ガスタービン翼腹面の全面膜冷却に関する実験的研究

概要

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Coolant was injected from three holes on the center line of a pressure surface of a gas turbine blade. The density ratio and mass flow ratio were changed in the ranges of 1〜3 and 0.1〜1.5 respectively. The film cooling effectiveness on the center line was mainly governed by the momentum ratio, and the optimum momentum ratio was about 0.01. The empirical formula for the film cooling effectiveness on the center line was decided as the functions of the dimensionless streamwise distance from the injection hole and the momentum ratio. The maximum and mean errors of this formula were 26.8% and 9.2% respectively. The normalized dimensionless spanwise distribution of the film principle of superposition, one can predict the distribution of full coverage film cooling effectiveness on the pressure surface under the optimum condition.
一般社団法人日本機械学会の論文
1988-09-25