CN102962694B - For the accurately machined clamping and positioning device of aero engine turbine blades - Google Patents
For the accurately machined clamping and positioning device of aero engine turbine blades Download PDFInfo
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- CN102962694B CN102962694B CN201210474401.1A CN201210474401A CN102962694B CN 102962694 B CN102962694 B CN 102962694B CN 201210474401 A CN201210474401 A CN 201210474401A CN 102962694 B CN102962694 B CN 102962694B
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Abstract
The invention discloses a kind of for the accurately machined clamping and positioning device of aero engine turbine blades tenon, comprise by front shroud, back shroud, left cover, right cover plate, the framework that upper cover plate and lower cover are consisted of 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 matched with blade pelvic surface of sacrum profile, and the position housing piece to match with blade air inlet or exhaust edge profile and the pressed component for compressing another edge of blade, one of described back side position housing piece and pelvic surface of sacrum position housing piece are arranged on front shroud or back shroud in compaction direction adjustably, right cover plate or left cover are designed with blade and insert opening, this cover plate is designed with sharf to align member.The present invention adopts the fixed form of cast low-melting alloy locating blades compared to prior art, greatly reduces blade processing cost, avoids the problems removed the low-melting alloy on blade and bring.
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 aero-engine adopts smart type casting moulding, and wherein blade is one-shot forming, does not have allowance for finish, does not need to carry out machined, but the integral shroud of blade and tenon also need to carry out further fine finishining by machined, to meet the matching requirements of blade.Due to the free form surface that blade surface is formed for space coordinates point, conventional fixture scheme is difficult to realize its location clamping.The fine finishining location of traditional engine turbine blade adopts in square chest, to pour into a mould low-melting alloy be fixed blade blade, although this mode can realize the location to blade, positioning precision and clamping force aspect have problems and hidden danger.This is because low-melting alloy has good ductility, bad to the positioning precision retentivity of blade, the clamping force provided is less, affects easy distortion, and then affect machining accuracy in finishing passes by cutting force.In addition, because low-melting alloy directly contacts with blade surface, melt after fine finishining completes and move back square chest, inevitably at blade remained on surface low-melting alloy, some model engine turbine blade is hollow blade besides, melting pour into a mould low-melting alloy fixed blade and blade fine finishining in square chest after moves back in the process of square chest, when misoperation molten state alloy can pour into blade cavity inside, for remain in blade surface and pour into cavity inside low-melting alloy remove process be very difficult, and the alloy pouring into cavity inside is had no idea to get rid of completely at all, the alloy that left behind is in turbine running, blade crystalline phase organization internal can be penetrated under the hot environment of turbine, with blade material component generation chemical reaction, blade material performance is caused to change, directly have influence on blade working performance and life-span.
In order to eliminate residual low-melting alloy over the paddle and enter the impact of the low-melting alloy in blade cavity on blade; tradition removes the method for low-melting alloy; high temperature bath is first adopted to dissolve for the low-melting alloy remaining in blade surface; but this measure can not ensure to get rid of the low-melting alloy remaining in blade surface completely, after high temperature bath, usually also need the alloy of polishing blade remained on surface.Polishing is removed blade remained on surface low-melting alloy and is needed to be very careful, and does not slightly note having influence on blade surface profile degree, and then affects blade fluid mechanical property, and extremely waste time and energy.For the low-melting alloy pouring into blade cavity inside, the method adopting high temperature bath to add acid cleaning process is only had to remove at present.Remaining alloy for high temperature bath removal cavity inside is also to ensure thorough removal, for acid cleaning process, although acid cleaning process carries out for the residual alloy of removal, can not ensure not produce corrosion impact to the composition matrix of blade material.
In square chest, pour into a mould low-melting alloy in view of prior art adopts to be fixed Problems existing to blade too many, production practices are badly in need of finding a kind of locate mode of not passing through to pour into a mould low-melting alloy fixed blade in square chest, the problems brought with the alloy avoided in removal blade remained on surface alloy and blade cavity.This mode preferably abandons cast low-melting alloy technique completely, comes one and takes away the firewood under the cauldron, puts things right once and for all.
Summary of the invention
In square chest, pour into a mould low-melting alloy for prior art employing and Problems existing is fixed to blade, object of the present invention aims to provide a kind of fine finishining realizing completing the device of blade location clamping blade tenon with mechanical clamping type, to realize fundamentally solving the various problem of the alloy existence of removing in blade remained on surface alloy and blade cavity with worried.
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, right cover plate, the framework that upper cover plate and lower cover are consisted of 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 matched with blade pelvic surface of sacrum profile, the position housing piece matched with blade air inlet or exhaust edge profile and the pressed component for compressing another edge of blade, described back side position housing piece and pelvic surface of sacrum position housing piece are separately positioned on relative two cover plates of formation framework, and both one of are at least arranged on the cover board adjustably in compaction direction, another the two relative cover plates forming framework are separately positioned on the position housing piece that blade air inlet or exhaust edge profile match and the pressed component for compressing another edge of blade, right cover plate or left cover are designed with the align member making blade insert opening in framework and axial location blade.
