CN102975061A - 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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- CN102975061A CN102975061A CN2012103778059A CN201210377805A CN102975061A CN 102975061 A CN102975061 A CN 102975061A CN 2012103778059 A CN2012103778059 A CN 2012103778059A CN 201210377805 A CN201210377805 A CN 201210377805A CN 102975061 A CN102975061 A CN 102975061A
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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 the aviation turbojet engine, the main machining method of Present Domestic on this type of blade is based on the processing mode of blade low-melting alloy cast, namely woollen without the blade of surplus finish forge and the processing of intake and exhaust limit to finishing blade, after the six point location clampings blade poured into a mould and become castable, complicated blade point location is converted to the face location of rule, and then carry out the processing of blade tenon.But this technique exists very significantly defective: the technique chain length, produce and prepare complicated, inefficiency, the cast of low-melting alloy and thawing have brought the residual of blade surface and cleaning problem, pour into a mould and to dissolve operating mode abominable etc.
Summary of the invention
For solving the above-mentioned problems in the prior art, the object of the invention is to propose a kind of precise machining process equipment and processing method of blade of aviation engine, directly the thin-wall curved-surface blade of blade positioned clamping, and then carry out tenon and process, can in blade is produced, realize continuous mechanically actuated and processing, 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 the basic table top 1, described positioner 2 is used for the blade curved surface location of blade, described clamping device 3 is used for realization to the clamping of 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 contacts with the tenon position of blade 7; Master controller 5 is controlled by the hydraulic jack on 6 pairs of clamping devices 3 of control loop and the auxiliary support apparatus 4.
Described positioner 2 comprises the location matrix 8 that is fixed on the basic table top 1, is installed in main locating piece 10 and side locating piece 9 on the matrix 8 of location, be distributed with three alignment pins 11 10 of described main locating pieces, three alignment pins 11 contact with the thin-wall curved-surface blade of blade 7 as main keeper, positioning pin column 13 is housed on main locating piece 10 tops is used for contacting with the listrium of blade 7, be provided with two keepers 12 at described side locating piece 9 and contact with the admission edge of blade 7.
Described clamping device 3 is comprised of the tight mechanism of main folder and side direction clamp mechanism, the tight mechanism of described main folder comprises the tight matrix 14 of the main folder that is fixed on the basic table top 1 and is connected the main clamp 16 that matrix 14 connects with main folder, the blade that three clamping heads 17 are used for clamping blade 7 is housed on the main clamp 16; Described side direction clamp mechanism clamps matrix 15 by side direction and the side direction clamping head 18 on it forms, side direction clamping head 18 is used for clamping from side direction the exhaust edge of blade 7, be equipped with hydraulic jack in the tight matrix 14 of the main folder of the tight mechanism of main folder and in the side direction of the side direction clamp mechanism clamping matrix 15, be respectively applied to drive separately clamp 16 and 18 motions of side direction clamping head.
Described auxiliary support apparatus 4 comprises four auxiliary support mechanisms that independently are oppositely arranged, and auxiliary support mechanism comprises the matrix 19 that is fixed on the basic table top 1, be fixed on the working head 21 on the matrix 19 and push the work forward 21 support hydraulic pressure oil cylinders 20 that contact and lock with the tenon of blade 7.
Described master controller 5 comprises PLC programmable control system and hydraulic control valve, and the PLC programmable control system is by hydraulic control valve and control loop 6 each hydraulic jacks of operation.
Method based on described precise machining process equipment is processed blade of aviation engine comprises the steps:
Step 1: weave the numerical control program of tenon processing, the numerical control program of frock;
Step 2: after in frock, putting into blade 7, by the tight mechanism of main folder and side direction clamp mechanism blade 7 is pushed to three alignment pins 11 of positioner 2 by hydraulic jack to realize the location, after the clamping the tight mechanism of main folder and side direction clamp mechanism are locked;
Step 3: the support hydraulic pressure oil cylinder 20 by four auxiliary support mechanisms stretches out working head 21 and touches blade 7 tenons, then locking;
Step 4: in the process, according to the numerical control program of frock, tool sharpening blade 7 tenon one party to surperficial the time, the working head 21 of the auxiliary support mechanism at this place is retreated to safe distance; After cutter leaves this surface, stretch out working head 21 and again contact with machined surface, until finish the processing of tenon.
