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US 2010/0061836 A1Published application
Process for producing a turbine blade or vane with an oxide on a metallic layer, use of such a turbine blade or vane, a turbine and a method for operating a turbine
OwnerWerner Stamminventor
Life of this patent
Estimating the term…
Abstract
A process for producing a component of a gas turbine having a substrate with a metallic layer is provided. The metallic layer is a MCrAlX layer which is treated at temperatures elevated above the operating temperature, by at least 50° C., so that the oxidation and corrosion behavior are improved. In particular a MCrAlX of the type, NiCoCrAlX is used.
Claims21
1-22. (canceled)
A method for producing a component of a gas turbine having a substrate with a metallic layer, comprising:
- oxidizing the metallic layer at a temperature which is 50° C. more than an operating temperature of the metallic layer in the gas turbine,
- wherein the metallic layer forms an oxide layer.
A turbine, comprising:
- a compressor;
- a combustion chamber;
- a turbine region;
- and
- a plurality of components having a substrate with a metallic layer wherein the metallic layer can form an oxidized layer,
- wherein a thermal barrier coating applied on the plurality of turbine blades or the plurality of turbine vanes of a third stage and a fourth stage of the turbine region is oxidized before being installed, and
- wherein the plurality of components are a plurality of turbine blades or a plurality of turbine vanes.
4 more elements
A method for operating a turbine, comprising:
- having a plurality of turbine blades or a plurality of vanes which have an oxidized metallic layer;
- producing the plurality of turbine blades or a plurality of vanes by oxidizing the metallic layer at a temperature which is 50° C. more than an operating temperature of the metallic layer in the turbine, and
- regulating an operating temperature of the turbine blade or the turbine vane so that the operating temperature is at least 50° C. lower than a temperature at which the oxidized metallic layer was formed on the turbine blade or the turbine vane.
Dependencies are inferred from the claim text.