Abstract: A blade for a rotor of a gas turbine has a cast substrate including: a root for connecting the blade to a rotor of a gas turbine, a platform having a lower surface from which the root extends and an upper surface opposite to the lower surface, an aerofoil extending from the upper surface of the platform, the lower surface and the root having an anti-corrosion layer of an high Cr blade alloy over the substrate. A method for manufacturing a blade where the lower surface and the root have the anti-corrosion layer.

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 sealing part for a turbine section of a gas turbine to seal a gap between two circumferentially adjacent rotor blades includes a body, and a coating applied on a surface of the body. The coating includes a soft heat resisting material that deforms under centrifugal force of the rotating rotor blades.

Abstract: A method of coating a superalloy substrate, includes (a) aluminising the surface of the substrate to form an inner coating layer; (b) applying a slurry with a solid content including Cr, Al, Ni and Co onto the inner coating layer, where the Cr-content of the solid content is between 15% and 30% by weight thereof, and diffusion heat treating the slurry applied to the inner coating layer at a temperature above 800° C. for 1 to 8 hours to form an intermediate coating layer; and (c) applying a Cr-free slurry with a solid content including Al and Ni onto the intermediate coating layer, where the Al-content of the solid content is between 15% and 30% by weight of the solid content, and diffusion heat treating the slurry applied onto the intermediate surface layer at a temperature above 800° C. for 1 to 8 hours to form an outer coating layer.

Abstract: A blade for a rotor of a gas turbine has a cast substrate including: a root for connecting the blade to a rotor of a gas turbine, a platform having a lower surface from which the root extends and an upper surface opposite to the lower surface, an aerofoil extending from the upper surface of the platform, the lower surface and the root having an anti-corrosion layer of an high Cr blade alloy over the substrate. A method for manufacturing a blade where the lower surface and the root have the anti-corrosion layer.

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 slurry composition for aluminizing a superalloy component is provided, wherein the slurry includes an organic binder and a solid content including at least aluminum, silicon, and at least one of hafnium or yttrium.

Abstract: A platform for supporting a nozzle guide vane for a gas turbine is provided. The platform has a gas passage surface arranged to be in contact with a streaming operation gas, and a cooling channel for guiding a cooling fluid within the cooling channel formed in an inside of the platform. A cooling portion of an inner surface of the cooling channel is in thermal contact with the gas passage surface. The platform is an integrally formed part representing a segment in a circumferential direction of the gas turbine. The cooling channel has a first cooling channel portion and a second cooling channel portion arranged downstream of the first cooling channel portion with respect to a streaming direction of the operation gas. The first cooling channel portion and the second cooling channel portion are interconnected.

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 nickel-base superalloy for turbine vanes or turbine blades is provided. The nickel-base superalloy has in wt %: C: equal to or greater 0.1; Si: </=0.2; Mn: </=0.2; P: </=0.005; S: </=0.0015; Al: 4.0 to 5.5; B: </=0.03; Co: 5.0 to 9.0; Cr: 18.0 to 22.0; Cu: </=0.1; Fe: </=0.5; Hf: 0.9 to 1.3; Mg: </=0.002; Mo: </=0.5; N: </=0.0015; Nb: </=0.01; O: </=0.0015; Ta: 4.8 to 5.2; Ti: 0.8 to 2.0; W: 1.8 to 2.5; Zr: </=0.01; Ni: balance; and inevitable impurities.

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: A slurry composition for aluminising a superalloy component is provided, wherein the slurry includes an organic binder and a solid content including at least aluminium, silicon, and at least one of hafnium or yttrium.

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: 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 coating system for a superalloy substrate is provided. The coating system has an inner coating layer, an intermediate coating layer and an outer coating layer. The inner coating layer is an aluminide layer, the intermediate coating layer is a diffusion layer including Cr, Al, Ni and Co, where the Cr-content is between 15% by weight and 30% by weight, and the outer coating layer is a Cr-free diffusion layer including Al and Ni, where the Al-content is between 15% by weight and 30% by weight.

Abstract: A method of improving a superalloy component is proposed. The method involves the introduction of at least one additive into the superalloy component, the at least one additive being selected from the group of Hf, La, and Y. The at least one additive is introduced into a surface layer of the component. Preferably, the surface layer has a depth of 0.5 mm or less. The component may include, for example, an airfoil of a gas turbine.

Abstract: A MCrAlY alloy, methods to produce a MCrAlY layer and a honeycomb seal are provided. The MCrAlY alloy includes chromium, aluminum, yttrium and iron and optionally titanium, hafnium or silicon. The honeycomb seal includes a substrate, honeycomb cells and a protective coating on side walls of the honeycomb cells or a diffusion area inside side walls of the honeycomb cells, the protective coating or the diffusion area including the MCrAlY alloy.

Abstract: A platform segment for supporting a nozzle guide vane for a gas turbine is provided. The platform segment includes a gas passage surface arranged to be in contact with a streaming gas exhausted from a combustor, wherein the streaming gas streams along the gas passage surface in a streaming direction, a cooling surface, opposite to and thermally connected to the gas passage surface and arranged to be in contact with a cooling fluid, a wall protruding from the cooling surface and extending at least partially in the streaming direction, wherein the wall is arranged circumferentially between positions, at which adjacent guide vanes are to be provided, such that cooling fluid is channeled by the wall for cooling a downstream portion of the cooling surface, and a further wall protruding from the cooling surface and extending at least partially in the streaming direction.

Abstract: A method of protecting a component, in particular a turbine blade, from the effects of hot corrosion includes the steps of applying a chromium diffusion coating to the component and applying a coating of a ceramic material to one or more selected regions of the chromium diffusion coating. The selected regions are regions which, in subsequent use of the component, are subjected to temperatures lower than a predetermined temperature. The ceramic material preferably includes a binder combined with a metal oxide. In a preferred embodiment, a turbine blade is coated over the whole of its internal and external surfaces with the chromium diffusion coating; an aluminum diffusion coating is then applied, through a mask, to the aerofoil surfaces and the internal surfaces of the blade; the mask is removed and the ceramic material is applied as an overlay to the chromium diffusion coating in a region between the platform and the root of the blade.

Abstract: A platform for supporting a nozzle guide vane for a gas turbine is provided. The platform has a gas passage surface arranged to be in contact with a streaming operation gas, and a cooling channel for guiding a cooling fluid within the cooling channel formed in an inside of the platform. A cooling portion of an inner surface of the cooling channel is in thermal contact with the gas passage surface. The platform is an integrally formed part representing a segment in a circumferential direction of the gas turbine. The cooling channel has a first cooling channel portion and a second cooling channel portion arranged downstream of the first cooling channel portion with respect to a streaming direction of the operation gas. The first cooling channel portion and the second cooling channel portion are interconnected.