Siemens Aktiengesellschaft

Praxair S.t. Technologies Inc.

Mick Whitehurst

Paul Mathew Walker

Paul Box

Bruce G McMordie

John Nicholls

Thomas Kircher

Paul Padley

Hugh Evans

Thomas Lewis

Nigel Simms

Jonathan Venezia

Adrian Weatherill

Bruce Mcmordie

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: &#x3c;/=0.2; Mn: &#x3c;/=0.2; P: &#x3c;/=0.005; S: &#x3c;/=0.0015; Al: 4.0 to 5.5; B: &#x3c;/=0.03; Co: 5.0 to 9.0; Cr: 18.0 to 22.0; Cu: &#x3c;/=0.1; Fe: &#x3c;/=0.5; Hf: 0.9 to 1.3; Mg: &#x3c;/=0.002; Mo: &#x3c;/=0.5; N: &#x3c;/=0.0015; Nb: &#x3c;/=0.01; O: &#x3c;/=0.0015; Ta: 4.8 to 5.2; Ti: 0.8 to 2.0; W: 1.8 to 2.5; Zr: &#x3c;/=0.01; Ni: balance; and inevitable impurities.

Nickel-base superalloy

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).

Layered coating system with a MCrAlX layer and a chromium rich layer and a method to produce it

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.

Method of protecting a component against hot corrosion and a component protected by said method

Turbine components with different types of coatings on different parts thereof are described. The coatings are chosen such that they are especially adapted to the thermal and corrosive conditions being present on the parts of the component during use. A method to coat a turbine component is also described.

Coated turbine component and method of coating a turbine component

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Hayle, United Kingdom

Mick Whitehurst