have definite conversion relation, therefore only need utilize location, blade smart casting surface to clamp three design basises of tenon are processed, integral shroud fine finishining benchmark afterwards just can be transformed into the tenon benchmark, namely the design basis of blade.Provided by the invention for the accurately machined clamping and positioning device of aero engine turbine blades tenon, the clamping position mentality of designing is to utilize blade leaf basin profile that basin is located dorsad, utilize the blade leading edge to turnover gas direction location, utilize the listrium upper surface that the length of blade direction is located, blade back side locating piece provides main clamping force, and the blade trailing edge is by screw in compression stop.
Employing the invention provides clamping and positioning device the aero engine turbine blades tenon is carried out fine finishining, because clamping device is combining structure, adopt mechanical force to step up the location, therefore in blade tenon fine finishining process, can realize resetting, Reusability, need not every blade and be equipped with a square chest, adopt compared to prior art square chest cast low-melting alloy blade locate mode, every blade all needs to join a square chest, greatly reduces manufacturing, use, maintenance, cost of upkeep.Also fundamentally avoided simultaneously square chest cast low-melting alloy locating blades to bring, after the blade finishing step is finished, remove the molten square chest that moves back and remain in blade surface low-melting alloy, and move back in the square chest process because careless manipulation causes the molten condition low-melting alloy to pour into worry and problem that the blade cavity brings molten.Also can take simultaneously owing to adopt cast-type, most of finishing size of square chest all be with the design drawing size conversion above square chest, producing benchmark when conversion designs figure size does not overlap, cause deviation accumulation, be unfavorable for rationally strict control design drawing size, in use distortion is loosening easily for the low-melting alloy of adding cast, directly reduces the problems such as blade processing precision.Adopt clamping and positioning device of the present invention, in use be difficult for becoming flexible, be conducive to improve positioning accuracy, be beneficial to control blade processing precision.
Description of drawings
Accompanying drawing 1 is the structural representation of facing of clamping and positioning device of the present invention.
Accompanying drawing 2 is left TV structure schematic diagrames of clamping and positioning device of the present invention.
Accompanying drawing 3 is the pelvic surface of sacrum compact heap Facad structure schematic diagrames in the clamping and positioning device.
Accompanying drawing 4 is the pelvic surface of sacrum compact heap side structure schematic diagrames in the clamping and positioning device.
Accompanying drawing 5 is the back side compact heap Facad structure schematic diagrames in the clamping and positioning device.
Accompanying drawing 6 is the back side compact heap side structure schematic diagrames in the clamping and positioning device.
In above-mentioned accompanying drawing, the object that each shown by reference numeral represents is respectively: 1-regulates housing screw; 2-air inlet leading edge position housing piece; The 3-left cover; The 4-joint bolt; 5-right cover plate; The 6-sharf is to alignment pin; 7-air inlet leading edge position housing piece; The 8-lower cover; The 9-back shroud; 10 blade pelvic surface of sacrum position housing pieces; 11-exhaust back edge housing screw; The 12-upper cover plate; 13-connects alignment pin; The 14-housing screw; The 15-front shroud; 16-blade back side position housing piece; The 17-joint bolt.
The specific embodiment
Provide embodiments of the invention below in conjunction with accompanying drawing, and in conjunction with the embodiments the present invention is conducted further description, so that people's the understanding of the present invention.Specific constructive form of the present invention is not limited to the described form of following embodiment; the thought that those skilled in the art can disclose according to the present invention also can be designed other specific embodiment not paying creatively work, but these specific embodiment that content design goes out according to the present invention still belong to protection scope of the present invention.
