CN115612965A - Preparation method of completely amorphous coating - Google Patents
Preparation method of completely amorphous coating Download PDFInfo
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- CN115612965A CN115612965A CN202211287375.1A CN202211287375A CN115612965A CN 115612965 A CN115612965 A CN 115612965A CN 202211287375 A CN202211287375 A CN 202211287375A CN 115612965 A CN115612965 A CN 115612965A
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- 239000011248 coating agent Substances 0.000 title claims abstract description 72
- 238000000576 coating method Methods 0.000 title claims abstract description 72
- 238000002360 preparation method Methods 0.000 title abstract description 11
- 238000000034 method Methods 0.000 claims abstract description 38
- XEEYBQQBJWHFJM-UHFFFAOYSA-N Iron Chemical compound [Fe] XEEYBQQBJWHFJM-UHFFFAOYSA-N 0.000 claims abstract description 30
- 239000000843 powder Substances 0.000 claims abstract description 30
- 238000010285 flame spraying Methods 0.000 claims abstract description 27
- 229910052742 iron Inorganic materials 0.000 claims abstract description 15
- 239000002245 particle Substances 0.000 claims abstract description 15
- 239000000758 substrate Substances 0.000 claims abstract description 7
- 230000003116 impacting effect Effects 0.000 claims abstract description 5
- 239000002994 raw material Substances 0.000 claims abstract description 4
- 229910000808 amorphous metal alloy Inorganic materials 0.000 claims description 19
- 230000008602 contraction Effects 0.000 claims description 16
- QVGXLLKOCUKJST-UHFFFAOYSA-N atomic oxygen Chemical compound [O] QVGXLLKOCUKJST-UHFFFAOYSA-N 0.000 claims description 15
- 239000001301 oxygen Substances 0.000 claims description 15
- 229910052760 oxygen Inorganic materials 0.000 claims description 15
- IJGRMHOSHXDMSA-UHFFFAOYSA-N Atomic nitrogen Chemical compound N#N IJGRMHOSHXDMSA-UHFFFAOYSA-N 0.000 claims description 14
- ATUOYWHBWRKTHZ-UHFFFAOYSA-N Propane Chemical compound CCC ATUOYWHBWRKTHZ-UHFFFAOYSA-N 0.000 claims description 14
- 238000005507 spraying Methods 0.000 claims description 13
- 229910052757 nitrogen Inorganic materials 0.000 claims description 7
- 239000001294 propane Substances 0.000 claims description 7
- 239000000155 melt Substances 0.000 claims description 2
- 230000007547 defect Effects 0.000 abstract description 7
- 230000003647 oxidation Effects 0.000 abstract description 5
- 238000007254 oxidation reaction Methods 0.000 abstract description 5
- 239000011148 porous material Substances 0.000 abstract description 5
- 239000011159 matrix material Substances 0.000 abstract description 3
- 238000005336 cracking Methods 0.000 abstract description 2
- 230000000052 comparative effect Effects 0.000 description 9
- 238000005516 engineering process Methods 0.000 description 5
- 238000002844 melting Methods 0.000 description 5
- 230000008018 melting Effects 0.000 description 5
- 238000005457 optimization Methods 0.000 description 5
- 239000000956 alloy Substances 0.000 description 4
- 230000007797 corrosion Effects 0.000 description 4
- 238000005260 corrosion Methods 0.000 description 4
- 239000000463 material Substances 0.000 description 4
- 239000011247 coating layer Substances 0.000 description 3
- 229910045601 alloy Inorganic materials 0.000 description 2
- 238000002485 combustion reaction Methods 0.000 description 2
- 238000002441 X-ray diffraction Methods 0.000 description 1
- 230000001133 acceleration Effects 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000015572 biosynthetic process Effects 0.000 description 1
- 238000005266 casting Methods 0.000 description 1
- 239000003153 chemical reaction reagent Substances 0.000 description 1
- 238000007796 conventional method Methods 0.000 description 1
- 230000032798 delamination Effects 0.000 description 1
- 238000009826 distribution Methods 0.000 description 1
- 238000010998 test method Methods 0.000 description 1
- 238000007751 thermal spraying Methods 0.000 description 1
- 239000002699 waste material Substances 0.000 description 1
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- Other Surface Treatments For Metallic Materials (AREA)
Abstract
