CN107805793A - A kind of turbine blade coating preparation facilities for intersecting clamp structure with bilateral - Google Patents
A kind of turbine blade coating preparation facilities for intersecting clamp structure with bilateral Download PDFInfo
- Publication number
- CN107805793A CN107805793A CN201710901332.0A CN201710901332A CN107805793A CN 107805793 A CN107805793 A CN 107805793A CN 201710901332 A CN201710901332 A CN 201710901332A CN 107805793 A CN107805793 A CN 107805793A
- Authority
- CN
- China
- Prior art keywords
- clamp structure
- tool disk
- electron beam
- bilateral
- turbine blade
- 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.)
- Pending
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Classifications
-
- C—CHEMISTRY; METALLURGY
- C23—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; CHEMICAL SURFACE TREATMENT; DIFFUSION TREATMENT OF METALLIC MATERIAL; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL; INHIBITING CORROSION OF METALLIC MATERIAL OR INCRUSTATION IN GENERAL
- C23C—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; SURFACE TREATMENT OF METALLIC MATERIAL BY DIFFUSION INTO THE SURFACE, BY CHEMICAL CONVERSION OR SUBSTITUTION; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL
- C23C14/00—Coating by vacuum evaporation, by sputtering or by ion implantation of the coating forming material
- C23C14/22—Coating by vacuum evaporation, by sputtering or by ion implantation of the coating forming material characterised by the process of coating
- C23C14/56—Apparatus specially adapted for continuous coating; Arrangements for maintaining the vacuum, e.g. vacuum locks
- C23C14/568—Transferring the substrates through a series of coating stations
-
- C—CHEMISTRY; METALLURGY
- C23—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; CHEMICAL SURFACE TREATMENT; DIFFUSION TREATMENT OF METALLIC MATERIAL; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL; INHIBITING CORROSION OF METALLIC MATERIAL OR INCRUSTATION IN GENERAL
- C23C—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; SURFACE TREATMENT OF METALLIC MATERIAL BY DIFFUSION INTO THE SURFACE, BY CHEMICAL CONVERSION OR SUBSTITUTION; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL
- C23C14/00—Coating by vacuum evaporation, by sputtering or by ion implantation of the coating forming material
- C23C14/22—Coating by vacuum evaporation, by sputtering or by ion implantation of the coating forming material characterised by the process of coating
- C23C14/24—Vacuum evaporation
- C23C14/28—Vacuum evaporation by wave energy or particle radiation
- C23C14/30—Vacuum evaporation by wave energy or particle radiation by electron bombardment
-
- C—CHEMISTRY; METALLURGY
- C23—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; CHEMICAL SURFACE TREATMENT; DIFFUSION TREATMENT OF METALLIC MATERIAL; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL; INHIBITING CORROSION OF METALLIC MATERIAL OR INCRUSTATION IN GENERAL
- C23C—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; SURFACE TREATMENT OF METALLIC MATERIAL BY DIFFUSION INTO THE SURFACE, BY CHEMICAL CONVERSION OR SUBSTITUTION; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL
- C23C14/00—Coating by vacuum evaporation, by sputtering or by ion implantation of the coating forming material
- C23C14/22—Coating by vacuum evaporation, by sputtering or by ion implantation of the coating forming material characterised by the process of coating
- C23C14/50—Substrate holders
- C23C14/505—Substrate holders for rotation of the substrates
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- Chemical & Material Sciences (AREA)
- Chemical Kinetics & Catalysis (AREA)
- Engineering & Computer Science (AREA)
- Materials Engineering (AREA)
- Mechanical Engineering (AREA)
- Metallurgy (AREA)
- Organic Chemistry (AREA)
- Health & Medical Sciences (AREA)
- Toxicology (AREA)
- Physical Vapour Deposition (AREA)
Abstract
The invention discloses a kind of turbine blade coating preparation facilities for intersecting clamp structure with bilateral：Including the load chamber interconnected and settling chamber, clamp structure is set in load chamber and the rotary shaft of clamp structure rotation is provided；Wherein clamp structure is extend into settling chamber, and rifle room is provided with above settling chamber, multiple electron beam guns are provided with rifle room, wherein the light beam of the first electron beam gun is penetrated on clamp structure, the light beam of the second electron beam gun is located on the material ingot immediately below clamp structure；The clamp structure includes the left tool disk interconnected and right tool disk, be provided between left tool disk and right tool disk it is multiple between the wrong rotation siphunculus set, be connected with frock box on rotation siphunculus；Left tool disk passes through frock bar and rotation axis connection.The device can be carried out 4 20 blade bilaterals and intersect installation, the processing efficiency of coating is greatly improved, reduce coating processing cost according to working-blade size and design coating area requirement.
