熱疲労下におけるガスタービン動翼の複数き裂進展挙動評価

概要

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Frequent start-stop operation of gas turbine sometimes causes coating cracks on the surface of first stage blades. The coating cracks at suction side of blade surface are caused in the form of multiple parallel cracks with narrow intervals. The objective of this paper is to evaluate the propagation behavior of this multiple cracks. Temperature distribution of cracked area during operation was evaluated by observation of microstructure change with long term operation and the resultant thermal stress distribution was calculated. A series of finite element analyses were performed for multiply edge cracked plate with finite width subjected to crack face pressure. The results were used to establish evaluation method of K values of multiple parallel cracks. The established method was used to evaluate crack propagation behavior of the blade surface together with the evaluated temperature distribution and the calculated stress distribution.
社団法人日本機械学会の論文
2005-09-25