Gas turbine blade internal cooling – 微熱傳增強研究室

Gas turbine blade internal cooling

Both stator and rotor turbine blade internal cooling (for both convective and impingement cooling) were/are being experimentally studied. Single pass and two pass with uneven boundary conditions are being studied through LDV and temperature measurements. 10 journal papers were published. The data will be applied to future aircraft development of the ROC (Taiwan).