CN115976451A - Preparation method of pneumatic heating surface high-temperature-resistant instantaneous oxidation ablation-resistant coating - Google Patents
Preparation method of pneumatic heating surface high-temperature-resistant instantaneous oxidation ablation-resistant coating Download PDFInfo
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Abstract
The invention provides a preparation method of a pneumatic heating surface high-temperature-resistant instantaneous oxidation ablation coating, relates to the technical field of thermal spraying coating processing, and is designed for solving the problem of poor spraying uniformity of a tip position. The preparation method of the high-temperature-resistant instantaneous oxidation ablation-resistant coating on the pneumatic heating surface comprises the following steps: and acquiring the offset of the actual plasma flame flow center and the physical center of the nozzle, adjusting the track of the physical center of the nozzle according to the offset, and preparing the coating. The preparation method of the pneumatic heating surface high-temperature-resistant instantaneous oxidation ablation coating can improve the spraying uniformity of the tip position.
Description
Technical Field
The invention relates to the technical field of processing of thermal spraying coatings, in particular to a preparation method of a pneumatic heating surface high-temperature-resistant instantaneous oxidation ablation coating.
Background
The hypersonic aircraft in the classical sense is an aircraft which remotely cruises and flies in the atmosphere or across the atmosphere at a speed of more than Mach 5 by taking an air suction type engine and a combined engine thereof as power. Compared with the traditional aircraft, the hypersonic aircraft has great advantages, the extremely high flying speed can ensure that the hypersonic aircraft reaches any position of the world within 2-3 hours, the target response time is effectively shortened, and the penetration capability and the survival capability of the hypersonic aircraft are improved. As the hypersonic aerocraft has great military and economic benefits, many countries in the world start to research the hypersonic technology, and will develop the hypersonic aerocraft as the national target.
With the continuous improvement of the flight speed of the hypersonic aircraft, the service environment is more and more severe, and in order to ensure the safe and stable flight of the aerospace aircraft, the research on the thermal protection problem of key hot end components such as the front edge of the aircraft and the like must be carried out. Because hypersonic aircrafts can encounter severe pneumatic heating during working, the structural design and material selection of the aircrafts must meet the heat protection requirement.
In order to realize high-speed flight, the hypersonic aerocraft must keep a good aerodynamic shape, and a sharp structure is selected in stagnation point regions such as a nose cone and a wing leading edge of a nose cone of a nose body head. According to the aerodynamic principle, the aerodynamic heat of the structure is inversely proportional to the radius, namely the aerodynamic heating is more severe at the position than other positions, and the aerodynamic heating becomes a key position for heat prevention of the hypersonic aircraft. In order to ensure the overall performance of the hypersonic aircraft, the front edge of the aircraft is not allowed to deform greatly, so that the front edge must meet the performance requirements of long-time oxidation resistance, ablation resistance and the like.
The thermal protection mode of the hypersonic aircraft can be divided into three modes of passive heat protection, semi-passive heat protection and active heat protection. The passive thermal protection means that the purposes of structural cooling and heat insulation are realized by utilizing heat-resistant materials and heat-insulating materials, and the method generally comprises heat insulation, heat sink, radiation heat dissipation and the like. The heat insulation method is to coat the heat insulation structure on the outer layer of the aircraft structure, so that the pneumatic heat flow is insulated from the surface of the aircraft, the heat flow is reduced to enter the internal structure, and meanwhile, a part of energy is emitted through the radiation of the surface of the heat insulation layer, so that the aim of carrying out heat protection on the aircraft structure is fulfilled.
Under the background, researchers and engineers at home and abroad propose a scheme of coating a YSZ coating on the surface of a hot-end part of an aircraft to carry out thermal protection on the hot-end part. The YSZ coating has excellent mechanical property, good chemical stability, low thermal conductivity and better comprehensive performance, and is applied to a gas turbine engine on a large scale. In order to further improve the high-temperature stability and the heat insulation effect of the coating, researchers at home and abroad develop the multi-element rare earth oxide doping modification research based on YSZ, and a series of coating materials with lower thermal conductivity and better high-temperature stability are invented.
