Abstract: A vane device for a gas turbine having an inner shroud and an outer shroud, an aerofoil arranged between the inner shroud and the outer shroud, the aerofoil and/or inner shroud and/or an outer shroud having a first layer of MCrAlY coating over a substrate, a coated surface section which is coated with a thermal barrier coating over the first layer of MCrAlY coating, a second layer of MCrAlY coating provided between the first layer of MCrAlY and the thermal barrier coating of the coated surface section.

Abstract: A vane device for a gas turbine having an inner shroud and an outer shroud, an aerofoil arranged between the inner shroud and the outer shroud, the aerofoil and/or inner shroud and/or an outer shroud having a first layer of MCrAlY coating over a substrate, a coated surface section which is coated with a thermal barrier coating over the first layer of MCrAlY coating, a second layer of MCrAlY coating provided between the first layer of MCrAlY and the thermal barrier coating of the coated surface section.

Abstract: A vane device for a gas turbine is provided. The vane device includes a first airfoil having a first suction side and a first pressure side, a second airfoil having a second suction side and a second pressure side, an inner shroud and an outer shroud. The first airfoil and the second airfoil are arranged between the inner shroud and the outer shroud, wherein the first airfoil and the second airfoil are at least partially coated with a MCrAlY coating. At least the first suction side has a first coated surface section which is coated with a thermal barrier coating and which represents at least a part of the total surface of the first suction side. At least the inner shroud or the outer shroud has a further coated surface section which is coated with a further thermal barrier coating. A corresponding method of manufacturing is also provided.

Abstract: A layer system and a method for producing a component having such a layer system are provided. The layer system includes a substrate a substrate, at least one MCrX layer on the substrate, and a chromium-rich layer on or in the at least one MCrX layer. X includes at least one element selected from the group consisting of yttrium (Y), silicon (Si), aluminum (Al) and boron (B). M includes at least one element selected from the group consisting of nickel (Ni) and cobalt (Co).

Abstract: An airfoil with a coated surface section which having a platinum aluminide and a TBC coating is provided herein. Furthermore, an airfoil arrangement for a gas turbine including an airfoil, an inner shroud, and an outer shroud, wherein the airfoil is arranged between the inner shroud and the outer shroud, wherein the airfoil comprises a coated surface section which is coated with a platinum-aluminide coating and a thermal barrier coating and which represents at least a part of the total surface of the airfoil, wherein the thermal barrier coating of the coated surface section is spaced from the inner shroud and/or the outer shroud with a distance (x) and wherein the distance (x) is between 5% and 25% of a total length of the airfoil between the inner shroud and the outer shroud is provided herein.

Abstract: A vane device for a gas turbine is provided. The vane device includes a first airfoil having a first suction side and a first pressure side, a second airfoil having a second suction side and a second pressure side, an inner shroud and an outer shroud. The first airfoil and the second airfoil are arranged between the inner shroud and the outer shroud, wherein the first airfoil and the second airfoil are at least partially coated with a MCrAIY coating. At least the first suction side has a first coated surface section which is coated with a thermal barrier coating and which represents at least a part of the total surface of the first suction side. At least the inner shroud or the outer shroud has a further coated surface section which is coated with a further thermal barrier coating. A corresponding method of manufacturing is also provided.

Abstract: A layer system and a method for producing a component having such a layer system are provided. The layer system includes a substrate a substrate, at least one MCrX layer on the substrate, and a chromium-rich layer on or in the at least one MCrX layer. X includes at least one element selected from the group consisting of yttrium (Y), silicon (Si), aluminum (Al) and boron (B). M includes at least one element selected from the group consisting of nickel (Ni) and cobalt (Co).