CN102975061B - Precision machining technological equipment and machining method for blade of aviation engine - Google Patents
Precision machining technological equipment and machining method for blade of aviation engine Download PDFInfo
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- CN102975061B CN102975061B CN201210377805.9A CN201210377805A CN102975061B CN 102975061 B CN102975061 B CN 102975061B CN 201210377805 A CN201210377805 A CN 201210377805A CN 102975061 B CN102975061 B CN 102975061B
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Abstract
The invention discloses precision machining technological equipment for a blade of an aviation engine. The precision machining technological equipment comprises a positioning device, a clamping device and an auxiliary supporting device, wherein the positioning device, the clamping device and the auxiliary supporting device are fixed on a foundation table top, the positioning device is used for positioning of a curved surface of a blade body, the clamping device is used for clamping the blade body, the auxiliary supporting device is fixed outside the positioning device and the clamping device, a working head of the auxiliary supporting device directly contacts a tenon portion of the blade, and a master controller controls each hydraulic cylinder on a tool through a control loop. According to the precision machining technological equipment, the blade body provided with a thin wall and the curved surface is directly positioned and clamped for machining the tenon, and therefore continuous mechanical operation and machining can be achieved in production of the blade, and working efficiency and machining quality can be improved.
Description
Technical field
The present invention relates to the processing technique field of blade of aviation engine, be specifically related to a kind of precise machining process equipment and processing method of blade of aviation engine.
Background technology
Compressor precision forging blade is the key components and parts in aviation turbojet engine, the main machining method of Present Domestic on this type of blade is the processing mode based on the cast of blade low-melting alloy, namely to complete blade without surplus finish forge and intake and exhaust limit processing blade woollen, after six point location clampings, cast is carried out to blade and become castable, the blade point location of complexity is converted to the location, face of rule, and then carry out the processing of blade tenon.But this technique also exists obviously defect: technique chain length, Operational preparation are complicated, inefficiency, the cast of low-melting alloy and thawing bring the residual of blade surface and cleaning problem, pour into a mould and to dissolve operating mode severe etc.
Summary of the invention
For solving the above-mentioned problems in the prior art, the object of the invention is to the precise machining process equipment and the processing method that propose a kind of blade of aviation engine, directly clamping is positioned to the thin-wall curved-surface blade of blade, and then carry out tenon processing, continuous print mechanically actuated and processing can be realized in blade is produced, increase work efficiency and crudy.
For achieving the above object, the technical solution adopted in the present invention is:
A kind of precise machining process equipment of blade of aviation engine, comprise the positioner 2, clamping device 3 and the auxiliary support apparatus 4 that are fixed on basic table top 1, described positioner 2 is located for the blade curved surface of blade, described clamping device 3 is for realizing the clamping to blade, described auxiliary support apparatus 4 is fixed on the outside of positioner 2 and clamping device 3, and the working head of auxiliary support apparatus 4 directly and the tenon location contacts of blade 7; Master controller 5 is controlled by the hydraulic jack on control loop 6 pairs of clamping devices 3 and auxiliary support apparatus 4.
Described positioner 2 comprises the location matrix 8 be fixed on basic table top 1, be arranged on main locating piece 10 on the matrix 8 of location and side locating piece 9, described main locating piece 10 is distributed with three alignment pins 11, three alignment pins 11 contact with the thin-wall curved-surface blade of blade 7 as main keeper, positioning pin column 13 being housed for contacting with the listrium of blade 7 on main locating piece 10 top, described side locating piece 9 being provided with two keepers 12 and contacting with the admission edge of blade 7.
Described clamping device 3 is made up of primary nip mechanism and side direction clamp system, described primary nip mechanism comprises the tight matrix of main folder 14 be fixed on basic table top 1 and the main clamp 16 be connected with the tight matrix of main folder 14, main clamp 16 is equipped with the blade of three clamping heads 17 for clamping blade 7; Described side direction clamp system clamps matrix 15 by side direction and the side direction clamping head 18 on it forms, side direction clamping head 18 is for the exhaust edge from side direction clamping blade 7, be equipped with hydraulic jack in the tight matrix 14 of main folder of primary nip mechanism and in the side direction clamping matrix 15 of side direction clamp system, be respectively used to drive respective clamp 16 and side direction clamping head 18 to move.
Described auxiliary support apparatus 4 comprises four auxiliary support mechanisms be independently oppositely arranged, and auxiliary support mechanism comprises the matrix 19 be fixed on basic table top 1, be fixed on the working head 21 on matrix 19 and push the work forward and 21 to contact and the support hydraulic pressure oil cylinder 20 of locking with the tenon of blade 7.
