阅读说明：本技术 Pvd粘合层 (PVD bond coat ) 是由 J·拉姆 B·韦德利格 P·波尔西克 M·金德拉特 于 2018-04-19 设计创作，主要内容包括：超级合金工件，其包含：?超级合金基底；?直接在超级合金基底表面上的具有基本上相同的超级合金组成的界面层(IF?1)；随后?过渡层(TL)，其具有基本上相同的超级合金和超级合金氧化物或不同的金属组成和不同的金属氧化物，由此过渡层的氧含量从IF?1向IF?2增加；具有超级合金氧化物或不同金属氧化物的屏障层(IF?2)。(A superalloy workpiece, comprising: -a superalloy substrate; -an interfacial layer (IF-1) having substantially the same superalloy composition directly on the superalloy substrate surface; a subsequent-Transition Layer (TL) having essentially the same superalloy and superalloy oxide or a different metal composition and a different metal oxide, whereby the oxygen content of the transition layer increases from IF-1 to IF-2; a barrier layer (IF-2) with a superalloy oxide or a different metal oxide.)

1. A coating method comprising the steps of:

-providing a Superalloy (SA) substrate in a PVD coating unit;

-providing a superalloy target as a cathode of an arc source of the coating unit;

-providing a substrate bias voltage to the substrate;

-depositing an interfacial layer (IF-1) of superalloy on the surface of the substrate from the superalloy target by vacuum arc deposition;

-providing a supply of reactive gas comprising oxygen to the coating unit;

-depositing a Transition Layer (TL) of the same superalloy or of a different metal composition by vacuum arc deposition, whereby the oxygen content of said layer is varied from (IF-1) towards the surface by varying the partial pressure of said reactive gas in the process atmosphere;

-depositing a barrier layer (IF-2) comprising a higher amount of superalloy oxide or a different metal oxide composition than in the transition layer after the transition layer by: as with the deposition of the Transition Layer (TL), vacuum arc is performed in a process atmosphere containing a higher concentration of reactive gases.

2. The coating process according to claim 1, characterized in that the superalloy target has substantially the same composition as the superalloy.

3. Coating method according to one of the preceding claims, characterized in that at least one further target with a further metal composition is provided for depositing a transition layer with a different metal composition and/or a barrier layer (IF-2) with a different metal oxide composition.

4. Coating process according to one of the preceding claims, characterized in that simultaneously with the vacuum arc deposition of the superalloy target, gaseous precursors are provided to deposit a transition layer with a different metal composition and/or a barrier layer (IF-2) with a different metal oxide composition.

5. Coating method according to one of the preceding claims, characterized in that the interface layer (IF-1) is deposited with a crystal structure that coincides with the crystal structure of the superalloy substrate.

6. Coating process according to one of the preceding claims, characterized in that a superalloy oxide and/or an oxide of a different metal composition of the barrier layer (IF-2) is deposited, wherein the ratio of oxygen atoms to metal atoms is at least 1.5 or even at least 5, in order to form a thermodynamically stable oxide, in particular the most stable oxide, from the superalloy metal and/or a different metal composition evaporating on deposition of the barrier layer (IF-2).

7. Coating method according to one of the preceding claims, characterized in that the interfacial layer is deposited in pure metal vapor without process gas.

8. Coating method according to one of the preceding claims, characterized in that an inert gas supply is provided to the coating unit for depositing at least one of the interface layer (IF-1), the transition layer and the barrier layer (IF-2) in a process atmosphere containing inert gas;

9. coating process according to one of the preceding claims, characterized in that the superalloy target has been produced by a powder metallurgy process.

10. Coating method according to one of the preceding claims, characterized in that a ceramic top layer is applied to the surface of the barrier layer (IF-2) in a further process step.

11. The coating method according to claim 10, characterized in that the ceramic top layer is applied by a thermal spraying technique.

12. A superalloy workpiece, comprising:

-a substrate of a superalloy,

-an interfacial layer (IF-1) having substantially the same superalloy composition directly on the surface of the superalloy substrate, followed by

-a Transition Layer (TL) having essentially the same superalloy and superalloy oxide or a different metal composition and a different metal oxide, whereby the oxygen content of said transition layer increases from IF-1 to IF-2,

-a barrier layer (IF-2) with a superalloy oxide or a different metal oxide.

13. The workpiece according to claim 12, characterized in that IF-1 has a crystal structure that is consistent with the crystal structure of the Superalloy (SA) substrate surface.