Embodiment 1
Present embodiment be used for the accurately machined clamping and positioning device of aero engine turbine blades tenon, its structure is shown in accompanying drawing 1 to 4, consist of and to comprise by front shroud 15, back shroud 9, left cover 3, right cover plate 5, upper cover plate 12 and lower cover 8 by joint bolt 17 etc. and the framework that connects alignment pin 13 etc. and consist of, be designed with at right cover plate 5 and make blade insert opening in the framework and the alignment pin 6 of axial location blade, realize the blade axial location by the listrium face that the alignment pin termination is supported between blade blade and the tenon.The back side position housing piece 16 that matches with blade back side profile in framework is arranged on the front shroud 15 in compaction direction adjustably by the adjusting housing screw 14 that is arranged on the front shroud, the pelvic surface of sacrum position housing piece 10 that matches with blade pelvic surface of sacrum profile is fixedly installed on the back shroud 9, the locating piece 2 that matches with blade admission edge profile, 7 arranges on the lower cover by regulating housing screw 1, and the housing screw 11 that is used for compressing blade exhaust trailing edge is arranged on the upper cover plate 12.The side that described back side position housing piece 16 and blade back side profile match, and the side that matches of described pelvic surface of sacrum position housing piece 10 and blade pelvic surface of sacrum profile, all be designed with for the in length and breadth groove of minimizing with the blade phase-contact surface, realize better clamping position to improve chucking power.
Because certain model aero engine turbine blades is whole smart casting, the blade of blade is smart type casting moulding once, does not have allowance.The tenon of blade is the reference for assembling of blade, and the precision of blade assembling is high, relies on the machining accuracy of tenon fully, and the processing of tenon is the emphasis of blade, and the molding surface size tolerance is very strict.The turbo blade tenon tooth is the vertical tree type tenon tooth, and the transverse tooth thickness tolerance is 0/-0.06, and working face profile tolerance tolerance is 0.015.The side set degree is 0.02, and the linearity tolerance on all working face is 0.01, and all profile surface roughnesses 1.6 add difficult assurance in man-hour.Now adopt locating and clamping apparatus of the present invention that the turbo blade of this model is processed, more than 300 turbo blade that has machined, tenon size and surface roughness meet designing requirement fully, the tenon passing rate of processing reaches more than 99%, thereby reduced the percent defective of part, greatly reduced the processing cost of blade.
Claims (10)
1. one kind is used for the accurately machined clamping and positioning device of aero engine turbine blades tenon, it is characterized in that mainly comprising: by front shroud, back shroud, left cover, the right cover plate, the framework that upper cover plate and lower cover consist of by screw, be positioned at the back side position housing piece that framework and blade back side profile match, the pelvic surface of sacrum position housing piece that matches with blade pelvic surface of sacrum profile, the position housing piece that matches with blade air inlet or exhaust edge profile and be used for compressing the pressed component at another edge of blade, described back side position housing piece is separately positioned on relative two cover plates that consist of framework with the pelvic surface of sacrum position housing piece, and both arrange on the cover board adjustably in compaction direction one of at least, the pressed component that the position housing piece that matches with blade air inlet or exhaust edge profile and being used for compresses another edge of blade is separately positioned on another two relative cover plates that consist of framework, is designed with at right cover plate or left cover to make blade insert opening in the framework and the align member of axial location blade.
2. according to claim 1 for the accurately machined clamping and positioning device of aero engine turbine blades tenon, it is characterized in that described back side position housing piece and pelvic surface of sacrum position housing piece are separately positioned on two cover plates of relative front and back, the pressed component that the position housing piece that matches with blade air inlet or exhaust edge profile and being used for compresses another edge of blade is separately positioned on relative up and down two cover plates.
3. according to claim 2 for the accurately machined clamping and positioning device of aero engine turbine blades tenon, one of it is characterized in that in described back side position housing piece and the pelvic surface of sacrum position housing piece being fixedly installed on front shroud or the back shroud, another is arranged on back shroud or the front shroud adjustably in compaction direction.
4. according to claim 3 for the accurately machined clamping and positioning device of aero engine turbine blades tenon, it is characterized in that described pelvic surface of sacrum position housing piece is fixedly installed on the back shroud, back side position housing piece is arranged on the front shroud adjustably in compaction direction.
5. according to claim 4 for the accurately machined clamping and positioning device of aero engine turbine blades tenon, it is characterized in that back side position housing piece is by being arranged on compression adjustment screw on the front shroud in the compaction direction adjustment.
6. according to claim 1 to one of 5 described for the accurately machined clamping and positioning device of aero engine turbine blades tenon, it is characterized in that a side that described back side position housing piece and blade back side profile match is designed with for the groove that reduces with the blade phase-contact surface.
