KR20170089293A - Thermal barrier coating layer structure improved a property of heat-resisting, oxidation-resisting and coating bonding - Google Patents

Abstract

The present invention relates to a heat shield coating layer structure of a turbine, including: a metal base material; a metallic bond coating layer coated onto the surface of the metal base material; a first ceramic composable coating layer which is coated onto the surface of the metallic bond coating layer, while including at least a Yttria-stabilized zirconium (YSZ); a second ceramic composable coating layer which is coated onto the surface of the first ceramic composable coating layer, and which includes at least the YSZ; and a composition stabilization layer, which is formed between the first ceramic composable coating layer and the second ceramic composable coating layer, while stabilizing the bond between the first and second ceramic composable coating layers. According to the present invention, by using the two stacks of YSZ, and by using the composition stabilization layer which is formed between the two while including Y, Gd, La, etc., the heat resistance, oxidation resistance, and coating composability of a turbine, which operates at an environment with high temperatures and high, can be enhanced.

Description

TECHNICAL FIELD [0001] The present invention relates to a thermal barrier coating layer structure of a turbine having improved heat resistance, oxidation resistance and coating bonding property,

More particularly, the present invention relates to a thermal barrier coating layer structure of a turbine, and more particularly, to a thermal barrier coating layer structure of a turbine using a yttria-stabilized zirconia layer (YSZ) , Oxidation resistance, oxidation resistance, and coating adhesion of a turbine operating in an environment such as a high temperature environment, a high oxidation state, and the like.

Turbine is a machine developed to convert the shape of a fuel into chemical energy by converting it into thermal energy and then converting it into mechanical energy for propulsion, power generation, and pumping of fluids.

The main method used to improve the efficiency of such a turbine is its use in a high temperature operating environment. The current operating environment of the turbine is a high temperature environment of approximately 850-950 ° C. However, the metal materials used in the turbine are approaching their thermal limits and tolerate that limit because they are air cooled during operation.

On the other hand, in order to improve the thermal resistance of such a metal material, coating technology is applied in the field of turbine technology. And thermal barrier coating (TBC) technology.

FIG. 1 shows an example of a conventional heat shielding coating layer structure 1. 1, an example of a conventional TBC layer structure includes a metal bonding layer 3 and a PCS layer 5 (Pyrochlore Crystal Structure layer) for coating a metal substrate 2 with a substrate 2, ). This is a structure for improving the thermal resistance of the metal base 2 in the operating environment of the turbine. In the case of the conventional TBC layer structure, if the PCS layer 5 wears due to continuous operation, And is oxidized with Al, which is one of the components of the metal bond coat layer 3, to form a TGO layer (thermally grown oxide layer 4).

This TGO layer 4 gradually grows in accordance with the infiltration of the working fluid, oxygen, etc., which causes cracks in the blades and vanes of the turbine, which may cause fatigue failure, shortening the life of the turbine, and the like.

Japanese Patent Application Publication No. 2008-169473

It is an object of the present invention to provide a yttria-stabilized zirconia layer (YSZ) having a two-stage structure and a binder stabilizing layer formed therebetween and containing Y, Gd, La, Layer of a turbine material that operates in an environment of high temperature and high oxidation, and which is improved in heat resistance, oxidation resistance and coating bonding property.

According to an aspect of the present invention, there is provided a thermal barrier coating layer structure for a turbine, comprising a metal substrate, a metal bond coat layer coated on the surface of the metal base layer, A second ceramic bond coat layer coated on the surface of the first ceramic bond coat layer and comprising at least yttria stabilized zirconia (YSZ), and a second ceramic bond coat layer coated on the surface of the first ceramic bond coat layer, And a bonding stabilizing layer formed between the second ceramic bonding coat layers and stabilizing bonding between the first ceramic bond coat layer and the second ceramic bond coat layer.

Further, in the embodiment of the present invention, the first ceramic bond coating layer may include a zirconia-based element and at least one other element selected from the group consisting of Y, Si, Ti, Al, Fe, have.

In addition, in the embodiment of the present invention, the first ceramic bond coat layer may be a 7 YSZ layer.

Further, in the embodiment of the present invention, the first ceramic bond coat layer may be a layered structure.

Also, in the embodiment of the present invention, the thickness of the first ceramic bonding coating layer may be 0.05-0.1 mm.

