CN203918539U - A kind of for processing the fixture of aviation thin wall vane pitch - Google Patents
A kind of for processing the fixture of aviation thin wall vane pitch Download PDFInfo
- Publication number
- CN203918539U CN203918539U CN201420057717.5U CN201420057717U CN203918539U CN 203918539 U CN203918539 U CN 203918539U CN 201420057717 U CN201420057717 U CN 201420057717U CN 203918539 U CN203918539 U CN 203918539U
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- China
- Prior art keywords
- blade
- hold
- positioning seat
- sagittal plane
- ring surface
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Expired - Lifetime
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- 230000007246 mechanism Effects 0.000 claims abstract description 81
- 238000003825 pressing Methods 0.000 claims description 28
- 230000013011 mating Effects 0.000 claims description 3
- 230000006835 compression Effects 0.000 claims description 2
- 238000007906 compression Methods 0.000 claims description 2
- 238000000034 method Methods 0.000 abstract description 8
- 238000003754 machining Methods 0.000 abstract description 5
- 238000003801 milling Methods 0.000 abstract description 4
- 239000000956 alloy Substances 0.000 description 6
- 229910045601 alloy Inorganic materials 0.000 description 5
- 238000010586 diagram Methods 0.000 description 4
- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 description 2
- 229910001069 Ti alloy Inorganic materials 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000005520 cutting process Methods 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 229910000743 fusible alloy Inorganic materials 0.000 description 1
- 238000000227 grinding Methods 0.000 description 1
- 238000010030 laminating Methods 0.000 description 1
- 238000004519 manufacturing process Methods 0.000 description 1
- 239000000463 material Substances 0.000 description 1
Abstract
It is a kind of for processing the fixture of aviation thin wall vane pitch that the utility model provides, the problem that machining accuracy is unstable, long processing time efficiency is low, cost is high of using the method for the regrind/milling of watering square chest to exist when it can solve such vanepiston of existing processing.It is characterized in that: it comprises clamp bottom board, clamp bottom board central authorities are longitudinally provided with blade hold-down mechanism, horizontal two outsides of blade hold-down mechanism are separately installed with blade inner ring surface detent mechanism and blade outer ring surface detent mechanism, blade inner ring surface detent mechanism, the lateral outer side of blade outer ring surface detent mechanism is separately installed with blade false boss hold-down mechanism, it passes through by blade inner ring surface detent mechanism, the manufactured interior ring sagittal plane of blade outer ring surface detent mechanism locating blades, outer shroud sagittal plane, and by blade hold-down mechanism, blade false boss hold-down mechanism compresses.
Description
Technical field
The utility model relates to the production frock field of aviation thin wall vane, is specially a kind of for processing the fixture of aviation thin wall vane pitch.
Background technology
Aviation thin wall vane is used titanium alloy material mostly, due to blade structure and material performance reason, causes blade cutting ability poor, processes yielding.The inner and outer rings pitch of this type of blade is important fitted position, and its surface quality, requirement on machining accuracy are all very high.General this type of vanepiston of processing is used " water square chest---mill/milling " method processing mostly, the method is had good positioning blade because of needs in square chest, then pour into alloy, after the alloy cooled and solidified in square chest, again square chest is located on grinding machine/milling machine table to clamping, and then processing pitch face.The method has following three drawbacks: the internal stress that (1) cast alloy produces, molten can Stress Release after removing alloy, make deformable blade, cause machining accuracy unstable.(2) because blade need to first be poured into a mould square chest, then wait alloy cooled and solidified in square chest, upper equipment processing, activity time is long.(3) water square chest fusible alloy price used high, and in use have inevitable loss, cause processing cost high.
Summary of the invention
For the problems referred to above, it is a kind of for processing the fixture of aviation thin wall vane pitch that the utility model provides, the problem that machining accuracy is unstable, long processing time efficiency is low, cost is high of using the method for the regrind/milling of watering square chest to exist when it can solve such vanepiston of existing processing.
Its technical scheme is such, it is characterized in that: it comprises clamp bottom board, described clamp bottom board central authorities are longitudinally provided with blade hold-down mechanism, horizontal two outsides of described blade hold-down mechanism are separately installed with blade inner ring surface detent mechanism and blade outer ring surface detent mechanism, described blade inner ring surface detent mechanism, the lateral outer side of blade outer ring surface detent mechanism is separately installed with blade false boss hold-down mechanism, it passes through by described blade inner ring surface detent mechanism, the manufactured interior ring sagittal plane of blade outer ring surface detent mechanism locating blades, outer shroud sagittal plane, and by described blade hold-down mechanism, blade false boss hold-down mechanism compresses.
