ガスタービン翼背面の膜冷却に関する実験的研究および全面膜冷却への試み

概要

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Coolant was injected from three holes on the center line of a suction surface of a gas turbine blade. The density ratio and mass flow ratio were changed in the ranges of l〜3 and 0.2〜0.9 respectively. The film cooling effectiveness on the center line is mainly governed by the momentum ratio, and the optimum ratio is about 0.05〜0.10. The empirical formula for the film cooling effectiveness on the center line was decided as the function of the dlmensionless streamwise distance from the injection hole and the momentum ratio. The muximum and mean errors of this formula were 55.8% and 8.5% respectively. The normalized dimensionless spanwise distribution of the film cooling effectiveness agreed well with Gaussian error curve. By using the above results and the principle of superposition, one can predict the distrlbution of full coverage film cooling effectiveness on the suction surface under the optimum condition.
社団法人日本ガスタービン学会の論文
1988-09-10