A method for anti-environmental corrosion of thermal barrier coating treated by laser composite pre-sintering

Abstract

The present invention provides a method for resisting environmental corrosion of a thermal barrier coating by laser composite pre-sintering treatment, comprising the following steps: Step S1, determining the critical power density P required for the surface of the thermal barrier coating to start melting m , and determining the critical power density P required for the surface of the thermal barrier coating to start gasification v ; Step S2, performing the first glazing on the surface of the thermal barrier coating with a high-energy pulsed laser at a power density P1: 1 / 2(P m + P v ); Step S3, performing the second glazing on the surface of the thermal barrier coating with a high-energy pulsed laser at a power density P2: 1 / 2(P m + P1); Step S4, performing the nth glazing on the surface of the thermal barrier coating with a high-energy pulsed laser at a power density P n : 1 / 2(P m + P n‑1 ), where n = 2, 3, 4..., until the width of the surface microcracks < 1 μm, and then stopping the glazing; Step S5, placing the glazed thermal barrier coating in a muffle furnace for pre-sintering to form a sintered layer. The method of the present invention reduces the surface roughness of the thermal barrier coating, improves its hardness and strain tolerance, and eliminates the cracks formed during the traditional laser glazing process.

Description

Technical Field

[0001] The invention relates to the field of aerospace precision machining, and in particular to a method for treating a thermal barrier coating against environmental corrosion by laser composite pre-sintering. Background Art

[0002] In order to improve the thrust and fuel thermal efficiency of aircraft engines, the temperature of the combustion chamber must be greatly increased. Due to the limited thermal load capacity of nickel-based high-temperature alloys (<1150℃), thermal barrier coatings are usually used to provide thermal protection (>1300℃) to increase the service life of key components. However, during service, impurities in the fuel and dust in the atmosphere will be deposited on the surface of the thermal barrier coating and melt at high temperatures to form molten salts, which penetrate through surface defects such as cracks and pits, causing the coating material to undergo phase change failure. Improving the thermal barrier coating's resistance to molten salt erosion has become a top priority in this field.

[0003] At present, the commonly used protection methods include using a more acidic stabilizer to prevent the phase change of zirconia in thermal barrier coating materials, or preparing a sacrificial layer on the surface of the original coating to protect the bottom by preferentially reacting with corrosive substances such as vanadium salts, CMAS and salt spray to reduce their concentration. Although these methods can effectively block the rapid penetration of corrosive substances, due to the change in material properties, its fracture toughness is far inferior to that of the original yttria-stabilized zirconia. Based on this, laser surface glazing technology came into being. On the basis of not changing the original composition of the coating, laser irradiation makes the surface of the thermal barrier coating more dense, eliminates micro-protrusions, micro-pits, and cracks, and greatly reduces the permeability of molten salt. However, in the traditional glazing process, in order to pursue a thicker glazing layer, the huge local thermal stress causes extremely wide cracks (>10μm) to appear inside it. Under the action of the short plate effect, the molten salt that quickly penetrates along the cracks causes a phase change inside the thermal barrier coating material, which eventually leads to the failure of the coating to peel off. Summary of the invention

[0004] In view of the above technical problems, the present invention provides a method for treating environmental corrosion of thermal barrier coatings by laser composite pre-sintering, so as to reduce the surface roughness of the thermal barrier coating, improve its hardness and strain tolerance, and eliminate cracks formed in the traditional laser glazing process.

[0005] Note that the description of these objects does not prevent the existence of other objects. The present invention can extract objects other than the above objects from the description of the specification, drawings, and claims.

[0006] The present invention uses a high-power laser to glaze the surface of the thermal barrier coating by using a high-energy pulse laser to remove micro-protrusions and pits on the surface and reduce the surface roughness. Then, the laser is used to perform gradient energy glazing on the glazed layer layer by layer, and the cracks are narrowed layer by layer in the glazed layer until they are less than 1 μm. Finally, the glazed thermal barrier coating is placed in a Ma Fuel furnace for pre-sintering, so that the ultra-narrow cracks on the surface of the glazed layer are self-healed to form a complete and dense glazed layer. The dense glazed layer prepared by the present invention, i.e., the sintered layer, can effectively prevent environmental corrosion such as vanadium salts, calcium magnesium aluminum silicate (CMAS), salt spray, and particle erosion.

[0007] The present invention achieves the above technical objectives through the following technical means.