7. according to claim 1 to one of 5 described for the accurately machined clamping and positioning device of aero engine turbine blades tenon, it is characterized in that a side that described pelvic surface of sacrum position housing piece and blade pelvic surface of sacrum profile match is designed with for the groove that reduces with the blade phase-contact surface.
8. according to claim 1 to one of 5 described for the accurately machined clamping and positioning device of aero engine turbine blades tenon, it is characterized in that describedly being arranged on position housing piece that lower cover and blade edge profile match and being the position housing piece of location blade air inlet leading edge.
9. according to claim 1 to one of 5 described for the accurately machined clamping and positioning device of aero engine turbine blades tenon, it is characterized in that being arranged on the pressed component that is used for compressing the blade edge on the upper cover plate is housing screw.
10. according to claim 1 to one of 5 described for the accurately machined clamping and positioning device of aero engine turbine blades tenon, it is characterized in that being arranged on the member that is used for the blade axial location on right cover plate or the left cover is alignment pin, realizes the blade axial location by the listrium face that the alignment pin termination is supported between blade blade and the tenon.
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| Application Number | Priority Date | Filing Date | Title |
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| CN201210474401.1A CN102962694B (en) | 2012-11-21 | 2012-11-21 | For the accurately machined clamping and positioning device of aero engine turbine blades |
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| CN201210474401.1A CN102962694B (en) | 2012-11-21 | 2012-11-21 | For the accurately machined clamping and positioning device of aero engine turbine blades |
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| CN102962694A true CN102962694A (en) | 2013-03-13 |
| CN102962694B CN102962694B (en) | 2015-09-30 |
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| CN103433511A (en) * | 2013-08-02 | 2013-12-11 | 常州市三维技术成套设备有限公司 | Group machining tooling and process for steam turbine blade multi-pass arc surface |
| CN103753443A (en) * | 2013-12-16 | 2014-04-30 | 中国民航大学 | Clamp of turbine blade |
| CN103846706A (en) * | 2014-03-20 | 2014-06-11 | 西北工业大学 | Special tension clamp for milling of blade type parts |
| CN105397465A (en) * | 2015-12-08 | 2016-03-16 | 四川成发航空科技股份有限公司 | Assembly device for engine turbine |
| CN106181468A (en) * | 2016-07-27 | 2016-12-07 | 西北工业大学 | A kind of finish forge blade tenon root and front and rear edge clamp for machining |
| CN106270859A (en) * | 2016-08-29 | 2017-01-04 | 中航动力股份有限公司 | A kind of guide vane listrium dustpan hole machined is quickly remodeled clamping device and method |
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| CN106670651A (en) * | 2016-12-20 | 2017-05-17 | 江苏大学 | Combined fixture used for laser shock strengthening of turbine blade |
| CN109249237A (en) * | 2018-11-06 | 2019-01-22 | 中国航发贵州黎阳航空动力有限公司 | A kind of blades efficient clamp for machining |
| CN109333099A (en) * | 2018-10-11 | 2019-02-15 | 西北工业大学 | Blade of aviation engine processes multiple spot slewing supporting device |
| CN110076595A (en) * | 2019-05-13 | 2019-08-02 | 无锡航亚科技股份有限公司 | The device without package processing aviation precision forged blade blade root can be achieved |
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| CN112276618A (en) * | 2020-10-20 | 2021-01-29 | 成都和鸿科技有限公司 | Method for machining tenon of blade of gas compressor |
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| CN113478262A (en) * | 2021-07-20 | 2021-10-08 | 中国航发航空科技股份有限公司 | Turbine blade sealing tooth machining clamp and clamping method thereof |