Described master controller 5 comprises PLC programmable control system and hydraulic control valve, and PLC programmable control system operates each hydraulic jack by hydraulic control valve and control loop 6.
Equip the method that blade of aviation engine is processed based on described precise machining process, comprise the steps:
Step 1: the numerical control program weaving the numerical control program of tenon processing, precise machining process equipment;
Step 2: put into blade 7 in precise machining process equipment after, blade 7 is pushed three alignment pins 11 of positioner 2 to realize location, by primary nip mechanism and the locking of side direction clamp system after clamping by primary nip mechanism and side direction clamp system by hydraulic jack;
Step 3: by the support hydraulic pressure oil cylinder 20 of four auxiliary support mechanisms working head 21 stretched out and touch blade 7 tenon, then lock;
Step 4: in process, according to the numerical control program of precise machining process equipment, when tool sharpening blade 7 tenon a direction surperficial, retreats to safe distance by the working head 21 of the auxiliary support mechanism at this place; Leave behind this surface until cutter, stretch out working head 21 and again contact with machined surface, until complete the processing of tenon.
The invention has the beneficial effects as follows: have employed the technology such as the clamping of direct location, the multi-direction supplemental support for tenon, the Digital Control for hydraulic system for thin-wall curved-surface blade, propose the digital control processing new technology without surplus precision forging blade; Directly can carry out numerical control clamping and processing to blade by this technological equipment, avoid cast and the melting process of low-melting alloy in traditional handicraft, improve working (machining) efficiency and the quality of part; The present invention has the features such as automatization level is high, processing quality good, process is novel, is applicable to the accurate digital control processing of blade of aviation engine, can provide key technology basis for extensive automation blade production line.
Accompanying drawing explanation
Fig. 1 is the overall structure schematic diagram of present invention process equipment.
Fig. 2 is the structural representation of positioner in present invention process equipment.
Fig. 3 is the structural representation of clamping device in present invention process equipment.
Fig. 4 is the schematic diagram of auxiliary support mechanism in present invention process equipment.
Detailed description of the invention
Below in conjunction with the drawings and specific embodiments, the present invention is described in further detail.
As shown in Figure 1, the precise machining process equipment of a kind of blade of aviation engine of the present invention, comprise the positioner 2, clamping device 3 and the auxiliary support apparatus 4 that are fixed on basic table top 1, described positioner 2 is located for the blade curved surface of blade, described clamping device 3 is for realizing the clamping to blade, described auxiliary support apparatus 4 is fixed on the outside of positioner 2 and clamping device 3, and the working head of auxiliary support apparatus 4 directly and the tenon location contacts of blade 7; Master controller 5 is controlled by the hydraulic jack on control loop 6 pairs of clamping devices 3 and auxiliary support apparatus 4.
As shown in Figure 2, positioner 2 comprises the location matrix 8 be fixed on basic table top 1, be arranged on main locating piece 10 on the matrix 8 of location and side locating piece 9, described main locating piece 10 is distributed with three alignment pins 11, three alignment pins 11 contact with the thin-wall curved-surface blade of blade 7 as main keeper, positioning pin column 13 is housed for contacting with the listrium of blade 7 on main locating piece 10 top, described side locating piece 9 is provided with two keepers 12 contact with the admission edge of blade 7, thus realizes six point locations to blade.
As shown in Figure 3, clamping device 3 is made up of primary nip mechanism and side direction clamp system, described primary nip mechanism comprises the tight matrix of main folder 14 be fixed on basic table top 1 and the main clamp 16 be connected with the tight matrix of main folder 14, the blade of three clamping heads 17 for clamping blade 7 main clamp 16 be equipped with, the connection of clamping device have employed matched in clearance, its principle is automatically to adjust based on fit clearance in stressed, thus guarantees that three clamping points can both touch curved surface blade; Described side direction clamp system clamps matrix 15 by side direction and the side direction clamping head 18 on it forms, side direction clamping head 18 is for the exhaust edge from side direction clamping blade 7, be equipped with hydraulic jack in the tight matrix 14 of main folder of primary nip mechanism and in the side direction clamping matrix 15 of side direction clamp system, be respectively used to drive respective clamp 16 and side direction clamping head 18 to move.
