Alstom Technology Limited

Ansaldo Energia IP UK Limited

Frigyes Szücs

Alexander Stankowski

Thomas Duda

Raphael Schweizer

Igor Zebec

Josip Stedul

Tobias Schmitt

Stefan Werner Kiliani

Stefan Kiliani

A method is provided for reconditioning a turbomachine vane cover plate, by a forming apparatus. The vane having a mounting portion, an airfoil extending radially outward therefrom and a vane head connected to the airfoil. The vane also having a cover plate connected to the vane head, bulged in a direction opposite to the root. In a first analysis step, dimensions of the vane in relation to the cover plate are determined in respect of predefined reference points. If, thereafter, forming of the cover plate seems necessary and possible based on comparison of measurement values from the analysis step with predefined dimension values, the bulged cover plate is formed, at least essentially pressed smooth, by pressing by the forming apparatus in a forming step. After the forming step, the cover plate is re-treated in one or more follow-up steps. An apparatus is also provided for carrying out the method.

Apparatus and method for the forming of turbine vane cover plates

A method for applying a heat insulation layer () or a metallic protective layer to a thermally stressed component () having a basic material () in order to eliminate local damage () or an untreated place in the coating, includes, in a first step, pretreating the local damage () or untreated place, and, in a second step, applying layers () necessary for eliminating the local damage () or untreated place. A markedly improved lifetime of the processed component can be achieved in that, within the first step, the edge regions () of the layers () ending at the local damage () or untreated place are processed so that they form uniformly sloped and terrace-shaped edge regions (). Furthermore, a precharacterization of the entire coated region of the operationally stressed component or critical places by FSECT makes it possible to reduce the risk in terms of otherwise overlooked layer regions, the remaining lifetime of which would not persist for the following operating time.

Method for the application of a protective coating to a thermally stressed component

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Langenbruck, Switzerland

Frigyes Szücs