14. The workpiece according to claim 12 or 13, characterized in that the oxygen content in the transition layer increases stepwise or gradually from IF-1 to IF-2.

15. The workpiece according to one of claims 12 to 14, characterised in that the different metal composition differs from the substantially identical superalloy composition by at least one further element.

16. A workpiece according to claim 15, characterised in that the at least one further element has an electronegativity equal to or less than 1.4.

17. The workpiece according to claim 15 or 16, characterized in that the at least one further element comprises a lanthanide, preferably at least one of La, Er or Yb.

18. The workpiece according to one of claims 12 to 17, characterized in that the different metal composition differs from the superalloy composition by the concentration and/or addition of at least one of the following further elements: mg, Al, Cr, Er, Y, Zr, La, Hf and Si.

19. Workpiece according to one of claims 16 to 18, characterised in that at least a part of the further elements is oxidised and deposited as Solid Solutions (SS) in the grains and/or as strengthening dispersed Oxides (ODS) along grain boundaries of the Transition Layer (TL) and/or the barrier layer (IF-2).

20. The workpiece according to one of claims 12 to 19, characterized in that the concentration of at least one metal element or silicon in the transition layer increases stepwise or gradually from IF-1 to IF-2.

21. The workpiece according to one of claims 12 to 20, characterized in that the different metal oxides comprise at least one of the following oxides or mixtures thereof:

alumina, alumina-chromia, erbium oxide, yttria-alumina, magnesia-alumina, alumina-silica, hafnia-silica.

22. A workpiece according to claim 21, characterised in that the aluminium oxide or aluminium oxide-chromium oxide is Al comprising a corundum crystal structure₂O₃Or (AlCr)₂O₃(ii) a Erbium oxide or yttrium oxide is a material containing cubic crystal junctionEr of structure₂O₃Or Y₂O₃。

23. A workpiece according to claim 22, characterised in that more than 55%, preferably more than 75%, of the individual crystal structures are corundum crystal structures or cubic crystal structures.

24. The workpiece according to one of claims 12 to 23, characterized in that the different metal oxide comprises an aluminum-containing oxide and the layer comprises aluminum-containing droplets.

25. The workpiece of one of claims 12-24, characterized in that the different metal oxide comprises chromium-containing oxide and the layer comprises chromium-containing droplets.

26. The workpiece according to one of claims 12 to 25, comprising a ceramic top layer on the surface of the barrier layer (IF-2).

27. Method for producing a Superalloy (SA) workpiece comprising the coating method according to one of claims 1 to 12.

Technical Field

The present invention relates to the field of coated Superalloy (SA) materials, in particular to a coating method according to claim 1, a workpiece according to claim 12 and a method of manufacturing a workpiece according to claim 26.

Technical Field

Superalloys exhibit several key properties: excellent mechanical strength, resistance to thermal creep deformation, good surface stability, and corrosion or oxidation resistance. The crystal structure is typically face centered cubic austenite. Examples of such alloys are Hastelloy (Hastelloy), Inconel (Inconel), maspaloy (Waspaloy), Rene alloys, haynes alloys, Inconel (Incoloy), MP98T, TMS alloys, and CMSX single crystal alloys. Superalloys develop high temperature strength through solid solution strengthening. An important strengthening mechanism is dispersion strengthening, which forms second phase precipitates (e.g., gamma prime and carbides). Oxidation or corrosion resistance is provided by elements such as aluminum and chromium. There are basically two types of superalloys, one being a Co-based superalloy containing cobalt as the major metal component and, for example, C, Cr, W, Ni, Ti, Al, Ir and Ta as alloying elements, the other and by far the most important class being Ni-based superalloys containing nickel as the major metal component and, for example, Cr, Fe, Co, Mo, W, Ta, Al, Ti, Zr, Nb, Re, Y, V, C, B or Hf as only some examples of alloying additives used with the superalloy component. One focus of the present invention is to improve the thermal and wear resistance properties of superalloys in general, and in particular for applications such as for aviation and industrial combustionApplications such as high and low pressure turbine assemblies for gas turbine (IGT) applications, whereby several successful experiments have been conducted with Ni-based superalloys such as PWA1483 and CM 247-DS. Other aluminide-based alloys, such as TiAl-based superalloys (e.g., γ -TiAl) or other aluminides that form high temperature and high wear resistant alloys, include: ni-aluminides, e.g. NiAl, also known as Raney nickel or NiAl₃(ii) a Fe-aluminide; hf-aluminide; cr-aluminide; nb-aluminides, e.g. Nb₃Al or NbAl₃(ii) a Ta-aluminides, e.g. Ta₃Al or TaAl₃(ii) a Pt-aluminide; zr-aluminide and the like are understood here as superalloy compositions.

