CN103878608B - Clamp used for processing aviation thin-wall blade pitch - Google Patents
Clamp used for processing aviation thin-wall blade pitch Download PDFInfo
- Publication number
- CN103878608B CN103878608B CN201410044262.8A CN201410044262A CN103878608B CN 103878608 B CN103878608 B CN 103878608B CN 201410044262 A CN201410044262 A CN 201410044262A CN 103878608 B CN103878608 B CN 103878608B
- Authority
- CN
- China
- Prior art keywords
- blade
- pressing plate
- hold
- seat
- sagittal plane
- 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.)
- Active
Links
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
- B23Q—DETAILS, COMPONENTS, OR ACCESSORIES FOR MACHINE TOOLS, e.g. ARRANGEMENTS FOR COPYING OR CONTROLLING; MACHINE TOOLS IN GENERAL CHARACTERISED BY THE CONSTRUCTION OF PARTICULAR DETAILS OR COMPONENTS; COMBINATIONS OR ASSOCIATIONS OF METAL-WORKING MACHINES, NOT DIRECTED TO A PARTICULAR RESULT
- B23Q3/00—Devices holding, supporting, or positioning work or tools, of a kind normally removable from the machine
- B23Q3/02—Devices holding, supporting, or positioning work or tools, of a kind normally removable from the machine for mounting on a work-table, tool-slide, or analogous part
- B23Q3/06—Work-clamping means
- B23Q3/062—Work-clamping means adapted for holding workpieces having a special form or being made from a special material
- B23Q3/065—Work-clamping means adapted for holding workpieces having a special form or being made from a special material for holding workpieces being specially deformable, e.g. made from thin-walled or elastic material
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B24—GRINDING; POLISHING
- B24B—MACHINES, DEVICES, OR PROCESSES FOR GRINDING OR POLISHING; DRESSING OR CONDITIONING OF ABRADING SURFACES; FEEDING OF GRINDING, POLISHING, OR LAPPING AGENTS
- B24B41/00—Component parts such as frames, beds, carriages, headstocks
- B24B41/06—Work supports, e.g. adjustable steadies
Abstract
The invention provides a clamp used for processing aviation thin-wall blade pitch. By the clamp, the problems of unstability in processing accuracy, long processing time, low efficiency and high cost in an existing method of watering prior to grinding or milling to process the blade pitch can be solved. The clamp is characterized by comprising a clamp baseplate, a blade body compressing mechanism is mounted in the middle of the clamp baseplate longitudinally, a blade inner ring face positioning mechanism and a blade outer ring face positioning mechanism are mounted on two transverse outer sides of the blade body compressing mechanism respectively, and a blade process boss compressing mechanism is mounted on the transverse outer side of each of the blade inner ring face positioning mechanism and the blade outer ring face positioning mechanism. An inner ring radial face and an outer ring radial face, which are already processed well, of a blade are positioned by the blade inner ring face positioning mechanism and the blade outer ring face positioning mechanism and compressed by the blade body compressing mechanism and the blade process boss compressing mechanism.
Description
Technical field
The present invention relates to the production frock field of aviation thin-wall blade, particularly for processing aviation thin-wall blade pitch
Fixture.
Background technology
Aviation thin-wall blade is used mostly titanium alloy material, due to blade structure and material performance reason, causes blade to be cut
Cut poor performance, processing is yielding.The inner and outer rings pitch of such blade is important fitted position, and its surface quality, machining accuracy will
Ask all very high.Typically process such vanepiston and be used mostly the processing of " pouring square chest mill/milling " method, the method is because needing
In square chest, blade is had good positioning, then pour into alloy, after the alloy cooled and solidified in square chest, then by square chest in grinding machine/milling
Positioning clamping on bed workbench, then reprocesses pitch face.The method has three below drawback：（1）It is interior that cast alloy produces
Stress, molten remove alloy after can Stress Release, make deformable blade, cause machining accuracy unstable.（2）Because blade needs first to pour into a mould
Square chest, then waits alloy cooled and solidified in square chest, upper apparatus processing, and activity time is long.（3）Pour fusible alloy valency used by square chest
Lattice are high, and have inevitable loss in use, cause high processing costs.
