CN106435433A - Thermal barrier coating spraying method applied to empennage - Google Patents
Thermal barrier coating spraying method applied to empennage Download PDFInfo
- Publication number
- CN106435433A CN106435433A CN201610859312.7A CN201610859312A CN106435433A CN 106435433 A CN106435433 A CN 106435433A CN 201610859312 A CN201610859312 A CN 201610859312A CN 106435433 A CN106435433 A CN 106435433A
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- CN
- China
- Prior art keywords
- spraying
- empennage
- spray
- coating
- nicr
- 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.)
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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
- C23C4/00—Coating by spraying the coating material in the molten state, e.g. by flame, plasma or electric discharge
- C23C4/04—Coating by spraying the coating material in the molten state, e.g. by flame, plasma or electric discharge characterised by the coating material
- C23C4/06—Metallic material
- C23C4/08—Metallic material containing only metal elements
-
- 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 thermal barrier coating spraying method applied to an empennage and belongs to the field of thermal spraying. The spraying method provided by the invention comprises the following steps: firstly, performing abrasive blasting treatment on a spraying region of the overall empennage, wherein the requirement that the roughness Ra of the spraying region is larger than or equal to 8.0 microns should be satisfied; subsequently spraying a NiCr bottom layer and a ZrO2 face layer, wherein the spraying sequence of each of the bottom layer and the face layer is wind receiving surface to top edge to front surface to rear surface. By adopting the spraying method provided by the invention, the uniformity and compactness of the microcosmic structure of an empennage coating are greatly improved, so the adhesive force between the coating and the empennage is remarkably increased, and the effective coating formed after spraying is as large as 0.9 mm in thickness, so the problem of ablation of the empennage during a flying process is effectively solved, and especially the quality of the coating on the wind receiving surface can satisfy the flying requirements of the present stage.
Description
Technical field
The present invention relates to a kind of thermal barrier coating spraying method for empennage, 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 the holding of intensity, rigidity and empennage of material
Loading capability, increases deformation.With the increase of rocket projectile range, the resistance to pneumatic heating efficiency of empennage is required to improve, particularly right
In the rocket projectile that the flight time is longer, lasting Aerodynamic Heating can bring serious ablation phenomen with pneumatic washing away, and make empennage in the past
Edge separately begins to melt, and causes aerofoil to destroy, affects control of the empennage to the flight stability of rocket projectile.Solve empennage ablation existing
As adopting the method for spraying thermal barrier coating in stabilizing surfaces, and the key of thermal barrier coating effect is to see spraying thermal boundary painting on empennage
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 do not play resistance to ablation effect completely, just lower and fin is washed away pneumatic
Sur-face peeling.With NiCr bottom conventional at present, ZrO2As a example by the thermal barrier coating of surface layer, using conventional spray paint technique on empennage
Sprayed, the effective thickness of thermal barrier coating is less than 0.4mm.How the effective of spraying thermal barrier coating is improved on empennage
Thickness, is the technological difficulties for restricting rocket projectile long-distance flight stability.
Content of the invention
The invention aims to improving the effective thickness for spraying thermal barrier coating on empennage, and provide a kind of for empennage
Thermal barrier coating spraying method.
The purpose of the present invention is achieved through the following technical solutions：
A kind of thermal barrier coating spraying method for empennage of the present invention, comprises the following steps that：
1) surface preparation
Blasting treatment is carried out to the spraying area of whole empennage, it is desirable to spraying area roughness Ra >=8.0 μm；
2) NiCr bottom is sprayed
Spraying order according to spraying windward side → top rib → front → reverse side successively completes to spray NiCr bottom to whole empennage
Layer, wherein, windward side is with top rib spraying direction using spraying in the width direction, and the spraying direction of front and reverse side is along windward side
The direction of angle；Each spray parameters are：Spraying current 500-550A, spray voltage 55-60V, spray distance 110-130mm, spray
Tu Ya road amount is 1 with spraying " hot spot " diameter ratio:3～1:5, powder sending quantity is that 40-50g/min, coating thickness is less than 0.3mm；
3) ZrO is sprayed2Surface layer
Using with spraying NiCr bottom identical spraying order, spraying direction, spray ZrO on NiCr bottom2Surface layer, respectively
Spray parameters are：Spraying current 600-650A, spray voltage 65-70V, spray distance 100-120mm, spraying pressure road amount and spraying
" hot spot " diameter ratio about 1:7～1:9, powder sending quantity 30-40g/min, coating thickness is less than 0.6mm.