The invention has the beneficial effects as follows: adopted direct location for the thin-wall curved-surface blade clamp, for the multi-direction supplemental support of tenon, for the technology such as Digital Control of hydraulic system, the digital control processing new technology without surplus precision forging blade has been proposed; Can directly carry out numerical control clamping and processing to blade by this technological equipment, avoid cast and the melting process of low-melting alloy in the traditional handicraft, improve working (machining) efficiency and the quality of part; The present invention has the characteristics such as automatization level height, processing quality is good, process is novel, is applicable to the accurate digital control processing of blade of aviation engine, can provide the key technology basis for extensive automation blade production line.
Description of drawings
Fig. 1 is the overall structure schematic diagram of technological equipment of the present invention.
Fig. 2 is the structural representation of positioner in the technological equipment of the present invention.
Fig. 3 is the structural representation of clamping device in the technological equipment of the present invention.
Fig. 4 is the schematic diagram of auxiliary support mechanism in the technological equipment of the present invention.
The specific embodiment
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 the basic table top 1, described positioner 2 is used for the blade curved surface location of blade, described clamping device 3 is used for realization to the clamping of 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 contacts with the tenon position of blade 7; Master controller 5 is controlled by the hydraulic jack on 6 pairs of clamping devices 3 of control loop and the auxiliary support apparatus 4.
As shown in Figure 2, positioner 2 comprises the location matrix 8 that is fixed on the basic table top 1, is installed in main locating piece 10 and side locating piece 9 on the matrix 8 of location, be distributed with three alignment pins 11 10 of described main locating pieces, three alignment pins 11 contact with the thin-wall curved-surface blade of blade 7 as main keeper, positioning pin column 13 is housed on main locating piece 10 tops to be used for contacting with the listrium of blade 7, be provided with two keepers 12 at described side locating piece 9 and contact with the admission edge of blade 7, thereby realization is to six point locations of blade.
As shown in Figure 3, clamping device 3 is comprised of the tight mechanism of main folder and side direction clamp mechanism, the tight mechanism of described main folder comprises the tight matrix 14 of the main folder that is fixed on the basic table top 1 and is connected the main clamp 16 that matrix 14 connects with main folder, the blade that three clamping heads 17 are used for clamping blade 7 is housed on the main clamp 16, matched in clearance has been adopted in the connection of clamping device, its principle is can automatically adjust based on fit clearance in stressed, thereby guarantees that three clamping points can both touch the curved surface blade; Described side direction clamp mechanism clamps matrix 15 by side direction and the side direction clamping head 18 on it forms, side direction clamping head 18 is used for clamping from side direction the exhaust edge of blade 7, be equipped with hydraulic jack in the tight matrix 14 of the main folder of the tight mechanism of main folder and in the side direction of the side direction clamp mechanism clamping matrix 15, be respectively applied to drive separately clamp 16 and 18 motions of side direction clamping head.
As shown in Figure 4, auxiliary support apparatus 4 comprises four auxiliary support mechanisms that independently are oppositely arranged, each auxiliary support mechanism independently is installed on the basic table top 1 with bolt connecting mode, and auxiliary support mechanism comprises the matrix 19 that is fixed on the basic table top 1, be fixed on the working head 21 on the matrix 19 and push the work forward 21 support hydraulic pressure oil cylinders 20 that contact and lock with the tenon of blade 7.This mode is not destroyed again the location of blade in the situation of guaranteeing to contact, can significantly improve blade because the lower problem of rigidity that the thin-wall curved-surface structure characteristics cause, on blade, do not need to apply excessive clamping force yet, therefore in process, can effectively reduce mismachining tolerance, improve crudy.