Content of the invention
For the problems referred to above, the invention provides for the fixture processing aviation thin-wall blade pitch, it can solve existing
Process during such vanepiston using pour square chest regrind/machining accuracy that exists of the method for milling is unstable, process time is long-acting
Rate is low, the problem of high cost.
Its technical scheme be such it is characterised in that：It includes clamp bottom board, and described clamp bottom board central authorities are along longitudinally peace
Equipped with blade hold-down mechanism, described blade hold-down mechanism horizontal two outside be separately installed with blade inner ring surface detent mechanism and leaf
Piece outer ring surface detent mechanism, described blade inner ring surface detent mechanism, the lateral outer side of blade outer ring surface detent mechanism are respectively mounted
There is blade production boss hold-down mechanism, it passes through by described blade inner ring surface detent mechanism, blade outer ring surface detent mechanism positioning
Blade manufactured internal ring sagittal plane, outer shroud sagittal plane, and by described blade hold-down mechanism, blade production boss hold-down mechanism
Compression.
It is further characterized by：
Described blade hold-down mechanism includes hinge pressing plate, blade internal ring side type face pressure block, blade outer rim side type face pressure block, institute
State hinge pressing plate and pass through hinge seat along longitudinally mounted on described clamp bottom board, the horizontal left and right sides of described hinge pressing plate is passed through
Band shoulder gyroaxis is separately installed with described blade internal ring side type face pressure block and blade outer rim side type face pressure block, described blade internal ring side
Type face pressure block, the bottom surface of blade outer rim side type face pressure block are respectively set to the locating surface mating with blade blade type face；
The longitudinally aft end of described hinge pressing plate is articulated and connected with described hinge seat；
Described band shoulder gyroaxis transversely right-to-left sequentially pass through described blade outer rim side type face pressure block, hinge pressing plate,
Locked by locking nut located lateral after the type face pressure block of blade internal ring side；
Longitudinal front end of described hinge pressing plate has spill draw-in groove, and described clamp bottom board is provided with studs base,
Studs is provided with described studs base, described studs snap in the spill draw-in groove of described hinge pressing plate and
And by longitudinal front end of described hinge pressing plate being pressed on described studs base with shoulder nut；
Described blade inner ring surface detent mechanism, blade outer ring surface detent mechanism include being installed on described clamp bottom board respectively
Blade internal ring sagittal plane positioning seat, blade outer shroud sagittal plane positioning seat, described blade internal ring sagittal plane positioning seat, blade outer shroud
Sagittal plane positioning seat is located at the horizontal arranged on left and right sides of described hinge pressing plate respectively；
Described blade internal ring sagittal plane positioning seat, longitudinal front side end of blade outer shroud sagittal plane positioning seat also correspond to peace respectively
Equipped with blade internal ring side positioning seat, blade outer shroud side positioning seat, described blade internal ring side positioning seat, blade outer shroud side
Horizontal milled screw is fitted with positioning seat；
On the horizontal left surface of described blade outer shroud sagittal plane positioning seat, axially position seat, described axially position seat are installed
On axially position pin is installed；
Described blade production boss hold-down mechanism includes pressed seat, mobile pressing plate and locking studs, described pressed seat
It is fixedly installed on described clamp bottom board by attachment screw, described pressed seat is provided with cushion block, described mobile pressing plate horizontal
Side pressure is on described cushion block, blade production boss is pressed on described pressed seat and by described locking studs the other end
And locking belt shoulder nut check；
Described blade production boss hold-down mechanism is provided with three groups, and described three groups of blade production boss hold-down mechanisms include one
Group internal ring side false boss hold-down mechanism and two groups of outer rim side false boss hold-down mechanisms；Described internal ring side false boss compacting machine
Structure is convex positioned at the horizontal left side of described blade internal ring sagittal plane positioning seat, its mobile pressing plate compression two internal ring side technique of blade
Platform；Described two groups of outer rim side false boss hold-down mechanisms be respectively positioned on described blade outer shroud sagittal plane positioning seat horizontal right side state,
And the mobile pressing plate of two groups of outer rim side false boss hold-down mechanisms compresses two outer rim side false bosses of blade respectively.