For the leading edge type parts containing the tip, the tip is most affected by pneumatic heating, so that the strategic significance of ensuring the appearance structure and further ensuring the pneumatic characteristic is very important, and when the surface coating is adopted to carry out thermal protection on the leading edge, the uniformity of the coating and the combination of the coating and a substrate are key indexes influencing the application effect of the coating. Under the influence of plasma flame flow (with a certain influence range), when the front edge side surface coating is prepared, the position of the tip end can not avoid depositing the coating, if the fixed position is adopted for regional spraying, the thickness of the coating at the superposed position is higher than that at other non-superposed positions, and meanwhile, the quality of the coating at the joint position can not be ensured; when the single mechanical arm is adopted for spraying, the uniform coating of the coating at the front edge tip position cannot be smoothly realized due to the limitation of the installation position of a spray gun, the size of a part to be sprayed and the like.
Disclosure of Invention
The invention aims to provide a preparation method of a pneumatic heating surface high-temperature-resistant instantaneous oxidation ablation-resistant coating, which aims to solve the technical problem of poor spraying uniformity of the existing tip position.
The invention provides a preparation method of a pneumatic heating surface high-temperature-resistant instantaneous oxidation ablation coating, which comprises the steps of obtaining the offset of the actual flame flow center of plasma and the physical center of a nozzle, adjusting the physical center track of the nozzle according to the offset and preparing the coating.
The preparation method of the pneumatic heating surface high-temperature-resistant instantaneous oxidation ablation coating has the beneficial effects that:
by obtaining the offset between the actual flame flow center of the plasma and the physical center of the nozzle, the actual highest accumulation position of the sprayed material on the surface of the material, namely the difference between the intersection point of the extension line of the nozzle and the surface of the material and the actual highest accumulation point, can be known in advance in the actual atmosphere plasma spraying process, and the spraying track can be adjusted in a targeted manner in advance, so that the error of the thickness of the sprayed coating caused by the fact that the actual accumulation position is deviated is avoided from being overlarge, particularly for the tip part, the situation that the coating material deviates from the surface of the part can be obviously reduced due to the fact that the deviation of the actual flame flow center of the plasma can cause that a considerable part of the coating material cannot fall on the surface of the part to be sprayed, and the uniformity of the thickness of the coating can be obviously improved.
In a preferred embodiment, the obtaining an offset between a center of an actual plasma flame flow and a physical center of a nozzle includes: and continuously spraying the sample to a fixed position, setting a reference surface by using a laser profiler, obtaining the appearance of a coating spot, and analyzing and determining the offset.
In a preferred embodiment, the sample is square or round.
In a preferred technical scheme, the physical center of the sample is located at the physical center of the nozzle, and the distance between the nozzle and the physical center is set as the spraying distance.
In a preferred technical solution, the adjusting the physical center trajectory of the nozzle and preparing the coating according to the offset includes: and spraying the tip part of the front edge part for three times, wherein one side surface of the tip part is gradually transited to the other side surface of the tip part.
In a preferred technical solution, the adjusting the physical center trajectory of the nozzle and preparing the coating according to the offset includes: and controlling the double manipulators to automatically spray the front edge parts.
In a preferred technical solution, the adjusting the physical center trajectory of the nozzle according to the offset and preparing the coating includes: a bonding layer, an 8YSZ coating and a multi-element rare earth oxide doped modified YSZ coating.
In the preferable technical scheme, in the process of adjusting the physical center track of the nozzle and preparing the coating according to the offset, the spraying current is 550A-650A, and the spraying voltage is 65V-75V.
In the preferable technical scheme, in the process of adjusting the physical center track of the nozzle and preparing the coating according to the offset, the spraying distance is set to be 65mm-105mm, and the spraying stepping length is set to be 3mm-5mm.