Discharge plasma sintering (SPS) is a powder metallurgical manufacturing process, preferably by pressurizing a powder composition under vacuum in a graphite die, e.g. between two graphite punches, and simultaneously applying a DC current or optionally a pulsed DC current between the two punches to assist in the forming process of the workpiece (in this case the target) to be manufactured. Thus, in the case of conductive samples such as superalloys, the DC current or pulsed DC current is passed directly through the graphite die and the powder compact. Thus, the heat generation is internal, in contrast to conventional hot pressing, where heat is provided by an external heating element. This results in achieving near theoretical densities at lower sintering temperatures compared to conventional sintering techniques and promotes very high heating or cooling rates (up to 1000K/min), so the sintering process is typically very fast (within minutes). The general speed of the process ensures that it has the potential to densify powders with nanometer dimensions or nanostructures while avoiding coarsening that accompanies standard densification approaches. As an example, for this procedure, a series of 3ms direct current pulses of intensity up to 1500A and low voltage of 25V can be passed directly through the powder sample and compaction tool.

Research into materials used at high temperatures and in oxidizing and corrosive environments is an ongoing effort for applications in aircraft, gas turbines, and internal combustion engines. Despite different end-uses and different designs and sizes, the trends in these industries are all towards the same goal, which is a continuing improvement in engine efficiency to reduceLow fuel consumption and also more stringent requirements regarding CO₂Regulation of emissions. This means that the engine is operated at higher temperatures, thus increasing the need for stronger, stable and durable base materials that operate in harsh environments at different parts of the turbine engine. Even with the most advanced materials (e.g., superalloys or composites), the coating technique cannot be bypassed when it comes to improving the life of the component by improving the oxidation resistance, wear resistance, erosion resistance and corrosion resistance at high operating temperatures. Despite the fact that the coating techniques introduced decades ago have been well established and are continually improved by the use of new methods and new coating materials, the resulting coating systems on engine components require increased complexity. Thus, issues such as interactions between layers, surface preparation methods, heat treatment and diffusion become increasingly important. In addition, the requirements of the next generation engines are quite challenging for these prior art technologies due to their limitations and inability to provide the required characteristics. Typical coating systems in gas turbines are made of several layers, usually consisting of a bond coat, a thermally grown oxide, and a top ceramic layer. The bond coat for protecting the turbine from oxidation is typically produced by a PtAl diffusion process, electron beam physical vapor deposition (EB-PVD) or MCrAlY Low Pressure Plasma Spray (LPPS). The bond coat PLANGE and the top ceramic layer form a so-called Thermal Barrier Coating (TBC). The top ceramic coating is produced as a porous coating by Atmospheric Plasma Spray (APS) or as a columnar structure coating by EB-PVD. The design of the adhesive layer is challenging because it must achieve two complex interfaces: one is directed to superalloy substrates to ensure mechanical stability over a wide temperature range, and the other is directed to porous oxides to provide an excellent oxygen barrier. This not only means an intelligent design of the adhesive layer, but also requires a high reproducibility in the manufacture of the coating system (layer stack).

Disclosure and examples

The object of the present invention is therefore to improve and simplify the coating processes of known superalloys by avoiding the disadvantages of the prior art methods, such as the use of expensive coating materials (like PtAl) and processes (like EB-PVD), which are complicated and difficult to operate if coatings consisting of elements with different vapor pressures have to be applied. Other objects of the present invention are to improve existing coatings with respect to overall performance, for example to overcome the limitations and inability of prior art coating systems.

It is therefore an object of the present invention to disclose a coating method, comprising the steps of:

-providing a Superalloy (SA) substrate in a PVD coating unit;

-providing a Superalloy (SA) target as a cathode of an arc evaporation source of a coating unit;

-providing a substrate bias voltage to the substrate;

-depositing an interfacial layer (IF-1) of superalloy on the surface of the substrate by vacuum arc deposition from a superalloy target;

-providing a supply of reactive gas comprising oxygen to the coating unit;

-depositing a Transition Layer (TL) of the same superalloy or of a different metal composition by vacuum arc deposition, whereby the oxygen content of the layer is varied from (IF-1) towards the surface by varying the partial pressure of the reactive gas in the process atmosphere, for example increasing the oxygen content of the layer from (IF-1) towards the surface by increasing and/or varying the partial pressure of the reactive gas;

-depositing a barrier layer (IF-2) after the transition layer by vacuum arc deposition in a process atmosphere containing a higher concentration of reactive gases, as with the deposition of the Transition Layer (TL), the barrier layer comprising a higher amount of superalloy oxide or a different metal oxide composition than in the transition layer.

