CN106756818A - A kind of protection device and method for turborotor variable-angle applying coating - Google Patents
A kind of protection device and method for turborotor variable-angle applying coating Download PDFInfo
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- CN106756818A CN106756818A CN201611081899.XA CN201611081899A CN106756818A CN 106756818 A CN106756818 A CN 106756818A CN 201611081899 A CN201611081899 A CN 201611081899A CN 106756818 A CN106756818 A CN 106756818A
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- China
- Prior art keywords
- protecting box
- turborotor
- curtain plate
- inner platform
- clip
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Classifications
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- 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
- C23C14/32—Vacuum evaporation by explosion; by evaporation and subsequent ionisation of the vapours, e.g. ion-plating
- C23C14/325—Electric arc evaporation
-
- 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
- C23C14/04—Coating on selected surface areas, e.g. using masks
- C23C14/042—Coating on selected surface areas, e.g. using masks using masks
Abstract
The invention belongs to engine turbine guide vane manufacture field, and in particular to a kind of protection device and method for turborotor variable-angle applying coating.Protection device; including upper clip, hook, lower clip, lower suspension hook, it is enclosed within turborotor inner platform and is used to the inner platform protecting box for covering Inner listriums and is enclosed within turborotor curtain plate be used to cover the curtain plate protecting box of curtain plate; the two ends of upper clip and lower clip bare terminal end accommodate inner platform protecting box and curtain plate protecting box respectively, and upper clip and lower clip can opposite inner edge plate protecting box and curtain plate protecting box can rotate；After upper clip hangs up the assembly of inner platform protecting box, curtain plate protecting box and turborotor, the turborotor throat portion potential energy of turborotor is enough just to the cathode arc source of multi-arc ion plating equipment.The present invention efficiently solves the problems, such as that the coating layer thickness of guide vane venturi shaded areas is unable to reach design requirement.
Description
【Technical field】
The invention belongs to engine turbine guide vane manufacture field, and in particular to one kind is variable for turborotor
The protection device and method of angle applying coating.
【Background technology】
Multi sphere ion plating technology is using a kind of ion plating technique in cathodic arc evaporation source, for turbo blade coating
The technique such as MCrAlY and compressor blade coating TiN coatings.Fig. 1 is multi-arc ion plating equipment structural map, cathode arc source (target in figure
Material) 101, argon inlet mouthfuls 102, air inlet 103, vacuum system 104, blade 105, grid bias power supply 106, suspension hook 107.
In depositing coating, the operation principle of itself determines that coating deposition process has physics to multi sphere ion plating technology
Masking phenomenon, some shaded areas cannot deposit to coating.And for duplex guide vane, the venturi position in the middle of blade
Depositing coating is also required that, how effectively to control the coating layer thickness of venturi shaded areas to perplex the trial-production of turborotor always
And production.
Found during patent retrieval, a kind of turborotor coating preparation protecting tool set-up, the patent No.
ZL201420107224.8, inventor：Wang Ruijun.Protecting tool set-up is by frock supporting rod, upper limb board clamp, lower edge board clamp group
Into；Turbo blade is arranged in the middle of upper limb fixture and lower edge board clamp.A kind of fixture for turbo blade topical application coating,
The patent No.：ZL201320650842.2, inventor：Cheng Yuxian.The technical scheme of the utility model：The fixture include mandrel,
Two disks, blade furniture box and baffle plates, described two disks be arranged in parallel, and the mandrel blade fixture box is fixed on affiliated circle
On disk, turbo blade is arranged on the blade fixture box, and the baffle plate blocks the non-coated areas of the turbo blade, described
Baffle plate is brought into close contact with the turbo blade type face, and the baffle edge carries out chamfered.
However, above-mentioned two invention and other invention it cannot be guaranteed that the coating layer thickness at the venturi position of turborotor and
Uniformity.
【The content of the invention】
To solve problems of the prior art, can for turborotor it is an object of the invention to provide one kind
The protection device and method of varied angle applying coating, the coating layer thickness for efficiently solving guide vane venturi shaded areas cannot reach
To the problem of design requirement.