Further, in the embodiment of the present invention, the second ceramic bonding coating layer may include a zirconia-based element and at least one other element selected from the group consisting of Y, Si, Ti, Al, Fe, have.

Also, in the embodiment of the present invention, the second ceramic bond coating layer may be an 8 YSZ layer.

Further, in the embodiment of the present invention, the second ceramic bond coat layer may be a layered structure.

Further, in the embodiment of the present invention, the thickness of the second ceramic bonding coating layer may be 0.05-0.1 mm.

Further, in the embodiment of the present invention, the bond stabilizing layer may include an element selected from the group including Y, Gd, La, Hf, and combinations thereof and at least one other element.

In embodiments of the present invention, the content of Y in the composition of stabilizing layer may be 7.5 to 8.5 wt%, Gd 0.1 to 1 wt%, La 0.1 to 1 wt%, and Hf 1.6 to 1.7 wt%.

In embodiments of the present invention, the components of the bond stabilizing layer may include 6.5 to 7.5 wt% of Y, 0.1 to 1 wt% of Gd, 0.1 to 1 wt% of La, and 1.6 to 1.7 wt% of Hf.

In addition, in the embodiment of the present invention, the bond stabilizing layer may be a columnar structure.

Further, in the embodiment of the present invention, the thickness of the bonding stabilizing layer may be 0.1 to 0.3 mm.

Further, in the embodiment of the present invention, the metal base may be a Ni-based superalloy.

Further, in the embodiment of the present invention, the metal bonding coating layer may be NiCrAlY or CoNiCrAlY.

Further, in the embodiment of the present invention, the thickness of the metal bonding coating layer may be 0.2 to 0.3 mm.

According to the present invention, it is possible to improve the heat resistance and oxidation resistance of the turbine material by coating the yttria-stabilized zirconia layer (YSZ) of the two ends, and to improve the heat resistance and oxidation resistance of the turbine material through the stabilization layer including Y, Gd and La The coating bonding force of the YSZ layer of the two-stage can be enhanced.

In addition, the YSZ layer of the two-stage structure is constituted by a layered structure and can effectively suppress the corrosion and oxidation of the turbine material exposed to the operating environment such as high temperature and high oxidation. It is possible to improve the coating bonding force and at the same time to increase the deformation resistance in the heating and cooling processes occurring in the operating environment.

BRIEF DESCRIPTION OF THE DRAWINGS FIG. 1 is a view of a heat shield coating layer structure of a conventional turbine. FIG.
2 shows an embodiment of a thermal barrier coating layer structure of a turbine according to the present invention.

DETAILED DESCRIPTION OF THE PREFERRED EMBODIMENTS Reference will now be made in detail to the preferred embodiments of the present invention, examples of which are illustrated in the accompanying drawings.

Fig. 2 is a view showing an embodiment of the heat-barrier coating layer structure of the turbine of the present invention. 2, the embodiment of the present invention includes a metal substrate 20, a metal bond coat layer 30, a first ceramic bond coat layer 40, a bond stabilization layer 50 and a second ceramic bond coat layer 60 .

The metal substrate 20 may be a gas turbine, a steam turbine, or the like. Specifically, in the embodiment of the present invention, the metal base 20 may be a material of a portion to be applied to a blade or a vane of a turbine. However, the present invention is not necessarily limited thereto, and may be applied to a portion of a turbine exposed to an operating environment such as high temperature and high oxidation.

The material of the metal base 20 may be steel, superalloy, titanium alloy, copper alloy, or the like. The metal substrate 20 can be appropriately selected from the above examples depending on the operating environment to which it is applied.

However, in the embodiment of the present invention, it may be a Ni-based super heat resistant alloy. Since turbines operate in high temperature, high pressure, and high oxidation environments, the metal material that forms the basis of the turbine is required to have excellent durability even in such environments. The Ni-base superalloy is excellent in environmental adaptability and can be selected as a material of the metal base 20.

The major component ratios of the Ni-base superalloy constituting the metal base 20 are shown in Table 1 below.

