CN202985187U - Precise machining process equipment of vane of aviation engine - Google Patents
Precise machining process equipment of vane of aviation engine Download PDFInfo
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- CN202985187U CN202985187U CN 201220512966 CN201220512966U CN202985187U CN 202985187 U CN202985187 U CN 202985187U CN 201220512966 CN201220512966 CN 201220512966 CN 201220512966 U CN201220512966 U CN 201220512966U CN 202985187 U CN202985187 U CN 202985187U
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- blade
- clamping
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- 238000003754 machining Methods 0.000 title claims abstract description 18
- 230000007246 mechanism Effects 0.000 claims description 35
- 239000011159 matrix material Substances 0.000 claims description 27
- 230000033001 locomotion Effects 0.000 claims description 3
- 238000000034 method Methods 0.000 abstract description 15
- 238000004519 manufacturing process Methods 0.000 abstract description 4
- 239000010720 hydraulic oil Substances 0.000 abstract 1
- 238000005516 engineering process Methods 0.000 description 10
- 229910000743 fusible alloy Inorganic materials 0.000 description 5
- 238000010586 diagram Methods 0.000 description 2
- 238000005242 forging Methods 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000004140 cleaning Methods 0.000 description 1
- 230000002950 deficient Effects 0.000 description 1
- 238000012423 maintenance Methods 0.000 description 1
- 238000010309 melting process Methods 0.000 description 1
- 238000003672 processing method Methods 0.000 description 1
- 230000001105 regulatory effect Effects 0.000 description 1
- 230000000153 supplemental effect Effects 0.000 description 1
- 238000010257 thawing Methods 0.000 description 1
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Abstract
Provided are precise machining process equipment of a vane of an aviation engine and a machining method. The equipment comprises a positioning device fixed on a foundation table face, a clamping device and an auxiliary supporting device, wherein the positioning device is used for vane body curved face positioning of the vane, the clamping device is used for clamping the vane body, the auxiliary supporting device is fixed outside the positioning device and the clamping device, and a work head of the auxiliary supporting device directly contacts with a tenon portion of the vane. A main controller controls hydraulic oil cylinders on a tool through control circuits. The equipment directly positions and clamps the thin-walled curved face vane body of the vane, carries out tenon machining, can achieve continuous mechanical operation and machining in production of the vane, and improves work efficiency and machining quality.
Description
Technical field
The utility model relates to the processing technique field of blade of aviation engine, is specifically related to a kind of precise machining process equipment 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 based on the processing mode of blade low-melting alloy cast, namely to completing blade without the blade woollen of surplus finish forge and intake and exhaust limit processing, after six point location clampings, blade is 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.
The utility model content
For solving the above-mentioned problems in the prior art, the purpose of this utility model is to propose a kind of precise machining process equipment of blade of aviation engine, directly the thin-wall curved-surface blade of blade positioned clamping, and then carry out tenon and process, can realize continuous mechanically actuated and processing in blade production, increase work efficiency and crudy.
For achieving the above object, the technical scheme that the utility model adopts 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 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 auxiliary support apparatus 4.
Described positioner 2 comprises the location matrix 8 that is fixed on basic table top 1, is arranged on main locating piece 10 and side locating piece 9 on the matrix 8 of location, be distributed with three alignment pins 11 on 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 and contact with the admission edge of blade 7 on described side locating piece 9.
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 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 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 side direction clamp mechanism clamping matrix 15, be respectively used 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 basic table top 1, be fixed on the working head 21 on 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 PCL programmable control system is by hydraulic control valve and control loop 6 each hydraulic jacks of operation.
The beneficial effects of the utility model are: 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 utlity model has the characteristics such as automatization level is high, processing quality good, process is novel, be applicable to the accurate digital control processing of blade of aviation engine, can provide key technology basic for extensive automation blade production line.
Description of drawings
Fig. 1 is the overall structure schematic diagram of the utility model technological equipment.
Fig. 2 is the structural representation of positioner in the utility model technological equipment.
Fig. 3 is the structural representation of clamping device in the utility model technological equipment.
Fig. 4 is the schematic diagram of auxiliary support mechanism in the utility model technological equipment.