The purpose of the present invention is realized by following technical solution：
A kind of protection device for turborotor variable-angle applying coating, including upper clip, hook, lower folder
Sub, lower suspension hook, be enclosed within turborotor inner platform be used for cover Inner listriums inner platform protecting box and be enclosed within turbine guiding
It is used to cover the curtain plate protecting box of curtain plate on blade curtain plate, is equipped with inner platform protecting box and curtain plate protecting box
Lower two blessings hole, the center of gravity after the assembling of inner platform protecting box, curtain plate protecting box and turborotor is in four folders
Hold the clamping hole difference of the cornerwise position of intersecting point of quadrangle that hole is summit, inner platform protecting box and curtain plate protecting box top
Positioned at the center of gravity top symmetrical both sides of sustained height, the clamping hole difference position of inner platform protecting box and curtain plate protecting box bottom
In the center of gravity lower section symmetrical both sides of sustained height；
The two ends of upper clip bare terminal end are inserted in the clamping hole on inner platform protecting box and curtain plate protecting box top respectively, and
Upper clip can be relatively rotated with inner platform protecting box and curtain plate protecting box, and hook connects with upper clip top center
Connect；
The two ends of lower clip bare terminal end are inserted in the clamping hole of inner platform protecting box and curtain plate protecting box bottom respectively, and
Lower clip can be relatively rotated with inner platform protecting box and curtain plate protecting box, and lower suspension hook connects with lower clip top center
Connect；
After upper clip hangs up the assembly of inner platform protecting box, curtain plate protecting box and turborotor, turbine
The turborotor throat portion potential energy of guide vane is enough just to the cathode arc source of multi-arc ion plating equipment.
The upper clip and lower clip are the rectangle mount structure of one end open, including cross bar, and the two ends of cross bar connect respectively
Be connected to montant, the free end of montant is the bare terminal end of upper clip and lower clip, the free end of montant is provided with hyphen bar, upper clip and
Lower clip is inserted in the clamping hole in inner platform protecting box and curtain plate protecting box by hyphen bar.
The middle part of the hook and lower suspension hook respectively with upper clip and the cross bar of lower clip is connected.
The inner platform protecting box includes the first side plate, and the two blessing holes up and down in inner platform protecting box are opened in first
On side plate, the surface of the first side plate is provided with the first side wall that a loop-shaped is adapted with turborotor inner platform profile,
When in use, the inner platform of turborotor is arranged in the cavity formed by the first side plate and the first side wall, and inner platform is protected
It is additionally provided with and can be offseted for the first support frame for supporting inner platform with inner platform outer arcuate face on shield box.
The curtain plate protecting box includes the second side plate, and the two blessing holes up and down in curtain plate protecting box are opened in second
On side plate, the surface of the second side plate is provided with the second sidewall that a loop-shaped is adapted with turborotor curtain plate profile,
When in use, the curtain plate of turborotor is arranged in the cavity formed by the second side plate and second sidewall, and curtain plate is protected
It is additionally provided with and can be offseted for the second support frame for supporting curtain plate with curtain plate outer arcuate face on shield box.
A kind of guard method for turborotor variable-angle applying coating, comprises the following steps：
Step one, inner platform protecting box and curtain plate protecting box are respectively fitted over the inner platform and outer rim of turborotor
On plate；
Step 2, then inner platform protecting box and curtain plate protecting box top are inserted respectively with the two ends of clip bare terminal end
In clamping hole, then the clamping hole for inserting inner platform protecting box and curtain plate protecting box bottom respectively with the two ends of lower clip bare terminal end
It is interior；
Step 3, repeat step one to step 2 assembles some groups by upper clip, hook, inner platform protecting box, turbine
The assembly of guide vane, curtain plate protecting box, lower clip and small suspension hook assembling；
Step 4, is stringed together each assembly hook by hook and lower suspension hook, then is deposited in multi-arc ion plating equipment
Coating.
In the step 4, when upper clip is by the assembling of inner platform protecting box, curtain plate protecting box and turborotor
After body is hung up, the turborotor throat portion potential energy of turborotor is enough just to the cathode arc source of multi-arc ion plating equipment.
In the step 4, often string has individual assembly, and string is hung in the circumferencial direction of multi-arc ion plating equipment planet rotating shaft.
