Abstract: The invention relates to a method for manufacturing a component, especially of a gas turbine, made of a single crystal (SX) or directionally solidified (DS) nickelbase superalloy, including a heat treatment and a machining and/or mechanical treatment step. The ductility of the component is improved by doing the machining and/or mechanical treatment step prior to said heat treatment and a solution heat treatment of the component is done prior to the machining/mechanical treatment step.

Abstract: The invention relates to a method for manufacturing a component, especially of a gas turbine, made of a single crystal (SX) or directionally solidified (DS) nickelbase superalloy, including a heat treatment and a machining and/or mechanical treatment step. The ductility of the component is improved by doing the machining and/or mechanical treatment step prior to said heat treatment and a solution heat treatment of the component is done prior to the machining/mechanical treatment step.

Abstract: A method of determining the elastoplastic behavior of components, in particular of gas turbine plants, at high temperatures.

Abstract: The present invention relates to a burner, substantially comprising a swirl generator for a combustion air stream and means for introducing fuel into the combustion air stream, the swirl generator having combustion-air inlet openings for the combustion air stream that enters the burner, and the means for introducing fuel into the combustion air stream comprising one or more first fuel feeds having a group of first fuel outlet openings, arranged distributed around the burner axis at a combustion chamber-side end of the burner. The burner is distinguished by the fact that the one or more first fuel feeds having the group of first fuel outlet openings are mechanically decoupled from the swirl generator. The present burner allows reliable and safe use of synthesis gas in both dilute and undiluted form as fuel.

Abstract: A method of determining the elastoplastic behavior of components, in particular of gas turbine plants, at high temperatures.

Abstract: In a method for determining the elasto-plastic behavior of components consisting of anisotropic material, in particular of gas turbine installations, at high temperatures, in which method, first of all, the linear-elastic behavior is determined and, on the basis of the linear-elastic results, the inelastic behavior is also taken into account by applying Neuber's rule, the anisotropic properties of the components, as occur in particular on account of the use of single crystal materials, are taken into account in a simple manner by using a modified anisotropic Neuber's rule of the form σ * 2 = σ ep 2 + σ ep 2 ⁢ D _ · E — —

Abstract: The invention relates to a method for producing a cast part of a thermal turbo-machine by way of a known casting process. Between a model mold and a ceramic insert, projections are located on the ceramic insert, whereby the projections have an angle (&agr;, &bgr;) between the center line and the outer edge of the projections of less than 30°, and whereby the projections are used both for the fixation of the insert during the casting process and for the reduction of the notch factor inside the recesses created in the cast part.

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: In a method for determining the elasto-plastic behavior of components consisting of anisotropic material, in particular of gas turbine installations, at high temperatures, in which method, first of all, the linear-elastic behavior is determined and, on the basis of the linear-elastic results, the inelastic behavior is also taken into account by applying Neuber's rule, the anisotropic properties of the components, as occur in particular on account of the use of single crystal materials, are taken into account in a simple manner by using a modified anisotropic Neuber's rule of the form 1 σ * 2 = σ e ⁢   ⁢ p 2 + σ e ⁢   ⁢ p 2 ⁢ D _ · E _ _ E R · D _ ⁢ σ v * 2 σ * 2 ⁢ α ⁡ ( σ e ⁢   ⁢ p 2 σ 0 2 ⁢ σ v * 2 σ * 2 ) n - 1

Abstract: The invention relates to a method for producing a cast part of a thermal turbo-machine by way of a known casting process. Between a model mold and a ceramic insert, projections are located on the ceramic insert, whereby the projections have an angle (&agr;, &bgr;) between the center line and the outer edge of the projections of less than 30°, and whereby the projections are used both for the fixation of the insert during the casting process and for the reduction of the notch factor inside the recesses created in the cast part.