In an optimal technical scheme, the physical center track of the nozzle is adjusted according to the offset, and in the coating prepared, the flow rate of Ar of the main gas is 25L/min-35L/min, and the flow rate of the auxiliary gas is H 2 The flow rate is 80-100L/h, the powder feeding speed is 20-40 g/min, and the flow rate of the powder feeding carrier gas is 6-8L/min.
Drawings
In order to more clearly illustrate the technical solutions in the embodiments or the background art of the present invention, the drawings needed to be used in the description of the embodiments or the background art will be briefly introduced below, it is obvious that the drawings in the following description are only embodiments of the present invention, and for those skilled in the art, other drawings can be obtained according to the provided drawings without creative efforts.
FIG. 1 is a schematic flow chart of a method for preparing a pneumatic heating surface high-temperature-resistant instantaneous oxidation ablation-resistant coating according to an embodiment of the present invention;
FIG. 2 is a schematic diagram of the spraying of the tip portion in the method for preparing the pneumatic heating surface high temperature resistant instantaneous oxidation ablation coating according to the embodiment of the invention;
FIG. 3 is a graph showing the results of the topography scan obtained in example 1 in the method for preparing a pneumatic heating surface high temperature resistant instantaneous oxidation ablation coating according to an embodiment of the present invention;
FIG. 4 is a contour diagram of a topographically scanned coating obtained in example 1 of a method for preparing a pneumatic heated surface high temperature resistant transient oxide ablation resistant coating according to an embodiment of the present invention;
FIG. 5 is a graph of the results of topography scan obtained in example 2 of the method for preparing a pneumatic heated surface high temperature resistant instantaneous oxidation ablative coating of the present invention;
FIG. 6 is a contour diagram of a topographically scanned coating obtained in example 1 of a method for producing a pneumatically heated surface high temperature resistant transient oxide ablation resistant coating according to an embodiment of the present invention;
Detailed Description
In order to make the aforementioned objects, features and advantages of the present invention comprehensible, embodiments accompanied with figures are described in detail below. It should be understood that the specific embodiments described herein are merely illustrative of the invention and are not intended to limit the invention.
Fig. 1 is a schematic flow chart of a method for preparing a pneumatic heating surface high-temperature-resistant instantaneous oxidation ablation-resistant coating according to an embodiment of the invention. As shown in FIG. 1, the method for preparing the high-temperature-resistant instantaneous oxidation ablation-resistant coating on the pneumatic heating surface provided by the embodiment of the invention comprises the steps of obtaining the offset between the actual flame flow center of the plasma and the physical center of the nozzle, adjusting the track of the physical center of the nozzle according to the offset, and preparing the coating.
The nozzle physical center is that a tool with a fixed length and a tip end is inserted into a nozzle, wherein the fixed length is a spraying distance, and the tip end is the nozzle physical center. The center of the plasma actual flame flow is the center of the thickest point of the coating sprayed onto the sample, or the area of greatest coating thickness. The relative difference between the physical center of the nozzle and the vertical projection of the plasma actual flame flow center on the surface of the sprayed sample is the offset.
Specifically, the offset amount includes not only the absolute distance between the plasma actual flame flow center and the physical center of the nozzle but also the relative direction of the plasma actual flame flow center with respect to the physical center of the nozzle, so that it is more advantageous to obtain the offset condition at the time of plasma spraying so as to perform reverse compensation in advance in the trajectory of the spraying.
By obtaining the offset between the actual flame flow center of the plasma and the physical center of the nozzle, the actual highest accumulation position of the sprayed material on the surface of the material, namely the difference between the intersection point of the extension line of the nozzle and the surface of the material and the actual highest accumulation point, can be known in advance in the actual atmosphere plasma spraying process, and the spraying track can be adjusted in a targeted manner in advance, so that the error of the thickness of the sprayed coating caused by the fact that the actual accumulation position is deviated is avoided from being overlarge, particularly for the tip part, the situation that the coating material deviates from the surface of the part can be obviously reduced due to the fact that the deviation of the actual flame flow center of the plasma can cause that a considerable part of the coating material cannot fall on the surface of the part to be sprayed, and the uniformity of the thickness of the coating can be obviously improved.
