Next-generation materials for turbine engines: Environmental and mechanical performance of a metallic ultra-high temperature materials system

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In order to meet Europe's vision for aviation, set out in Flightpath 2050, the aviation industry must significantly reduce emissions of environmentally harmful gases, such as CO 2 and NO x . The efficiency of a gas turbine engines can be significantly improved and emissions reduced by increasing the turbine entry temperature (TET).Currently, turbine blades in the hottest part of the engine are made from Nickel-based superalloys. However, surface temperatures of these materials are approaching their melting temperatures, so new metallic ultra-high temperature materials with capabilities beyond Nickel-based superalloys are needed. Refractory metal intermetallic composites, such as Niobium-silicide based alloys, can meet property targets set by industry. These alloys have excellent high temperature strength and creep resistance. However, they will require environmental coatings to boost oxidation resistance. The coating will be of the bond coat/thermally grown oxide/top coat design.In this project, you will develop a materials system (substrate and coating(s)) using advanced powder metallurgy processes (e.g. Field-assisted sintering technology/Spark plasma sintering (FAST/SPS) or Hot isostatic pressing (HIP)) utilising the world class facilities within the Royce Institute. The materials system will comprise of a Niobium-silicide based substrate with a balance of properties and a bond coat comprising of refractory high entropy alloy(s). Microstructure, mechanical and environmental properties will be characterised and the oxidation and properties of the substrate/bond-coat interface will be modelled. This work will accelerate the application of these new materials in aero engines, driving energy efficiency and reducing emissions within the aviation industry.