報告書番号

Q06009

タイトル（和文）

ガスタービン動翼用簡易損傷評価プログラムの開発 －第2報：三次元損傷評価機能の組み込み－

タイトル（英文）

Development of Simplified Damage Assessment Program for Gas Turbine First Row Blade - 2nd Report: Implementation of 3-D Damage Evaluation Function -

概要 （図表や脚注は「報告書全文」に掲載しております）

本研究では，ニッケル基耐熱超合金の統一型非弾性構成式と熱疲労寿命評価法を組み合わせた損傷評価プログラムを開発し，ガスタービン初段動翼の熱応力解析と熱疲労損傷評価を少ない労力で簡便に行えるように工夫した。本プログラムで評価された熱疲労損傷は詳細なFEMモデルによる損傷評価結果と同程度の値であり，実用上十分の評価機能を有していることが確認された。適用事例では，1300℃級ガスタービン初段動翼の様々な運転パターンによる損傷評価を実施し，燃焼ガス温度をわずかに低下することで動翼の損傷が大きく改善されることが示された。

概要 （英文）

All of gas turbine (GT) blades that come to the end of those lives recommended by the manufacturers are replaced with new ones in the scheduled inspection period. The blade is so expensive that the expansion of its life is considered as one of important subject to reduce the maintenance cost in power utilities. In this study, to resolve its subject, we developed a computer program that made three-dimensional modeling, three-dimensional thermal stress analysis with original inelastic constitutive equations, and thermal fatigue damage estimation more convenient for the beginners of life assessment. Then, using this program, the three-dimensional thermal stress analysis was carried out and thermal fatigue damage was estimated for a 1300C-class GT blade under assumed daily-start-stop operation. As a result in the three-dimensional thermal stress analysis, it was revealed that the outer surface of the blade was under bi-axial compressive stress condition in start stage and steady state operation and was oppositely under bi-axial tensile stress condition in stop stage. Then consequently in the damage estimation, it was clarified the middle of suction side of the blade was the most severe in terms of thermal fatigue damage and the reduction of combustion gas temperature had the effect of the reduction of damage, namely, the extension of crack initiation life.

報告者

キーワード