Any change in the oxygen content in the transition layer may be performed by increasing/varying the flow of the oxygen-containing reactive gas in steps or continuously (ramp-wise) and/or by varying the power of the arc source. Oxygen (O) in general₂) The gas will be used as a reactive gas, however any other volatile oxygen-containing compound, such as ozone (O), may be used₃) Or otherwise.

Such coating processes may be performed by using a superalloy target having substantially the same composition as the superalloy. Thus, the powder composition used for target production is selected according to the composition of the superalloy to be coated to produce a target having substantially the same composition as the superalloy itself. In this case, "substantially the same composition" for a target (as produced by SPS or any other powder metallurgy method) means that the primary elements constituting about 9% or more by weight percent of the powder mixture due to manufacturing and/or, for example, EDX measurement effects, take PWA1483 as an example, like Ni, Co and Cr, differ by no more than ± 20%, preferably by no more than ± 10%, relative to the original powder composition. Similarly applies to targets used with reactive or non-reactive processes, where the difference from the original powder composition may be slightly higher for a single major component. The same applies to the meaning of the term "composition substantially the same as the composition of the interface layer (IF-1)". In particular, Ni powder, Al powder, C powder, Co powder, Cr powder, Mo powder, Ta powder, Ti powder and W powder are used to produce targets for cathodic vacuum arc coating, as described below.

Alternatively, a suitable powder may also be produced by comminuting the superalloy solids and then forming the target by SPS or another powder metallurgy method.

In the most basic approach, the same superalloy target is used to deposit all layers of the bond coat, and oxygen is used as the only process gas.

It has further been demonstrated that providing targets with predominantly the same crystal structure (which means about 80-99% fcc crystal target structure for Ni-or Co-based superalloys) is beneficial in terms of process stability, e.g. due to the formation of fewer droplets and the establishment of a perfectly matched IF-1 layer (e.g. with respect to crystallographic consistency and epitaxy to the substrate).

In a further embodiment of the invention, at least one further target having a further metal composition is provided for depositing a transition layer having a different metal composition and/or a barrier layer (IF-2) having a different metal oxide composition. This can be done by providing additional elemental or composite targets to the coating unit. This can be accomplished by co-striking with the superalloy target and/or by independent striking of at least one target having another metallic composition, whereby preferably two types of targets are used to deposit the transition phase of the respective coatings. Thus, the composition of the target having the additional metal composition is selected such that layers having different metal compositions and/or different metal oxide compositions can be deposited from the target having the additional metal composition alone or by co-arcing with the superalloy target.

Alternatively, or even in combination with the use of a target having a different metal composition as mentioned, gaseous precursors comprising the further metal to be deposited may be introduced into the PVD coating unit in parallel with the vacuum arc deposition of the superalloy target to deposit a transition layer having a different metal composition and/or a barrier layer (IF-2) having a different metal oxide composition. Such precursors may be introduced into the coating unit by using supply lines for inert or reactive gases or by separate lines.

Despite the fact that in general the ratio of at least the main metal component within the transition layer and the main metal component within IF-2 will be substantially the same, it should be mentioned that the ratio of any metal may be varied stepwise or continuously between or even within the layers, for example by co-arcing two or more targets having different metal compositions and varying the respective power input of one or both targets, or by varying the flow rate of one or more gaseous precursors or by applying a mixture of the mentioned methods separately. Such variations in metal content can be particularly applied when forming oxides with oxidation barrier properties, which are formed by high temperature oxidation of high aluminum content surfaces prior to porous oxide deposition in standard TBC designs. One of the goals of the new PVD adhesion layer designs described herein is to replace high temperature oxidation by forming oxides in a PVD in situ process.

