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Turbine blades for airplanes work in adverse conditions, under corrosive environment and high temperatures and pressure conditions. Ti-6Al-2Sn-4Zr-2Mo alloy was developed for high temperatures applications in aerospace area. In this work, Ti-6Al-2Sn-4Zr-2Mo alloy was obtained by powder metallurgy using titanium hydride powders. Samples were manufactured by blended elemental method from a sequence of uniaxial and cold isostatic pressing with subsequent densification by sintering among 800 up to 1400°C, in vacuum. The objective of this work is the analysis of microstructural evolution from the powders dissolution with the increase of the sintering temperature. The alloy was characterized by scanning electron microscopy, X-ray diffraction and Vickers microhardness measurement. Density was measured by Archimedes method.

Titanium alloys parts are ideally suited for advanced aerospace systems, chemical and naval applications and surgical implants because of its high strength-to-weight ratio, high resistance to many corrosive environments, and can be used over a wide range of temperatures. Powder metallurgy of titanium and Ti-based alloys may lead to the obtainment of components having weak-to-absent textures, uniform grain structure and higher homogeneity compared with conventional wrought products. In this work, results of the densification of Ti-6Al-4V, Ti-6Al-7Nb and Ti-13Nb-13Zr alloys after cold and isostatic pressing with subsequent densification by sintering between 900-1400°C using hydride titanium powders are presented. The samples were characterized by X-ray diffraction, scanning electron microscopy, Vickers indentation and density measurements.