C Si Mn P S Cr B Mo Cu Pb 0.10 0.05 0.02 0.002 0.001 16.21 0.011 1.54 0.05 0.001 Ti Al Nb Fe Zr Bi W Co Ta Ni 3.43 3.42 0.71 0.09 0.06 0.001 2.56 8.26 1.64 Balance

[Main Component Ratio (Unit wt%) of Metal Substrate 20]

Concretely, it is preferable to have a composition of approximately 0.10 wt% of C, 0.05 wt% of Si, 0.02 wt% of Mn, 0.002 wt% of P, 0.001 wt% of S, 16.21 wt% of Cr, 0.011 wt% of B, 1.54 wt% 0.001 wt% of Cu, 3.43 wt% of Ti, 3.42 wt% of Al, 0.71 wt% of Nb, 0.09 wt% of Fe, 0.06 wt% of Zr, 0.001 wt% of Bi, 0.001 wt% of Bi, : 2.56 wt%, Co: 8.26 wt%, and Ta: 1.64 wt%, which constitute 38.156 wt% of the total weight ratio and the remaining 61.844 wt% Ni element. However, the present invention is not limited thereto, and the weight ratio of the element may be increased or decreased according to the application environment. The ratio of the changed weight ratio may be adjusted by adjusting the weight ratio of Ni element to 100 wt% .

Next, the metal bonding coating layer 30 may be coated on the surface of the metal substrate 20. [ At this time, the metal bonding coating layer 30 may be deposited by an overlay coating method.

In the embodiment of the present invention, the metal bonding coating layer 30 may be made of a material of MCrAlY (M + Cr).

When the operating temperature of the turbine is in the range of 850 ° C to 950 ° C, hot corrosion of the turbine material occurs actively. When the temperature exceeds 950 ° C, oxidation is accelerated.

Therefore, MCrAlY coating is applied to prevent such oxidation and corrosion phenomenon. Among the constituents of MCrAlY, Cr and Al serve to form a protective oxide film having a strong binding force, and Y plays a role in promoting the formation of such an oxide film.

The basic component, M, may be Co, Ni or a combination thereof (CoNi or NiCo), with different resistance to oxidation and corrosion depending on the basic components used.

Specifically, the metal bonding coating layer 30 may be NiCrAlY (nickel) or CoNiCrAlY (nickel). In the embodiment of the present invention, the major component ratios of the metal bonding coating layer 30 are shown in Table 2 below.

coating Ni Co Cr Al Y Si etc NiCrAlY Balance 21-23 9-11 0.8 to 1.2 ≤0.2 CoNiCrAlY 29 to 35 Balance 18-24 5 ~ 11 0.1 to 0.8 ≤0.2 ≤0.2

[Main Component Ratio (Unit wt%) of Metal Bonding Coating Layer 30]

Specifically, when the metal bonding coating layer 30 is made of NiCrAlY (nickel), it is composed of approximately 21 to 23 wt% of Cr, 9 to 11 wt% of Al and 0.8 to 1.2 wt% of Y, Other weight ratios in which at least one other element is included may be 0 (optional) to 0.2 wt% or less. The minimum weight ratio by the above elements may be 30.8 wt% and the maximum weight ratio may be 35.4 wt%. Accordingly, the weight ratio of the Ni element can be at most 69.2 wt%, and at least 64.6 wt%. When the metal-bonding coating layer 30 is made of NiCrAlY (nickel), the weight ratio of the Ni element is adjusted to achieve a balance of 100 wt%.

However, the present invention is not limited to this. It is possible to increase or decrease the weight ratio of the elements required according to the application environment, and to change the ratio according to the changed weight ratio, the balance of the total component ratio can be adjusted by controlling the weight ratio of Ni element .

(Ni: 29 to 35 wt%, Cr: 18 to 24 wt%, Al: 5 to 11 wt%, Y: 0.1 to 0.8 wt%) when the metal bonding coating layer 30 is made of CoNiCrAlY , Si: 0 (optional component) to 0.2 wt% or less. Other weight ratios in which at least one other element is included may be 0 (optional component) to 0.2 wt% or less. The minimum weight ratio by the above elements may be 52.1 wt% and the maximum weight ratio may be 71.0 wt%. Accordingly, the weight ratio of the Co element can be at most 47.9 wt%, and at least 29.0 wt%. When the metal-bonding coating layer 30 is made of CoNiCrAlY (nichorchalli), the weight ratio of the Co element is adjusted to achieve a balance of 100 wt%.

However, the present invention is not limited to this. The weight ratio of the elements required may be increased or decreased according to the application environment. The ratio of the changed weight ratio may be adjusted by adjusting the weight ratio of the Co element to balance the overall composition ratio. .