The beneficial effects of the present invention is：Its using the manufactured sagittal plane of blade as main locating surface, by blade
Blade is compressed blade blade and blade production boss by hold-down mechanism, blade production boss hold-down mechanism, and whole blade is subject to foot
Enough and equally distributed thrust, thus effectively prevent the deformation of blade, and improve machining accuracy and stability；And its
Structure is simple, simple operation, more traditional method pouring square chest positioning, can greatly shorten the time of blade Set and Positioning, thus
Improve production efficiency.
Brief description
Fig. 1 is the perspective view using present clip positioning and clamping blade；
Fig. 2 is used for for the present invention processing the main structure diagram of the fixture of aviation thin-wall blade pitch；
Fig. 3 is used for for the present invention processing the overlooking the structure diagram of the fixture of aviation thin-wall blade pitch；
Fig. 4 is used for the knot of hinge pressing plate in blade hold-down mechanism in the fixture process aviation thin-wall blade pitch for the present invention
Structure schematic diagram；
Fig. 5 is the overlooking the structure diagram of Fig. 4；
Fig. 6 is to be subject to thrust schematic diagram using blade during present clip positioning and clamping blade；
Fig. 7 is thin wall vane structural representation to be processed in the present invention.
Specific embodiment
See Fig. 1～Fig. 5, present clip it include clamp bottom board 1, clamp bottom board 1 central authorities are along being longitudinally provided with blade pressure
Tight mechanism, blade hold-down mechanism horizontal two outside be separately installed with blade inner ring surface detent mechanism and blade outer ring surface localization machine
Structure, blade inner ring surface detent mechanism, the lateral outer side of blade outer ring surface detent mechanism are separately installed with blade production boss compression
Mechanism, its pass through blade inner ring surface detent mechanism, the manufactured internal ring sagittal plane of blade outer ring surface detent mechanism locating blades,
Outer shroud sagittal plane, and by blade hold-down mechanism, blade production boss hold-down mechanism compression.
Blade hold-down mechanism includes hinge pressing plate 2, blade internal ring side type face pressure block 3, blade outer rim side type face pressure block 4, hinge
Chain pressing plate 2 passes through hinge seat 5 along longitudinally mounted on clamp bottom board 1, and band shoulder revolution is passed through in the horizontal left and right sides of hinge pressing plate 3
Axle 6 is separately installed with blade internal ring side type face pressure block 3 and blade outer rim side type face pressure block 4, blade internal ring side type face pressure block 3, leaf
The bottom surface of piece outer rim side type face pressure block 4 is respectively set to the locating surface mating with blade blade type face；After the longitudinal direction of hinge pressing plate 2
End is articulated and connected with hinge seat 5；Transversely right-to-left sequentially passes through blade outer rim side type face pressure block 4, hinge to band shoulder gyroaxis 6
Locked by locking nut 7 located lateral after pressing plate 2, blade internal ring side type face pressure block 3；Longitudinal front end of hinge pressing plate 2 has recessed
Shape draw-in groove 8, clamp bottom board 1 is provided with studs base 9, and studs base 9 is provided with studs 10, double end spiral shell
Post 10 snaps in the spill draw-in groove 8 of hinge pressing plate 2 and by being pressed in longitudinal front end of hinge pressing plate 2 with shoulder nut 11
On studs base 9；
Blade inner ring surface detent mechanism, blade outer ring surface detent mechanism include the blade being installed on clamp bottom board 1 respectively
