Ti6Al4V-SiCf composite, manufactured by Hot Isostatic Pressing (HIP) at Centro Sviluppo Materiali, has been submitted to long-term heat treatments (up to 1000 hours) at 400 and 600°C. The mechanical properties of the material, in as-fabricated condition and after heat treatments, have been investigated by instrumented indentation (FIMEC), dynamic modulus, tensile and fatigue tests. For comparison some experiments have been carried out also on the monolithic Ti6Al4V alloy. Results show that heat treatments, also the most severe examined here, do not produce remarkable variations of mechanical characteristics. In agreement with the microstructure examinations presented in part I, this behaviour, quite promising for future aeronautical applications, can be primarily ascribed to the stability of fibre-matrix interface. © (2009) Trans Tech Publications, Switzerland.
Long-term heat treatments on Ti6Al4V-SiCf Composite. Part II - Mechanical characterization / P., Deodati; R., Donnini; R., Montanari; C., Testani; Valente, Teodoro. - 604-605:(2009), pp. 341-350. (Intervento presentato al convegno International Conference Recent Developments in the Processing and Applications of Structural Metals and Alloys tenutosi a Ancona nel 22 June 2008 through 25 June 2008) [10.4028/3-908453-09-7.341].
Long-term heat treatments on Ti6Al4V-SiCf Composite. Part II - Mechanical characterization
VALENTE, Teodoro
2009
Abstract
Ti6Al4V-SiCf composite, manufactured by Hot Isostatic Pressing (HIP) at Centro Sviluppo Materiali, has been submitted to long-term heat treatments (up to 1000 hours) at 400 and 600°C. The mechanical properties of the material, in as-fabricated condition and after heat treatments, have been investigated by instrumented indentation (FIMEC), dynamic modulus, tensile and fatigue tests. For comparison some experiments have been carried out also on the monolithic Ti6Al4V alloy. Results show that heat treatments, also the most severe examined here, do not produce remarkable variations of mechanical characteristics. In agreement with the microstructure examinations presented in part I, this behaviour, quite promising for future aeronautical applications, can be primarily ascribed to the stability of fibre-matrix interface. © (2009) Trans Tech Publications, Switzerland.I documenti in IRIS sono protetti da copyright e tutti i diritti sono riservati, salvo diversa indicazione.