Preferably, obtaining the offset of the plasma actual flame flow center from the nozzle physical center comprises: continuously spraying the sample at a fixed position, setting a reference surface by using a laser profiler, obtaining the spot morphology of the coating, and analyzing and determining the offset.
Specifically, taking the sample surface as a plane, the reference plane may coincide with the sample surface.
By continuously spraying the sample to a fixed position, the accumulation center position of the actual spraying material can be ensured not to shake, the continuously sprayed material can be accumulated at the same position along with the time, and the height difference of the peripheral part can also sufficiently reflect the difference of the accumulation speed, thereby being convenient for controlling the track of the nozzle. And with the laser profilometer, the surface appearance of the sample after spraying can be known more accurately, thereby being beneficial to knowing the position of the highest point and the peripheral position of the highest point, being beneficial to providing a more comprehensive and accurate data base for the planning of the spraying track and leading the whole spraying to be more uniform.
As shown in fig. 1, the sample is preferably square or circular.
The sample is selected to be in an axial symmetry or central symmetry pattern of a circle or a square, and no matter which side of the actual flame flow center of the plasma to the physical center of the nozzle is cheap, more surface space is provided for the accumulation of the spraying material on the surface of the sample, so that a more complete accumulation appearance is formed, and the whole pattern of the coating impact area is favorably obtained.
As shown in fig. 1, it is preferable that the physical center of the sample is located at the physical center of the nozzle, and the nozzle is located at a set spray distance from the physical center.
The physical center of the sample is coincided with that of the nozzle, namely the nozzle is away from the physical center by a set spraying distance, so that the condition of actual atmospheric plasma spraying can be completely simulated, the obtained offset has a great reference significance to the actual spraying, the precision of track planning is improved, and the uniformity of the coating and the utilization rate of materials are further improved.
As shown in fig. 1 and 2, preferably, adjusting the physical center trajectory of the nozzle according to the offset and preparing the coating includes: and the tip part of the front edge part is sprayed for three times, and one side surface of the tip part is gradually transited to the other side surface of the tip part.
For the tip part of the front edge part, namely the part with smaller curvature radius, three-pass spraying is adopted, namely the spraying is respectively carried out along the angular bisector position of the tip part and from the two side surfaces of the front edge part, so that the thickness of each area of the tip part can be uniform, and the coating quality of the front edge part is improved.
As shown in fig. 2, preferably, adjusting the physical center trajectory of the nozzle according to the offset and preparing the coating includes: and controlling the double manipulators to automatically spray the front edge parts.
Specifically, as shown in FIG. 2, the three arrows shown in the figure as spraying the part from the left and right sides do not represent that the spraying from that direction is absolutely 3 passes. The three arrows from below towards the tip region in the figure indicate that the spraying is performed in three passes, namely, straight upward, left-down-right-up, and right-down-left-up.
By adopting the double manipulators, the spraying can be carried out from two surfaces of the front edge part, each pass is gradually close to the tip part, and the coating uniformity of the adjacent surfaces of the tip part is improved.
Preferably, the physical center locus of the nozzle is adjusted according to the offset, and the coating is prepared, wherein the coating comprises: a bonding layer, an 8YSZ coating and a multi-element rare earth oxide doped modified YSZ coating (namely RE-YSZ).
Preferably, the physical center track of the nozzle is adjusted according to the offset, and the spraying current is 550A-650A, and the spraying voltage is 65V-75V in the process of preparing the coating.