In a further embodiment of the invention, the interfacial layer (IF-1) is deposited with a crystal structure that is consistent with the crystal structure of the superalloy substrate. It is thus possible to deposit an epitaxial structure which even mirrors the crystal structure of the corresponding surface position of the superalloy SA. Such a uniform and in particular epitaxial crystal structure applied to polycrystalline, Directionally Solidified (DS) or single crystal (SX) SA surfaces has been shown to give the overall coating excellent properties in terms of oxidation resistance and adhesion.

Preferably, the superalloy oxide and/or the oxide of different metal composition of the barrier layer (IF-2) is deposited with excess oxygen in a reactive gas atmosphere. The ratio of oxygen atoms to metal atoms (surplus) may be at least 1.5 or even at least 5 to form thermodynamically stable oxides, especially the most stable oxides, from the superalloy metal and/or the dissimilar metal composition (composition) that evaporates when the barrier layer (IF-2) is deposited. Thereby, a barrier layer comprising substantially stoichiometric oxides may be formed, in particular in the thermodynamically most stable phase for most or even all metallic elements and/or alloys of the superalloy or of the different metallic composition. Such barrier layer (IF-2) exhibits a dense columnar structure, very different from the nearly randomly grain oriented polycrystalline structure of, for example, the interfacial layer (IF-1) deposited on the surface of the polycrystalline SA.

In contrast to the barrier layer, the interface layer may be deposited in pure metal vapor without any process gas.

Alternatively, a supply of inert gas may be provided to the coating unit to deposit at least one of the interface layer (IF-1), the transition layer and the barrier layer (IF-2) in a process atmosphere containing inert gas.

With regard to basic coating parameters, such as process pressure, arc current and substrate bias, the following should be mentioned.

IF an inert gas is not used, the process pressure for depositing the interface (IF-1) ranges from 0.1mPa to 100 mPa. With the addition of an inert gas, the pressure is increased to about 0.1Pa to 5 Pa. Other process parameters of the interface layer, wherein:

arc current of superalloy target: 80A to 250A;

substrate bias: direct current from-20V to-800V and bipolar pulsed bias.

The process pressure for depositing the Transition Layer (TL) in the oxygen reactive gas ranges from 0.1Pa to 5Pa with and without addition of inert gas. Typically, the process pressure during deposition of the transition layer has been increased from a very low process pressure without any reactive gas being used to deposit the interface (IF-1, see above) to a process pressure (see below) at which the barrier layer (IF-2) is deposited with a large amount of reactive gas. Other process parameters for the transition layer, wherein:

arc current of superalloy target: from 80A to 200A;

arc current of targets with additional metal composition: from 60A to 200A;

substrate bias: from-20V to-800 DC, and unipolar and bipolar pulses.

IF no inert gas is used, the process pressure for depositing the barrier layer (IF-2) ranges between 0.1Pa and 8 Pa. With the addition of inert gas, the pressure is increased to about 0.2Pa to 10 Pa. Other process parameters of the interface layer, wherein:

arc current of superalloy target: from 60A to 200A;

arc current of targets with additional metal composition: from 60A to 220A;

substrate bias: DC from-20V to-600V, preferably unipolar or bipolar pulses.

The composition of the targets having the additional metal composition is selected such that layers having different metal compositions and/or different metal oxide compositions can be deposited from at least one target having the additional metal composition alone or by co-arcing with at least one superalloy target. Alternatively or additionally, precursors containing at least one additional metal to be deposited in the transition and/or barrier layers may be used.

It has proven beneficial to the method of the present invention to use superalloy targets that have been produced by a powder metallurgy process. Examples of such methods are hot pressing, Hot Isostatic Pressing (HIP) and especially Spark Plasma Sintering (SPS).

In a further embodiment of the invention, a further preferably porous ceramic top layer is applied to the surface of the barrier layer (IF-2) in a further process step.

Such a top layer may be applied by thermal spray techniques such as detonation spray, wire arc spray, flame spray, high velocity oxygen fuel coating spray (HVOF), High Velocity Air Fuel (HVAF), thermal spray, cold spray, and preferably plasma spray or vacuum plasma spray.

The invention also has the following objects: methods of producing coated superalloy articles are provided, including the coating methods described above. Such a workpiece may be any component used, for example, in the high temperature region of an industrial gas turbine or aircraft engine, like a turbine blade, vane, or the like.

It is a further object of the present invention to provide a superalloy workpiece comprising:

superalloy substrate

-an interfacial layer (IF-1) of substantially the same superalloy composition directly on the superalloy substrate surface, followed by

-a Transition Layer (TL) having essentially the same superalloy and superalloy oxide or a different metal composition and a different metal oxide, whereby the oxygen content of the transition layer increases from IF-1 to IF-2

-a barrier layer (IF-2) with superalloy oxides or different metal oxides.