Compared with prior art, the present invention has the advantages that：
Protection device for turborotor variable-angle applying coating of the invention is enclosed within turbine and leads by setting
To on vane inside edge plate be used for cover Inner listriums inner platform protecting box and be enclosed within turborotor curtain plate be used for cover
Upper and lower two blessings hole, inner platform are equipped with the curtain plate protecting box of curtain plate, inner platform protecting box and curtain plate protecting box
It is the quadrangle pair on summit that center of gravity after the assembling of protecting box, curtain plate protecting box and turborotor is in four clamping holes
It is same that the clamping hole on the position of intersecting point of linea angulata, inner platform protecting box and curtain plate protecting box top is located at center of gravity top respectively
The clamping hole of high degree of symmetry both sides, inner platform protecting box and curtain plate protecting box bottom is located at the same height in center of gravity lower section respectively
Spend symmetrical both sides；The clamping hole on inner platform protecting box and curtain plate protecting box top is inserted respectively in the two ends of upper clip bare terminal end
It is interior, and upper clip can relatively rotate with inner platform protecting box and curtain plate protecting box, hook and upper clip top center position
Put connection；The two ends of lower clip bare terminal end are inserted in the clamping hole of inner platform protecting box and curtain plate protecting box bottom respectively, and
Lower clip can be relatively rotated with inner platform protecting box and curtain plate protecting box, and lower suspension hook connects with lower clip top center
Connect, therefore, the angle of turborotor can be adjusted by the position for adjusting clamping hole；When upper clip protects inner platform
After the assembly of box, curtain plate protecting box and turborotor is hung up, the turborotor throat portion of turborotor
Potential energy is enough just to the cathode arc source of multi-arc ion plating equipment；When turborotor in multi-arc ion plating equipment applying coating
When, first inner platform protecting box and curtain plate protecting box are respectively fitted on the inner platform and curtain plate of turborotor, then use
The two ends of upper clip bare terminal end are inserted in the clamping hole on inner platform protecting box and curtain plate protecting box top respectively, then use lower clip
The two ends of bare terminal end are inserted in the clamping hole of inner platform protecting box and curtain plate protecting box bottom respectively, make clip, hook,
Inner platform protecting box, turborotor, curtain plate protecting box, lower clip and small suspension hook are assembled into assembly, and each assembly leads to
Hook is stringed together according to this to cross hook and lower suspension hook, depositing coating in multi-arc ion plating equipment is reinstalled, due to inner platform protecting box
With the bridging effect of curtain plate protecting box, effective screening can be carried out to non-coating area to surface of inner platform and curtain plate etc.
Protection is covered, and turborotor throat portion potential energy is enough effectively coated；Due to being provided with upper and lower clip and upper and lower suspension hook, because
This device of the invention disposably loads multigroup assembly when enabling to the depositing coating in multi-arc ion plating equipment, carries significantly
Operating efficiency high；Therefore apparatus of the present invention simple structure, accessory is less, it is easy to Product processing and dismounting, and can be according to leading
The matched design of frock size is carried out to blade dimensions.
Further, inner platform protecting box of the invention include the first side plate, in inner platform protecting box up and down two plus
Hold hole to be opened on the first side plate, the surface of the first side plate is provided with a loop-shaped and is mutually fitted with turborotor inner platform profile
The first side wall matched somebody with somebody, when in use, the inner platform of turborotor is arranged on the chamber formed by the first side plate and the first side wall
In vivo, it is additionally provided with to be offseted with inner platform outer arcuate face in inner platform protecting box and first is supported for support inner platform
Frame, effective masking has been carried out by the first side plate and the first side wall to the non-coating area of inner platform, while passing through first
The supporting role of support so that stabilization is contacted between inner platform protecting box and inner platform, after upper and lower clip is clamped, inner platform is protected
Shield box, turborotor and curtain plate protecting box are by stable holding, it is ensured that the safety of operation process.
Further, curtain plate protecting box of the invention include the second side plate, in curtain plate protecting box up and down two plus
Hold hole to be opened on the second side plate, the surface of the second side plate is provided with a loop-shaped and is mutually fitted with turborotor curtain plate profile
The second sidewall matched somebody with somebody, when in use, the curtain plate of turborotor is arranged on the chamber formed by the second side plate and second sidewall
In vivo, it is additionally provided with to be offseted with curtain plate outer arcuate face in curtain plate protecting box and second is supported for support curtain plate
Frame, effective masking has been carried out by the second side plate and second sidewall to the non-coating area of curtain plate, while passing through second
The supporting role of support so that stabilization is contacted between curtain plate protecting box and curtain plate, after upper and lower clip is clamped, inner platform is protected
Shield box, turborotor and curtain plate protecting box are by stable holding, it is ensured that the safety of operation process.