Internal ring sagittal plane positioning seat 12, blade outer shroud sagittal plane positioning seat 13, blade internal ring sagittal plane positioning seat 12, blade outer shroud are radially
Face positioning seat 13 is located at the horizontal arranged on left and right sides of hinge pressing plate respectively；
Blade internal ring sagittal plane positioning seat 12, longitudinal front side end of blade outer shroud sagittal plane positioning seat 13 also correspond to peace respectively
Equipped with blade internal ring side positioning seat 14, blade outer shroud side positioning seat 15；A horizontal left side for blade outer shroud sagittal plane positioning seat 13
Axially position seat 16 is provided with side, axially position seat 16 is provided with axially position pin 17；
Blade production boss hold-down mechanism includes pressed seat 18, mobile pressing plate 19 and locking studs 20, pressed seat 18
It is fixedly installed on clamp bottom board 1 by attachment screw 21, pressed seat 18 is provided with cushion block 22, the mobile horizontal side pressure of pressing plate 19
On cushion block 22, the other end blade production boss 23 is pressed on pressed seat 18 and by locking studs 20 and locking
Band shoulder nut 24 is locked；Blade production boss hold-down mechanism is provided with three groups, and three groups of blade production boss hold-down mechanisms include one
Group internal ring side false boss hold-down mechanism and two groups of outer rim side false boss hold-down mechanisms；Internal ring side false boss hold-down mechanism position
Horizontal left side, its mobile pressing plate 191 compression two internal ring side false boss of blade in blade internal ring sagittal plane positioning seat；Two groups
Outer rim side false boss hold-down mechanism is respectively positioned on laterally right side and two groups of outer rim side techniques of blade outer shroud sagittal plane positioning seat
The mobile pressing plate 192,193 of boss hold-down mechanism compresses two outer rim side false bosses of blade respectively.
The detailed process of of the present invention clamping blade is detailed below：Blade is placed on fixture, has made blade
The sagittal plane of processing is fitted, and is made blade-side with the internal ring sagittal plane positioning seat 12 of fixture, outer shroud sagittal plane positioning seat 13 respectively
Fitted with blade internal ring side positioning seat 14, blade outer shroud side positioning seat 15 in face, blade is axially positioned with axially position pin 17；
After blade positioning, put down hinge pressing plate 2, push down blade with blade internal ring side type face pressure block 3, blade outer rim side type face pressure block 4, so
After screw band shoulder nut 11, more successively by corresponding for the mobile pressing plate 191,192,193 of three groups of blade production boss hold-down mechanisms peace
Be loaded on locking studs 201,202,203 on, screw respectively on mobile pressing plate 191,192,193 locking belt shoulder nut 241,
242nd, 243 make them compress corresponding blade production boss respectively, wherein move pressing plate 191 compression blade internal ring side false boss
231 and 232, mobile pressing plate 192 compression blade outer rim side false boss 233, mobile pressing plate 193 compression blade outer rim side technique is convex
Milled screw 251,252 on blade internal ring side positioning seat 14, blade outer rim side positioning seat 15 is finally twisted by platform 234 respectively
Tightly, that is, complete blade clamping.
In Fig. 7,231,232 is blade internal ring side false boss, and 233,234 is blade outer rim side false boss, and 27 is leaf
The blade portion of piece, the stressing conditions after blade clamping are shown in Fig. 6, and 28 is blade internal ring side type face pressure block 3 and blade outer rim side type
Face pressure block 4 is illustrated to the force region of blade blade portion, 29 pressures blade production boss 23 being applied by mobile pressing plate 19
Power is illustrated.