As shown in Figure 4, auxiliary support apparatus 4 comprises four auxiliary support mechanisms be independently oppositely arranged, each auxiliary support mechanism is independently arranged on basic table top 1 with bolt connecting mode, and auxiliary support mechanism comprises the matrix 19 be fixed on basic table top 1, be fixed on the working head 21 on matrix 19 and push the work forward and 21 to contact and the support hydraulic pressure oil cylinder 20 of locking with the tenon of blade 7.This mode does not destroy again the location of blade when guaranteeing contact, significantly can improve the problem that rigidity that blade causes due to thin-wall curved-surface structure feature is lower, blade does not need yet apply excessive clamping force, therefore effectively can reduce mismachining tolerance in process, improve crudy.
Above-mentioned master controller 5 is made up of PLC programmable control system, hydraulic control valve etc., and PLC operates each hydraulic jack by hydraulic control valve and control loop.The frock control routine woven according to part program can be loaded in PLC, automatically each supporting mechanism of auxiliary support apparatus is adjusted according to advancing of machine tool in process, thus guarantee that in process, cutter can not interfere with supporting mechanism, guarantee cutter track is unobstructed, guarantees the smooth execution of tenon processing technology.
In the present invention, equip the method that blade of aviation engine is processed based on precise machining process, comprise the steps:
Step 1: the numerical control program weaving the numerical control program of tenon processing, precise machining process equipment;
Step 2: put into blade 7 in precise machining process equipment after, blade 7 is pushed three alignment pins 11 of positioner 2 to realize location, by primary nip mechanism and the locking of side direction clamp system after clamping by primary nip mechanism and side direction clamp system by hydraulic jack;
Step 3: by the support hydraulic pressure oil cylinder 20 of four auxiliary support mechanisms working head 21 stretched out and touch blade 7 tenon, then lock;
Step 4: in process, according to the numerical control program of precise machining process equipment, when tool sharpening blade 7 tenon a direction surperficial, retreats to safe distance by the working head 21 of the auxiliary support mechanism at this place; Leave behind this surface until cutter, stretch out working head 21 and again contact with machined surface, until complete the processing of tenon.
Pour into a mould blade tenon process technology with the low-melting alloy generally adopted now to contrast, the present invention has the following advantages:
1, directly position for the thin-wall curved-surface blade of blade and clamp, eliminate the cast of low-melting alloy and melt removing step, significantly shortening the technology chain of blade processing, achieve technology innovation.
2, adjustable auxiliary support apparatus is devised, support cylinder is adopted to keep the contact of working head and blade tenon, this mode does not affect again the curved surface location of blade when guaranteeing contact, significantly can improve the Low rigidity problem that blade causes due to the design feature of thin-wall curved-surface, and the clamping force that can reduce on blade, therefore effectively can reduce mismachining tolerance in process, improve crudy.
3, the master control system based on PLC Programmable is devised, be loaded into the frock control routine according to part program establishment, can according to each supporting mechanism of automatic telescopic of advancing of machine tool in process, thus guarantee that in process, cutter can not interfere with support member, guarantee cutter track is unobstructed, guarantees the execution of tenon processing technology.The present invention significantly can improve the technical merit of blade processing, and producing for automation blade provides key technology basis.
Claims (3)
1. the precise machining process equipment of a blade of aviation engine, it is characterized in that: comprise the positioner (2) be fixed on basic table top (1), clamping device (3) and auxiliary support apparatus (4), described positioner (2) is located for the blade curved surface of blade, described clamping device (3) is for realizing the clamping to blade, described auxiliary support apparatus (4) is fixed on the outside of positioner (2) and clamping device (3), and the working head of auxiliary support apparatus (4) directly and the tenon location contacts of blade (7), master controller (5) is controlled the hydraulic jack on clamping device (3) and auxiliary support apparatus (4) by control loop (6), described positioner (2) comprises the location matrix (8) be fixed on basic table top (1), be arranged on the main locating piece (10) on location matrix (8) and side locating piece (9), described main locating piece (10) face is distributed with three alignment pins (11), three alignment pins (11) contact as the thin-wall curved-surface blade of main keeper with blade (7), positioning pin column (13) is housed for contacting with the listrium of blade (7) on main locating piece (10) top, described side locating piece (9) is provided with two keepers (12) contact with the admission edge of blade (7), described clamping device (3) is made up of primary nip mechanism and side direction clamp system, described primary nip mechanism comprises the tight matrix of main folder (14) be fixed on basic table top (1) and the main clamp (16) be connected with the tight matrix of main folder (14), main clamp (16) is equipped with the blade of three clamping heads (17) for clamping blade (7), described side direction clamp system clamps matrix (15) by side direction and the side direction clamping head (18) on it forms, side direction clamping head (18) is for the exhaust edge from side direction clamping blade (7), be equipped with hydraulic jack in the tight matrix of main folder (14) of primary nip mechanism and in side direction clamping matrix (15) of side direction clamp system, be respectively used to drive respective clamp (16) and side direction clamping head (18) motion, described auxiliary support apparatus (4) comprises four auxiliary support mechanisms be independently oppositely arranged, and auxiliary support mechanism comprises the matrix (19) be fixed on basic table top (1), be fixed on working head (21) on matrix (19) and the head that pushes the work forward (21) contacts with the tenon of blade (7) and the support hydraulic pressure oil cylinder (20) of locking.