The invention relates to a preparation method of a complete amorphous coating, belonging to the technical field of supersonic flame spraying. A method for preparing a complete amorphous coating is a supersonic flame spraying method, wherein the raw material is amorphous powder, a nozzle of a adopted supersonic flame spraying device is a Laval nozzle, the Laval nozzle consists of a divergent section and a convergent section, the length of the convergent section is 21-56 mm, and the linear form of the convergent section adopts a Witosynsky curve design method; the length of the divergent section is 170-200 mm, and the diameter of the throat part is 12-16 mm. The supersonic flame spraying nozzle adopts a Laval nozzle, optimizes the structure of a divergent section and a convergent section of the Laval nozzle, and promotes powder particles to be in a semi-molten state, higher impact speed and shorter residence time before impacting a substrate, thereby reducing pores and oxidation defects in the prepared iron-based amorphous coating, increasing the bonding strength with a matrix and preventing the coating from cracking.
Description
Technical Field
The invention relates to a preparation method of a complete amorphous coating, belonging to the technical field of supersonic flame spraying.
Background
The appearance of the block amorphous alloy realizes the preparation of large-size amorphous alloy by using a conventional casting method and makes the application of the amorphous alloy as a structural material possible. Amorphous alloys exhibit superior properties in many respects to conventional alloy materials, such as high hardness, high elastic modulus, high wear resistance, and excellent corrosion resistance. In the 21 st century that the requirements for various properties of materials are increasingly severe, amorphous alloy materials are expected to become one of the most important novel engineering materials.
However, bulk amorphous alloys have poor plasticity, which severely limits their practical applications. As the brittleness of the amorphous alloy can be greatly improved under the micron scale, the amorphous alloy micro powder is sprayed on the tough matrix to prepare the amorphous coating, which is a method for effectively improving the brittleness and exerting the wear-resistant and corrosion-resistant characteristics of the amorphous alloy. The amorphous alloy coating prepared by the thermal spraying method has high strength, high wear resistance and excellent corrosion resistance, and has important application prospect in key components in the national important fields of oceans, electric power, petrifaction and the like. However, one of the outstanding problems in the in-service process of thermal spray coating is that it is prone to delamination or local cracking, which ultimately leads to coating failure, and is closely related to defects such as oxides and pores formed during the coating preparation process. The formation of oxides and pores in the coating is determined by the speed and temperature variation law of the powder particles during the spraying process, and the speed and temperature characteristics of the particles are closely related to the structure of the supersonic flame spraying nozzle. Therefore, the structural characteristics of the supersonic flame spraying nozzle are the key for preparing the amorphous alloy coating with high density, low oxidation defect and high performance.
Disclosure of Invention
The invention aims to provide a supersonic flame spraying nozzle optimization method and a preparation method of a high-performance amorphous coating, wherein the method is used for optimizing the structure of the supersonic flame spraying nozzle and specifically comprises the following steps: the supersonic flame spraying nozzle adopts a Laval nozzle, the contraction section and the divergence section of the Laval nozzle are optimally designed, so that the amorphous powder is in a semi-molten state at a high speed when impacting a substrate, and then an iron-based completely amorphous coating is formed on the substrate.
A method for preparing a complete amorphous coating is a supersonic flame spraying method, wherein the raw material is amorphous powder, the adopted supersonic flame spraying device adopts a nozzle which is a Laval nozzle, the Laval nozzle consists of a divergent section and a convergent section, wherein,
the length of the contraction section is 21-56 mm, and the linear shape of the contraction section adopts a Wittonsisky curve design method;
the length of the divergent section is 170-200 mm, and the diameter of the throat part is 12-16 mm.