The metal bond coating layer 30 is applied with an overlay coating technique, which forms an aluminide or chromium coating layer on the surface of the component to improve oxidation and corrosion resistance in a high temperature and high oxidation environment . And the thermal stress due to the difference in thermal expansion coefficient between the metal base 20 and the first ceramic bond coat layer 40 is alleviated and the adhesive strength is improved. In addition, it has advantages of low processing cost and mass production.

The overlay coating technique may be specifically applied to a coating method such as a slurry method, a pack cementation method, a vapor phase method, a low-pressure plasma spray (LPPS) method, an air plasma spray method ) Method, a high-velocity oxy-fuel spray (HVOF) method, and the like. The differentiated coating techniques can be appropriately selected depending on the operating environment in which the turbine is used.

Next, the first ceramic bond coat layer 40 is coated on the surface of the metal bond coat layer 30 and may include at least yttria stabilized zirconia (YSZ). Yttria-stabilized zirconia is a generic term for ceramic materials that stabilize even at room temperature by adding yttrium oxide to zirconium oxide.

Specifically, the first ceramic bond coat layer 40 may include a zirconia-based element and at least one other element selected from the group consisting of Y, Si, Ti, Al, Fe, and combinations thereof .

In an embodiment of the present invention, the first ceramic bond coat layer 40 may be a 7 YSZ layer. The above 7 YSZ has characteristics such as high hardness, chemical stability, heat resistance, and heat insulation, and main component ratios are shown in Table 3 below.

CHEMICAL COMPOSITION  MIN.  MAX. ZrO ₂
(Zirconium dioxide) balance balance Y ₂ O ₃
(Yttrium oxide) 6.5 7.5 SiO ₂
(Silicon dioxide) 0 (optional component) 0.7 TiO ₂
(Titanium dioxide) 0 (optional component) 0.2 Al ₂ O ₃
(Aluminum oxide) 0 (optional component) 0.2 Fe ₂ O ₃
(Ironoxide) 0 (optional component) 0.2 Other oxides 0 (optional component) 0.5

[Main Component Ratio (Unit wt%) of First Ceramic Bonding Coating Layer]

As can be seen in Table 3, approximately 6.5 to 7.5% by weight of Y ₂ O ₃ , 0 to 0.7 wt% of SiO ₂ , TiO ₂ : 0 to 0.2 wt% Al ₂ O ₃ : 0 to 0.2 wt% 0 to 0.2 wt% Fe ₂ O ₃ , Other oxides: 0 ~ 0.5wt%, and it is possible to adjust the balance of total composition ratio by controlling the weight ratio of ZrO ₂ . Accordingly, the maximum weight ratio of ZrO ₂ may be approximately 93.5 wt%, and the minimum weight ratio may be approximately 90.7 wt%.

Alternatively, the first ceramic bond coat layer 40 may be composed of components and components constituting 7 YSZ commonly used in the market.

The first ceramic bond coat layer 40 may be deposited by APS (Air Plasma Spray). Plasma generated gas is generated by using argon, helium, nitrogen, hydrogen gas, etc., and the coating layer is laminated at a distance of 2 to 10 inches from the coating gun and the base material, and the powder supply amount is 10 to 100 g / min set-up can be used. When the distance between the coating gun and the base material is more than 10 inches and the powder feed rate is less than 10 g / min, the hardness, heat resistance and heat insulation are lower than those required. On the other hand, if the distance from the base material is closer than 2 inches and the amount of powder supplied is more than 100 g / min, the deposition thickness of the first ceramic bond coat layer 40 becomes too thick, resulting in low bond stability. In addition, the deposition method is not necessarily limited to the above-described methods, but may be applied to electron beam plasma vapor deposition (EB-PVD), sputtering, high-velocity oxygene (HVOF) Fuel spray) method can also be used.

Next, the second ceramic bond coat layer 60 may be coated on the surface of the first ceramic bond coat layer 40 and may include at least yttria stabilized zirconia (YSZ).

Specifically, the second ceramic bonding coating layer 60 may include a zirconia-based element and at least one other element selected from the group consisting of Y, Si, Ti, Al, Fe, and combinations thereof .

In an embodiment of the present invention, the first ceramic bond coating layer 40 may be an 8 YSZ layer. The above 8 YSZ has characteristics such as high hardness, chemical stability, heat resistance, and heat insulation, and major component ratios are shown in Table 4 below.