Beneficial effect：
Using the spraying method of the present invention, the uniformity of empennage coating microstructure, compactness are greatly improved,
And then so that the adhesive force between coating and empennage is significantly improved, the effective coating after spraying is effectively solved up to 0.9mm
The coating quality of problem, particularly windward side of empennage ablation in flight course of having determined disclosure satisfy that flight at this stage will
Ask.
Description of the drawings
Fig. 1 needs the schematic diagram of spray-coating surface for empennage；
Fig. 2 is windward side, the schematic diagram in top rib spraying direction；
In figure, 1- front, 2- windward side, 3- pushes up rib, 4- reverse side.
Specific embodiment
With reference to the accompanying drawings and examples present disclosure is further described：
Embodiment
As shown in figure 1, using the spraying method of the present invention, certain rocket projectile empennage is sprayed, specifically
Step is as follows：
1) surface preparation
Blasting treatment is carried out to the spraying area of whole empennage, it is desirable to spraying area roughness Ra >=8.0 μm.
2) NiCr bottom is sprayed
Spraying order for first spray windward side → top rib → front → reverse side, windward side with top rib spraying direction using along
Width is sprayed, as illustrated, direction of the spraying direction of front and reverse side along windward side angle.Each spray parameters are：
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) ZrO is sprayed2Surface layer
ZrO2The spraying order of surface layer, spraying direction are consistent with NiCr bottom powder, regulation spray parameters, spraying current 600A,
Spray voltage 65-70V, spray distance 100-110mm, spraying pressure road amount is 1 with spraying " hot spot " diameter ratio:8, powder sending quantity 32-
35g/min, sprays ZrO2Thickness 0.6mm.
The coating integral thickness is up to 0.9mm, and coating resistance to elevated temperatures and flushing resistance meet pneumatic in flight course
The hot and pneumatic requirement that washes away.
Claims (1)
1. a kind of thermal barrier coating spraying method for empennage, is characterized in that：Comprise the following steps that：
1) surface preparation
Blasting treatment is carried out to the spraying area of whole empennage, it is desirable to spraying area roughness Ra >=8.0 μm；
2) NiCr bottom is sprayed
Spraying order according to spraying windward side → top rib → front → reverse side successively completes to spray NiCr bottom to whole empennage；Respectively
Spray parameters are：Spraying current 500-550A, spray voltage 55-60V, spray distance 110-130mm, spraying pressure road amount and spraying
" hot spot " diameter ratio is 1:3～1:5, powder sending quantity is 40-50g/min；
3) ZrO is sprayed2Surface layer
Using with the spraying of spraying NiCr bottom identical sequentially, ZrO is sprayed on NiCr bottom2Surface layer, each spray parameters are：Spray
Apply electric current 600-650A, spray voltage 65-70V, spray distance 100-120mm, spraying pressure road amount and spraying " hot spot " diameter ratio
About 1:7～1:9, powder sending quantity 30-40g/min.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610859312.7A CN106435433A (en) | 2016-09-28 | 2016-09-28 | Thermal barrier coating spraying method applied to empennage |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610859312.7A CN106435433A (en) | 2016-09-28 | 2016-09-28 | Thermal barrier coating spraying method applied to empennage |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN106435433A true CN106435433A (en) | 2017-02-22 |
Family
ID=58170703
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201610859312.7A Pending CN106435433A (en) | 2016-09-28 | 2016-09-28 | Thermal barrier coating spraying method applied to empennage |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN106435433A (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108950457A (en) * | 2018-06-11 | 2018-12-07 | 中国航发哈尔滨东安发动机有限公司 | A kind of impeller chimney class part heat spraying method |
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 CN201610859312.7A patent/CN106435433A/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》 * |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108950457A (en) * | 2018-06-11 | 2018-12-07 | 中国航发哈尔滨东安发动机有限公司 | A kind of impeller chimney class part heat spraying method |
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| C06 | Publication | ||
| PB01 | Publication | ||
| C10 | Entry into substantive examination | ||
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| WD01 | Invention patent application deemed withdrawn after publication | ||
| WD01 | Invention patent application deemed withdrawn after publication |
Application publication date: 20170222 |