[0008] A method for treating a thermal barrier coating against environmental corrosion by laser composite pre-sintering, comprising the following steps:

[0009] Step S1: Determine the critical power density P required for the thermal barrier coating surface to begin melting m , determine the critical power density P required for the thermal barrier coating surface to begin vaporization v ;

[0010] Step S2: high energy pulse laser with power density P1: 1 / 2 (P m +P v ) performing the first glazing on the surface of the thermal barrier coating;

[0011] Step S3: high energy pulse laser with power density P2: 1 / 2 (P m +P1) performing a second glazing on the surface of the thermal barrier coating;

[0012] Step S4: high energy pulse laser with power density P n :1 / 2(P m +P n-1 ), where n = 2, 3, 4, ..., the surface of the thermal barrier coating is glazed for the nth time until the width of the surface microcrack is less than 1 μm, and the glazing is stopped;

[0013] Step S5: placing the glazed thermal barrier coating in a muffle furnace for pre-sintering to form a sintered layer.

[0014] In the above solution, the thermal barrier coating is provided with ceramic material.

[0015] Preferably, the ceramic material is a mixed material of one or more of yttria-stabilized zirconia, gadolinium zirconate, and gadolinium tantalate, but is not limited thereto.

[0016] In the above scheme, the thermal barrier coating is prepared by atmospheric plasma spraying, electron beam physical vapor deposition or plasma physical vapor deposition.

[0017] In the above scheme, the pulse width of the high energy pulse laser is in the range of 2-30ns, the frequency is in the range of 2-4MHz, and the power density is in the range of 10 3 -10 4 GW / cm 2 , scanning speed is 100-500mm / s.

[0018] Preferably, the pulse width of the high energy pulse laser is 2 ns, the frequency is 2 MHz, and the power density is 1.99×10 3 GW / cm 2 , the scanning speed is 500mm / s.

[0019] Preferably, the pulse width of the high energy pulse laser is 7 ns, the frequency is 1.5 MHz, and the power density is 2.36×10 3 GW / cm 2 , scanning speed is 350mm / s.

[0020] Preferably, the pulse width range of the high energy pulse laser is 4 ns, the frequency is 4 MHz, and the power density is 1.76×10 3 GW / cm 2 , the scanning speed is 400mm / s.

[0021] In the above scheme, the temperature range of the Ma Fuel is 1000-1100° C., and the pre-sintering time is 0.5-1 h.

[0022] Preferably, the temperature in the Ma Fei furnace is 1000° C., and the pre-sintering time is 1 hour; or the temperature in the Ma Fei furnace is 1100° C., and the pre-sintering time is 1 hour; or the temperature in the Ma Fei furnace is 1000° C., and the pre-sintering time is 0.5 hour.

[0023] The working principle of the present invention is that the surface of the thermal barrier coating is rapidly melted and solidified under the irradiation of a high-energy pulsed laser to form a glazed layer. However, due to the large height difference between the micro-pits and micro-protrusions on the initial surface of the thermal barrier coating, the laser energy required for the initial glazing is relatively high, and the crack width formed during the cooling process is relatively large. The present invention uses multiple gradient energy laser glazing of the thermal barrier coating to reduce the crack width of the glazed layer layer by layer. When the crack width is less than <1μm, the glazing is stopped and a pre-sintering treatment is performed. During the sintering process of the thermal barrier coating material, the grains on both sides of the crack will gradually grow and approach each other. When the crack width is <1μm, the crack self-healing phenomenon will be achieved. Therefore, after pre-sintering, there will be no cracks on the surface of the thermal barrier coating glazed by gradient energy laser, and the channels for rapid penetration of corrosive substances such as vanadium salts, CMAS, and salt spray will be completely eliminated. If gradient energy glazing is not performed, the excessive crack width formed after the first glazing exceeds the grain growth limit, and the self-healing effect cannot be achieved.

[0024] Compared with the prior art, the present invention has the following beneficial effects:

[0025] The present invention greatly reduces the surface roughness of the thermal barrier coating, reduces the contact area and thermochemical reaction with corrosive substances such as vanadium salts, CMAS and salt spray; the present invention completely eliminates crack defects on the surface of the coating, and delays the rapid penetration of corrosive substances such as vanadium salts, CMAS and salt spray; the surface cracks of the glazed layer of the present invention are staggered, which prolongs the internal penetration path of corrosive substances such as vanadium salts, CMAS and salt spray after the crystal infiltration, thereby delaying corrosion; the longitudinal cracks inside the glazed layer of the present invention improve the strain tolerance of the thermal barrier coating and improve its thermal shock resistance; as the energy of the high-energy pulse laser is reduced layer by layer, the cooling rate of the glazed layer is increased layer by layer, and its grains are also refined layer by layer. Compared with the surface of the first glazing, the surface hardness and particle erosion resistance of the final thermal barrier coating are greatly improved.

