Archivio Istituzionale della RicercaThe intermetallic alloy Ti-48Al-2Cr-2Nb is used for fabrication of low pressure turbine blades, because its good mechanical properties, low density and oxidation resistance at high temperature. However, the alloy application is still limited by significant oxidation above 850 °C. A thin AlTiN ceramic coating of about 3 µm, applied by magnetron spattering, can improve the surface oxidation resistance of this intermetallic alloy. The objective of this work is to investigate the integrity and oxidation resistance of TiAlN coating after thermal cycling under oxidizing atmosphere at temperatures up to 850°C and 950°C. Thermal cycling was performed in a burner rig specifically designed to simulate the operating conditions of turbine engine components.
Oxidation and Thermal Shock Resistance of AlTiN Ceramic Thin Coating Deposited by Magnetron Sputtering (Hipims) on Ti-48Al-2Cr-2Nb Intermetallic Alloy / Ostrovskaya, Oxana; Badini, CLAUDIO FRANCESCO; Miorin, Enrico. - STAMPA. - 2:(2017), pp. 35-35. (Intervento presentato al convegno International Conference on Materials Science and Research tenutosi a Dubai, (Emirati Arabi Uniti) nel November 16-18, 2017).
Oxidation and Thermal Shock Resistance of AlTiN Ceramic Thin Coating Deposited by Magnetron Sputtering (Hipims) on Ti-48Al-2Cr-2Nb Intermetallic Alloy
Oxana Ostrovskaya;Claudio Francesco Badini;
2017
Abstract
The intermetallic alloy Ti-48Al-2Cr-2Nb is used for fabrication of low pressure turbine blades, because its good mechanical properties, low density and oxidation resistance at high temperature. However, the alloy application is still limited by significant oxidation above 850 °C. A thin AlTiN ceramic coating of about 3 µm, applied by magnetron spattering, can improve the surface oxidation resistance of this intermetallic alloy. The objective of this work is to investigate the integrity and oxidation resistance of TiAlN coating after thermal cycling under oxidizing atmosphere at temperatures up to 850°C and 950°C. Thermal cycling was performed in a burner rig specifically designed to simulate the operating conditions of turbine engine components.
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https://hdl.handle.net/11583/2693405
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