【Brief description of the drawings】
Fig. 1 is multi-arc ion plating equipment structural map；
Fig. 2 (a) is front view when apparatus of the present invention are assembled with turborotor, and Fig. 2 (b) is apparatus of the present invention and whirlpool
Side view when wheel guide vane is assembled；
Fig. 3 (a) is the front view of apparatus of the present invention clip and suspension hook, and Fig. 3 (b) is the side of apparatus of the present invention clip and suspension hook
View；
Fig. 4 (a) is the top view of apparatus of the present invention inner platform protecting box, and Fig. 4 (b) is apparatus of the present invention inner platform protecting box
Side view；
Fig. 5 (a) is the top view of apparatus of the present invention curtain plate protecting box, and Fig. 5 (b) is apparatus of the present invention curtain plate protecting box
Side view；
Fig. 6 is turborotor coat thickness detection position schematic diagram.
Wherein, 101- markings arc source, 102- argon gas imports, 103- air intlets, 104- vacuum systems, 105- shells,
106- grid bias power supplies, 107- planet rotating shafts, the upper clips of 1-, 1-1- cross bars, 1-2- montants, 1-3- hyphen bars, 2- hooks, in 3-
Listrium protecting box, clamps hole on 3-1- first, first time clamping hole of 3-2-, the side plates of 3-3- first, 3-4- the first side walls, 3-5- the
One support frame, 4- curtain plate protecting box clamps hole on 4-1- second, second time clamping hole of 4-2-, the side plates of 4-3- second, 4-4- the
Two side walls, the support frames of 4-5- second, 5- turborotors, 5-1- inner platforms, 5-2- curtain plates, 6- turborotor venturis
Position, clip under 7-, suspension hook under 8-, 9- turborotors hanging angle, 10- assemblies, the 11- Left-wing Federations, 12- is right, 13- detections
Section.
【Specific embodiment】
Come that the present invention is further illustrated below in conjunction with the accompanying drawings.
As shown in figures 1 to 6, a kind of protection device bag for turborotor variable-angle applying coating of the invention
Include clip 1, hook 2, lower clip 7, lower suspension hook 8, be enclosed within the inner platform of turborotor 5 be used for cover the interior of Inner listriums
Listrium protecting box 3 is protected with the curtain plate protecting box 4 for covering curtain plate, inner platform is enclosed within the curtain plate of turborotor 5
Upper and lower two blessings hole, inner platform protecting box 3, curtain plate protecting box 4 and turbine are equipped with shield box 3 and curtain plate protecting box 4
Center of gravity after guide vane 5 is assembled is in the cornerwise position of intersecting point of quadrangle formed as summit with four clamping holes, inner edge
The clamping hole on plate protecting box 3 and the top of curtain plate protecting box 4 is located at the center of gravity top symmetrical both sides of sustained height, inner edge respectively
The clamping hole of plate protecting box 3 and the bottom of curtain plate protecting box 4 is located at the center of gravity lower section symmetrical both sides of sustained height respectively；
As shown in Fig. 3 (a) and Fig. 3 (b), upper clip 1 and lower clip 7 are the rectangle mount structure of one end open, including horizontal stroke
The two ends of bar 1-1, cross bar 1-1 are connected to montant 1-2, and the free end of montant 1-2 is the clamping of upper clip 1 and lower clip 7
End, the free end of montant 1-2 is provided with hyphen bar 1-3, and upper clip 1 and lower clip 7 insert inner platform protecting box by hyphen bar 1-3
3 and curtain plate protecting box 4 on clamping hole in, hook 2 and lower suspension hook 8 respectively with the cross bar of upper clip 1 and lower clip 7 in
Portion connects；
As shown in Fig. 4 (a) and Fig. 4 (b), inner platform protecting box 3 includes the first side plate 3-3, upper in inner platform protecting box 3
Lower two accommodate hole (3-1,3-2) and are opened on the first side plate 3-3, and the surface of the first side plate 3-3 is provided with a loop-shaped and whirlpool
The first side wall 3-4 that the wheel inner platform profile of guide vane 5 is adapted, when in use, the inner platform of turborotor 5 is arranged on
In the cavity formed by the first side plate 3-3 and the first side wall 3-4, being additionally provided with inner platform protecting box 3 can be with inner platform outside
Arcwall face offsets for the first support frame 3-5 for supporting inner platform；
As shown in Fig. 5 (a) and Fig. 5 (b), curtain plate protecting box 4 includes the second side plate 4-3, upper in curtain plate protecting box 4
