Siemens Aktiengesellschaft

Siemens Aktiengesellscaft

Michael Dankert

Fathi Ahmad

Werner Stamm

Eckart Schumann

Matthias Oechsner

Stefan Irmisch

Martin Feldhege

Günther Walz

A turbine vane for a stationary gas turbine is provided. The turbine vane includes a hollow vane blade, wherein a rib is provided inside the vane blade to allow a pressure side wall and a suction side wall to support one another. The rib has an opening penetrating the rib near a wall at a height of an external fillet between a side wall, and a platform surface for extending a life of the turbine vane. By the opening, material accumulations in a transition region are avoided or the accumulation is reduced, whereby increases in stiffness and higher temperature gradients associated therewith are avoided.

Turbine vane for a stationary gas turbine

Disclosed is a turbine or compressor component with an integrated cooling channel, in particular a turbine blade, and a method for producing the same. The cooling channel of the component is subjected to internal pressure during a pressure impingement phase, the internal pressure being at a level sufficiently high that it causes the at least semiplastic deformation of the wall regions delimiting the cooling channel.

Method of producing a turbine or compressor component, and turbine or compressor component

The invention refers to a coated turbine blade for a gas turbine, having blade walls divided into sections with locally adapted material temperatures. The cooler material temperatures of the blade walls are at the points where the support ribs merge into the blade walls. The regions with higher material temperatures of the blade walls are at the positions where cavities are arranged inside the blade walls. This is achieved via a ceramic thermal barrier coating having different layer thicknesses that allow different material temperatures. The region of the surface of the blade wall which faces the working medium and lies opposite an internal rib has a thicker thermal barrier coating than a region of the surface of the blade wall which is cooled via a cooling medium that flows in the cavities. This results in homogenization of the material temperature in the connecting regions, which results in prolonged blade life.

Coated turbine blade

A hollow turbine blade is provided including an airfoil profile which is formed by a suction-side profile wall and a pressure-side profile wall and around which a hot gas can flow and which has a profile height, directed along a blade axis, from a platform up to a profile tip, having at least one supporting rib which is provided in the interior of the turbine blade and connects the pressure-side profile wall to the suction-side profile wall in a respective connecting region, and having at least one slot provided in the profile wall on the hot-gas side and extending along the blade axis. The slot of the turbine blade, on the hot-gas side in the profile wall, is opposite the connecting region formed by the supporting rib and the profile wall.

Hollow turbine blade

Method for recording microstructural changes in a layer system component. A specific material parameter of the component is measured. The layer system may include an alloy substrate and an alloy or porous ceramic layer. The material parameter may be measured a plurality of times. The measured material parameter may include electrical capacitance, specific heat capacity, peltier coefficient or magnetic susceptibility. The material parameter may first be measured on a new component and subsequent measurements may be performed at a time interval after operational use. The recorded material parameter is then used to determine microstructural changes in the substrate or the layer material of the component caused by changes in precipitation, cracks, or depletion of an alloying element.

Method for recording microstructural changes in a component

The invention relates to a rotating blade for a turbomachine which can be cross flown by a flow medium, especially for a gas turbine which can be cross flown by a working fluid. The gas turbine comprises a rotating blade base, a platform region which extends in a perpendicular manner thereto and a curved blade profile all of which are arranged in a successive manner. The blade profile extends from a front edge, against which a liquid can flow, to a rear edge between which a suction side and a pressure side of the blade profile are formed by means of a relief slot comprising a longitudinal extension in the blade profile. In order to produce a rotating blade which has increased durability, the relief slot on the end of the blade profile oriented towards the platform region is arranged in the region of the rear edge, extending through the blade profile from the suction side to the pressure side and the longitudinal extension thereof is oriented in an essentially transversal manner in relation to the direction of flow of the working fluid.

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Offenbach, Germany

Michael Dankert