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Iranian Journal of Materials Science and Engineering، جلد ۱۶، شماره ۱، صفحات ۰-۰
عنوان فارسی
چکیده فارسی مقاله
کلیدواژه‌های فارسی مقاله
عنوان انگلیسی Microstructural Investigation into Premature Failure of Compressor Turbine (CT) Blade Material of High Pressure (HP) PT6A-114A Engine
چکیده انگلیسی مقاله This paper investigates premature failure of High Pressure (HP) PT6A-114A Compressor Turbine (CT) blades used for short-haul aircraft fleet at 6378 hours, contrary to 10000 hours pre-set by the manufacturer. The CT blades were sectioned both transversely and longitudinally and subjected to several microstructural examinations; X-ray Diffraction (XRD), X-ray Fluorescence (XRF), Energy Dispersive Spectroscopy-Scanning Electron Microscopy (EDS-SEM) 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.
کلیدواژه‌های انگلیسی مقاله Inconel 713LC, XRD, XRF, EDS-SEM
نویسندگان مقاله | J. K. Ngoret
Department of Mechanical Engineering, University of Botswana.


| V. P. Kommula
Department of Mechanical Engineering, University of Botswana.
نشانی اینترنتی http://ijmse.iust.ac.ir/browse.php?a_code=A-10-1676-1&slc_lang=en&sid=1
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کد مقاله (doi)
زبان مقاله منتشر شده en
موضوعات مقاله منتشر شده
نوع مقاله منتشر شده Research paper
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