Claims (6)
1. be used for process aviation thin-wall blade pitch fixture it is characterised in that：It includes clamp bottom board, in described clamp bottom board
Centre along being longitudinally provided with blade hold-down mechanism, described blade hold-down mechanism horizontal two outside to be separately installed with blade inner ring surface fixed
Position mechanism and blade outer ring surface detent mechanism, described blade inner ring surface detent mechanism, blade outer ring surface detent mechanism are lateral out
Side is separately installed with blade production boss hold-down mechanism, and it passes through fixed by described blade inner ring surface detent mechanism, blade outer ring surface
The manufactured internal ring sagittal plane of position mechanism locating blades, outer shroud sagittal plane, and convex by described blade hold-down mechanism, blade production
Platform hold-down mechanism compresses；
Described blade hold-down mechanism includes hinge pressing plate, blade internal ring side type face pressure block, blade outer rim side type face pressure block, described hinge
Chain pressing plate passes through hinge seat along longitudinally mounted on described clamp bottom board, and the horizontal left and right sides of described hinge pressing plate is takeed on by band
Gyroaxis is separately installed with described blade internal ring side type face pressure block and blade outer rim side type face pressure block, described blade internal ring side type face
Briquetting, the bottom surface of blade outer rim side type face pressure block are respectively set to the locating surface mating with blade blade type face；
The longitudinally aft end of described hinge pressing plate is articulated and connected with described hinge seat；
Longitudinal front end of described hinge pressing plate has spill draw-in groove, and described clamp bottom board is provided with studs base, described
Studs is provided with studs base, described studs snaps in the spill draw-in groove of described hinge pressing plate and leads to
Cross and with shoulder nut, longitudinal front end of described hinge pressing plate is pressed on described studs base.
2. the fixture for processing aviation thin-wall blade pitch according to claim 1 it is characterised in that：In described blade
The blade internal ring sagittal plane that anchor ring detent mechanism, blade outer ring surface detent mechanism include being installed on described clamp bottom board respectively is fixed
Position seat, blade outer shroud sagittal plane positioning seat, described blade internal ring sagittal plane positioning seat, blade outer shroud sagittal plane positioning seat position respectively
Horizontal arranged on left and right sides in described hinge pressing plate.
3. the fixture for processing aviation thin-wall blade pitch according to claim 2 it is characterised in that：In described blade
Ring sagittal plane positioning seat, longitudinal front side end of blade outer shroud sagittal plane positioning seat also correspond to respectively and are provided with blade internal ring side calmly
Position seat, blade outer shroud side positioning seat, described blade internal ring side positioning seat, blade outer shroud side positioning seat are fitted with horizontal stroke
To milled screw.
4. the fixture for processing aviation thin-wall blade pitch according to claim 3 it is characterised in that：Outside described blade
Axially position seat is provided with the horizontal left surface of ring sagittal plane positioning seat, described axially position seat is provided with axially position
Pin.
5. the fixture for processing aviation thin-wall blade pitch according to claim 4 it is characterised in that：Described blade work
Skill boss hold-down mechanism includes pressed seat, mobile pressing plate and locking studs, and described pressed seat is fixedly mounted by attachment screw
On described clamp bottom board, described pressed seat is provided with cushion block, the horizontal one end of described mobile pressing plate is pressed on described cushion block, another
One end blade production boss is pressed on described pressed seat and by described locking studs and locking belt shoulder nut lock
Tightly.
