OS6-06 ガスタービン静翼の熱疲労き裂進展評価(OS6 設備診断・運用保全技術)

概要

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Long cracks have frequently been detected at vanes and/or shrouds of the gas turbine nozzle. This paper describes crack propagation evaluation at trailing edge of the vane. Temperature distribution during operation was first estimated by observing microstructure and by measuring hardness distribution of first-stage nozzle that had been used in power station for a long time. Finite element creep analysis was next performed where the estimated temperature distribution was used as the boundary condition. The result was utilized to estimate residual stress distribution caused when the nozzle cooled down. Finally, crack propagation behavior at the trailing edge was evaluated in which the shape of the vane was simply considered to be a flat plate.
社団法人日本機械学会の論文
2005-06-28