トランスピレーション冷却を有するタービン翼前縁周りの流れの数値解析 : 第1報,基本パラメータに対する諸特性(流体工学,流体機械)

概要

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The further improvement of gas turbines requires the development of cooling technique with reduction of the cooling air mass flow rate as well as the increase of the turbine inlet temperature. The theoretically most effective air cooling method is the transpiration cooling, which will be expected to reduce the cooling air mass flow rate. In the present study, the two-dimentional flow simulating the flow around the leading edge of a turbine blade model (LEM) are analyzed numerically by the CFD code. The calculations are performed in order to examine the influence of parameters on the flow through the LEM, such as the porosity and the mean diameter of perticles of the porous media and the blowing ratio. The results reveal the effects of those parameters on the temperature inside the porous media and the cooling air pressure. Furthermore, the effects of the variations of the viscosity and the fluid density inside the porous media are also clarified.
2003-10-25