IF-1 may thus have a crystal structure that is consistent with or even epitaxial to the crystal structure of the superalloy substrate surface.

The oxygen content in the transition layer may be increased gradually or gradually from IF-1 to IF-2.

The different metal composition in the transition layer may differ from the substantially identical superalloy composition by at least one additional element. It is also possible to differ from the metal composition of the different metal oxides of the barrier layer by at least one further metal, which further metal will be present in the form of an oxide.

The at least one further element may have an electronegativity according to Pauling equal to or less than 1.4. Such low electronegativity is generally directed to metals that have a high potential to bind oxygen, for example when such metals are dispersed in a solid metal matrix that has less tendency to form oxides. Such further element may be a lanthanide, preferably at least one of La, Er or Yb.

Alternatively, the different metal composition may differ from the superalloy composition by the concentration of at least one element or by the concentration and/or addition of at least one of the following additional elements: mg, Al, Cr, Er, Y, Zr, La, Hf and Si.

At least a portion of the additional elements may be oxidized and deposited as Solid Solutions (SS) in the grains and/or as strengthening dispersed Oxides (ODS) along the grain boundaries of the Transition Layer (TL) and/or the barrier layer (IF-2).

It is known that such metals of low electronegativity, like alkali metals, alkaline earth metals, lanthanides, actinides and some metals of groups 3 and 4 of the periodic system of the elements (transition metals), tend to form Solid Solutions (SS) or solids of oxide-enhanced dispersions (ODS) within the grains of the solid host matrix when such metals are located along the grain boundaries of the polycrystalline solid and oxidized by the diffusing oxygen atoms. It is known from the oxide dispersion hardening process that the use of such thermodynamically stable materials (SS and/or ODS) is to strengthen such alloys, e.g. superalloys, by adding only small amounts (about 2 vol%) of such oxide forming elements. However, the coatings according to the invention, when deposited, proved to have a similar effect for the first time. The effect of SS and/or ODS strengthening with partially oxidized superalloys in the transition layer can be shown.

The concentration of at least one metal element or silicon in the transition layer may be adjusted or increased stepwise or gradually from IF-1 to IF-2.

The different metal oxides may comprise at least one of the following oxides or mixtures thereof:

alumina, alumina-chromia, erbium oxide, yttria-alumina, magnesia-alumina, alumina-silica, hafnia-silica.

Whereby the alumina or alumina-chromia may be Al comprising a corundum crystal structure₂O₃Or (AlCr)₂O₃And erbium oxide or yttrium oxide may be Er comprising a cubic crystal structure₂O₃Or Y₂O₃And more than 55%, preferably more than 75%, of each crystal structure may be a corresponding corundum or cubic crystal structure.

The different metal oxide may comprise an aluminum-containing oxide, and the TL layer and/or IF-2 layer may comprise aluminum droplets or droplets having a high content of metallic aluminum.

In the case of oxides containing alumina-chromia, for example of corundum structure and/or dispersed as SS or ODS in the transition and/or barrier layers, the layers may also contain droplets with a high metallic chromium content.

As an example, for IGT and aerospace applications, a ceramic top layer may be provided as a terminal layer on the surface of the barrier layer (IF-2) on top of the bond coat. Such top layers can be made with a porous structure to better accommodate thermal expansion in high temperature applications.

About by continuous

-an interface layer (IF-1)

-a Transition Layer (TL) and

barrier layer (IF-2)

The adhesive layer, of which the following total coating thicknesses can be selected:

1μm≤d_bonding≤200μm

Wherein the layer thickness of the interfacial layer (IF-1):

0.01μm≤d_IF-1≤20μm

wherein the layer thickness of the Transition Layer (TL):

0.1μm≤d_TL≤100μm

wherein the layer thickness of the barrier layer (IF-2):

1μm≤d_IF-2≤50μm

the thickness of the subsequent thermally sprayed ceramic top layer for aerospace or IGT applications is chosen between 10 μm and 3mm and shows excellent adhesion and wear resistance.

Hereinafter, the present invention will be further explained with reference to examples and drawings. It should be mentioned that any combination of any embodiment, modification or example of the invention, if not explicitly mentioned in the present description or claims, is also considered part of the present invention as long as it cannot immediately be considered as dysfunctional by a person skilled in the art.