The laval nozzle opening of the present invention is connected to the combustion chamber and has a size matching the inlet of the combustion chamber. Preferably, the diameter of the nozzle opening of the laval nozzle is 71mm.
The supersonic flame spraying device used in the preparation method of the complete amorphous coating is a supersonic flame spraying device disclosed in the prior art and can be commercially obtained.
The supersonic flame spraying device of the invention is different from the prior art mainly in the design and the use of a nozzle.
In the preparation method of the complete amorphous coating, the obtained coating is a complete amorphous alloy coating, the porosity is lower than 2.1%, and the oxygen content is lower than 1.8%.
Preferably, the amorphous powder particles have a melt index of less than 1 prior to impacting the substrate.
Preferably, the diameter of the amorphous powder is 10 to 60 μm; further preferably, the diameter of the amorphous powder is 20 to 30 μm.
Preferably, in the supersonic flame spraying method, the spraying distance is 150-200 mm; the air pressure is 850-940 KPa; the pressure of the propane is 900 to 980KPa; the nitrogen pressure is 700-800 KPa.
According to the invention, through the optimization of the supersonic flame spraying Laval nozzle, in the spraying process, the amorphous powder obtains higher speed, the amorphous powder is in a semi-molten state before impacting a substrate, the residence time of powder particles is short, and the defect quantity of pores and oxidation in the coating is reduced.
The invention has the beneficial effects that: the invention provides an optimization method of a supersonic flame spraying nozzle and a preparation method of a high-performance amorphous coating.
Compared with the prior art, the invention has the following characteristics:
(1) The method solves the problem of resource waste in the prior spraying process parameter optimization process by optimizing the structure of the supersonic nozzle, reduces the preparation cost of the amorphous coating, obtains the iron-based amorphous coating with low porosity and low oxidation defect, improves the binding force and corrosion resistance of the iron-based amorphous coating and a matrix, and promotes wider application.
(2) Compared with the traditional linear line adopted by the contraction section, the Vickers curve has the advantages of faster inlet contraction, smaller contraction of the middle and rear parts compared with the inlet, and more uniform outlet speed and acceleration, so that the Vickers curve of the contraction section has the characteristics of uniform speed and temperature distribution, the temperature field and the speed field of the flame flow of the contraction section are increased more uniformly, the powder particles obtain higher impact speed, and more importantly, the residence time of the powder particles in the spraying process is greatly reduced, thereby reducing the generation of the oxidation defects of the coating. In addition, the optimization of the length of the converging section of the Laval nozzle effectively controls the melting state of powder particles, reduces the pore defects in the coating, and improves the compactness of the coating and the bonding strength with the substrate.
Drawings
FIG. 1 (a) is a schematic view of a Laval nozzle configuration; (b) Is a schematic view of the nozzle structure of comparative example 1 in which the convergent line profile of the laval nozzle is a straight line;
FIG. 2 is the XRD pattern of the coating prepared in example 1;
FIG. 3 is a graph of the melting behavior of powder particles of different diameters in flight;
fig. 4 is a graph showing the change in velocity of powder particles of different diameters during flight.
FIG. 5 is a surface and cross-sectional SEM photograph of the coating prepared in example 1; wherein: (a) a surface; (b) cross section.
Detailed Description
The following non-limiting examples are presented to enable those of ordinary skill in the art to more fully understand the present invention and are not intended to limit the invention in any way.
The test methods described in the following examples are all conventional methods unless otherwise specified; the reagents and materials are commercially available, unless otherwise specified.
In the following examples, the supersonic flame spray coating used was AK07 from KERMETICO. .
