microstructural investigation into premature failure of compressor turbine (ct) blade material of high pressure (hp) pt6a-114a engine

This paper investigates premature failure of high pressure (hp) pt6a114a compressor turbine (ct) blades used for shorthaul aircraft fleet at 6378 hours, contrary to 10000 hours preset by the manufacturer. the ct blades were sectioned both transversely and longitudinally and subjected to several microstructural examinations; xray diffraction (xrd), xray fluorescence (xrf), energy dispersive spectroscopyscanning electron microscopy (edssem) of the tips, airfoils, as well as the bases. it was observed that from repeated elevated heating, incomplete solutioning and recrystallization of the substrate material, brittle carbides were initiated and developed. the tips were more affected, followed by the airfoils and least at the bases. impingement of heat from the combustors on the ct blades led to rapid graining and rafting with eventual cracking upon cooling. the results further suggested that pores which are typically manufacturing defects were pronounced at the bases than either at the airfoils and the tips. however, contrary to the expectation that the bases would degrade more and rapider, a more near uniform distribution of the cuboidal phase was evident relative to the tips and airfoils, confirming that degradation of the ct blades originated from creep and fatigue.