CHEMICAL COMPOSITION  MIN.  MAX. ZrO ₂
(Zirconium dioxide) balance balance Y ₂ O ₃
(Yttrium oxide) 7.5 8.5 SiO ₂
(Silicon dioxide) 0 (optional component) 0.7 TiO ₂
(Titanium dioxide) 0 (optional component) 0.2 Al ₂ O ₃
(Aluminum oxide) 0 (optional component) 0.2 Fe ₂ O ₃
(Ironoxide) 0 (optional component) 0.2 Other oxides 0 (optional component) 0.5

[Main Component Ratio (Unit wt%) of Second Ceramic Bonding Coating Layer]

As can be seen from Table 4, approximately 7.5 to 8.5 wt% Y ₂ O ₃ , 0 to 0.7 wt% of SiO ₂ , TiO ₂ : 0 to 0.2 wt% Al ₂ O ₃ : 0 to 0.2 wt% 0 to 0.2 wt% Fe ₂ O ₃ , Other oxides: 0 ~ 0.5wt%, and it is possible to adjust the balance of total composition ratio by controlling the weight ratio of ZrO ₂ . Accordingly, the maximum weight ratio of ZrO ₂ may be approximately 92.5 wt%, and the minimum weight ratio may be approximately 89.7 wt%.

Or the second ceramic bond coat layer 60 may be composed of components and components constituting 8 YSZ commonly used in the market.

The second ceramic bond coat layer 60 may be deposited by APS (Air Plasma Spray). Plasma generated gas is generated by using argon, helium, nitrogen, hydrogen gas, etc., and the coating layer is laminated at a distance of 2 to 10 inches from the coating gun and the base material, and the powder supply amount is 10 to 100 g / min set-up can be used. When the distance between the coating gun and the base material is more than 10 inches and the powder feed rate is less than 10 g / min, the hardness, heat resistance and heat insulation are lower than those required. On the other hand, if the distance from the base material is closer than 2 inches and the amount of powder supplied is more than 100 g / min, the deposition thickness of the first ceramic bond coat layer 40 becomes too thick, resulting in low bond stability. In addition, the deposition method is not necessarily limited to the above-described methods, but may be applied to electron beam plasma vapor deposition (EB-PVD), sputtering, high-velocity oxygene (HVOF) Fuel spray) method can also be used.

Here, 8 YSZ has a relatively high thermal expansion coefficient (10-12 × 10 ^-6 m / K), so that the weight ratio of ZrO ₂ is about 1 wt% higher than 7 YSZ, And the thermal expansion coefficient can be reduced, thereby reducing the mechanical peeling phenomenon and improving the chemical stability. ZrO ₂ has excellent mechanical properties, hardness of about 11.8 GPa, modulus of elasticity of about 210 GPa and fracture toughness of about 7.0 MPa · m ^1/2 .

Here, 8 YSZ can be selected for the purpose of enhancing heat resistance, heat insulation and oxidation resistance, and 7 YSZ can be selected for the purpose of strengthening the bonding strength and oxidation resistance.

That is, since the second ceramic bond coat layer 60 is disposed at the outermost layer of the entire coating layer, heat resistance and oxidation resistance are required to be high in an environment such as high temperature and high oxidation. Therefore, 8 YSZ, which has a relatively high weight ratio of ZrO ₂ as well as heat resistance, may be suitable.

Since the first ceramic bond coat layer 40 is disposed between the metal bond coat layer 30 and the bond stabilizer layer 50, the bonding strength between the metal bond coat layer 30 and the bond stabilizer layer 50, It is required to have a high oxidation inhibiting ability by the working fluid, oxygen, etc. which can permeate through the bonding stabilizing layer 50 and penetrate. Therefore, 7 YSZ may be appropriate. 7 YSZ has high resistance to corrosion in high temperature environment because it has excellent thermal shock resistance.

Next, the bonding stabilizing layer 50 is formed between the first ceramic bonding coat layer 40 and the second ceramic bond coat layer 60, and the first ceramic bond coat layer 40 and the second ceramic bond bond 40 And may be configured to stabilize the bonding between the coating layers 60.

The bond stabilization layer 50 may be composed of an element selected from the group consisting of Y, Gd, La, Hf, and combinations thereof and at least one other element.

