Creep Damage Evaluation of Ni-base Superalloys for Gas-Turbine by X-ray Diffraction Method

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  • Ｘ線回折手法を利用したガスタービン用ニッケル基超耐熱合金のクリープ損傷評価
  • Xセン カイセツ シュホウ オ リヨウシタ ガスタービンヨウ ニッケルキ チョウタイネツ ゴウキン ノ クリープ ソンショウ ヒョウカ

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The cost of the turbine blades for the gas turbine engines is increasing, because the latest superalloys for the turbine blades contain precious elements (i.e. precious metals, rate-earth metals) and the casting processes come to be complicated (i.e. directionally solidification, single crystal) to give higher creep resistivity against the increasing turbine inlet gas-temperature (TIT). Therefore, provision of a proper exchange period for the turbine blade can effectively reduce the life cycle cost in the gas-turbine engine operation. In this study, X-ray super-lattice reflections from the γ′ precipitate with L12 type crystalline structure were carefully evaluated, and the full width at half maximum (FWHM) of ω rocking curves of them were increased as the creep life fraction. On the other hands, θ-2θ profiles of the γ′ remained sharp even the creep ruptured sample. Therefore, the increase in the FWHM of the ω rocking curves was thought not to reflect the lattice disordering in γ′, but to reflect the degree of the misorientation among the γ′ precipitates. It was also supported by the electron backscatter patterns (EBSP) analysis. Although the reason of the relationship between creep life fraction and the γ′ misorientation must be revealed in further study, this evaluation method is expected as a non-destructive inspection to determine the creep damage level for the turbine blade.

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