Example 1
Preparing the iron-based amorphous coating by adopting a supersonic flame spraying technology, wherein: selecting a converging section line type of a Laval nozzle as a Wittonsisky curve, wherein the converging section length is as follows: 50mm, laval nozzle divergent length: 190mm, throat diameter 14mm, as shown in FIG. 1. The size of the amorphous powder is 20-30 μm, the spraying distance is 180mm, and the air pressure is 900KPa; the propane pressure was 950KPa; the nitrogen pressure was 760KPa. The iron-based amorphous coating prepared according to the method is shown in fig. 2, and the prepared coating is completely amorphous. Fig. 3 is a graph showing the melting characteristics of powder particles having different diameters in flight, wherein the powder particles having diameters of 10 μm and 20 μm have a melting index of less than 1 and are in a semi-melted state, and fig. 4 is a graph showing the speed change characteristics of powder particles having different diameters in flight, and it can be seen from fig. 5 (a) that the surface of the coating layer is in a good melted state without unmelted particles and excessive melting, and the porosity of the coating layer is 1.1% and the oxygen content of the coating layer is 0.75% as calculated from fig. 5 (b).
Example 2
Preparing the iron-based amorphous coating by adopting a supersonic flame spraying technology, wherein: selecting a Laval nozzle contraction section line type as a Wittonsisi curve, wherein the contraction section length is as follows: 21mm, laval nozzle divergent length: 190mm, throat diameter 14mm. The size of the amorphous powder is 20-30 μm, the spraying distance is 180mm, and the air pressure is 900KPa; the propane pressure was 950KPa; the nitrogen pressure was 760KPa. The porosity of the iron-based amorphous coating prepared by the method is 2.0%, and the oxygen content of the coating is 1.03%.
Example 3
Preparing the iron-based amorphous coating by adopting a supersonic flame spraying technology, wherein: selecting a converging section line type of a Laval nozzle as a Wittonsisky curve, wherein the converging section length is as follows: 28mm, laval nozzle divergent length: 190mm, throat diameter 14mm. The size of the amorphous powder is 20-30 μm, the spraying distance is 180mm, and the air pressure is 900KPa; the propane pressure was 950KPa; the nitrogen pressure was 760KPa. The porosity of the iron-based amorphous coating prepared by the method is 1.8%, and the oxygen content of the coating is 1.33%.
Example 4
Preparing the iron-based amorphous coating by adopting a supersonic flame spraying technology, wherein: selecting a Laval nozzle contraction section line type as a Wittonsisi curve, wherein the contraction section length is as follows: 36mm, laval nozzle divergent length: 190mm, throat diameter 14mm. The size of the amorphous powder is 20-30 μm, the spraying distance is 180mm, and the air pressure is 900KPa; the propane pressure was 950KPa; the nitrogen pressure was 760KPa. The porosity of the iron-based amorphous coating prepared by the method is 1.7%, and the oxygen content of the coating is 1.59%.
Example 5
Preparing the iron-based amorphous coating by adopting a supersonic flame spraying technology, wherein: selecting a Laval nozzle contraction section line type as a Wittonsisi curve, wherein the contraction section length is as follows: 56mm, laval nozzle divergent length: 190mm, throat diameter 14mm. The size of the amorphous powder is 20-30 μm, the spraying distance is 180mm, and the air pressure is 900KPa; the propane pressure was 950KPa; the nitrogen pressure was 760KPa. The porosity of the iron-based amorphous coating prepared by the method is 1.4%, and the oxygen content of the coating is 1.71%.
Comparative example 1
The difference from example 1 is that: the converging section line type of the Laval nozzle is a straight line, the length of the converging section is 60mm, the length of the diverging section of the Laval nozzle is 210mm, and the diameter of the throat part is 17mm. As a result: the porosity of the prepared complete amorphous alloy coating is 3.33%, and the oxygen content of the coating is 5.31%, which is higher than that of the coating in example 1.
Comparative example 2
The difference from example 1 is that: the line type of the convergent section of the laval nozzle is a straight line, the length of the convergent section is 19mm, the length of the divergent section of the laval nozzle is 210mm, and the diameter of the throat part is 17mm. As a result: the porosity of the prepared complete amorphous alloy coating is 5.01%, and the oxygen content of the coating is 4.09%, which is higher than that of the coating in example 1.