Preferably, the physical center track of the nozzle is adjusted according to the offset, and in the preparation of the coating, the spraying distance is set to be 65mm-105mm, and the spraying stepping length is set to be 3mm-5mm.
Preferably, the physical center track of the nozzle is adjusted according to the offset, and in the coating preparation, the flow rate of the main gas Ar is 25L/min-35L/min, and the auxiliary gas H 2 The flow rate is 80L/h-100L/h, the powder feeding speed is 20g/min-40g/min, and the flow rate of the powder feeding carrier gas is 6L/min-8L/min.
The flow of the preparation method of the pneumatic heating surface high-temperature-resistant instantaneous oxidation ablation coating is shown in figure 1, and specifically comprises the following steps:
s1, adopting an atmospheric plasma spraying process, adapting different powder materials to continuously spray a square sample at a fixed position, wherein in the spraying process, the physical center of a nozzle is superposed with the physical center of the square sample, and the distance between the surface of the nozzle and the physical center of the square sample is equal to the set spraying distance;
specifically, the spraying parameters are 550A-650A, and the spraying voltage is 65V-75V; setting the spraying distance to be 65-105 mm; main gas Ar flow rate is 25-35L/min, auxiliary gas H 2 The flow rate is 80-100L/h, the powder feeding speed is 20-40 g/min, and the flow rate of the powder feeding carrier gas is 6-8L/min.
S2, setting a reference surface by using a laser profiler to obtain the appearance of the coating spots;
s3, deriving original data of the morphology, and analyzing and determining the offset of the plasma flame flow center relative to the physical center of the nozzle;
s4, combining the offset to finish the automatic spraying programming of the front edge parts;
and S5, preparing a coating, wherein the spraying parameters are the same as those in the step S1, and the spraying step length is 3-5 mm. And (3) flexible automatic spraying by two manipulators, reserving a programming allowance according to the offset when programming an automatic spraying program, continuously spraying the side surface of the front edge and the position of the tip, smoothly transiting from one side surface to the other side surface through the tip, wherein the position near the tip is sprayed for three times, and respectively spraying one time on one side surface, the position right opposite to the tip and the other side surface, so as to ensure the smooth transition and the thickness uniformity of the coating.
The preparation method has the following beneficial effects:
1. rapidly and accurately determining the offset of the actual flame flow center of the plasma relative to the physical center of the nozzle outlet, and guiding the point position correction amount during automatic spraying programming;
2. continuous spraying and smooth transition of different spraying surfaces of the part to be sprayed are realized through flexible linkage spraying of the double manipulators, high-precision processing and thickness control of the part coating are realized, and the uniformity of the coating thickness reaches +/-50 microns;
3. the technology quantifies the deviation of the spraying flame flow, has low requirements on field operators, and can determine the flame flow deviation by the operation process determined by technicians according to the fixed point position continuous spraying, one-dimensional shape scanning and data comparison of the process, thereby guiding the automatic spraying programming;
4. the technology is flexible, offset confirmation can be quickly completed after the spray gun and the powder material are replaced, and effective guidance is provided for improving the thickness control of the spraying coating of the front-edge parts;
5. the high-temperature oxidation ablation resistant coating prepared by the invention can resist scouring and ablation for more than 2000s under the simulated high-speed oxygen-kerosene flame condition, the coating and parts are kept in good condition, and the coating can be used for protecting tip hot end parts such as the front edge of a hypersonic aircraft and the like.
To illustrate the methods of the invention, the following examples are set forth:
example 1:
s1, adopting an atmospheric plasma spraying process, adapting different powder materials to continuously spray a square sample at a fixed position, wherein in the spraying process, the physical center of a nozzle is superposed with the physical center of the square sample, and the distance between the surface of the nozzle and the physical center of the square sample is equal to the set spraying distance;
specifically, the spraying parameter is 650A, and the spraying voltage is 75V; setting the spraying distance to be 65mm; main Ar flow 25L/min, auxiliary H 2 The flow rate is 80L/h, the powder feeding speed is 20g/min, and the flow rate of the powder feeding carrier gas is 6L/min.