Lower two accommodate hole (4-1,4-2) and are opened on the second side plate 4-3, and the surface of the second side plate 4-3 is provided with a loop-shaped and whirlpool
The second sidewall 4-4 that the wheel curtain plate profile of guide vane 5 is adapted, when in use, the curtain plate of turborotor 5 is arranged on
In the cavity formed by the second side plate 4-3 and second sidewall 4-4, being additionally provided with curtain plate protecting box 4 can be with curtain plate outside
Arcwall face offsets for the second support frame 4-5 for supporting curtain plate；
As shown in Fig. 2 (a) to Fig. 5 (b), the hyphen bar 1-3 of the both sides of upper clip 1 inserts inner platform protecting box 3 and outer respectively
In the clamping hole (3-1,4-1) on the top of listrium protecting box 4, and upper clip 1 and inner platform protecting box 3 and the energy of curtain plate protecting box 4
It is enough to relatively rotate；The hyphen bar 1-3 of the lower both sides of clip 7 inserts the folder of inner platform protecting box 3 and the bottom of curtain plate protecting box 4 respectively
Hold in hole (3-2,4-2), and lower clip 7 can be relatively rotated with inner platform protecting box 3 and curtain plate protecting box 4；
After upper clip 1 hangs up the assembly of inner platform protecting box 3, curtain plate protecting box 4 and turborotor 5,
The turborotor venturi position 6 of turborotor 5 can just to the cathode arc source 101 of multi-arc ion plating equipment.
The angle that protection device of the invention can hang angle 9 by adjusting turborotor ensures turborotor
The coating layer thickness of venturi position 6 and uniformity meet design requirement, and last hook 1 is connected with the planet rotating shaft 107 in Fig. 1.This
The protection device of invention is connected by lower suspension hook 8 when device interior is hung with the hanging that carries out of another protection device, is formed
1-5 layers of leaf blade hanging, while being gone here and there in equipment circumferencial direction hanging 12.
As shown in Fig. 2 (a) and Fig. 2 (b), protection device of the invention is connected to fix by clip with the hole in protecting box
Good turborotor, then hung in the planet rotating shaft of equipment frock by the suspension hook on clip, it is achieved thereby that turbine is led
To ensureing angularly to carry out the motion mode that rotation adds revolution during blade applying coating；The protection device applying coating
Angle can be adjusted by bore position in protecting box, how effectively to control the painting at the venturi position in the middle of turborotor
Thickness degree and uniformity, need angle of the turborotor during applying coating to ensure；The protection device passes through physics
The masking internal curtain plate of principle is protected, and the motion mode of revolution is added using the applying coating variable-angle of the device and rotation
Ensure that and effectively coated in the whole water passage surface of turborotor, especially ensure that the venturi position of turborotor
Coating layer thickness and uniformity.
Protection device of the invention compared with prior art, with advantages below：
(1) the protection device simple structure, accessory is less, it is easy to Product processing and dismounting, and can be according to guide vane
Size carries out the matched design of frock size；
(2) protection device can effectively ensure that the whole water passage surface of turborotor is effectively coated, and especially ensure
The coating layer thickness and uniformity at the venturi position of turborotor, while can also reach preventing the masking of non-coating area
Shield.
When using multi-arc ion coating deposition technique in engine turbine guide vane surface metallization coating, using this
The protection device of turborotor variable-angle applying coating can be carried out effectively in the whole water passage surface of turborotor
Coating, especially ensure that the coating layer thickness and uniformity at the venturi position of turborotor, and have to non-coating area
Effect protection.
The present invention is, by analyzing the design requirement of guide vane profile characteristics and whole water passage surface applying coating, and to tie
The operation principle of multi-arc ion plating equipment is closed, design obtains a kind of protection for turborotor variable-angle applying coating
Device, the device can design coating needs according to guide vane, carry out the adjustment of angle, and the coating of final coating meets design
It is required that.
