ガスタービン翼背面の三次元吹出し膜冷却

概要

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The distributions of film cooling effectiveness on the suction surface of a gas turbine blade were measured by using the analogy of heat and mass transfer. A rectangular injection hole was made on a midspan-line of the blade. As a result, the following were clarified: (1) the optimum blowing rate is about 1.0, (2) the distribution of film cooling effctiveness in the spanwise direction agrees well with Gaussian error function. (3) the effects of the pitch-chord ratio and incidence angle on the film cooling effectiveness are slight, (4) a universal distribution of the film cooling effectiveness on the midspan-line of the blade was introduced, (5) by using the above results and the principle of superposition, one can predict the distribution of film cooling effectiveness on the suction surface of a gas turbine blade on which many injection holes are laid out in an arbitrary position and injection angle.
一般社団法人日本機械学会の論文
1986-11-25