Above-mentioned master controller 5 is comprised of PLC programmable control system, hydraulic control valve etc., and the PLC controller operates each hydraulic jack by hydraulic control valve and control loop.Can be written into the frock control routine that weaves according to part program in the PLC controller, in process, automatically adjust each supporting mechanism of auxiliary support apparatus according to advancing of machine tool, thereby guarantee that cutter can not interfere with supporting mechanism in the process, the assurance cutter track is unobstructed, guarantees the smooth execution of tenon processing technology.
Among the present invention, the method based on the precise machining process equipment is processed blade of aviation engine comprises the steps:
Step 1: weave the numerical control program of tenon processing, the numerical control program of frock;
Step 2: after in frock, putting into blade 7, by the tight mechanism of main folder and side direction clamp mechanism blade 7 is pushed to three alignment pins 11 of positioner 2 by hydraulic jack to realize the location, after the clamping the tight mechanism of main folder and side direction clamp mechanism are locked;
Step 3: the support hydraulic pressure oil cylinder 20 by four auxiliary support mechanisms stretches out working head 21 and touches blade 7 tenons, then locking;
Step 4: in the process, according to the numerical control program of frock, tool sharpening blade 7 tenon one party to surperficial the time, the working head 21 of the auxiliary support mechanism at this place is retreated to safe distance; After cutter leaves this surface, stretch out working head 21 and again contact with machined surface, until finish the processing of tenon.
With the low-melting alloy cast blade tenon process technology contrast of generally adopting now, the present invention has the following advantages:
1, direct thin-wall curved-surface blade for blade positions and clamps, and has cancelled the cast of low-melting alloy and has melted removing step, has significantly shortened the technology chain of blade processing, has realized the technology innovation.
2, designed the capable of regulating auxiliary support apparatus, employing support cylinder maintenance working head contacts with blade tenon, this mode does not affect again the curved surface location of blade in the situation of guaranteeing to contact, can significantly improve blade because the low Rigidity that the design feature of thin-wall curved-surface causes, and can reduce clamping force on the blade, therefore in process, can effectively reduce mismachining tolerance, improve crudy.
3, designed master control system based on the PLC Programmable, be written into the frock control routine according to the part program establishment, can be in process according to each supporting mechanism of automatic telescopic of advancing of machine tool, thereby guarantee that cutter can not interfere with support member in the process, the assurance cutter track is unobstructed, guarantees the execution of tenon processing technology.The present invention can significantly improve the technical merit of blade processing, for the production of automation blade provides the key technology basis.
Claims (6)
1. the precise machining process of a blade of aviation engine is equipped, it is characterized in that: comprise the positioner (2), clamping device (3) and the auxiliary support apparatus (4) that are fixed on the basic table top (1), described positioner (2) is used for the blade curved surface location of blade, described clamping device (3) is used for realization to the clamping of 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 contacts with the tenon position of blade (7); Master controller (5) is controlled the hydraulic jack on clamping device (3) and the auxiliary support apparatus (4) by control loop (6).
2. the precise machining process of blade of aviation engine according to claim 1 is equipped, it is characterized in that: described positioner (2) comprises the location matrix (8) that is fixed on the basic table top (1), be installed in main locating piece (10) and side locating piece (9) on the location matrix (8), be distributed with three alignment pins (11) at described main locating piece (10) face, three alignment pins (11) contact as the thin-wall curved-surface blade of main keeper with blade (7), positioning pin column (13) is housed on main locating piece (10) top is used for contacting with the listrium of blade (7), be provided with two keepers (12) at described side locating piece (9) and contact with the admission edge of blade (7).
3. the precise machining process of blade of aviation engine according to claim 1 is equipped, it is characterized in that: described clamping device (3) is comprised of the tight mechanism of main folder and side direction clamp mechanism, the tight mechanism of described main folder comprises the tight matrix of main folder (14) that is fixed on the basic table top (1) and is connected the main clamp (16) that matrix (14) connects with main folder, the blade that three clamping heads (17) are used for clamping blade (7) is housed on the main clamp (16); Described side direction clamp mechanism clamps matrix (15) by side direction and the side direction clamping head (18) on it forms, side direction clamping head (18) is used for clamping from side direction the exhaust edge of blade (7), be equipped with hydraulic jack in the tight matrix of the main folder of the tight mechanism of main folder (14) and in the side direction of the side direction clamp mechanism clamping matrix (15), be respectively applied to drive separately clamp (16) and side direction clamping head (18) motion.
