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Advanced aero engine design focuses on reduced specific fuel consumption and increased thrust-toweight ratio. This ultimately calls for increased pressure ratios as well as higher operating temperatures and certainly represents a major challenge to the structural design and the materials employed. Increased high temperature capability materials are required as well as extremely lightweight structures. For the high pressure turbine design concepts incorporating ceramic heat-shielding coatings, i.e. thermal barrier coatings (TBCs), would overcome the natural limits given by the melting point. Utilising the insulating materials properties of the ceramic top coating, TBCsp predominantly exert their beneficial effect by reducing the average metal temperature and mitigating the effect of hot spots. However, increasing demands placed on the high-temperature capabilities of future turbine components require TBC solutions, i.e. the TBC is an integral part of the component and thus vital for its safe operation. Based on the extensive body of knowledge available from the field and laboratory tests, the paper highlights both research and development status and trends devoted to future generation electron beam physical vapour deposition (EB-PVD) TBC systems with significant improvements in performance and reliability. The paper highlights the present developments in improving the ceramic top coating, particularly looking for advanced systems with reduced thermal conductivity.