[0026] Note that the description of these effects does not prevent the existence of other effects. One embodiment of the present invention does not necessarily have all of the above effects. Effects other than the above can be clearly seen and extracted from the description of the specification, drawings, claims, etc. BRIEF DESCRIPTION OF THE DRAWINGS

[0027] Figure 1 This is a schematic diagram of a method for treating environmental corrosion of a thermal barrier coating by laser composite pre-sintering in one embodiment; wherein (a) is a cross section of the original thermal barrier coating, (b) is a cross section of the thermal barrier coating after the first laser glazing, (c) is a cross section of the thermal barrier coating after the second laser glazing, (d) is a cross section of the thermal barrier coating after the third laser glazing, (e) is a cross section of the thermal barrier coating after the Nth laser glazing, and (f) is a cross section of the pre-sintered thermal barrier coating after laser glazing.

[0028] In the figure: 1. Thermal barrier coating; 2. Micro pits; 3. Micro protrusions; 4. Cracks; 5. Unmelted particles; 6. Glaze layer; 7. High-energy pulse laser; 8. Sintered layer. DETAILED DESCRIPTION

[0029] Embodiments of the present invention are described in detail below, examples of which are shown in the accompanying drawings, wherein the same or similar reference numerals throughout represent the same or similar elements or elements having the same or similar functions. The embodiments described below with reference to the accompanying drawings are exemplary and are intended to be used to explain the present invention, and should not be construed as limiting the present invention.

[0030] The present invention provides a method for treating thermal barrier coatings with laser composite pre-sintering to resist environmental corrosion. Figure 1 As shown,

[0031] The method for treating the thermal barrier coating against environmental corrosion by laser composite pre-sintering comprises the following steps:

[0032] Step S1: Determine the critical power density P required for the thermal barrier coating surface to begin meltingm , determine the critical power density P required for the thermal barrier coating surface to begin vaporization v ;

[0033] Step S2: high energy pulse laser with power density P1: 1 / 2 (P m +P v ) performing the first glazing on the surface of the thermal barrier coating;

[0034] Step S3: high energy pulse laser with power density P2: 1 / 2 (P m +P1) performing a second glazing on the surface of the thermal barrier coating;

[0035] Step S4: high energy pulse laser with power density P n :1 / 2(P m +P n-1 ), where n = 2, 3, 4, ..., the surface of the thermal barrier coating is glazed for the nth time until the width of the surface microcrack is less than 1 μm, and the glazing is stopped;

[0036] Step S5: placing the glazed thermal barrier coating in a muffle furnace for pre-sintering.

[0037] The thermal barrier coating is provided with a ceramic material. Preferably, the ceramic material is a mixed material of one or more of yttria-stabilized zirconia, gadolinium zirconate, and gadolinium tantalate, but is not limited thereto.

[0038] The thermal barrier coating is prepared by atmospheric plasma spraying, electron beam physical vapor deposition or plasma physical vapor deposition, but is not limited thereto.

[0039] Preferably, the pulse width of the high energy pulse laser is in the range of 2-30 ns, the frequency is in the range of 2-4 MHz, and the power density is in the range of 10 3 -10 4 GW / cm 2 , scanning speed is 100-500mm / s.

[0040] Preferably, the temperature in the Ma Fuel Furnace ranges from 1000 to 1100° C., and the pre-sintering time is from 0.5 to 1 h.

[0041] Figure 1 (a) is the cross section of the original thermal barrier coating. There are micro pits 2, micro protrusions 3, cracks 4, and unmelted particles 5 on the thermal barrier coating 1; Figure 1 (b) is a cross section of the thermal barrier coating after the first laser glazing by a high-energy pulse laser 7, with a glazing layer 6; Figure 1 (c) is the cross section of the thermal barrier coating after the second laser glazing. Figure 1 (d) is the cross section of the thermal barrier coating after the third laser glazing. Figure 1 (e) is the cross section of the thermal barrier coating after the Nth laser glazing. Figure 1 (f) is a cross section of a pre-sintered thermal barrier coating after laser glazing, which has a sintered layer 8. The sintered layer 8 is formed by pre-sintering the glazed thermal barrier coating in a furnace.