Description
Technical field
The invention belongs to engine turbine working-blade manufacturing technology field；More particularly to one kind there is bilateral to intersect clamping
The turbine blade coating preparation facilities of structure.
Background technology
At present, because electro beam physics vapour deposition (abbreviation EB-PVD) has coating and substrate combinating strength height, can obtain
To the advantages that columanar structure, coating chemical composition are easy to accurate control, coating life is long, heterogenous hair is had been widely used for
The preparation processing of motivation turbo blade high-temperature protection coating, significantly improve the resistance to high temperature oxidation and corrosion resistance of turbo blade
Energy, heat-proof quality, extend engine operational life.
EB-PVD technologies are in depositing coating, and using an electron beam gun heated components, one evaporates material ingot electron beam gun,
Blade is placed in above material ingot, coating steam deposits to blade surface, forms typical columanar structure's structure.EB-PVD equipment
The structure of itself just determines that the width of the electronics light beams of heater blade is unsuitable excessive, and crossing conference causes the hot spoke that blade is subject to
Penetrate less, technological requirement can not be met.The width adjusting scope of electronics light beams is 10~200mm, can not further be increased
The width of electronics light beams 4.
At present, moving turbine blade is in EB-PVD equipment during applying coating, due to by electron beam scanning heated perimeter
Limitation, coating clamping uses unilateral clamping.According to the difference of blade dimensions, one side can be 2~10 with clamping, coating processing effect
Rate is low, high processing costs.
The content of the invention
The invention provides a kind of turbine blade coating preparation facilities for intersecting clamp structure with bilateral, the device can
According to working-blade size and design coating area requirement, carry out 4-20 part blades bilateral and intersect installation, painting is greatly improved
The processing efficiency of layer, reduce coating processing cost.
The technical scheme is that：A kind of turbine blade coating preparation facilities for intersecting clamp structure with bilateral：Bag
The load chamber interconnected and settling chamber are included, clamp structure is set in load chamber and the rotary shaft of clamp structure rotation is provided；Its
Middle clamp structure is extend into settling chamber, and rifle room is provided with above settling chamber, multiple electron beam guns are provided with rifle room, wherein
The light beam of first electron beam gun is penetrated on clamp structure, and the light beam of the second electron beam gun is located at the material ingot immediately below clamp structure
On；The clamp structure includes the left tool disk interconnected and right tool disk, is provided between left tool disk and right tool disk
The multiple wrong rotation siphunculus set, frock box is connected with rotation siphunculus；Left tool disk passes through frock bar and rotation axis connection.
Further, the features of the present invention also resides in：
Connected between wherein left tool disk and right tool disk by connecting rod, the both ends of connecting rod are consolidated by attaching nut
It is fixed.
Wherein left tool disk is fixedly connected by nut structure with frock bar.
Wherein the first electron beam gun and the second electron beam gun are arranged in the rifle room of diverse location.
The frock box that is connected in wherein left tool disk and there is the frock box connected in tool disk to be mutually staggered.
Wherein left tool disk and right tool disk are circular configuration.