The specific embodiment
Below in conjunction with the drawings and specific embodiments, the utility model 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 utility model, 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 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 auxiliary support apparatus 4.
As shown in Figure 2, positioner 2 comprises the location matrix 8 that is fixed on basic table top 1, is arranged on main locating piece 10 and side locating piece 9 on the matrix 8 of location, be distributed with three alignment pins 11 on 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 and contact with the admission edge of blade 7 on described side locating piece 9, 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 basic table top 1 and is connected the main clamp 16 of matrix 14 connections with main folder, the blade that three clamping heads 17 are used for clamping blade 7 is housed on 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 side direction clamp mechanism clamping matrix 15, be respectively used 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 arranged on basic table top 1 with bolt connecting mode, and auxiliary support mechanism comprises the matrix 19 that is fixed on basic table top 1, be fixed on the working head 21 on 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 in the situation that guarantee to contact and do not destroy the location of blade, can significantly improve the lower problem of rigidity that blade causes due to the thin-wall curved-surface structure characteristics, do not need to apply excessive clamping force on blade yet, therefore can effectively reduce mismachining tolerance in process, 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, automatically adjust each supporting mechanism of auxiliary support apparatus according to advancing of machine tool in process, thereby guarantee that in process, cutter can not interfere with supporting mechanism, the assurance cutter track is unobstructed, guarantees the smooth execution of tenon processing technology.
The utility model to the processing method of blade is: at first weave the numerical control program of tenon processing, the numerical control program of frock; Then after putting into blade 7 in frock, 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 clamping, the tight mechanism of main folder and side direction clamp mechanism are locked; Support hydraulic pressure oil cylinder 20 by four auxiliary support mechanisms stretches out working head 21 and touches blade 7 tenons subsequently, then locking; In process, according to the numerical control program of frock, when tool sharpening blade 7 tenon a direction surperficial, 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 complete the processing of tenon.
Low-melting alloy cast blade tenon process technology contrast with generally adopting now the utlity model has following advantage:
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 is in the situation that guarantee to contact and do not affect the curved surface location of blade, can significantly improve the low Rigidity that blade causes due to the design feature of thin-wall curved-surface, and can reduce clamping force on blade, therefore can effectively reduce mismachining tolerance in process, 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 in process, cutter can not interfere with support member, the assurance cutter track is unobstructed, guarantees the execution of tenon processing technology.The utility model can significantly improve the technical merit of blade processing, for the production of automation blade provides key technology basic.
Claims (5)
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 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 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 basic table top (1), be arranged on main locating piece (10) and side locating piece (9) on location matrix (8), be distributed with three alignment pins (11) on 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 to be used for contacting with the listrium of blade (7), being provided with two keepers (12) on described side locating piece (9) contacts 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 main clamp (16) that the tight matrix of main folder (14) that is fixed on basic table top (1) and the matrix (14) that is connected with main folder connect, and the clamping head (17) of three is housed for the blade that clamps blade (7) on 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 side direction clamp mechanism clamping matrix (15), be respectively used 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 basic table top (1), be fixed on the working head (21) on 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).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 201220512966 CN202985187U (en) | 2012-10-08 | 2012-10-08 | Precise machining process equipment of vane of aviation engine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 201220512966 CN202985187U (en) | 2012-10-08 | 2012-10-08 | Precise machining process equipment of vane of aviation engine |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN202985187U true CN202985187U (en) | 2013-06-12 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN 201220512966 Expired - Fee Related CN202985187U (en) | 2012-10-08 | 2012-10-08 | Precise machining process equipment of vane of aviation engine |
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| Country | Link |
|---|---|
| CN (1) | CN202985187U (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102975061A (en) * | 2012-10-08 | 2013-03-20 | 清华大学 | Precision machining technological equipment and machining method for blade of aviation engine |
-
2012
- 2012-10-08 CN CN 201220512966 patent/CN202985187U/en not_active Expired - Fee Related
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102975061A (en) * | 2012-10-08 | 2013-03-20 | 清华大学 | Precision machining technological equipment and machining method for blade of aviation engine |
| CN102975061B (en) * | 2012-10-08 | 2015-06-17 | 清华大学 | Precision machining technological equipment and machining method for blade of aviation engine |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20130612 Termination date: 20171008 |