[0042] Example 1

[0043] In this example, the pulse width of the high-energy pulse laser 7 is 2ns, the frequency is 2MHz, the laser spot diameter is 25μm, and the line spacing is 12μm. The thermal barrier coating 1 is yttria-stabilized zirconia, and the preparation process is atmospheric plasma spraying. It is found through experiments that when the scanning speed is 500mm / s, the laser power is P m :1.7×10 3 GW / cm 2 When the coating surface begins to melt, the power is P v :6.4×10 3 GW / cm 2 Therefore, when the laser power is 4.05×10 3 GW / cm 2 The surface was glazed and then 2.88×10 3 GW / cm 2 , 2.29×10 3 GW / cm 2 , 1.99×10 3 GW / cm 2 ...gradient glazing is performed on its surface. Through electron microscope observation, it is found that the material has a high 3 GW / cm 2 At this time, the width of the micro-cracks in the surface glaze layer is less than 1 μm. The glazed thermal barrier coating is then placed in a Ma-boiling furnace and kept at 1000°C for 1 hour to completely eliminate the surface cracks and form a flat and dense sintered layer 8.

[0044] The treated thermal barrier coating 1 and the original thermal barrier coating were coated with CMAS and placed in a furnace for a thermal corrosion test at 1250°C for 20 hours. The results showed that the penetration depth of the treated thermal barrier coating CMAS was only 4μm, while the penetration depth of the original thermal barrier coating was as high as 40μm.

[0045] The treated thermal barrier coating 1 and the original thermal barrier coating were subjected to thermal shock tests. The samples were placed in a furnace at 1100°C for 5 minutes, air-cooled for 5 minutes, and the surface was observed every 100 cycles. 60% peeling was considered as coating failure. According to experimental tests, the original thermal barrier coating can withstand 8547 impacts, while the treated thermal barrier coating 1 can withstand 10254 impacts.

[0046] The treated thermal barrier coating 1 and the original thermal barrier coating were subjected to hardness and friction and wear tests. The results showed that the surface hardness of the original sample was 598HV, the surface hardness of the thermal barrier coating after the first glazing was 680HV, and the surface hardness of the thermal barrier coating after the last glazing was 802HV, and the hardness after pre-sintering was 780HV. Polygonal alumina particles with an average particle size of 20μm were used. After 120s of erosion, the original thermal barrier coating lost 120mg of mass, and the treated thermal barrier coating lost 20mg of mass.

[0047] Example 2

[0048] In this example, the pulse width of the high-energy pulse laser 7 is 7ns, the frequency is 3MHz, the laser spot diameter is 25μm, and the line spacing is 12μm. The thermal barrier coating 1 is gadolinium zirconate, and the preparation process is electron beam physical vapor deposition. It is found through experiments that when the scanning speed is 350mm / s, the laser power is P m :2.1×10 3 GW / cm 2 When the coating surface begins to melt, the power is P v :6.3×10 3 GW / cm 2 Therefore, when the laser power is 4.2×10 3 GW / cm 2 The surface was glazed and then 3.15×10 3 GW / cm 2 , 2.63×10 3 GW / cm 2 ...gradient glazing is performed on its surface. Through electron microscope observation, it is found that the material has a laser power of 2.36×10 3 GW / cm 2 At this time, the width of the micro-cracks in the surface glaze layer is less than 1 μm. The glazed thermal barrier coating is then placed in a Ma-boiling furnace and kept at 1100°C for 1 hour to completely eliminate the surface cracks and form a flat and dense sintered layer 8.

[0049] The treated thermal barrier coating and the original thermal barrier coating were coated with V2O5+Na2SO4 mixed salt and placed in a Mabo furnace for a thermal corrosion test at 1100℃ for 20 hours. The results showed that the molten salt penetration depth of the treated thermal barrier coating was only 6.8μm, while the original one had penetrated to the bottom of the coating.

[0050] The treated thermal barrier coating and the original thermal barrier coating were subjected to salt spray corrosion test. The samples were placed in an environment containing air, NaCl and water vapor at 1050℃, the carrier gas flow was set to 100ml / min for 55min, and air-cooled for 5min. 30% peeling was considered as thermal barrier coating failure. According to experimental tests, the original thermal barrier coating can withstand 39 cycles, while the treated thermal barrier coating can withstand 74 cycles.

