Abstract: A method of estimating the lifetime of a thermal barrier coating (14), which is applied to the surface of a member subjected to cyclical thermal loads, especially a vane and/or blade of a gas turbine, by means of a bond coat (12) lying in between the coating and the member, leads to more accurate results with simplified calculation by determining, in a first step, the amplitude of the normal stress (&Dgr;&sgr;n) perpendicular to the interface between the bond coat (12) and the thermal barrier coating (14) during cyclical loading, and calculating, in a second step, the number Ni of cycles to failure for every normal stress amplitude (&Dgr;&sgr;n) in accordance with the formula N i ⁢   = C ⁡ ( △σ n σ 0 ) m

Abstract: A method of estimating the lifetime of a thermal barrier coating (14), which is applied to the surface of a member subjected to cyclical thermal loads, especially a vane and/or blade of a gas turbine, by means of a bond coat (12) lying in between, leads to more accurate results with simplified calculation by determining, in a first step, the amplitude of the normal stress (&Dgr;&sgr;n) perpendicular to the interface between the bond coat (12) and the thermal barrier coating (14) during cyclical loading, and calculating, in a second step, the number Ni of cycles to failure for every normal stress amplitude (&Dgr;&sgr;n) in accordance with the formula 1 N i = ( C ⁢ ( Δσ n σ 0 ) ) m

Abstract: The invention relates to a sealing coating for a thermally stressed component, particularly a turbine component, for protection from corrosion and/or oxidation and/or erosion. To improve the life of the protective coating or of the component, the protective coating has a single-layer or multilayer sealing coating of an amorphous material.

Abstract: A turbine blade and a method for its production. In order to protect the turbine blade from being damaged by particles carried in the gas, surfaces of the turbine blade are melted down to a predetermined depth in order to form a defined amorphous region on a crystalline structure of a base material. The surfaces are then cooled down at a predetermined temperature reduction rate per unit time.

Abstract: A coating composition for superalloy structural parts, especially, for gas turbine vanes and blades, which has high resistance to oxidation and corrosion and has excellent mechanical behavior. The coating preferably comprises: 18 to 28 wt % of Co; 11 to 15 wt % of Cr; 11.5 to 14 wt % of Al; 1 to 8 wt % of Re; 1 to 2.3 wt % of Si; 0.2 to 1.5 wt % of Ta; 0.2 to 1.5 wt % of Nb; 0.3 to 1.3 wt % of Y; 0 to 1.5 wt % of Mg; 0 to 0.5 wt % of a total of La and La-series; 0 to 0.1 wt % of B; less than 0.1 wt % of Hf; and less than 0.1 wt % of C. The balance of the coating is Ni. A total of Y, La, and La-series is from 0.3 to 2.0 wt %, and a total of Si and Ta is equal to or less than 2.5 wt %.

Abstract: The invention relates to a coating composition for superalloy structural parts, especially for gas turbine vanes and blades, which provides simultaneously excellent environmental resistance and highly improved thermomechanical behavior. The coating consists essentially of, by weight, 28-35% Co, 11-15% Cr, 10-13% Al, 0-1% Re, 1-2% Si, 0.2-1% Ta, 0.005-0.5% Y, 0-5% Ru, 0-1% Ca, 0-1% Mg, 0-0.5% La (or elements from the La series), 0-0.1% B, balance Ni and incidental impurities.