Comparative example 3
The difference from example 1 is that: the converging section line of the laval nozzle is a straight line, the converging section is 60mm in length, the diverging section of the laval nozzle is 110mm in length, and the diameter of the throat part is 17mm. As a result: the porosity of the prepared complete amorphous alloy coating is 6.13%, and the oxygen content of the coating is 3.01%, which is higher than that of the coating in example 1.
Comparative example 4
The difference from example 1 is that: the line type of the convergent section of the laval nozzle is a straight line, the length of the convergent section is 19mm, the length of the divergent section of the laval nozzle is 110mm, and the diameter of the throat part is 17mm. As a result: the porosity of the prepared complete amorphous alloy coating is 6.94%, and the oxygen content of the coating is 2.47%, which is higher than that of the coating in example 1.
Comparative example 5
The difference from example 1 is that: the line type of the convergent section of the laval nozzle is a straight line, the length of the convergent section is 60mm, the length of the divergent section of the laval nozzle is 210mm, and the diameter of the throat part is 11mm. As a result: the porosity of the prepared complete amorphous alloy coating is 2.98%, and the oxygen content of the coating is 6.03%, which is higher than that of the coating in example 1.
Comparative example 6
The difference from example 1 is that: the line type of the convergent section of the laval nozzle is a straight line, the length of the convergent section is 19mm, the length of the divergent section of the laval nozzle is 210mm, and the diameter of the throat part is 11mm. As a result: the porosity of the prepared complete amorphous alloy coating is 4.49%, and the oxygen content of the coating is 5.04%, which is higher than that of the coating in example 1.
Comparative example 7
The difference from example 1 is that: the converging section line of the laval nozzle is a straight line, the converging section is 60mm in length, the diverging section of the laval nozzle is 110mm in length, and the diameter of the throat part is 11mm. As a result: the porosity of the prepared complete amorphous alloy coating is 5..89%, and the oxygen content of the coating is 3.49%, which is higher than that of the coating in example 1.
Comparative example 8
The difference from example 1 is that: the converging section line of the laval nozzle is a straight line, the converging section is 19mm in length, the diverging section of the laval nozzle is 110mm in length, and the diameter of the throat part is 11mm. As a result: the porosity of the prepared complete amorphous alloy coating is 6.71%, and the oxygen content of the coating is 3.07%, which is higher than that of the coating in example 1.
Claims (8)
1. A method for preparing a complete amorphous coating is characterized by comprising the following steps: the method is a supersonic flame spraying method, wherein the raw material is amorphous powder,
the nozzle of the adopted supersonic flame spraying device is a Laval nozzle which consists of a divergent section and a convergent section, wherein,
the length of the contraction section is 21-56 mm, and the linear shape of the contraction section adopts a Wittonsisky curve design method;
the length of the divergent section is 170-200 mm, and the diameter of the throat part is 12-16 mm.
2. The method of claim 1, wherein: the diameter of the nozzle opening of the Laval nozzle is 71mm.
3. The method of claim 1, wherein: the obtained coating is a complete amorphous alloy coating, the porosity is lower than 2.1%, and the oxygen content is lower than 1.8%.
4. The method of claim 1, wherein: the diameter of the amorphous powder is 10-60 mu m.
5. The method of claim 4, wherein: the diameter of the amorphous powder is 20-30 μm.
6. Method according to claim 1, 4, 5, characterized in that: the raw material of the supersonic flame spraying method is iron-based amorphous powder.
7. The method according to any one of claims 1 to 6, wherein: the amorphous powder particles have a melt index of less than 1 prior to impacting the substrate.
8. The method of claim 1, wherein: in the supersonic flame spraying method, the spraying distance is 150-200 mm; the air pressure is 850-940 KPa; the pressure of the propane is 900 to 980KPa; the nitrogen pressure is 700-800 KPa.
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