S2, setting a reference surface by using a laser profiler to obtain the appearance of the coating spots; the obtained topography scan results are shown in fig. 3, and the obtained contour map of the coating is shown in fig. 4;
s3, deriving original data of the morphology, and analyzing and determining the offset of the plasma flame flow center relative to the physical center of the nozzle; the specific offset is: the X direction is deviated by-2.44 mm and the Y direction is deviated by-5.85 mm;
s4, combining the offset to finish the automatic spraying programming of the front edge parts;
and S5, preparing a coating, wherein the spraying parameters are the same as those in the step S1, and the spraying step length is 3-5 mm. And (3) flexible automatic spraying by two manipulators, reserving a programming allowance according to the offset when programming an automatic spraying program, continuously spraying the side surface of the front edge and the position of the tip, smoothly transiting from one side surface to the other side surface through the tip, wherein the position near the tip is sprayed for three times, and respectively spraying one time on one side surface, the position right opposite to the tip and the other side surface, so as to ensure the smooth transition and the thickness uniformity of the coating.
Example 2:
s1, adopting an atmospheric plasma spraying process, adapting different powder materials to continuously spray a square sample at a fixed position, wherein in the spraying process, the physical center of a nozzle is superposed with the physical center of the square sample, and the distance between the surface of the nozzle and the physical center of the square sample is equal to the set spraying distance;
specifically, the spraying parameter is 550A, and the spraying voltage is 65V; setting the spraying distance to be 105mm; main gas Ar flow 35L/min, auxiliary gas H 2 The flow rate is 100L/h, the powder feeding speed is 40g/min, and the flow rate of the powder feeding carrier gas is 8L/min.
S2, setting a reference surface by using a laser profiler to obtain the appearance of the coating spots; the obtained profile scanning result is shown in fig. 5, and the obtained coating contour map is shown in fig. 6, wherein it should be noted that the upper left and lower right positions of the highest position in fig. 6 are gray due to the dense contour lines, and the areas between the contour lines are not gray;
s3, deriving original data of the morphology, and analyzing and determining the offset of the plasma flame flow center relative to the physical center of the nozzle; the specific offset is: the X direction is deviated by-6.36 mm and the Y direction is deviated by-8.20 mm;
s4, combining the offset to finish the automatic spraying programming of the front edge parts;
and S5, preparing a coating, wherein the spraying parameters are the same as those in the step S1, and the spraying step length is 3-5 mm. And (3) flexible automatic spraying by two manipulators, reserving a programming allowance according to the offset when programming an automatic spraying program, continuously spraying the side surface of the front edge and the position of the tip, smoothly transiting from one side surface to the other side surface through the tip, wherein the position near the tip is sprayed for three times, and respectively spraying one time on one side surface, the position right opposite to the tip and the other side surface, so as to ensure the smooth transition and the thickness uniformity of the coating.
Although the present invention is disclosed above, the present invention is not limited thereto. Various changes and modifications may be effected therein by one skilled in the art without departing from the spirit and scope of the invention as defined in the appended claims.
Finally, it should also be noted that, herein, relational terms such as first and second, and the like may be used solely to distinguish one entity or action from another entity or action without necessarily requiring or implying any actual such relationship or order between such entities or actions. Also, the terms "comprises," "comprising," or any other variation thereof, are intended to cover a non-exclusive inclusion, such that a process, method, article, or apparatus that comprises a list of elements does not include only those elements but may include other elements not expressly listed or inherent to such process, method, article, or apparatus. Without further limitation, an element defined by the phrases "comprising a," "...," or "comprising" does not exclude the presence of additional like elements in a process, method, article, or apparatus that comprises the element.
In the above embodiments, the descriptions of the orientations such as "up", "down", etc. are based on the drawings.
