タービン翼の非定常温度分布の数値計算（翼後縁厚みの影響）

概要

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The development of material and the research of turbine cooling method make the increase in the turbine inlet temperature possible. Recent1y the gasturbine performance and power are remarkably increased because of the increase in the turbine inlet temperature. The turbine nozzle and the rotor blade which need cooling must be thicken the trailing edge thickness. In this occasion, the blade strength increases in spite of the decrease of the aerodynamic turbine performance. In this paper, the heat transfer coefficients along the blade surfaces are theoretically calculated, and the unsteady temperature distribution in the blade is numerically calculated by means of the difference method for two kinds of blades which have the different trailing edge thickness. Furthermore the influence of the blade trailing edge thickness on the aerodynamic performance of the turbine blade and on the thermal stress which is estimated by the temperature distribution is discussed.
長崎大学工学部,Faculty of Engineering, Nagasaki Universityの論文