ガスタービン冷却動翼の達成温度解析(ガスタービン技術の最先端 : 伝熱・燃焼,ガスタービン技術の最先端)

概要

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The present paper reports on a numerical analysis of a temperature distribution of a rotor blade in a gas turbine, which has ribbed serpentine passages for internal cooling. Three-dimensional steady-state numerical analysis was conducted by thermal conjugation of inside and outside fields of the blade, which consists of convection heat transfer around the blade, thermal conduction in the blade material and internal blade cooling. In order to evaluate heat transfer in the internal cooling passages, correlations derived from calculations of convection in the ribbed passage were applied. As a result, predicted temperature profile on the blade coincides with the distinctive features on real blades, which are due to damages by oxidation, and that predicted temperature profile is in agreement with local wall temperature estimated on the basis of the material of the real spent blade.
一般社団法人日本機械学会の論文
2004-09-04