The composition of the bond stabilizing layer 50 may include 7.5 to 8.5 wt% of Y, 0.1 to 1 wt% of Gd, 0.1 to 1 wt% of La, and 1.6 to 1.7 wt% of Hf. The remaining weight ratio can be adjusted to a balance of 100 wt% as a component ratio of at least one or more other elements that can be contained in addition to the above elements.

Or from 0.1 to 1 wt% of La and from 1.6 to 1.7 wt% of Hf in the components of the bond stabilizing layer 50. [ The remaining weight ratio can be adjusted to a balance of 100 wt% as a component ratio of at least one or more other elements that can be contained in addition to the above elements.

The coating of the bond stabilization layer 50 may be deposited by APS (Air Plasma Spray). Plasma generated gas is generated by using argon, helium, nitrogen, hydrogen gas, etc., and the coating layer is laminated at a distance of 2 to 10 inches from the coating gun and the base material, and the powder supply amount is 10 to 100 g / min set-up can be used. When the distance between the coating gun and the base material is more than 10 inches and the powder feed rate is less than 10 g / min, the hardness, heat resistance and heat insulation are lower than those required. On the other hand, if the distance from the base material is closer than 2 inches and the amount of powder supplied is more than 100 g / min, the deposition thickness of the first ceramic bond coat layer 40 becomes too thick, resulting in low bond stability. In addition, the deposition method is not necessarily limited to the above-described methods, but may be applied to electron beam plasma vapor deposition (EB-PVD), sputtering, high-velocity oxygene (HVOF) Fuel spray) method can also be used.

The bond stabilizing layer 50 may be a vertical structure. In the case of the columnar structure, there is a gap between the columns arranged in the vertical direction formed by the elements bonded with the longitudinal structure, so that resistance against deformation during heating and cooling is excellent. That is, since it is a columnar structure, expansion and contraction in the horizontal direction due to thermal expansion in a high temperature environment is possible between the gaps. In addition, the vertical expansion and contraction can be achieved by finely pushing or pulling the second ceramic bonding coating layer 60 outwardly according to the degree of thermal expansion based on the first ceramic bonding coating layer 40. As a result, deformation and breakage due to thermal resistance are alleviated.

Here, the bonding stability between the first ceramic bond coat layer 40 and the second ceramic bond coat layer 60 is improved because the bond-stabilizing layer 50 has a longitudinal structure. The first ceramic bond coat layer 40 is contacted to one end of the vertically arranged columns and the second ceramic bond coat layer 60 is contacted to the other end thereof to firmly bond the two.

 The first and second ceramic bonding coating layers 40 and 60 may have a layered structure. In the case of the layered structure, penetration of the working fluid, oxygen and the like can be suppressed more effectively than the vertical structure. This is because the gaps between the array structures are formed in the horizontal direction, so that penetration is not easy. Therefore, 7 YSZ and 8 YSZ are preferably formed in a layered structure.

Since the first and second ceramic bonding coating layers 40 and 60 have a layered structure, not only heat resistance and thermal insulation but also oxidation resistance are further improved.

Next, the thicknesses of the metal substrate 20, the metal bond coat layer 30, the first ceramic bond coat layer 40, the bond stabilization layer 50, and the second ceramic bond coat layer 60 will be described. First, the metal substrate 20 may have a thickness of about 3 to 5 mm, and the metal bonding coating layer 30 may have a thickness of about 0.2 to 0.3 mm. The first ceramic bond coat layer 40 may be about 0.05-0.1 mm and the bond stabilizer layer 50 may be 0.1-0.3 mm and the second ceramic bond coat layer 60 may be 0.05-0.1 mm Lt; / RTI > The thicknesses of the metal substrate 20, the metal bonding coat layer 30, the first ceramic bond coat layer 40, the bond stabilization layer 50 and the second ceramic bond coat layer 60 are sufficiently low when the thickness is smaller than the lower limit, Heat resistance and oxidation resistance are insufficient, and when it is larger than the upper limit value, the thickness becomes too thick, and the bonding stability is lowered.

The thickness of the first and second ceramic bonding coating layers 40 and 60 may be selected in consideration of heat resistance, heat insulation, oxidation resistance, etc., in consideration of economical efficiency, productivity, etc. The thickness of the bonding stabilizing layer 50, 2 ceramic bonding coat layers 40 and 60 and an arrangement space enough to form a strain gap due to thermal resistance.