It is further characterized in that:
Described blade hold-down mechanism comprises ring side profile briquetting, blade outer rim side profile briquetting in hinge pressing plate, blade, described hinge pressing plate is longitudinally installed on described clamp bottom board by hinge seat, the horizontal left and right sides of described hinge pressing plate is takeed on gyroaxis by band and is separately installed with and in described blade, encircles side profile briquetting and blade outer rim side profile briquetting, and in described blade, the bottom surface of ring side profile briquetting, blade outer rim side profile briquetting is set to respectively the locating surface mating with blade blade profile;
Longitudinal rear end and the described hinge seat of described hinge pressing plate are articulated and connected;
Described band shoulder gyroaxis passes successively in described blade outer rim side profile briquetting, hinge pressing plate, blade and by locking nut located lateral, is locked after ring side profile briquetting along horizontal right-to-left;
Longitudinal front end of described hinge pressing plate has spill draw-in groove, on described clamp bottom board, be provided with studs base, on described studs base, studs is installed, described studs snaps in the spill draw-in groove of described hinge pressing plate and takes on nut by band longitudinal front end of described hinge pressing plate is pressed on described studs base;
Described blade inner ring surface detent mechanism, blade outer ring surface detent mechanism comprise respectively ring sagittal plane positioning seat, blade outer shroud sagittal plane positioning seat in the blade being installed in described clamp base, and in described blade, ring sagittal plane positioning seat, blade outer shroud sagittal plane positioning seat lay respectively at the horizontal arranged on left and right sides of described hinge pressing plate;
In described blade longitudinal front side end of ring sagittal plane positioning seat, blade outer shroud sagittal plane positioning seat also respectively correspondence ring side positioning seat, blade outer shroud side positioning seat in blade are installed, in described blade, on ring side positioning seat, blade outer shroud side positioning seat, horizontal milled screw is all installed;
On the horizontal left surface of described blade outer ring surface positioning seat, axial location seat is installed, on described axial location seat, axial location pin is installed;
Described blade false boss hold-down mechanism comprises pressed seat, moving press plate and locking studs, described pressed seat is fixedly installed on described clamp bottom board by attachment screw, on described pressed seat, cushion block is installed, the horizontal one end of described moving press plate is pressed on described cushion block, the other end is pressed on described pressed seat and by described locking studs and the nut check of locking belt shoulder by blade false boss;
Described blade false boss hold-down mechanism is provided with three groups, and described three groups of blade false boss hold-down mechanisms encircle side false boss hold-down mechanism and two groups of outer rim side false boss hold-down mechanisms in comprising one group; Horizontal left side, its two, blade of moving press plate compression that described interior ring side false boss hold-down mechanism is positioned at described blade ring sagittal plane positioning seat encircle side false boss; Described two groups of outer rim side false boss hold-down mechanisms are all positioned at the horizontal right side state of described blade outer shroud sagittal plane positioning seat and the moving press plate of two groups of outer rim side false boss hold-down mechanisms compresses respectively two outer rim side false bosses of blade.
The beneficial effects of the utility model are: it usings the manufactured sagittal plane of blade as main locating surface, by blade hold-down mechanism, blade false boss hold-down mechanism, blade is compressed to blade blade and blade false boss, whole blade is subject to enough and equally distributed thrust, thereby effectively avoided the distortion of blade, and machining accuracy and stability have been improved; And it is simple in structure, simple operation, more traditional method of building square chest location, can greatly shorten the time of blade clamping location, thereby enhance productivity.
Accompanying drawing explanation
Fig. 1 is for adopting the perspective view of the utility model fixture positioning and clamping blade;
Fig. 2 is that the utility model is for processing the main TV structure schematic diagram of the fixture of aviation thin wall vane pitch;
Fig. 3 is that the utility model is for processing the plan structure schematic diagram of the fixture of aviation thin wall vane pitch;
Fig. 4 is the utility model for processing the structural representation of hinge pressing plate in the fixture blade hold-down mechanism of aviation thin wall vane pitch;
Fig. 5 is the plan structure schematic diagram of Fig. 4;
Fig. 6 is that while adopting the utility model fixture positioning and clamping blade, blade is subject to thrust schematic diagram;
Fig. 7 is thin wall vane structural representation to be processed in the utility model.
The specific embodiment
See Fig. 1～Fig. 5, it comprises clamp bottom board 1 the utility model fixture, clamp bottom board 1 central authorities are longitudinally provided with blade hold-down mechanism, horizontal two outsides of blade hold-down mechanism are separately installed with blade inner ring surface detent mechanism and blade outer ring surface detent mechanism, blade inner ring surface detent mechanism, the lateral outer side of blade outer ring surface detent mechanism is separately installed with blade false boss hold-down mechanism, it is by blade inner ring surface detent mechanism, the manufactured interior ring sagittal plane of blade outer ring surface detent mechanism locating blades, outer shroud sagittal plane, and by blade hold-down mechanism, blade false boss hold-down mechanism compresses.
Blade hold-down mechanism comprises ring side profile briquetting 3, blade outer rim side profile briquetting 4 in hinge pressing plate 2, blade, hinge pressing plate 2 is longitudinally installed on clamp bottom board 1 by hinge seat 5, the horizontal left and right sides of hinge pressing plate 3 is takeed on gyroaxis 6 by band and is separately installed with and in blade, encircles side profile briquetting 3 and blade outer rim side profile briquetting 4, and in blade, the bottom surface of ring side profile briquetting 3, blade outer rim side profile briquetting 4 is set to respectively the locating surface mating with blade blade profile; Longitudinal rear end and the hinge seat 5 of hinge pressing plate 2 are articulated and connected; Band shoulder gyroaxis 6 passes successively in blade outer rim side profile briquetting 4, hinge pressing plate 2, blade and by locking nut 7 located lateral, is locked after ring side profile briquetting 3 along horizontal right-to-left; Longitudinal front end of hinge pressing plate 2 has spill draw-in groove 8, on clamp bottom board 1, be provided with studs base 9, studs 10 is installed on studs base 9, and studs 10 snaps in the spill draw-in groove 8 of hinge pressing plate 2 and takes on nut 11 by band longitudinal front end of hinge pressing plate 2 is pressed on studs base 9;
Blade inner ring surface detent mechanism, blade outer ring surface detent mechanism comprise respectively ring sagittal plane positioning seat 12, blade outer shroud sagittal plane positioning seat 13 in the blade being installed in clamp base 1, and in blade, ring sagittal plane positioning seat 12, blade outer shroud sagittal plane positioning seat 13 lay respectively at the horizontal arranged on left and right sides of hinge pressing plate;
In blade longitudinal front side end of ring sagittal plane positioning seat 12, blade outer shroud sagittal plane positioning seat 13 also respectively correspondence ring side positioning seat 14, blade outer shroud side positioning seat 15 in blade are installed; On the horizontal left surface of blade outer ring surface positioning seat 13, axial location seat 16 is installed, axial location pin 17 is installed on axial location seat 16;
Blade false boss hold-down mechanism comprises pressed seat 18, moving press plate 19 and locking studs 20, pressed seat 18 is fixedly installed on clamp bottom board 1 by attachment screw 21, cushion block 22 is installed on pressed seat 18, and the horizontal one end of moving press plate 19 is pressed on cushion block 22, the other end is pressed on pressed seat 18 and by locking studs 20 and 24 lockings of locking belt shoulder nut by blade false boss 23; Blade false boss hold-down mechanism is provided with three groups, and three groups of blade false boss hold-down mechanisms encircle side false boss hold-down mechanism and two groups of outer rim side false boss hold-down mechanisms in comprising one group; Horizontal left side, its moving press plate 191 that interior ring side false boss hold-down mechanism is positioned at blade ring sagittal plane positioning seat compress two, blade and encircle side false boss; Two groups of outer rim side false boss hold-down mechanisms are all positioned at the horizontal right side of blade outer shroud sagittal plane positioning seat and the moving press plate 192,193 of two groups of outer rim side false boss hold-down mechanisms compresses respectively two outer rim side false bosses of blade.
Specifically describe the detailed process of the utility model clamping blade below: blade is placed on fixture, the sagittal plane that blade has been processed is fitted with interior ring sagittal plane positioning seat 12, the outer shroud sagittal plane positioning seat 13 of fixture respectively, and making ring side positioning seat 14 in blade side and blade, 15 laminatings of blade outer shroud side positioning seat, sharf is to locating with axial location pin 17, behind blade location, put down hinge pressing plate 2, with encircling side profile briquetting 3 in blade, blade outer rim side profile briquetting 4 is pushed down blade, then screw band shoulder nut 11, again successively by the moving press plate 191 of three groups of blade false boss hold-down mechanisms, 192, 193 correspondences are installed on locking studs 201, 202, on 203, screw respectively moving press plate 191, 192, locking belt shoulder nut 241 on 193, 242, 243 make them compress respectively corresponding blade false boss, wherein moving press plate 191 compresses ring side false boss 231 and 232 in blade, moving press plate 192 compresses blade outer rim side false boss 233, moving press plate 193 compresses blade outer rim side false boss 234, finally side positioning seat 14 will be encircled respectively in blade, milled screw 251 on blade outer rim side positioning seat 15, 252 tighten, complete blade clamping.
In Fig. 7,231,232 is ring side false boss in blade, 233,234 is blade outer rim side false boss, 27 is the blade part of blade, stressing conditions after blade clamping is shown in Fig. 6,28 is ring side profile briquetting 3 and the application of force region signal partly of 4 pairs of blade blades of blade outer rim side profile briquetting in blade, and 29 is 23 applied pressures signals of 19 pairs of blade false bosses of moving press plate.
Claims (9)
1. one kind for processing the fixture of aviation thin wall vane pitch, it is characterized in that: it comprises clamp bottom board, described clamp bottom board central authorities are longitudinally provided with blade hold-down mechanism, horizontal two outsides of described blade hold-down mechanism are separately installed with blade inner ring surface detent mechanism and blade outer ring surface detent mechanism, described blade inner ring surface detent mechanism, the lateral outer side of blade outer ring surface detent mechanism is separately installed with blade false boss hold-down mechanism, it passes through by described blade inner ring surface detent mechanism, the manufactured interior ring sagittal plane of blade outer ring surface detent mechanism locating blades, outer shroud sagittal plane, and by described blade hold-down mechanism, blade false boss hold-down mechanism compresses.
2. according to claim 1 a kind of for processing the fixture of aviation thin wall vane pitch, it is characterized in that: described blade hold-down mechanism comprises hinge pressing plate, ring side profile briquetting in blade, blade outer rim side profile briquetting, described hinge pressing plate is longitudinally installed on described clamp bottom board by hinge seat, the horizontal left and right sides of described hinge pressing plate is takeed on gyroaxis by band and is separately installed with and in described blade, encircles side profile briquetting and blade outer rim side profile briquetting, ring side profile briquetting in described blade, the bottom surface of blade outer rim side profile briquetting is set to respectively the locating surface mating with blade blade profile.
3. according to claim 2 a kind of for processing the fixture of aviation thin wall vane pitch, it is characterized in that: longitudinal rear end and the described hinge seat of described hinge pressing plate are articulated and connected.
4. according to claim 3 a kind of for processing the fixture of aviation thin wall vane pitch, it is characterized in that: longitudinal front end of described hinge pressing plate has spill draw-in groove, on described clamp bottom board, be provided with studs base, on described studs base, studs is installed, described studs snaps in the spill draw-in groove of described hinge pressing plate and takes on nut by band longitudinal front end of described hinge pressing plate is pressed on described studs base.
5. according to arbitrary described a kind of for processing the fixture of aviation thin wall vane pitch in claim 2～4, it is characterized in that: described blade inner ring surface detent mechanism, blade outer ring surface detent mechanism comprise respectively ring sagittal plane positioning seat, blade outer shroud sagittal plane positioning seat in the blade being installed in described clamp base, and in described blade, ring sagittal plane positioning seat, blade outer shroud sagittal plane positioning seat lay respectively at the horizontal arranged on left and right sides of described hinge pressing plate.
6. according to claim 5 a kind of for processing the fixture of aviation thin wall vane pitch, it is characterized in that: in described blade longitudinal front side end of ring sagittal plane positioning seat, blade outer shroud sagittal plane positioning seat also respectively correspondence ring side positioning seat, blade outer shroud side positioning seat in blade are installed, in described blade, on ring side positioning seat, blade outer shroud side positioning seat, horizontal milled screw is all installed.
7. according to claim 6 a kind of for processing the fixture of aviation thin wall vane pitch, it is characterized in that: on the horizontal left surface of described blade outer ring surface positioning seat, axial location seat is installed, on described axial location seat, axial location pin is installed.
8. according to claim 7 a kind of for processing the fixture of aviation thin wall vane pitch, it is characterized in that: described blade false boss hold-down mechanism comprises pressed seat, moving press plate and locking studs, described pressed seat is fixedly installed on described clamp bottom board by attachment screw, on described pressed seat, cushion block is installed, the horizontal one end of described moving press plate is pressed on described cushion block, the other end is pressed on described pressed seat and by described locking studs and the nut check of locking belt shoulder by blade false boss.
