Abstract: A method for determining fatigue lifetime consumption of an engine component, by defining a reference thermal load cycle, the reference thermal load cycle being characterized by a reference load cycle amplitude and a reference load cycle time, and determining a reference load cycle lifetime consumption. The method includes measuring a temperature of the engine component, determining a thermal load cycle based upon the temperature measurement, determining a load cycle amplitude, determining a load cycle time, relating the load cycle time to the reference load cycle time, thereby determining a load cycle time factor, relating the load cycle amplitude to the reference load cycle amplitude, thereby determining a load cycle amplitude factor, combining the load cycle time factor and the load cycle amplitude factor into a combined load cycle factor for determining a load cycle lifetime consumption.

Abstract: A turbomachine component includes a basic component including a first outer wall having a first joint face. An additional part includes a second outer wall having a second joint face, wherein the first and the second wall enclose an internal cavity, and wherein the first and the second joint faces are joined together between the basic component and the additional part. At least one wall-like intermediate piece is disposed in at least one of the basic component and the additional part and extends from the respective outer wall into the internal cavity, the at least one wall-like intermediate piece including a cutout having a transition contour that deviates from a straight line and is disposed at at least one transition between the at least one wall-like intermediate piece and the outer wall so as to relieve at least one of a mechanical and a thermal stress.

Abstract: A turbomachine component includes a basic component including a first outer wall having a first joint face. An additional part includes a second outer wall having a second joint face, wherein the first and the second wall enclose an internal cavity, and wherein the first and the second joint faces are joined together between the basic component and the additional part. At least one wall-like intermediate piece is disposed in at least one of the basic component and the additional part and extends from the respective outer wall into the internal cavity, the at least one wall-like intermediate piece including a cutout having a transition contour that deviates from a straight line and is disposed at at least one transition between the at least one wall-like intermediate piece and the outer wall so as to relieve at least one of a mechanical and a thermal stress.

Abstract: A method for increasing the fatigue life of a blade root of a turbomachine blade, wherein the blade root has at least one slot for back-gripping fixing of the blade root in a shaft component or a casing component of a turbomachine. The method comprises impressing a mechanical stress field in the notch root in a section of the slot, wherein the impressed mechanical stress field brings about a plastic deformation of the notch root. The impressed mechanical stress field is then progressively moved in the slot longitudinal direction of the slot. After this, the impressed mechanical stress field is removed again, wherein residual compression stresses remain in the notch root of the slot in the region of the slot in which the mechanical stress field was impressed.

Abstract: A turbomachine blade is disclosed having a shroud element, wherein plastic deformations and lifting of the shroud element on one side result during operation under centrifugal load. This load may result in high-temperature creep of the blade. A sealing strip which is arranged on the shroud element can be configured with a thickness varying in a circumferential direction. The mass of the shroud element and thus the asymmetrical centrifugal load and the lifting of the shroud element on one side resulting therefrom can be reduced by material removal at regions lying on the outside in the circumferential direction.

Abstract: A method for increasing the fatigue life of a blade root of a turbomachine blade, wherein the blade root has at least one slot for back-gripping fixing of the blade root in a shaft component or a casing component of a turbomachine. The method comprises impressing a mechanical stress field in the notch root in a section of the slot, wherein the impressed mechanical stress field brings about a plastic deformation of the notch root. The impressed mechanical stress field is then progressively moved in the slot longitudinal direction of the slot. After this, the impressed mechanical stress field is removed again, wherein residual compression stresses remain in the notch root of the slot in the region of the slot in which the mechanical stress field was impressed.

Abstract: A turbomachine blade is disclosed having a shroud element, wherein plastic deformations and lifting of the shroud element on one side result during operation under centrifugal load. This load may result in high-temperature creep of the blade. A sealing strip which is arranged on the shroud element can be configured with a thickness varying in a circumferential direction. The mass of the shroud element and thus the asymmetrical centrifugal load and the lifting of the shroud element on one side resulting therefrom can be reduced by material removal at regions lying on the outside in the circumferential direction.