6. the fixture for processing aviation thin-wall blade pitch according to claim 5 it is characterised in that：Described blade work
Skill boss hold-down mechanism is provided with three groups, and described three groups of blade production boss hold-down mechanisms include one group of internal ring side false boss pressure
Tight mechanism and two groups of outer rim side false boss hold-down mechanisms；Described internal ring side false boss hold-down mechanism is located at described blade internal ring
The horizontal left side of sagittal plane positioning seat, its mobile pressing plate compression two internal ring side false boss of blade；Described two groups of outer rim side works
Skill boss hold-down mechanism is respectively positioned on the horizontal right side state of described blade outer shroud sagittal plane positioning seat and two groups of outer rim side techniques are convex
The mobile pressing plate of platform hold-down mechanism compresses two outer rim side false bosses of blade respectively.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410044262.8A CN103878608B (en) | 2014-01-30 | 2014-01-30 | Clamp used for processing aviation thin-wall blade pitch |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410044262.8A CN103878608B (en) | 2014-01-30 | 2014-01-30 | Clamp used for processing aviation thin-wall blade pitch |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN103878608A CN103878608A (en) | 2014-06-25 |
| CN103878608B true CN103878608B (en) | 2017-02-15 |
Family
ID=50947899
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201410044262.8A Active CN103878608B (en) | 2014-01-30 | 2014-01-30 | Clamp used for processing aviation thin-wall blade pitch |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN103878608B (en) |
Families Citing this family (17)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104120235B (en) * | 2014-06-27 | 2016-02-24 | 中航飞机股份有限公司西安飞机分公司 | A kind of stud height unequal slide rail class part method for controlling heat treatment deformation |
| CN104213059B (en) * | 2014-06-27 | 2016-08-03 | 中航飞机股份有限公司西安飞机分公司 | Titanium alloy bilayer curved surface wing plate part method for controlling heat treatment deformation |
| CN104084814B (en) * | 2014-07-01 | 2017-03-22 | 东方电气集团东方汽轮机有限公司 | Quick clamping and alignment method and fixture for milling arc segments of stationary blade grid |
| CN104190904A (en) * | 2014-08-01 | 2014-12-10 | 南京赛达机械制造有限公司 | Fixture special for steam turbine die forging blades |
| US10105804B2 (en) | 2014-10-15 | 2018-10-23 | United Technologies Corporation | Fixture system and method for securing an airfoil during material removal operations |
| CN104476223B (en) * | 2014-11-10 | 2017-01-11 | 沈阳黎明航空发动机(集团)有限责任公司 | Following adaptive supporting mechanism for thin-wall cover hood like parts |
| CN105538096B (en) * | 2015-12-10 | 2018-11-27 | 中国南方航空工业(集团)有限公司 | Blade tenon clamp |
| CN108031948A (en) * | 2018-01-12 | 2018-05-15 | 中国航发哈尔滨东安发动机有限公司 | The vacuum brazing frock of rectifier assembly |
| CN109514466B (en) * | 2018-12-24 | 2020-10-30 | 海马汽车有限公司 | Compressing tool |
| CN110238776A (en) * | 2019-07-10 | 2019-09-17 | 无锡航亚科技股份有限公司 | The special fixture of precision forged blade leading edge contour machining |
| CN111644791B (en) * | 2020-06-12 | 2022-07-12 | 中国航发航空科技股份有限公司 | Cooling welding device for thin-wall sheet metal part |
| CN112496469A (en) * | 2020-11-19 | 2021-03-16 | 中国航发沈阳黎明航空发动机有限责任公司 | Clamp mechanism for slowly feeding and grinding tenon tooth of turbine blade |
| CN112518513B (en) * | 2020-12-23 | 2021-11-09 | 贵阳航发精密铸造有限公司 | Device and method for machining symmetrical straight grooves on large-radius arc of turbine blade |
| CN113695557A (en) * | 2021-08-27 | 2021-11-26 | 中国航发沈阳黎明航空发动机有限责任公司 | Clamp for stator blade assembly edge plate machining and using method |
| CN114227536A (en) * | 2021-12-30 | 2022-03-25 | 无锡透平叶片有限公司 | Grinding fixture suitable for turbine multi-connected guide vane part assembly |
| CN115194499B (en) * | 2022-05-31 | 2023-12-22 | 中国第二重型机械集团德阳万航模锻有限责任公司 | Clamping tool, die forging and numerical control machining method for die forging |
