The estimation of fatigue life of an intact gas turbine compressor blade and the same blade with foreign object damage based on critical plane methods

Zolfaghari, A.; Shahani, A. R.

doi:10.22061/jcarme.2026.113064.2825

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	The estimation of fatigue life of an intact gas turbine compressor blade and the same blade with foreign object damage based on critical plane methods
Journal of Computational & Applied Research in Mechanical Engineering (JCARME)
مقالات آماده انتشار، اصلاح شده برای چاپ، انتشار آنلاین از تاریخ 20 مرداد 1405 اصل مقاله (1.09 M)
نوع مقاله: Research Paper
شناسه دیجیتال (DOI): 10.22061/jcarme.2026.113064.2825
نویسندگان
A. Zolfaghari¹؛ A. R. Shahani^* ²
¹Department of Applied Mechanics, Faculty of Mechanical Engineering, K. N. Toosi University of Technology, Tehran, Iran
²Department of Applied Mechanics, Faculty of Mechanical Engineering, K. N. Toosi University of Technology, Tehran, 19395-1999, Iran
تاریخ دریافت: 23 اردیبهشت 1405، تاریخ بازنگری: 14 مرداد 1405، تاریخ پذیرش: 20 مرداد 1405
چکیده
The first stage compressor blades of the gas turbine are subject to occasional failure due to their operating conditions. Initial evaluations indicate that microcracks that form in critical areas of the blade during fatigue loading make the blade prone to failure. Therefore, it is of great importance to find the locations of the blade where microcracks are most likely to form. In this study, extensive numerical and analytical investigations were performed to evaluate the observed failures, and Abaqus software was used for finite element analysis of the first stage compressor blade of the gas turbine model. In pursuit of this goal, initially, finite element simulations were conducted on an intact blade, followed by analyses on a blade incorporating a V-shaped notch, and subsequently, applying stress analysis, the critical positions that are the main candidates for the formation and initiation of microcracks in the blade were determined. In addition, a new critical plane fatigue model was applied to evaluate and investigate the fatigue behaviour of the compressor blade. Then, through coding in MATLAB software, the plane that suffered the maximum damage based on the critical plane fatigue model was determined and its direction was calculated for the critical positions of the compressor blade. Finally, the compressor blade fatigue life was determined based on this criterion and compared with traditional critical plane fatigue criteria such as Brown-Miller and SWT, and the reduction in life due to foreign object damage to the blade was determined and compared to an intact blade.
کلیدواژه‌ها
Fatigue life prediction؛ gas turbine compressor؛ foreign object damage (FOD)؛ critical plane method؛ structural integrity

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The estimation of fatigue life of an intact gas turbine compressor blade and the same blade with foreign object damage based on critical plane methods