The previous description of the disclosed embodiments is provided to enable any person skilled in the art to make or use the present invention. Various modifications to these embodiments will be readily apparent to those skilled in the art, and the generic principles defined herein may be applied to other embodiments without departing from the spirit or scope of the invention.
Thus, the present invention is not intended to be limited to the embodiments shown herein but is to be accorded the widest scope consistent with the principles and novel features disclosed herein.
Claims (10)
1. A preparation method of a pneumatic heating surface high-temperature-resistant instantaneous oxidation ablation coating is characterized by comprising the following steps: and acquiring the offset of the actual plasma flame flow center and the physical center of the nozzle, adjusting the track of the physical center of the nozzle according to the offset, and preparing the coating.
2. The method for preparing the high-temperature-resistant instantaneous oxidation ablation coating on the pneumatic heating surface according to claim 1, wherein the step of obtaining the offset of the actual plasma flame flow center and the physical center of the nozzle comprises the following steps: and continuously spraying the sample to a fixed position, setting a reference surface by using a laser profiler, obtaining the appearance of a coating spot, and analyzing and determining the offset.
3. The method for preparing the high-temperature-resistant instantaneous oxidation ablation coating of the pneumatic heating surface according to claim 2, characterized in that the sample is square or round.
4. The method for preparing a high temperature transient oxidative ablation resistant coating for a pneumatically heated surface as claimed in claim 3, wherein the physical center of said sample is located at the physical center of said nozzle, said nozzle being located at a set spray distance from said physical center.
5. The method for preparing the pneumatic heating surface high-temperature-resistant instantaneous oxidation ablation coating according to claim 1, wherein the adjusting the physical center track of the nozzle according to the offset and preparing the coating comprises the following steps of: and spraying the tip part of the front edge part for three times, wherein one side surface of the tip part is gradually transited to the other side surface of the tip part.
6. The method for preparing the pneumatic heating surface high temperature transient oxidation ablation resistant coating according to claim 5, wherein the adjusting the physical center track of the nozzle according to the offset and preparing the coating comprises: and controlling the double manipulators to automatically spray the front edge parts.
7. The method for preparing a pneumatic heating surface high temperature transient oxidative ablation resistant coating according to claim 1, wherein the adjusting of the nozzle physical center trajectory according to the offset and preparing the coating comprises: a bonding layer, an 8YSZ coating and a multi-element rare earth oxide doped modified YSZ coating.
8. The method for preparing the coating with the pneumatically-heated surface resistant to the high-temperature instantaneous oxidative ablation according to claim 7, wherein the spraying current is 550A-650A and the spraying voltage is 65V-75V in the process of adjusting the physical center track of the nozzle according to the offset and preparing the coating.
9. The method for preparing the high-temperature-resistant instantaneous oxidation ablation coating on the pneumatic heating surface according to the claim 1, wherein in the step of adjusting the physical center track of the nozzle according to the offset and preparing the coating, the spraying distance is set to be 65mm-105mm, and the spraying step length is set to be 3mm-5mm.
10. The method for preparing the high-temperature-resistant instantaneous oxidation ablation coating on the pneumatic heating surface according to claim 1, wherein in the process of adjusting the physical center track of the nozzle according to the offset and preparing the coating, the flow rate of the main gas Ar is 25L/min-35L/min, and the auxiliary gas H is 2 The flow rate is 80L/h-100L/h, the powder feeding speed is 20g/min-40g/min, and the flow rate of the powder feeding carrier gas is 6L/min-8L/min.
