In order to meet future demands on gas turbines like increased efficiencies and reduced emissions an increase of combustion temperatures is necessary. An increase of combustion temperatures consequently leads to increased thermal loads of parts in the hot gas path. To withstand increased turbine temperatures new material and cooling concepts are especially required for the turbine blades. State-of-the-art materials, namely superalloys as substrate and Yttria Stabilized Zirconia (YSZ) as insulation material will not meet these demands. The scope of this work is to show an innovative approach for a blade design. This work emphasizes application of thermal barrier coatings (TBCs) on intermetallic blade material using electron beam physical vapour deposition (EB-PVD). There are results shown dealing with aspects of the coating process as well as test results with different material combinations.
Application of thermal barrier coatings on intermetallic turbine blade materials
2008
16 Seiten, 12 Bilder, 1 Tabelle, 13 Quellen
Aufsatz (Konferenz)
Englisch
Feingießverfahren , Flugzeugbau , intermetallische Verbindung , Laves-Phase , Materialforschung , mechanische Festigkeit , Nickelaluminiumlegierung , physikalisches Aufdampfen , thermisches Spritzen , Turbinenschaufel , Wärmebelastung , Wärmeleitfähigkeit , Wärmeschutzschicht , XRD (Röntgenstrahlbeugung)
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