In order to solve technical problem to be solved in the utility model better, the utility model also can take following technical measures further.Following every technical measures can be taked separately, also may be combined with and take, take even in the lump.
In technique scheme, described back side position housing piece and pelvic surface of sacrum position housing piece are preferentially separately positioned on relative front and back two cover plate, are separately positioned on relative two cover plates up and down with the position housing piece that blade air inlet or exhaust edge profile match and the pressed component for compressing another edge of blade.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 back shroud, another is arranged on back shroud or front shroud adjustably in compaction direction.Further preferred mode again, pelvic surface of sacrum position housing piece is fixedly installed on back shroud, and back side position housing piece is arranged on front shroud adjustably in compaction direction.Back side position housing piece adjusts in compaction direction by the adjustment screw be arranged on front shroud.
In technique scheme, the side that described back side position housing piece and blade back side profile match preferably is designed with for reducing the groove with 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 reducing the groove with blade phase-contact surface, to improve chucking power, and clamping position blade better.
In technique scheme, described in be arranged on position housing piece that lower cover and blade edge profile match and pay the utmost attention to locating piece into locating blade air inlet leading edge.
In technique scheme, described in be arranged on upper cover plate for compressing the pressed component at blade edge be housing screw, the blade edge compressed is exhaust back edge.
In technique scheme, described in be arranged on right cover plate or left cover and preferentially select alignment pin for the component of blade axial location, the listrium face supported between blade blade and tenon by alignment pin termination realizes blade axial location.
Provided by the invention for the accurately machined clamping and positioning device of aero engine turbine blades tenon, be based on inventor, the profound understanding of benchmark relation between the blade of engine turbine blade and tenon has been designed.Engine turbine blade adopts smart type casting moulding, wherein blade is one-shot forming, 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 the conversion relation determined, therefore the location clamping of blade essence casting surface only need be utilized to be processed by tenon three design basises, and integral shroud fine finishining benchmark afterwards just can be transformed into tenon benchmark, the namely design basis of blade.Provided by the invention for the accurately machined clamping and positioning device of aero engine turbine blades tenon, clamping position mentality of designing utilizes blade leaf basin profile to locate dorsad basin, utilize blade leading edge to entering outgassing direction location, listrium upper surface is utilized to locate length of blade direction, blade back side locating piece provides main clamping force, and blade trailing edge is by screw in compression stop.
Employing the invention provides clamping and positioning device and carries out fine finishining to aero engine turbine blades tenon, because clamping device is combining structure, mechanical force is adopted to step up location, therefore resetting, Reusability can be realized in blade tenon finishing passes, a square chest is equipped with without the need to every part blade, adopt square chest cast low-melting alloy blade locate mode compared to prior art, every part blade all needs to join a square chest, greatly reduces manufacture, use, maintenance, cost of upkeep.Also fundamentally avoid that square chest cast low-melting alloy locating blades brings simultaneously, after blade finishing step completes, remove the molten square chest that moves back and remain in blade surface low-melting alloy, and move back in square chest process due to careless manipulation cause molten condition low-melting alloy to pour into worry that blade cavity brings and problem molten.Also can take owing to adopting cast-type simultaneously, most of finishing size of square chest is all by above design drawing size conversion to square chest, Reference misalignment is produced when conversion designs figure size, cause deviation accumulation, be unfavorable for reasonable strict control design case figure size, the low-melting alloy of adding cast is in use easily out of shape loosening, directly reduces the problems such as blade processing precision.Adopt clamping and positioning device of the present invention, in use not easily loosen, be conducive to improving positioning precision, be beneficial to and control blade processing precision.
Accompanying drawing explanation
Accompanying drawing 1 be clamping and positioning device of the present invention face structural representation.
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 clamping and positioning device.
Accompanying drawing 4 is the pelvic surface of sacrum compact heap side structure schematic diagrames in clamping and positioning device.
Accompanying drawing 5 is the back side compact heap Facad structure schematic diagrames in clamping and positioning device.
Accompanying drawing 6 is the back side compact heap side structure schematic diagrames in 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; 3-left cover; 4-joint bolt; 5-right cover plate; 6-sharf is to alignment pin; 7-air inlet leading edge position housing piece; 8-lower cover; 9-back shroud; 10 blade pelvic surface of sacrum position housing pieces; 11-is vented back edge housing screw; 12-upper cover plate; 13-connects alignment pin; 14-housing screw; 15-front shroud; 16-blade back side position housing piece; 17-joint bolt.
