Experimental Studies on Ti–6Al–4V Alloy for Its Suitability in Gas Turbine Engines

Titanium alloys have a desirable balance of mechanical properties, which is required for gas turbine engine material. Among the titanium alloys, Ti–6Al–4V is found to be the most suitable due to its relatively high strength to weight ratio, good fatigue properties at high temperature, low density, high corrosion resistance, and good weldability. Hence, the study of this alloy for its applicability in gas turbine engines is required. In the present work, the mechanical properties of the selected alloy are tested to find its suitability in the gas turbine engine. Microstructure, hardness, density, and surface roughness are determined and results are presented and discussed. Both as- received and heat-treated samples were characterized. Heat treatment is carried out at 900, 950, and 1000 °C in an electric furnace for 30 min holding time. The microstructural analysis is done using a scanning electron microscope. Comparative analysis of the Rockwell hardness of Ti–6Al–4V alloy with nickel-based superalloys used for blade material is done to determine its suitability for gas turbine blades. From the study, it is found that with the increase in heating temperature, microstructural changes occur in the material. Mechanical properties like hardness and density vary with heat treatment.