Embodiment
By comprising the concrete steps that for the guard method of protection device of the invention：
Step 1, cleaning：Cleaning agent is used acetone as, turborotor and frock is cleaned up, prepare clamping,
Cleaning is to prevent part to be contaminated, influenceing coating binding force；
Step 2, clamping, specific steps include：Step 2.1, inner platform protecting box 3 and curtain plate protecting box 4 are covered respectively
On the inner platform and curtain plate of turborotor 5；Step 2.2, then inner edge is inserted respectively with the two ends of the bare terminal end of clip 1
In the clamping hole on plate protecting box 3 and the top of curtain plate protecting box 4, then inner platform is inserted respectively with the two ends of the bare terminal end of lower clip 7
In the clamping hole of protecting box 3 and the bottom of curtain plate protecting box 4；Step 2.3, repeat step 2.1 to step 2.1 assemble some groups by
8 groups of upper clip 1, hook 2, inner platform protecting box 3, turborotor 5, curtain plate protecting box 4, lower clip 7 and small suspension hook
The assembly 10 of dress；
Step 3, applying coating：The detailed process of the applying coating is：
Shove charge：By turborotor and frock shove charge, the hook of each assembly 10 is strung by hook 2 and lower suspension hook 8
Come, often string has 1-5 assembly 10, gone here and there in the circumferencial direction hanging 12 of multi-arc ion plating equipment planet rotating shaft, then hang
Multi-arc ion coating is on the hook of equipment, then adjusts angle, makes the turborotor venturi position 6 of turborotor 5
Can just to the cathode arc source 101 of multi-arc ion plating equipment, being then turned on tumbler carries out depositing coating, checks whether rotation
Normally, suspension member (suspension member is made up of turborotor and frock) can not touch furnace wall and striking pin；
Vacuumize：6.7 × 10 are evacuated to settling chamber-2During Pa, begin to warm up, when temperature is setting value stabilization 5 minutes
Afterwards, aura cleaning, Bombardment and cleaning are carried out；
Depositing coating：Bias：(100~300) ± 10V, electric current：95 ± 5A, sedimentation time 15h+30 '；
Cooling, less than 100 DEG C are as cold as by part vacuum, to being filled with air in vacuum drying oven, to environment blade balance after, beat
Blow-on door takes out turborotor and frock, lays down frock, and obtaining the whole water passage surface of turborotor has the coating to carry out
Effectively coating, especially ensure that the coating layer thickness and uniformity at the venturi position of turborotor, and non-coating area is entered
Row effectively protection.
Coat thickness detection section is the detection sectional plane 13 shown in Fig. 6 dotted lines, every a segment distance in detection sectional plane
As coat thickness detection point, through measurement, the thickness and uniform sexual satisfaction design requirement (30~100 μ of the present embodiment gained coating
M), specific data are shown in Table 1, and table 1 is turborotor coating thickness measurement result.
Table 1
| Left-wing Federation's test point | Left-wing Federation's coating layer thickness/μm | Right joint inspection measuring point | Right coating layer thickness/μm |
| A1 | 37.5 | B1 | 43.7 |
| A2 | 43.5 | B2 | 43.7 |
| A3 | 46.8 | B3 | 53.1 |
| A4 | 50 | B4 | 53.1 |
| A5 | 31.3 | B5 | 34.3 |
| A6 | 31.3 | B6 | 34.3 |
| A7 | 31.3 | B7 | 31.3 |
| A8 | 31.3 | B8 | 31.3 |
| A9 | 31.3 | B9 | 31.3 |
| A10 | 62.5 | B10 | 34.3 |
| A01 | 27.5 | B11 | 53.1 |
| A02 | 40.6 | B12 | 53.1 |
| A03 | 46.8 | B01 | 46.8 |
| A04 | 50 | B02 | 37.5 |
| A05 | 50 | B03 | 46.8 |
| A06 | 56.2 | B04 | 53.1 |
| A07 | 62.5 | B05 | 53.1 |
| A08 | 62.5 | B06 | 62.5 |
| A09 | 34.3 | B07 | 46.8 |
| A10 | 40.6 | B08 | 46.8 |
| A011 | 40.6 | ||
| A012 | 43.7 |
Claims (8)
1. a kind of protection device for turborotor variable-angle applying coating, it is characterised in that including upper clip
(1), hook (2), lower clip (7), lower suspension hook (8), be enclosed within the inner platform of turborotor (5) (5-1) be used for cover
The inner platform protecting box (3) of Inner listriums (5-1) and be enclosed within the curtain plate of turborotor (5) (5-2) be used for cover outer rim
Upper and lower two blessings are equipped with the curtain plate protecting box (4) of plate (5-2), inner platform protecting box (3) and curtain plate protecting box (4)
Hole, the center of gravity after the assembling of inner platform protecting box (3), curtain plate protecting box (4) and turborotor (5) is in four clampings
Hole is the folder of the cornerwise position of intersecting point of quadrangle that summit is formed, inner platform protecting box (3) and curtain plate protecting box (4) top
Hold hole and be located at the center of gravity top symmetrical both sides of sustained height, inner platform protecting box (3) and curtain plate protecting box (4) bottom respectively
Clamping hole be located at center of gravity lower section sustained height symmetrical both sides respectively；
The clamping hole on inner platform protecting box (3) and curtain plate protecting box (4) top is inserted respectively in the two ends of upper clip (1) bare terminal end
It is interior, and upper clip (1) can relatively rotate with inner platform protecting box (3) and curtain plate protecting box (4), hook (2) and upper folder
Sub (1) top center connection；
The clamping hole of inner platform protecting box (3) and curtain plate protecting box (4) bottom is inserted respectively in the two ends of lower clip (7) bare terminal end
It is interior, and lower clip (7) and inner platform protecting box (3 and curtain plate protecting box (4) can relatively rotate, lower suspension hook (8) and lower clip
(7) top center connection；
When upper clip (1) hangs up the assembly of inner platform protecting box (3), curtain plate protecting box (4) and turborotor (5)
Afterwards, the turborotor venturi position (6) of turborotor (5) can just to the cathode arc source of multi-arc ion plating equipment
(101)。
2. a kind of protection device for turborotor variable-angle applying coating according to claim 1, it is special
Levy and be, the upper clip (1) and lower clip (7) are the rectangle mount structure of one end open, including cross bar (1-1), cross bar (1-
1) two ends are connected to montant (1-2), and the free end of montant (1-2) is the bare terminal end of upper clip (1) and lower clip (7),
The free end of montant (1-2) is provided with hyphen bar (1-3), and upper clip (1) and lower clip (7) insert inner edge by hyphen bar (1-3)
In clamping hole in plate protecting box (3) and curtain plate protecting box (4).
3. a kind of protection device for turborotor variable-angle applying coating according to claim 2, it is special
Levy and be, the middle part of the hook (2) and lower suspension hook (8) respectively with upper clip (1) and the cross bar of lower clip (7) is connected.
4. a kind of protection device for turborotor variable-angle applying coating according to claim 1, it is special
Levy and be, the inner platform protecting box (3) includes the first side plate (3-3), the two blessing holes up and down in inner platform protecting box (3)
It is opened on the first side plate (3-3), it is interior with turborotor (5) that the surface of the first side plate (3-3) is provided with a loop-shaped
The first side wall (3-4) that listrium (5-1) profile is adapted, when in use, the inner platform (5-1) of turborotor (5) is set
In the cavity formed by the first side plate (3-3) and the first side wall (3-4), be additionally provided with inner platform protecting box (3) can with it is interior
Listrium (5-1) outer arcuate face offsets for the first support frame (3-5) for supporting inner platform (5-1).
5. a kind of protection device for turborotor variable-angle applying coating according to claim 1, it is special
Levy and be, the curtain plate protecting box (4) includes the second side plate (4-3), the two blessing holes up and down in curtain plate protecting box (4)
It is opened on the second side plate (4-3), it is outer with turborotor (5) that the surface of the second side plate (4-3) is provided with a loop-shaped
The second sidewall (4-4) that listrium (5-2) profile is adapted, when in use, the curtain plate (5-2) of turborotor (5) is set
In the cavity formed by the second side plate (4-3) and second sidewall (4-4), be additionally provided with curtain plate protecting box (4) can with it is outer
Outer (5-2) side arcwall face of listrium offsets for the second support frame (4-5) for supporting curtain plate (5-2).
6. a kind of guard method for turborotor variable-angle applying coating, based on the protection described in claim 1
Device, it is characterised in that comprise the following steps：
Step one, inner platform protecting box (3) and curtain plate protecting box (4) are respectively fitted over the inner platform of turborotor (5)
On curtain plate；
Step 2, then inner platform protecting box (3) and curtain plate protecting box (4) are inserted respectively with the two ends of clip (1) bare terminal end
In the clamping hole on top, then inner platform protecting box (3) and curtain plate protecting box are inserted respectively with the two ends of lower clip (7) bare terminal end
(4) in the clamping hole of bottom；
Step 3, repeat step one to step 2 assemble some groups by upper clip (1), hook (2), inner platform protecting box (3),
The assembly (10) of turborotor (5), curtain plate protecting box (4), lower clip (7) and small suspension hook (8) assembling；
Step 4, is stringed together each assembly (10) hook by hook (2) and lower suspension hook (8), then in multi-arc ion plating equipment
Middle depositing coating.
7. a kind of guard method for turborotor variable-angle applying coating according to claim 6, it is special
Levy and be, in the step 4, when upper clip (1) is by inner platform protecting box (3), curtain plate protecting box (4) and turbine directing vane
After the assembly of piece (5) is hung up, the turborotor venturi position (6) of turborotor (5) can just to multi sphere ion
The cathode arc source (101) of coating apparatus.
8. a kind of guard method for turborotor variable-angle applying coating according to claim 6, it is special
Levy and be, in the step 4, often string has 1-5 assembly (10), in the circumferencial direction of multi-arc ion plating equipment planet rotating shaft
Hanging 12 is gone here and there.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201611081899.XA CN106756818B (en) | 2016-11-30 | 2016-11-30 | A kind of protective device and method for turborotor variable-angle applying coating |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201611081899.XA CN106756818B (en) | 2016-11-30 | 2016-11-30 | A kind of protective device and method for turborotor variable-angle applying coating |
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| Publication Number | Publication Date |
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| CN106756818A true CN106756818A (en) | 2017-05-31 |
| CN106756818B CN106756818B (en) | 2019-03-15 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN201611081899.XA Active CN106756818B (en) | 2016-11-30 | 2016-11-30 | A kind of protective device and method for turborotor variable-angle applying coating |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109457223A (en) * | 2018-11-14 | 2019-03-12 | 中国航发动力股份有限公司 | A kind of protective device and method for turborotor variable-angle applying coating |
| CN114411087A (en) * | 2021-12-29 | 2022-04-29 | 西安鑫垚陶瓷复合材料有限公司 | Turbine guide blade coating preparation tool and coating preparation method |
Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20070110910A1 (en) * | 2005-09-09 | 2007-05-17 | Thomas Beck | Method of preparing turbine blades for spray coating and mounting for fixing such a turbine blade |
| CN104874509A (en) * | 2015-05-21 | 2015-09-02 | 西安航空动力股份有限公司 | Automatic spraying support protection fixture for turbine guide vanes |
| CN105274479A (en) * | 2015-10-26 | 2016-01-27 | 西安航空动力股份有限公司 | Combined tool used for turbine blade multi-arc ion coating and use method of combined tool |
-
2016
- 2016-11-30 CN CN201611081899.XA patent/CN106756818B/en active Active
Patent Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20070110910A1 (en) * | 2005-09-09 | 2007-05-17 | Thomas Beck | Method of preparing turbine blades for spray coating and mounting for fixing such a turbine blade |
| CN104874509A (en) * | 2015-05-21 | 2015-09-02 | 西安航空动力股份有限公司 | Automatic spraying support protection fixture for turbine guide vanes |
| CN105274479A (en) * | 2015-10-26 | 2016-01-27 | 西安航空动力股份有限公司 | Combined tool used for turbine blade multi-arc ion coating and use method of combined tool |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109457223A (en) * | 2018-11-14 | 2019-03-12 | 中国航发动力股份有限公司 | A kind of protective device and method for turborotor variable-angle applying coating |
| CN114411087A (en) * | 2021-12-29 | 2022-04-29 | 西安鑫垚陶瓷复合材料有限公司 | Turbine guide blade coating preparation tool and coating preparation method |
| CN114411087B (en) * | 2021-12-29 | 2023-09-29 | 西安鑫垚陶瓷复合材料有限公司 | Turbine guide vane coating preparation tool and coating preparation method |
Also Published As
| Publication number | Publication date |
|---|---|
| CN106756818B (en) | 2019-03-15 |
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Address after: Weiyang Xu Jia Wan 710021 Shaanxi city of Xi'an Province Patentee after: AECC AVIATION POWER CO., LTD. Address before: Weiyang Xu Jia Wan 710021 Shaanxi city of Xi'an Province Patentee before: AVIC AVIATION ENGINE CORPORATION PLC |