The above is only a specific example of the structure of the thermal barrier coating layer of the turbine.

Therefore, it should be understood by those skilled in the art that various changes in form and details may be made therein without departing from the spirit and scope of the present invention as defined by the following claims. do.

10: Thermal barrier coating structure of turbine
20: metal substrate
30: metal bond coating layer
40: first ceramic bond coating layer
50: bond stabilization layer
60: Second ceramic bonding coating layer

Claims (15)

Metal substrates;
A metal bond coating layer coated on the surface of the metal substrate;
A first ceramic bond coating layer coated on the surface of the metal bond coat layer and including at least yttria stabilized zirconia (YSZ);
A second ceramic bond coating layer coated on the surface of the first ceramic bond coat layer and comprising at least yttria stabilized zirconia (YSZ); And
A bond stabilizing layer formed between the first ceramic bond coat layer and the second ceramic bond coat layer and stabilizing bonding between the first ceramic bond coat layer and the second ceramic bond coat layer;
A thermal barrier coating layer structure of a turbine having improved heat resistance, oxidation resistance and coating bonding property.
The method according to claim 1,
Wherein the first ceramic bond coat layer is a 7 YSZ layer, and the thermal barrier coating layer structure of the turbine improved in heat resistance, oxidation resistance and coating adhesion.
3. The method of claim 2,
Wherein the first ceramic bond coating layer is a layered structure, and the thermal barrier coating layer structure of the turbine having improved heat resistance, oxidation resistance and coating bondability.
3. The method of claim 2,
Wherein the first ceramic bond coating layer has a thickness of 0.05 to 0.1 mm. The thermal barrier coating layer structure of a turbine having improved heat resistance, oxidation resistance and coating bondability.
The method according to claim 1,
Wherein the second ceramic bonding coating layer is an 8 YSZ layer. The thermal barrier coating layer structure of a turbine improved in heat resistance, oxidation resistance, and coating adhesion.
6. The method of claim 5,
Wherein the second ceramic bond coat layer is a layered structure. The thermal barrier coating layer structure of a turbine having improved heat resistance, oxidation resistance and coating bondability.
6. The method of claim 5,
Wherein the second ceramic bond coating layer has a thickness of 0.05 to 0.1 mm. The thermal barrier coating layer structure of a turbine having improved heat resistance, oxidation resistance and coating bonding property.
8. The method according to any one of claims 1 to 7,
Wherein the bond stabilizing layer comprises an element selected from the group consisting of Y, Gd, La, Hf, and combinations thereof and at least one other element. The heat shielding of the turbine having improved heat resistance, Coating layer structure.
9. The method of claim 8,
Wherein the composition of the bond stabilizing layer is 7.5 to 8.5 wt% of Y, 0.1 to 1 wt% of Gd, 0.1 to 1 wt% of La and 1.6 to 1.7 wt% of Hf in the components of the bond stabilizing layer. Improved thermal barrier coating structure of turbine.
9. The method of claim 8,
Wherein the composition of the bond stabilizing layer comprises 6.5 to 7.5 wt% of Y, 0.1 to 1 wt% of Gd, 0.1 to 1 wt% of La, and 1.6 to 1.7 wt% of Hf in the components of the bond stabilizing layer. Improved thermal barrier coating structure of turbine.
9. The method of claim 8,
Wherein the bonding stabilizing layer is a columnar structure, wherein the thermal barrier coating layer structure of the turbine is improved in heat resistance, oxidation resistance and coating bondability.
9. The method of claim 8,
Wherein the bonding stabilizing layer has a thickness of 0.1 to 0.3 mm. The thermal barrier coating layer structure of a turbine having improved heat resistance, oxidation resistance and coating bonding property.
The method according to claim 1,
Wherein the metal base is a Ni-based superalloy. The thermal barrier coating layer structure of a turbine improved in heat resistance, oxidation resistance, and coating bondability.
The method according to claim 1,
Wherein the metal bond coat layer is NiCrAlY or CoNiCrAlY. The thermal barrier coating layer structure of the turbine having improved heat resistance, oxidation resistance and coating bondability.
15. The method of claim 14,
Wherein the thickness of the metal bonding coating layer is 0.2 to 0.3 mm. The thermal barrier coating layer structure of a turbine improved in heat resistance, oxidation resistance and coating adhesion.

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