Compared with prior art, the beneficial effects of the invention are as follows：The apparatus structure is simple, and accessory is less, is easy to blade production
The processing and dismounting of product, and the matched design of frock size can be carried out according to the size of blade；Clamp structure lifting simultaneously
The batch of preparation facilities, according to the size of the size of working-blade, it can will be less than 20 blade bilaterals and intersect installation, together
Shi Jinhang coatings are processed, and improve production efficiency.
Further, connecting rod and nut connect left tool disk and right tool disk, make left tool disk and right frock
Disk is rotated under the drive of frock bar simultaneously.
Further, the frock box in left tool disk and right tool disk is mutually staggered, in blade coatings coating procedure
Prevent blade from colliding with each other, influence to coat effect.
Brief description of the drawings
Fig. 1 is the structural representation of the present invention；
Fig. 2 is the structural representation of clamp structure in the present invention；
Fig. 3 is that the present invention clamps part distribution schematic diagram.
In figure：1 is rotary shaft；2 be load chamber；3 be rifle room；4 be the first electron beam；5 be the second electron beam；6 are
Blade；7 be clamp structure；8 be the second electron beam gun；9 be settling chamber；10 be material ingot；11 be the first electron beam gun；12 be frock
Bar；13 be rotation siphunculus；14 be attaching nut；15 be connecting rod；16 be nut structure；17 be frock box；18 be right tool disk；19
For left tool disk；20 be workpiece rotational trajectory；21 be frock box rotational trajectory.
Embodiment
Technical scheme is further illustrated with specific embodiment below in conjunction with the accompanying drawings.
The invention provides a kind of turbine blade coating preparation facilities for intersecting clamp structure with bilateral, as shown in figure 1,
Including load chamber 2, mud chamber 9 is connected with load chamber 2, and rotary shaft 1 is provided with load chamber 2, and clamping dress is connected with rotary shaft 1
7 are put, and clamping device 7 is stretched into mud chamber 9；The top of mud chamber 9 is provided with 2 rifle rooms 3, and the bottom of mud chamber 9 is set
There are multiple material ingots 10, material ingot 10 is located at the underface of blade clamped by clamping device 7；The is wherein provided with the rifle room 3 in left side
One electron beam gun 11, the first electron beam gun 11 launch the first electron beam 4, and the first electron beam 4 is the leaf that clamping device 7 clamps
Piece heats；The second electron beam gun 8 is provided with the rifle room on right side, the second electron beam gun 8 launches the second electron beam 5, the second electricity
Beamlet 5 heats for material ingot 10.
As shown in Fig. 2 clamping device 7 includes circular left tool disk 19 and right tool disk 18, left tool disk 19 and right work
Through hole is provided with sabot 18, and by setting connecting rod 15, and connecting rod in the relative through hole of left tool disk 19 and right tool disk 18
15 both ends are fastened using attaching nut 14, are fastenedly connected left tool disk 19 and right tool disk 18；Left tool disk 19 passes through spiral shell
Parent structure 16 is connected with frock bar 12, and frock bar 12 is connected in rotary shaft 1；Wherein left tool disk 19 and right tool disk 18 are submitted
Mistake is provided with multiple rotation siphunculus 13, and frock box 17 is provided with rotation siphunculus 13, is used to clamp blade in frock box 17.
As shown in figure 3, thick line circumference is the rotation siphunculus 13 installed in left tool disk 19 in figure, and pacify on rotation siphunculus 13
The frock box of dress, the rotation schematic diagram of blade, wherein frock box rotational trajectory 21 is in the outside of blade rotational trajectory 20；Hachure
For the rotation siphunculus 13 installed in right tool disk 18, and frock box, the rotation schematic diagram of blade installed on rotation siphunculus 13, its
Middle frock box rotational trajectory 21 is in the outside of blade rotational trajectory 20.Rotation siphunculus 13 on left rotary table 19 and Yougong rotating disk 18
In rotary course, the phenomenon collided with mutually will not occur for the blade clamped by it, while can also be according to the chi of left and right blade
Very little size, the quantity of adjustment rotation siphunculus 13.
The present invention application method be：Moving turbine blade 6 and clamp structure 7 are cleaned up first by acetone,
Then blade 6 is placed on clamp structure 7, and frock bar 12 is connected in rotary shaft 1, then start rotary shaft 1.So
Load chamber 2 and settling chamber 9 are vacuumized afterwards, clamp structure 7 is sent into mud chamber 9 by rotary shaft 1, and vacuum is small in mud chamber 9
In 5-10-3During Pa, the first electron beam gun 11 and the second electron beam gun 8 heat to blade 6 and material ingot 10 respectively, start to deposit
Coating；Coating complete after, clamp structure 7 is exited to load chamber 2, when blade be cooled under vacuum conditions 300 DEG C with
Under, air is filled with into load chamber, then takes out moving turbine blade 6 and clamp structure 7.
The moving turbine blade coating coated using the device of the present invention, is measured to its coating layer thickness, for analyzing
The uniformity of coating layer thickness, measured coating layer thickness can meet 80-120 μm of design requirement.
Claims (6)
1. a kind of turbine blade coating preparation facilities for intersecting clamp structure with bilateral, it is characterised in that including interconnecting
Load chamber (2) and settling chamber (9), clamp structure (7) is set in load chamber (2) and the rotation that clamp structure (7) rotates is provided
Axle (1)；Wherein clamp structure (7) is extend into settling chamber (9), rifle room (3) is provided with above settling chamber (9), in rifle room (3)
Multiple electron beam guns are provided with, wherein the light beam of the first electron beam gun (11) is penetrated on clamp structure (7), the second electron beam gun
(8) light beam is located on the material ingot (10) immediately below clamp structure (7)；
The clamp structure (7) includes the left tool disk (19) and right tool disk (18) interconnected, left tool disk (19) and the right side
The multiple wrong rotation siphunculus (13) set are provided between tool disk (18), rotation siphunculus is connected with frock box on (13)
(17)；Left tool disk (19) is connected by frock bar (12) with rotary shaft (1).
2. the turbine blade coating preparation facilities according to claim 1 for intersecting clamp structure with bilateral, its feature exist
In being connected between the left tool disk (6) and right tool disk (9) by connecting rod (4), the both ends of connecting rod (4) pass through connection
Nut (3) is fixed.
3. the turbine blade coating preparation facilities according to claim 1 for intersecting clamp structure with bilateral, its feature exist
In the left tool disk (19) is fixedly connected by nut structure (16) with frock bar (12).
4. the turbine blade coating preparation facilities according to claim 1 for intersecting clamp structure with bilateral, its feature exist
In first electron beam gun (11) and the second electron beam gun (8) are arranged in the rifle room of diverse location.
5. the turbine blade coating preparation facilities according to claim 1 for intersecting clamp structure with bilateral, its feature exist
In, the frock box that is connected on the left tool disk (19) and there is the frock box connected in tool disk (18) to be mutually staggered.