9. according to claim 8 a kind of for processing the fixture of aviation thin wall vane pitch, it is characterized in that: described blade false boss hold-down mechanism is provided with three groups, described three groups of blade false boss hold-down mechanisms encircle side false boss hold-down mechanism and two groups of outer rim side false boss hold-down mechanisms in comprising one group; Horizontal left side, its two, blade of moving press plate compression that described interior ring side false boss hold-down mechanism is positioned at described blade ring sagittal plane positioning seat encircle side false boss; Described two groups of outer rim side false boss hold-down mechanisms are all positioned at the horizontal right side state of described blade outer shroud sagittal plane positioning seat and the moving press plate of two groups of outer rim side false boss hold-down mechanisms compresses respectively two outer rim side false bosses of blade.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201420057717.5U CN203918539U (en) | 2014-01-30 | 2014-01-30 | A kind of for processing the fixture of aviation thin wall vane pitch |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201420057717.5U CN203918539U (en) | 2014-01-30 | 2014-01-30 | A kind of for processing the fixture of aviation thin wall vane pitch |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN203918539U true CN203918539U (en) | 2014-11-05 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201420057717.5U Expired - Lifetime CN203918539U (en) | 2014-01-30 | 2014-01-30 | A kind of for processing the fixture of aviation thin wall vane pitch |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN203918539U (en) |
Cited By (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103878608A (en) * | 2014-01-30 | 2014-06-25 | 无锡透平叶片有限公司 | Clamp used for processing aviation thin-wall blade pitch |
| CN105344975A (en) * | 2015-11-26 | 2016-02-24 | 沈阳黎明航空发动机(集团)有限责任公司 | Datum transformation fixture and datum transformation method for guide blades |
| CN106514022A (en) * | 2016-12-27 | 2017-03-22 | 无锡透平叶片有限公司 | Positioning clamping device for total length machining of turbine hollow blade |
| CN106695499A (en) * | 2016-11-25 | 2017-05-24 | 沈阳黎明航空发动机(集团)有限责任公司 | Multi-station continuous grinding device and method for guide vane |
| CN108818058A (en) * | 2018-08-13 | 2018-11-16 | 贵州安吉华元科技发展有限公司 | A kind of part blade processing positioning special tooling |
| CN110514086A (en) * | 2019-08-30 | 2019-11-29 | 中国航发动力股份有限公司 | A kind of device and method for obturaging groove location measurement |
| CN113290401A (en) * | 2021-06-08 | 2021-08-24 | 浙江中柴机器有限公司 | Reverse-pulling type clamp device for machining thin-wall gearbox body |
| CN113618127A (en) * | 2021-08-20 | 2021-11-09 | 中国航发航空科技股份有限公司 | Machining process of aero-engine blade |
-
2014
- 2014-01-30 CN CN201420057717.5U patent/CN203918539U/en not_active Expired - Lifetime
Cited By (12)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103878608A (en) * | 2014-01-30 | 2014-06-25 | 无锡透平叶片有限公司 | Clamp used for processing aviation thin-wall blade pitch |
| CN103878608B (en) * | 2014-01-30 | 2017-02-15 | 无锡透平叶片有限公司 | Clamp used for processing aviation thin-wall blade pitch |
| CN105344975A (en) * | 2015-11-26 | 2016-02-24 | 沈阳黎明航空发动机(集团)有限责任公司 | Datum transformation fixture and datum transformation method for guide blades |
| CN105344975B (en) * | 2015-11-26 | 2017-10-24 | 沈阳黎明航空发动机(集团)有限责任公司 | A kind of guide vane Reference Transforming fixture and Reference Transforming method |
| CN106695499A (en) * | 2016-11-25 | 2017-05-24 | 沈阳黎明航空发动机(集团)有限责任公司 | Multi-station continuous grinding device and method for guide vane |
| CN106695499B (en) * | 2016-11-25 | 2018-07-13 | 沈阳黎明航空发动机(集团)有限责任公司 | A kind of guide vane multistation continuous grinding device and method |
| CN106514022A (en) * | 2016-12-27 | 2017-03-22 | 无锡透平叶片有限公司 | Positioning clamping device for total length machining of turbine hollow blade |
| CN108818058A (en) * | 2018-08-13 | 2018-11-16 | 贵州安吉华元科技发展有限公司 | A kind of part blade processing positioning special tooling |
| CN108818058B (en) * | 2018-08-13 | 2020-07-28 | 贵州安吉华元科技发展有限公司 | Special tool for machining and positioning part blade |
| CN110514086A (en) * | 2019-08-30 | 2019-11-29 | 中国航发动力股份有限公司 | A kind of device and method for obturaging groove location measurement |
| CN113290401A (en) * | 2021-06-08 | 2021-08-24 | 浙江中柴机器有限公司 | Reverse-pulling type clamp device for machining thin-wall gearbox body |
| CN113618127A (en) * | 2021-08-20 | 2021-11-09 | 中国航发航空科技股份有限公司 | Machining process of aero-engine blade |
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| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant |