CN106319422A - Method for spraying thermal barrier coating onto empennage - Google Patents
Method for spraying thermal barrier coating onto empennage Download PDFInfo
- Publication number
- CN106319422A CN106319422A CN201610859228.5A CN201610859228A CN106319422A CN 106319422 A CN106319422 A CN 106319422A CN 201610859228 A CN201610859228 A CN 201610859228A CN 106319422 A CN106319422 A CN 106319422A
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- CN
- China
- Prior art keywords
- spraying
- empennage
- coating
- nicr
- thermal barrier
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- 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.)
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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
- C23C4/00—Coating by spraying the coating material in the molten state, e.g. by flame, plasma or electric discharge
- C23C4/12—Coating by spraying the coating material in the molten state, e.g. by flame, plasma or electric discharge characterised by the method of spraying
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- Chemical & Material Sciences (AREA)
- Engineering & Computer Science (AREA)
- Physics & Mathematics (AREA)
- Plasma & Fusion (AREA)
- Chemical Kinetics & Catalysis (AREA)
- Materials Engineering (AREA)
- Mechanical Engineering (AREA)
- Metallurgy (AREA)
- Organic Chemistry (AREA)
- Application Of Or Painting With Fluid Materials (AREA)
Abstract
The invention relates to a method for spraying a thermal barrier coating onto an empennage and belongs to the field of thermal spraying. The method comprises the following steps: first, performing sand blasting on the spraying area of the whole empennage, wherein the roughness Ra of the spraying area is required to be higher than or equal to 8.0 [mu]m; and then, spraying a NiCr bottom layer and a ZrO2 surface layer, wherein the bottom layer and the surface layer are sprayed in the following order: the windward sides, the top edges, the obverse sides and the reverse sides, the windward sides and the top edges are sprayed along the width direction, and the obverse sides and the reverse sides are sprayed along the windward side angle direction. By adoption of the method provided by the invention, the microstructure uniformity and uniformity of the coating on the empennage can be greatly improved, and then the adhesive force between the coating and the empennage can be obviously improved; after the spraying, an effective coating of 0.9 mm can be formed, thereby effectively solving the problem about ablation of the empennage in a flight process; and particularly, the coating quality of the windward sides can meet the flight requirement at the present stage.
Description
Technical field
The method that the present invention relates to a kind of empennage spraying thermal barrier coating, belongs to field of thermal spray.
Background technology
Empennage is one of vitals of rocket projectile, the flight stability of principal security rocket projectile.When rocket projectile flight speed
When degree exceedes certain Mach number, during flight, pneumatic heating phenomena is more serious, can reduce holding of the intensity of material, rigidity and empennage
Loading capability, increases deformation.Along with the increase of rocket projectile range, require to improve to the resistance to pneumatic heating efficiency of empennage, the most right
In the rocket projectile that the flight time is longer, lasting Aerodynamic Heating and pneumatic washing away can bring serious ablation phenomen, make empennage in the past
Edge portion starts fusing, causes aerofoil to destroy, affects the empennage control to the flight stability of rocket projectile.Solve empennage ablation existing
As can use stabilizing surfaces spraying thermal barrier coating method, and thermal barrier coating effect it is crucial that see on empennage spray thermal boundary be coated with
The effective thickness of layer.The thickness of spraying thermal barrier coating is too low, and resistance to ablation effect is limited, but the thickness of coating is too high can affect coating
With the adhesive force of fin, may result in before thermal barrier coating plays resistance to ablation effect the most completely, just wash away lower and fin pneumatic
Sur-face peeling.With the most conventional NiCr bottom, ZrO2As a example by the thermal barrier coating of surface layer, use conventional spray paint technique on empennage
Spraying, the effective thickness of thermal barrier coating is less than 0.4mm.How can improve the effective of spraying thermal barrier coating on empennage
Thickness, is the technological difficulties of restriction rocket projectile long-distance flight stability.
Summary of the invention
The invention aims to improve the effective thickness spraying thermal barrier coating on empennage, and a kind of empennage spraying is provided
The method of thermal barrier coating.
It is an object of the invention to be achieved through the following technical solutions:
The method of a kind of empennage spraying thermal barrier coating of the present invention, specifically comprises the following steps that
1) surface preparation
The spraying area of whole empennage is carried out blasting treatment, it is desirable to spraying area roughness Ra >=8.0 μm；
2) spraying NiCr bottom
Complete at the bottom of whole empennage spraying NiCr according to the spraying order spraying windward side → top rib → front → reverse side successively
Layer, wherein, windward side uses with rib spraying direction, top and sprays in the width direction, and the spraying direction of front and reverse side is along windward side
The direction of angle；Each spray parameters is: spraying current 500-550A, spray voltage 55-60V, spray distance 110-130mm, spray
Tu Ya road amount and spraying " hot spot " diameter ratio are for 1:3～1:5, and powder sending quantity is 40-50g/min, and coating thickness is less than 0.3mm；
3) spraying ZrO2Surface layer
Use with spraying NiCr bottom identical spraying order, spraying direction, on NiCr bottom spraying ZrO2Surface layer, respectively
Spray parameters is: spraying current 600-650A, spray voltage 65-70V, spray distance 100-120mm, spraying pressure road amount and spraying
" hot spot " diameter is less than 0.6mm than about 1:7～1:9, powder sending quantity 30-40g/min, coating thickness.
Beneficial effect:
Using the spraying method of the present invention, the uniformity of empennage coating microstructure, compactness are greatly improved,
And then making the adhesive force between coating and empennage be significantly improved, the effective coating after spraying, up to 0.9mm, effectively solves
Empennage coating quality of the problem of ablation, particularly windward side in flight course of having determined disclosure satisfy that the flight of present stage is wanted
Ask.
Accompanying drawing explanation
Fig. 1 is the schematic diagram that empennage needs spray-coating surface；
Fig. 2 is windward side, the schematic diagram in rib spraying direction, top；
In figure, 1-front, 2-windward side, 3-pushes up rib, 4-reverse side.
Detailed description of the invention
With embodiment, present disclosure is further described below in conjunction with the accompanying drawings:
Embodiment
As it is shown in figure 1, use the spraying method of the present invention that certain rocket projectile empennage is sprayed, specifically
Step is as follows:
1) surface preparation
The spraying area of whole empennage is carried out blasting treatment, it is desirable to spraying area roughness Ra >=8.0 μm.
2) spraying NiCr bottom
Spraying order for first spraying windward side → top rib → front → reverse side, windward side and top rib spraying direction employing along
Width sprays, as it can be seen, the spraying direction of front and reverse side is along the direction of windward side angle.Each spray parameters is:
Spraying current 500A, spray voltage 55-60V, spray distance 110-120mm, spraying pressure road amount with spraying " hot spot " diameter ratio is
1:4, powder sending quantity 42-45g/min, coating thickness is 0.3mm.
3) spraying ZrO2Surface layer
ZrO2Surface layer spraying order, spraying direction consistent with powder at the bottom of NiCr, regulation spray parameters, spraying current 600A,
Spray voltage 65-70V, spray distance 100-110mm, spraying pressure road amount and spraying " hot spot " diameter ratio is for 1:8, powder sending quantity 32-
35g/min, sprays ZrO2Thickness 0.6mm.
This coating integral thickness meets in flight course pneumatic up to 0.9mm, coating resistance to elevated temperatures and flushing resistance
Hot and the pneumatic requirement washed away.
Claims (3)
1. a method for empennage spraying thermal barrier coating, is characterized in that: specifically comprise the following steps that
1) surface preparation
The spraying area of whole empennage is carried out blasting treatment, it is desirable to spraying area roughness Ra >=8.0 μm；
2) spraying NiCr bottom
Complete whole empennage is sprayed NiCr bottom according to the spraying order spraying windward side → top rib → front → reverse side successively, its
In, windward side uses with rib spraying direction, top and sprays in the width direction, and the spraying direction of front and reverse side is along windward side angle
Direction；Each spray parameters is: spraying current 500-550A, spray voltage 55-60V, spray distance 110-130mm, spraying pressure
Road amount and spraying " hot spot " diameter ratio are for 1:3～1:5, and powder sending quantity is 40-50g/min；
3) spraying ZrO2Surface layer
Use with spraying NiCr bottom identical spraying order, spraying direction, on NiCr bottom spraying ZrO2Surface layer, respectively sprays
Parameter is: spraying current 600-650A, spray voltage 65-70V, spray distance 100-120mm, spraying pressure road amount and spraying " light
Speckle " diameter is than about 1:7～1:9, powder sending quantity 30-40g/min.
The method of a kind of empennage the most as claimed in claim 1 spraying thermal barrier coating, is characterized in that: the coating thickness of NiCr bottom
Less than 0.3mm.
The method of a kind of empennage the most as claimed in claim 1 spraying thermal barrier coating, is characterized in that: ZrO2The coating thickness of surface layer
Less than 0.6mm.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610859228.5A CN106319422A (en) | 2016-09-28 | 2016-09-28 | Method for spraying thermal barrier coating onto empennage |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610859228.5A CN106319422A (en) | 2016-09-28 | 2016-09-28 | Method for spraying thermal barrier coating onto empennage |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN106319422A true CN106319422A (en) | 2017-01-11 |
Family
ID=57820189
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201610859228.5A Pending CN106319422A (en) | 2016-09-28 | 2016-09-28 | Method for spraying thermal barrier coating onto empennage |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN106319422A (en) |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102094164A (en) * | 2009-12-15 | 2011-06-15 | 沈阳天贺新材料开发有限公司 | Nanometer zirconium oxide thermal barrier coating and preparation method thereof |
| CN103026003A (en) * | 2010-08-05 | 2013-04-03 | 西门子公司 | Turbine airfoil and method for thermal barrier coating |
| JP2013163480A (en) * | 2012-02-13 | 2013-08-22 | Mitsubishi Heavy Ind Ltd | Anti-icing device and aircraft main wing |
| CN104897009A (en) * | 2015-05-04 | 2015-09-09 | 晋西工业集团有限责任公司 | Ablation-resisting interlayer compound structure tail wing |
-
2016
- 2016-09-28 CN CN201610859228.5A patent/CN106319422A/en active Pending
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102094164A (en) * | 2009-12-15 | 2011-06-15 | 沈阳天贺新材料开发有限公司 | Nanometer zirconium oxide thermal barrier coating and preparation method thereof |
| CN103026003A (en) * | 2010-08-05 | 2013-04-03 | 西门子公司 | Turbine airfoil and method for thermal barrier coating |
| JP2013163480A (en) * | 2012-02-13 | 2013-08-22 | Mitsubishi Heavy Ind Ltd | Anti-icing device and aircraft main wing |
| CN104897009A (en) * | 2015-05-04 | 2015-09-09 | 晋西工业集团有限责任公司 | Ablation-resisting interlayer compound structure tail wing |
Non-Patent Citations (1)
| Title |
|---|
| 田永生等: ""ZrO2热障涂层研究进展"", 《中国机械工程》 * |
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| WD01 | Invention patent application deemed withdrawn after publication | ||
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Application publication date: 20170111 |