2. the precise machining process equipment of blade of aviation engine according to claim 1, it is characterized in that: described master controller (5) comprises PLC programmable control system and hydraulic control valve, PLC programmable control system operates each hydraulic jack by hydraulic control valve and control loop (6).
3. the processing method of precise machining process equipment to blade of the blade of aviation engine described in claim 1 or 2, comprises the steps:
Step 1: the numerical control program weaving the numerical control program of tenon processing, precise machining process equipment;
Step 2: put into blade (7) in precise machining process equipment after, blade (7) is pushed three alignment pins (11) of positioner (2) to realize location, by primary nip mechanism and the locking of side direction clamp system after clamping by primary nip mechanism and side direction clamp system by hydraulic jack;
Step 3: by the support hydraulic pressure oil cylinder (20) of four auxiliary support mechanisms working head (21) stretched out and touch blade (7) tenon, then lock;
Step 4: in process, according to the numerical control program of precise machining process equipment, when tool sharpening blade (7) tenon a direction surperficial, retreats to safe distance by the working head (21) of the auxiliary support mechanism at this place; Leave behind this surface until cutter, stretch out working head (21) and again contact with machined surface, until complete the processing of tenon.
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| CN201210377805.9A CN102975061B (en) | 2012-10-08 | 2012-10-08 | Precision machining technological equipment and machining method for blade of aviation engine |
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| CN201210377805.9A CN102975061B (en) | 2012-10-08 | 2012-10-08 | Precision machining technological equipment and machining method for blade of aviation engine |
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| CN102975061B true CN102975061B (en) | 2015-06-17 |
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Families Citing this family (6)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN105312483B (en) * | 2015-12-03 | 2017-04-19 | 中国南方航空工业(集团)有限公司 | Method for forging beryllium bronze blade of engine |
| CN107553224A (en) * | 2017-09-28 | 2018-01-09 | 中国航发动力股份有限公司 | A kind of low-pressure turbine guide vane multistation processing technology |
| CN107627041B (en) * | 2017-11-08 | 2023-11-03 | 深圳市杰普特光电股份有限公司 | Strip resistor clamping device |
| CN111570873B (en) * | 2020-05-27 | 2021-03-23 | 菏泽学院 | Blade ultrasonic metal surface machining device |
| CN113319341B (en) * | 2021-06-08 | 2022-05-03 | 清华大学 | Blade machining system and method on blisk |
| CN114985814B (en) * | 2022-06-29 | 2023-12-29 | 中国航发动力股份有限公司 | Machining tool and system for blade body and use method |
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB2458738A (en) * | 2008-04-04 | 2009-10-07 | Heller Machine Tools Ltd | Holding device for non planar work piece |
| CN202985187U (en) * | 2012-10-08 | 2013-06-12 | 清华大学 | Precise machining process equipment of vane of aviation engine |
Family Cites Families (2)
| Publication number | Priority date | Publication date | Assignee | Title |
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| US6844515B2 (en) * | 2001-10-10 | 2005-01-18 | Brett Wayne Byrnes | Method and apparatus for turbine blade machining |
| US7219408B2 (en) * | 2002-09-24 | 2007-05-22 | General Electric Company | Tool for securing a component |
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Patent Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB2458738A (en) * | 2008-04-04 | 2009-10-07 | Heller Machine Tools Ltd | Holding device for non planar work piece |
| CN202985187U (en) * | 2012-10-08 | 2013-06-12 | 清华大学 | Precise machining process equipment of vane of aviation engine |
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Effective date of registration: 20210517 Address after: 100084 Tsinghua Yuan, Beijing, Haidian District Patentee after: TSINGHUA University Patentee after: AECC AVIATION POWER Co.,Ltd. Address before: 100084, Haidian District, 100084 mailbox, 82 boxes, Tsinghua University patent office, Beijing Patentee before: TSINGHUA University |
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