[0051] The treated thermal barrier coating and the original thermal barrier coating were subjected to hardness and friction and wear tests. The results showed that the surface hardness of the original sample was 475HV, the surface hardness of the thermal barrier coating after the first glazing was 658HV, and the surface hardness of the thermal barrier coating after the last glazing was 794HV, and the hardness after pre-sintering was 755HV. Polygonal alumina particles with an average particle size of 20μm were used. After 120s of erosion, the original thermal barrier coating lost 158mg of mass, and the treated thermal barrier coating lost 45mg of mass.

[0052] Example 3

[0053] In this example, the pulse width of the high-energy pulse laser 7 is 4ns, the frequency is 4MHz, the laser spot diameter is 25μm, and the line spacing is 12μm. The thermal barrier coating 1 is gadolinium tantalate, and the preparation process is plasma physical vapor deposition. It is found through experiments that when the scanning speed is 400mm / s, the laser power is P m :1.2×10 3 GW / cm 2 W, the coating surface begins to melt, the power is P v :5.7×10 3 GW / cm 2 Therefore, when the laser power is 3.45×10 3 GW / cm 2 The surface was glazed and then 2.33×10 3 GW / cm 2 , 1.76×10 3 GW / cm 2 ...gradient glazing is performed on its surface. Through electron microscope observation, it is found that the material has a high 3 GW / cm 2 At this time, the width of the micro-cracks in the surface glaze layer is less than 1 μm. The glazed thermal barrier coating is then placed in a Ma-boiling furnace and kept at 1000°C for 0.5 h to completely eliminate the surface cracks and form a flat and dense sintered layer 8.

[0054] The treated thermal barrier coating 1 and the original thermal barrier coating were coated with CMAS and placed in a furnace for a thermal corrosion test at 1250°C for 20 hours. The results showed that the penetration depth of the treated thermal barrier coating CMAS was only 8μm, while the penetration depth of the original thermal barrier coating was as high as 54μm.

[0055] The treated thermal barrier coating 1 and the original thermal barrier coating were coated with V2O5+Na2SO4 mixed salt and placed in a Ma Furnace for a thermal corrosion test at 1100℃ for 20h. The results showed that the molten salt penetration depth of the treated thermal barrier coating was only 5.5μm, while the original one had penetrated to the bottom of the coating.

[0056] The treated thermal barrier coating 1 and the original thermal barrier coating were subjected to thermal shock tests. The samples were placed in a furnace at 1100°C for 5 minutes, air-cooled for 5 minutes, and the surface was observed every 100 cycles. 60% peeling was considered as coating failure. According to experimental tests, the original thermal barrier coating can withstand 8965 impacts, while the treated thermal barrier coating can withstand 11574 impacts.

[0057] It should be understood that although this specification is described according to various embodiments, not every embodiment contains only one independent technical solution. This narrative method of the specification is only for the sake of clarity. Those skilled in the art should regard the specification as a whole. The technical solutions in each embodiment may also be appropriately combined to form other implementation methods that can be understood by those skilled in the art.

[0058] The series of detailed descriptions listed above are only specific descriptions of feasible embodiments of the present invention. They are not intended to limit the scope of protection of the present invention. All equivalent embodiments or changes that do not deviate from the technical spirit of the present invention should be included in the scope of protection of the present invention.

Claims

1. A method for treating thermal barrier coatings against environmental corrosion by laser composite pre-sintering, characterized in that: The following steps are involved: Step S1, determining the critical power density P required for the surface of the thermal barrier coating (1) to begin melting m , determine the critical power density P required for the thermal barrier coating (1) to start vaporization on the surface v ; Step S2: high energy pulse laser (7) with a power density of P1:1 / 2 (P m +P v ) performing a first glazing on the surface of the thermal barrier coating (1); Step S3: high energy pulse laser (7) with a power density of P2: 1 / 2 (P m +P1) performing a second glazing on the surface of the thermal barrier coating (1); Step S4: high energy pulse laser (7) with a power density P n : 1 / 2 (P m +P n-1 ), where n=2,3,4..., the surface of the thermal barrier coating is glazed for the nth time until the width of the surface microcrack is less than 1 μm, and the glazing is stopped; Step S5: placing the glazed thermal barrier coating (1) in a muffle furnace for pre-sintering to form a sintered layer (8).