Detailed description of the invention
Provide embodiments of the invention below in conjunction with accompanying drawing, and the present invention is conducted further description in conjunction with the embodiments, so that people's the understanding of the present invention.Specific constructive form of the present invention is not limited to the form described by following embodiment; the thought that those skilled in the art can disclose according to the present invention also can design other detailed description of the invention not paying creatively to work, but these detailed description of the invention gone out according to content design of the present invention still belong to protection scope of the present invention.
Embodiment 1
The present embodiment for the accurately machined clamping and positioning device of aero engine turbine blades tenon, its structure is as shown in accompanying drawing 1 to 4, form and 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 connecting alignment pin 13 etc. and form, right cover plate 5 is designed with the alignment pin 6 making blade insert opening in framework and axial location blade, and the listrium face supported between blade blade and tenon by alignment pin termination realizes blade axial location.The back side position housing piece 16 matched with blade back side profile in framework is arranged on front shroud 15 by the adjustment housing screw 14 be arranged on front shroud in compaction direction adjustably, the pelvic surface of sacrum position housing piece 10 matched with blade pelvic surface of sacrum profile to be fixedly installed on back shroud 9, the locating piece 2,7 matched with blade admission edge profile is by regulating housing screw 1 to arrange on lower cover, and the housing screw 11 being vented trailing edge for compressing blade to be arranged on upper cover plate 12.The side that described back side position housing piece 16 and blade back side profile match, and the side that described pelvic surface of sacrum position housing piece 10 matches with blade pelvic surface of sacrum profile, all being designed with for reducing the groove in length and breadth with blade phase-contact surface, realizing clamping position better to improve chucking power.
Because certain model aero engine turbine blades is overall essence casting, the blade of blade is once smart type casting moulding, does not have allowance.The tenon of blade is the reference for assembling of blade, and the precision of blade assernbling is high, relies on the machining accuracy of tenon completely, and the processing of tenon is the emphasis of blade, and molding surface size tolerance is very strict.Turbo blade tenon tooth is vertical tree type tenon tooth, and transverse tooth thickness tolerance is 0/-0.06, and working face profile tolerance tolerance is 0.015.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 and be comparatively difficult to ensure card man-hour.The turbo blade of locating and clamping apparatus of the present invention to this model is now adopted to process, the 300 more than one piece turbo blades machined, tenon size and surface roughness meet designing requirement completely, tenon passing rate of processing reaches more than 99%, thus reduce the percent defective of part, greatly reduce the processing cost of blade.
Claims (8)
1. one kind 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, right cover plate, the framework that upper cover plate and lower cover are consisted of 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 matched with blade pelvic surface of sacrum profile, the position housing piece matched with blade air inlet or exhaust edge profile and the pressed component for compressing another edge of blade, right cover plate or left cover are designed with the align member making blade insert opening in framework and axial location blade, back side position housing piece and pelvic surface of sacrum position housing piece are separately positioned on other two relative cover plates of formation framework, and both one of are at least arranged on the cover board adjustably in compaction direction, other another relative two cover plates forming framework are separately positioned on the position housing piece that blade air inlet or exhaust edge profile match and the pressed component for compressing another edge of blade, the side that described back side position housing piece and blade back side profile match is designed with for reducing the groove with blade phase-contact surface, the side that described pelvic surface of sacrum position housing piece and blade pelvic surface of sacrum profile match is designed with for reducing the groove with blade phase-contact surface.
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 relative front and back two cover plate, being separately positioned on relative two cover plates up and down with the position housing piece that blade air inlet or exhaust edge profile match and the pressed component for compressing another edge of blade.
3. according to claim 2 for the accurately machined clamping and positioning device of aero engine turbine blades tenon, one of to it is characterized in that in described back side position housing piece and pelvic surface of sacrum position housing piece being fixedly installed on front shroud or back shroud, another is arranged on back shroud or 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 back shroud, back side position housing piece is arranged on 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 adjusted in compaction direction by the compression adjustment screw be arranged on front shroud.
6. according to one of claim 1 to 5 Suo Shu for the accurately machined clamping and positioning device of aero engine turbine blades tenon, it is characterized in that the described position housing piece matched with blade edge profile is arranged on lower cover, this position housing piece is the position housing piece of location blade air inlet leading edge.
7. according to one of claim 1 to 5 Suo Shu for the accurately machined clamping and positioning device of aero engine turbine blades tenon, it is characterized in that described being arranged on upper cover plate for the pressed component compressing blade edge, this pressed component is housing screw.
8. according to one of claim 1 to 5 Suo Shu for the accurately machined clamping and positioning device of aero engine turbine blades tenon, it is characterized in that being arranged on right cover plate or left cover for the component of blade axial location is alignment pin, and the listrium face supported between blade blade and tenon by alignment pin termination realizes blade axial location.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| 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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| 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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| CN102962694A CN102962694A (en) | 2013-03-13 |
| CN102962694B true CN102962694B (en) | 2015-09-30 |
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| CN102962694A (en) | 2013-03-13 |
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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. |