4. the precise machining process of blade of aviation engine according to claim 1 is equipped, it is characterized in that: described auxiliary support apparatus (4) comprises four auxiliary support mechanisms that independently are oppositely arranged, and auxiliary support mechanism comprises the matrix (19) that is fixed on the basic table top (1), be fixed on the working head (21) on the matrix (19) and support hydraulic pressure oil cylinder (20) that push the work forward head (21) and the tenon of blade (7) contact and lock.
5. the precise machining process of blade of aviation engine according to claim 1 is equipped, it is characterized in that: described master controller (5) comprises PLC programmable control system and hydraulic control valve, and the PLC programmable control system operates each hydraulic jack by hydraulic control valve and control loop (6).
6. the precise machining process of each described blade of aviation engine of claim 1 to 5 equipment comprises the steps: the processing method of blade
Step 1: weave the numerical control program of tenon processing, the numerical control program of frock;
Step 2: after in frock, putting into blade (7), by the tight mechanism of main folder and side direction clamp mechanism blade (7) is pushed to three alignment pins (11) of positioner (2) by hydraulic jack to realize the location, after the clamping the tight mechanism of main folder and side direction clamp mechanism are locked;
Step 3: the support hydraulic pressure oil cylinder (20) by four auxiliary support mechanisms stretches out working head (21) and touches blade (7) tenon, then locking;
Step 4: in the process, according to the numerical control program of frock, tool sharpening blade (7) tenon one party to surperficial the time, the working head (21) of the auxiliary support mechanism at this place is retreated to safe distance; After cutter leaves this surface, stretch out working head (21) and again contact with machined surface, until finish 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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Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105312483A (en) * | 2015-12-03 | 2016-02-10 | 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 |
| CN107627041A (en) * | 2017-11-08 | 2018-01-26 | 深圳市杰普特光电股份有限公司 | Strip resistance clamping device |
| CN111570873A (en) * | 2020-05-27 | 2020-08-25 | 菏泽学院 | Blade ultrasonic metal surface machining device |
| CN113319341A (en) * | 2021-06-08 | 2021-08-31 | 清华大学 | Blade machining system and method on blisk |
| CN114985814A (en) * | 2022-06-29 | 2022-09-02 | 中国航发动力股份有限公司 | Machining tool and system for blade body and using method |
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| 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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| US20030066820A1 (en) * | 2001-10-10 | 2003-04-10 | Byrnes Brett Wayne | Method and apparatus for turbine blade machining |
| US20040055134A1 (en) * | 2002-09-24 | 2004-03-25 | Jones Daniel Edward | Methods and apparatus for securing components for manufacture |
| GB2458738A (en) * | 2008-04-04 | 2009-10-07 | Heller Machine Tools Ltd | Holding device for non planar work piece |
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Cited By (10)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN105312483A (en) * | 2015-12-03 | 2016-02-10 | 中国南方航空工业(集团)有限公司 | Method for forging beryllium bronze blade of engine |
| 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 |
| CN107627041A (en) * | 2017-11-08 | 2018-01-26 | 深圳市杰普特光电股份有限公司 | Strip resistance clamping device |
| 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 |
| CN111570873A (en) * | 2020-05-27 | 2020-08-25 | 菏泽学院 | Blade ultrasonic metal surface machining device |
| CN113319341A (en) * | 2021-06-08 | 2021-08-31 | 清华大学 | Blade machining system and method on blisk |
| CN113319341B (en) * | 2021-06-08 | 2022-05-03 | 清华大学 | Blade machining system and method on blisk |
| CN114985814A (en) * | 2022-06-29 | 2022-09-02 | 中国航发动力股份有限公司 | Machining tool and system for blade body and using method |
| 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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| CN102975061B (en) | 2015-06-17 |
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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 |