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Citations (11)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPH03275230A (en) * | 1990-03-23 | 1991-12-05 | Komatsu Ltd | Method and apparatus for positioning work in composite working machine |
| CN1531464A (en) * | 2000-09-29 | 2004-09-22 | Լɪ�������� | Device for applying adhesive to workpiece |
| CN104233178A (en) * | 2014-09-21 | 2014-12-24 | 北京金轮坤天科技发展有限公司 | Automatic preparation method of long-service-life cylinder-like crystal structural thermal barrier coating on surface of guide blade of hot end part of fuel machine |
| CN104674217A (en) * | 2015-03-09 | 2015-06-03 | 河南普莱姆涂层科技有限公司 | Preparation method of thermal barrier coating containing bilayer structure of bonding layers |
| CN105652797A (en) * | 2016-01-06 | 2016-06-08 | 广东工业大学 | Real-time monitoring device and real-time monitoring method of surface flow water film |
| CN106380210A (en) * | 2016-08-26 | 2017-02-08 | 中国农业机械化科学研究院 | Multi-component rare earth oxide-doped modified YSZ thermal spraying powder and preparation method thereof |
| CN112176274A (en) * | 2020-10-13 | 2021-01-05 | 洛阳轴承研究所有限公司 | Track calibration method for thermal spraying spray gun and bearing spraying method |
| CN112184820A (en) * | 2020-12-02 | 2021-01-05 | 中国航空制造技术研究院 | Laser double-sided shot blasting spot positioning method and system and computer readable storage medium |
| CN112359312A (en) * | 2020-10-23 | 2021-02-12 | 航天材料及工艺研究所 | High-temperature oxidation-resistant coating on surface of wing structural member and low-pressure plasma spraying preparation method thereof |
| CN113388801A (en) * | 2021-06-18 | 2021-09-14 | 北京理工大学 | Thermal barrier coating with composite double-ceramic-layer structure and preparation method thereof |
| CN114411082A (en) * | 2022-01-20 | 2022-04-29 | 矿冶科技集团有限公司 | Thermal barrier coating, heat-resistant material, preparation method of heat-resistant material and engine |
-
2022
- 2022-12-12 CN CN202211589201.0A patent/CN115976451A/en active Pending
Patent Citations (11)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPH03275230A (en) * | 1990-03-23 | 1991-12-05 | Komatsu Ltd | Method and apparatus for positioning work in composite working machine |
| CN1531464A (en) * | 2000-09-29 | 2004-09-22 | Լɪ�������� | Device for applying adhesive to workpiece |
| CN104233178A (en) * | 2014-09-21 | 2014-12-24 | 北京金轮坤天科技发展有限公司 | Automatic preparation method of long-service-life cylinder-like crystal structural thermal barrier coating on surface of guide blade of hot end part of fuel machine |
| CN104674217A (en) * | 2015-03-09 | 2015-06-03 | 河南普莱姆涂层科技有限公司 | Preparation method of thermal barrier coating containing bilayer structure of bonding layers |
| CN105652797A (en) * | 2016-01-06 | 2016-06-08 | 广东工业大学 | Real-time monitoring device and real-time monitoring method of surface flow water film |
| CN106380210A (en) * | 2016-08-26 | 2017-02-08 | 中国农业机械化科学研究院 | Multi-component rare earth oxide-doped modified YSZ thermal spraying powder and preparation method thereof |
| CN112176274A (en) * | 2020-10-13 | 2021-01-05 | 洛阳轴承研究所有限公司 | Track calibration method for thermal spraying spray gun and bearing spraying method |
| CN112359312A (en) * | 2020-10-23 | 2021-02-12 | 航天材料及工艺研究所 | High-temperature oxidation-resistant coating on surface of wing structural member and low-pressure plasma spraying preparation method thereof |
| CN112184820A (en) * | 2020-12-02 | 2021-01-05 | 中国航空制造技术研究院 | Laser double-sided shot blasting spot positioning method and system and computer readable storage medium |
| CN113388801A (en) * | 2021-06-18 | 2021-09-14 | 北京理工大学 | Thermal barrier coating with composite double-ceramic-layer structure and preparation method thereof |
| CN114411082A (en) * | 2022-01-20 | 2022-04-29 | 矿冶科技集团有限公司 | Thermal barrier coating, heat-resistant material, preparation method of heat-resistant material and engine |
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