The invention provides a molten Al—Si alloy corrosion resistant composite coating and a preparation method and application thereof. The composite coating layer comprises an aluminized layer and a TiO.sub.2 film layer from a surface of a substrate to the outside in sequence. The preparation method of the coating layer comprises the following steps: (step S1) making a surface treatment to an Fe-based alloy, and then aluminizing with a solid powder penetrant; (step S2) sand-blasting the aluminized Fe-based alloy; (step S3) washing and drying the Fe-based alloy which has been sand-blasted; and (step S4) depositing the TiO.sub.2 film layer on a surface of the dried aluminized Fe-based alloy by using an atom layer vapor deposition. The application of the molten Al—Si alloy corrosion resistant composite coating is used for a solar thermal power generation heat exchange tube.

A preparation method of a zirconium-titanium-based alloy embedded aluminized layer includes putting a zirconium-titanium-based alloy and an aluminiferous penetrant into a mould from bottom to top in a sequence of a first penetrant layer, a first zirconium-titanium-based alloy, a second penetrant layer, a second zirconium-titanium-based alloy and a third penetrant layer, and compacting to obtain a mixed sample; sequentially covering a surface of a mixed sample with activated carbon powder and alkali metal halide, and then carrying out heating and cooling treatments to obtain a zirconium-titanium-based alloy embedded aluminized layer. The preparation method does not need to adopt a special heating furnace or carry out heat treatment under a vacuum condition in an actual application, which simplifies operation process and condition and is suitable for large-scale production and application due to few technical difficulties and low equipment investment cost.

A preparation method of a zirconium-titanium-based alloy embedded aluminized layer includes putting a zirconium-titanium-based alloy and an aluminiferous penetrant into a mould from bottom to top in a sequence of a first penetrant layer, a first zirconium-titanium-based alloy, a second penetrant layer, a second zirconium-titanium-based alloy and a third penetrant layer, and compacting to obtain a mixed sample; sequentially covering a surface of a mixed sample with activated carbon powder and alkali metal halide, and then carrying out heating and cooling treatments to obtain a zirconium-titanium-based alloy embedded aluminized layer. The preparation method does not need to adopt a special heating furnace or carry out heat treatment under a vacuum condition in an actual application, which simplifies operation process and condition and is suitable for large-scale production and application due to few technical difficulties and low equipment investment cost.

A method for coating a component of an aircraft engine with a wear-resistant layer, wherein the component is first coated at least regionally with a nickel- or cobalt-based alloy and subsequently aluminized. Also disclosed is a method for producing a spray powder for producing a wear-resistant layer of a component of an aircraft engine.

Various embodiments herein relate to electrochromic devices, methods of fabricating electrochromic devices, and apparatus for fabricating electrochromic devices. In a number of cases, the electrochromic device may be fabricated to include a particular counter electrode material. The counter electrode material may include a base anodically coloring material. The counter electrode material may further include one or more halogens. The counter electrode material may also include one or more additives.

Various embodiments herein relate to electrochromic devices, methods of fabricating electrochromic devices, and apparatus for fabricating electrochromic devices. In a number of cases, the electrochromic device may be fabricated to include a particular counter electrode material. The counter electrode material may include a base anodically coloring material. The counter electrode material may further include one or more halogens. The counter electrode material may also include one or more additives.

A turbomachine part includes (i) a nickel-based superalloy substrate including, in mass content, 5.0% to 8.0% cobalt, 6.5% to 10% chromium, 0.5% to 2.5% molybdenum, 5.0% to 9.0% tungsten, 6.0% to 9.0% tantalum, 4.5% to 5.8% aluminum, hafnium in a mass content greater than or equal to 2000 ppm, and optionally including niobium in a mass content less than or equal to 1.5%, and optionally at least one of carbon, zirconium and boron each in a mass content less than or equal to 100 ppm, the remainder being composed of nickel and unavoidable impurities; and (ii) a β-structured nickel aluminide coating covering the substrate.

A coated part includes a metallic substrate, a thermal barrier comprising a ceramic material and covering the metallic substrate, wherein the coated part further includes a protective coating covering the thermal barrier, the protective coating including, in a first region, a first MAX phase, denoted PZ2, of formula (Zr.sub.xTi.sub.1-x,).sub.2AlC or a first MAX phase, denoted PC2, of formula (Cr.sub.xTi.sub.1-x,).sub.2AlC with x non-zero and less than or equal to 1 in the MAX phases PZ2 and PC2, and the protective coating includes, in a second region covering the first region, a second MAX phase of formula Ti.sub.2AlC.

A thin-walled metal part, and a method to fabricate such a part out of various alloys. A plurality of layers are formed, each of the layers being formed on a polymer template or on a previously formed layer. A homogenizing heat treatment is used to cause chemical elements in the layers to interdiffuse, to form a single continuous layer with a substantially uniform alloy composition.

A coating composition for a heat exchanger tube including vanadium (V), a flux, and a binder, wherein the vanadium is included in an amount of 28 to 38 parts by weight with respect to 100 parts by weight of the composition, and a coating method of a heat exchanger tube using the same are provided.