2. The method for anti-environmental corrosion of thermal barrier coating by laser composite pre-sintering treatment according to claim 1, characterized in that: The thermal barrier coating (1) is provided with ceramic material.

3. The method for anti-environmental corrosion of thermal barrier coating by laser composite pre-sintering treatment according to claim 2, characterized in that: The ceramic material is a mixed material of one or more of yttria-stabilized zirconia, gadolinium zirconate, and gadolinium tantalate.

4. The method for anti-environmental corrosion of thermal barrier coating by laser composite pre-sintering treatment according to claim 1, characterized in that: The thermal barrier coating (1) is prepared by atmospheric plasma spraying, electron beam physical vapor deposition or plasma physical vapor deposition.

5. The method for anti-environmental corrosion of thermal barrier coating by laser composite pre-sintering treatment according to claim 1, characterized in that: The high energy pulse laser (7) has a pulse width range of 2-30 ns, a frequency range of 2-4 MHz, and a power density range of 10 3 -10 4 GW / cm 2 , scanning speed is 100-500 mm / s.

6. The method for anti-environmental corrosion of thermal barrier coating by laser composite pre-sintering treatment according to claim 5, characterized in that: The pulse width range of the high energy pulse laser (7) is 2 ns, the frequency is 2 MHz, the laser spot diameter is 25 μm, the line spacing is 12 μm, the thermal barrier coating (1) is yttria stabilized zirconia, the preparation process is atmospheric plasma spraying, the scanning speed is 500 mm / s, the laser power is P m :1.7×10 3 GW / cm 2 When the coating surface begins to melt, the power is P v :6.4×10 3 GW / cm 2 When the laser power was 4.05×10 3 GW / cm 2 The surface was glazed and then 2.88×10 3 GW / cm 2 , 2.29×10 3 GW / cm 2 , 1.99×10 3 GW / cm 2 ...gradient glazing was performed on its surface. At a laser power of 1.99×10 3 GW / cm 2 The width of micro cracks in the surface glaze layer is less than 1μm.

7. The method for anti-environmental corrosion of thermal barrier coating by laser composite pre-sintering treatment according to claim 5, characterized in that: The high energy pulse laser (7) has a pulse width range of 7 ns, a frequency of 3 MHz, a laser spot diameter of 25 μm, a line spacing of 12 μm, a thermal barrier coating (1) of gadolinium zirconate, a preparation process of electron beam physical vapor deposition, a scanning speed of 350 mm / s, and a laser power of P m :2.1×10 3 GW / cm 2 When the coating surface begins to melt, the power is P v :6.3×10 3 GW / cm 2 When the laser power is 4.2×10 3 GW / cm 2 The surface was glazed and then 3.15×10 3 GW / cm 2 , 2.63×10 3 GW / cm 2 ...gradient glazing was performed on its surface. At a laser power of 2.36×10 3 GW / cm 2 The width of micro cracks in the surface glaze layer is less than 1 μm.

8. The method for anti-environmental corrosion of thermal barrier coating by laser composite pre-sintering treatment according to claim 5, characterized in that: The high energy pulse laser (7) has a pulse width range of 4 ns, a frequency of 4 MHz, a laser spot diameter of 25 μm, a line spacing of 12 μm, a thermal barrier coating (1) of gadolinium tantalate, a preparation process of plasma physical vapor deposition, a scanning speed of 400 mm / s, and a laser power of P m :1.2×10 3 GW / cm 2 W, the coating surface begins to melt, the power is P v :5.7×10 3 GW / cm 2 When the laser power is 3.45×10 3 GW / cm 2 The surface was glazed and then 2.33×10 3 GW / cm 2 , 1.76×10 3 GW / cm 2 ...gradient glazing was performed on its surface. At a laser power of 1.76×10 3 GW / cm 2 The width of micro cracks in the surface glaze layer is less than 1 μm.

9. The method for anti-environmental corrosion of thermal barrier coating by laser composite pre-sintering treatment according to claim 1, characterized in that: The temperature range in the muffle furnace is 1000-1100° C., and the pre-sintering time is 0.5-1 h.

10. The method for anti-environmental corrosion of thermal barrier coating by laser composite pre-sintering treatment according to claim 1, characterized in that: The temperature in the muffle furnace is 1000° C. and the pre-sintering time is 1 h; or the temperature in the muffle furnace is 1100° C. and the pre-sintering time is 1 h; or the temperature in the muffle furnace is 1000° C. and the pre-sintering time is 0.5 h.

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