6. the turbine blade coating preparation facilities according to claim 1 for intersecting clamp structure with bilateral, its feature exist
In the left tool disk (19) and right tool disk (18) are circular configuration.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710901332.0A CN107805793A (en) | 2017-09-28 | 2017-09-28 | A kind of turbine blade coating preparation facilities for intersecting clamp structure with bilateral |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710901332.0A CN107805793A (en) | 2017-09-28 | 2017-09-28 | A kind of turbine blade coating preparation facilities for intersecting clamp structure with bilateral |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN107805793A true CN107805793A (en) | 2018-03-16 |
Family
ID=61584682
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201710901332.0A Pending CN107805793A (en) | 2017-09-28 | 2017-09-28 | A kind of turbine blade coating preparation facilities for intersecting clamp structure with bilateral |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN107805793A (en) |
Citations (11)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3993018A (en) * | 1975-11-12 | 1976-11-23 | International Business Machines Corporation | Centrifugal support for workpieces |
| JPH1036966A (en) * | 1996-04-22 | 1998-02-10 | Sekisui Chem Co Ltd | Production of ceramic coating cutting tool |
| CA2388293A1 (en) * | 2002-05-30 | 2003-11-30 | Revision Eyewear Inc. | Eyewear and system |
| CN101255515A (en) * | 2008-04-08 | 2008-09-03 | 北京航空航天大学 | Pyrogenic oxidation resistant nickel-aluminium-dysprosium coat bond material and preparation of hot screening coating |
| CN101269557A (en) * | 2008-05-08 | 2008-09-24 | 北京航空航天大学 | Composite binding course material and method for producing composite binding course by using combination of plating and electro beam physics vapour deposition |
| CN101845609A (en) * | 2010-05-17 | 2010-09-29 | 北京航空航天大学 | Method for preparing diffusion-resistant coating for single-crystal high-temperature alloy |
| US20100272894A1 (en) * | 2005-07-12 | 2010-10-28 | David Sharp | Method for simultaneously coating a plurality of workpieces |
| CN102676973A (en) * | 2011-03-17 | 2012-09-19 | 苏舍美特科公司 | Component manipulator for dynamic positioning of a substrate, coating method and use of a component manipulator |
| CN202543312U (en) * | 2012-04-16 | 2012-11-21 | 上海金科纳米涂层技术有限公司 | Multi-drum combined type sleeving jig device |
| CN203498465U (en) * | 2013-10-19 | 2014-03-26 | 沈阳黎明航空发动机(集团)有限责任公司 | Clamp for local coating of turbine blade |
| CN108950509A (en) * | 2018-08-27 | 2018-12-07 | 成都工业职业技术学院 | A kind of planetary three-stage cylindrical gear insert clamp device |
-
2017
- 2017-09-28 CN CN201710901332.0A patent/CN107805793A/en active Pending
Patent Citations (11)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3993018A (en) * | 1975-11-12 | 1976-11-23 | International Business Machines Corporation | Centrifugal support for workpieces |
| JPH1036966A (en) * | 1996-04-22 | 1998-02-10 | Sekisui Chem Co Ltd | Production of ceramic coating cutting tool |
| CA2388293A1 (en) * | 2002-05-30 | 2003-11-30 | Revision Eyewear Inc. | Eyewear and system |
| US20100272894A1 (en) * | 2005-07-12 | 2010-10-28 | David Sharp | Method for simultaneously coating a plurality of workpieces |
| CN101255515A (en) * | 2008-04-08 | 2008-09-03 | 北京航空航天大学 | Pyrogenic oxidation resistant nickel-aluminium-dysprosium coat bond material and preparation of hot screening coating |
| CN101269557A (en) * | 2008-05-08 | 2008-09-24 | 北京航空航天大学 | Composite binding course material and method for producing composite binding course by using combination of plating and electro beam physics vapour deposition |
| CN101845609A (en) * | 2010-05-17 | 2010-09-29 | 北京航空航天大学 | Method for preparing diffusion-resistant coating for single-crystal high-temperature alloy |
| CN102676973A (en) * | 2011-03-17 | 2012-09-19 | 苏舍美特科公司 | Component manipulator for dynamic positioning of a substrate, coating method and use of a component manipulator |
| CN202543312U (en) * | 2012-04-16 | 2012-11-21 | 上海金科纳米涂层技术有限公司 | Multi-drum combined type sleeving jig device |
| CN203498465U (en) * | 2013-10-19 | 2014-03-26 | 沈阳黎明航空发动机(集团)有限责任公司 | Clamp for local coating of turbine blade |
| CN108950509A (en) * | 2018-08-27 | 2018-12-07 | 成都工业职业技术学院 | A kind of planetary three-stage cylindrical gear insert clamp device |
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| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| RJ01 | Rejection of invention patent application after publication |
Application publication date: 20180316 |
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| RJ01 | Rejection of invention patent application after publication |