| CN113664578A (en) * | 2021-08-27 | 2021-11-19 | 中国航发沈阳黎明航空发动机有限责任公司 | Automatic machining tool and process method for low-pressure turbine working blade |
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| CN103433511B (en) * | 2013-08-02 | 2016-02-24 | 常州市三维技术成套设备有限公司 | The processed in batches frock of turbine blade multiple tracks arc surface and technique |
| CN103433511A (en) * | 2013-08-02 | 2013-12-11 | 常州市三维技术成套设备有限公司 | Group machining tooling and process for steam turbine blade multi-pass arc surface |
| CN103753443A (en) * | 2013-12-16 | 2014-04-30 | 中国民航大学 | Clamp of turbine blade |
| CN103846706A (en) * | 2014-03-20 | 2014-06-11 | 西北工业大学 | Special tension clamp for milling of blade type parts |
| CN103846706B (en) * | 2014-03-20 | 2016-04-20 | 西北工业大学 | The special stretching device of a kind of blade parts milling |
| CN105397465B (en) * | 2015-12-08 | 2017-05-31 | 四川成发航空科技股份有限公司 | For the device of engine turbine assembling |
| CN105397465A (en) * | 2015-12-08 | 2016-03-16 | 四川成发航空科技股份有限公司 | Assembly device for engine turbine |
| CN106181468A (en) * | 2016-07-27 | 2016-12-07 | 西北工业大学 | A kind of finish forge blade tenon root and front and rear edge clamp for machining |
| CN106181468B (en) * | 2016-07-27 | 2019-01-04 | 西北工业大学 | A kind of precision forged blade tenon root and front and rear edge clamp for machining |
| CN106270859A (en) * | 2016-08-29 | 2017-01-04 | 中航动力股份有限公司 | A kind of guide vane listrium dustpan hole machined is quickly remodeled clamping device and method |
| CN106441856B (en) * | 2016-11-23 | 2018-12-14 | 沈阳黎明航空发动机(集团)有限责任公司 | A kind of big leaf quality square measuring device of complicated surface |
| CN106441856A (en) * | 2016-11-23 | 2017-02-22 | 沈阳黎明航空发动机(集团)有限责任公司 | Device for measuring mass moment of complex surface large blade |
| CN106670651A (en) * | 2016-12-20 | 2017-05-17 | 江苏大学 | Combined fixture used for laser shock strengthening of turbine blade |
| CN106670651B (en) * | 2016-12-20 | 2018-06-01 | 江苏大学 | A kind of built-up jig for laser impact intensified turbine blade |
| CN109333099A (en) * | 2018-10-11 | 2019-02-15 | 西北工业大学 | Blade of aviation engine processes multiple spot slewing supporting device |
| CN109249237B (en) * | 2018-11-06 | 2020-10-16 | 中国航发贵州黎阳航空动力有限公司 | Efficient blade machining clamp |
| CN109249237A (en) * | 2018-11-06 | 2019-01-22 | 中国航发贵州黎阳航空动力有限公司 | A kind of blades efficient clamp for machining |
| CN110076595A (en) * | 2019-05-13 | 2019-08-02 | 无锡航亚科技股份有限公司 | The device without package processing aviation precision forged blade blade root can be achieved |
| CN110500931A (en) * | 2019-08-12 | 2019-11-26 | 无锡航亚科技股份有限公司 | A kind of the measurement fixture and measurement method of vane foil size and blade tip size |
| CN110500931B (en) * | 2019-08-12 | 2021-07-16 | 无锡航亚科技股份有限公司 | Clamp and method for measuring blade profile size and blade tip size of blade |
| CN112276618A (en) * | 2020-10-20 | 2021-01-29 | 成都和鸿科技有限公司 | Method for machining tenon of blade of gas compressor |
| CN112571217A (en) * | 2020-12-04 | 2021-03-30 | 江苏源清动力技术有限公司 | Turbine blade grinding clamping frock |
| CN113478262A (en) * | 2021-07-20 | 2021-10-08 | 中国航发航空科技股份有限公司 | Turbine blade sealing tooth machining clamp and clamping method thereof |
| CN113664578A (en) * | 2021-08-27 | 2021-11-19 | 中国航发沈阳黎明航空发动机有限责任公司 | Automatic machining tool and process method for low-pressure turbine working blade |
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Address after: Xindu District of Chengdu city in Sichuan province 610503 Shulong avenue into the industrial park into the Group Technology Center Patentee after: China Hangfa aviation Polytron Technologies Inc Address before: Xindu District of Chengdu city in Sichuan province 610503 Shulong avenue into the industrial park into the Group Technology Center Patentee before: Sichuan Chengfa Aviation Science & Technology Co., Ltd. |