| CN116604374B (en) * | 2023-07-20 | 2023-09-15 | 沈阳强航时代精密科技有限公司 | Clamp for positioning and compacting turbine guide blade of aero-engine |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP2145734A1 (en) * | 2008-07-17 | 2010-01-20 | Ansaldo Energia S.P.A. | Vice for withholding a turbine blade |
| FR2976203A1 (en) * | 2011-06-07 | 2012-12-14 | Snecma | Method for machining composite blade in aircraft industry, involves calculating difference between measured profile and predetermined theoretical profile, and machining faces of central portion of blade based on difference |
| CN103240617A (en) * | 2013-04-25 | 2013-08-14 | 哈尔滨汽轮机厂有限责任公司 | Guide blade positioning clamp |
| CN203918539U (en) * | 2014-01-30 | 2014-11-05 | 无锡透平叶片有限公司 | A kind of for processing the fixture of aviation thin wall vane pitch |
-
2014
- 2014-01-30 CN CN201410044262.8A patent/CN103878608B/en active Active
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP2145734A1 (en) * | 2008-07-17 | 2010-01-20 | Ansaldo Energia S.P.A. | Vice for withholding a turbine blade |
| FR2976203A1 (en) * | 2011-06-07 | 2012-12-14 | Snecma | Method for machining composite blade in aircraft industry, involves calculating difference between measured profile and predetermined theoretical profile, and machining faces of central portion of blade based on difference |
| CN103240617A (en) * | 2013-04-25 | 2013-08-14 | 哈尔滨汽轮机厂有限责任公司 | Guide blade positioning clamp |
| CN203918539U (en) * | 2014-01-30 | 2014-11-05 | 无锡透平叶片有限公司 | A kind of for processing the fixture of aviation thin wall vane pitch |
Also Published As
| Publication number | Publication date |
|---|---|
| CN103878608A (en) | 2014-06-25 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN103878608B (en) | Clamp used for processing aviation thin-wall blade pitch | |
| CN203918539U (en) | A kind of for processing the fixture of aviation thin wall vane pitch | |
| CN206883223U (en) | A kind of machining fixture for being easy to regulation | |
| CN204321698U (en) | A kind of jaw type self-centering clamping structure | |
| CN204545995U (en) | A kind of processing unit (plant) of novel Machining of Vortex Disk of Vortex Compressor | |
| CN206598088U (en) | A kind of drift cuts sanding apparatus | |
| CN203031655U (en) | Film delimiting machine structure | |
| CN205341604U (en) | Ni -mh power battery channelling machine | |
| CN203918553U (en) | A kind of sawing machine bar clamping device | |
| CN202877394U (en) | Fixing structure of upper mould and lower mould of mould | |
| CN203266193U (en) | Milling jig used for machining end faces of large wine bottle die blank | |
| CN102886714A (en) | Hub grinding device | |
| CN207139330U (en) | One kind production pump case boring and milling stationary fixture | |
| CN202388256U (en) | Clamp for calipers | |
| CN103264300A (en) | Fixture for milling small-end oblique planes of connecting rods | |
| CN203053387U (en) | Three-dimensional arc rod testing fixture | |
| CN103240629B (en) | For the fraise jig of the end face of machining large bottle die blank | |
| CN204035302U (en) | A kind of Furniture manufacturing is with cutting oblique pin mould | |
| CN206912252U (en) | It is a kind of to be used for the special framed of diamond tool bit hot pressed sintering | |
| CN102501090A (en) | Machining fixture device used for base seat part | |
| CN209632771U (en) | Fixture is used in a kind of grinding of bearing outer ring | |
| CN203751319U (en) | Clamping device of precision casting part pouring gate cutting machine | |
| CN203751341U (en) | Ball turning clamp | |
| CN203254196U (en) | Workpiece hold-down device with horizontal direction adjustable for lathe | |
| CN212169186U (en) | Herringbone frame forge piece raw blank distributing device based on numerical control sawing machine |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C06 | Publication | ||
| PB01 | Publication | ||
| C10 | Entry into substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant |