Thermal analysis and design optimization for cooling passage of turbine blades

Numerical studies of turbine blade cooling passage heat transfer were presented and new structure was proposed to improve the blade performance. Coupled aero-thermal analysis methods were used for flow and heart transfer analysis. The distribution of blade static pressure and temperature were obtained. The results demonstrate that the maximum temperature appears at the tip of blade trailing edge. So two new cooling passage designs were proposed, in which blade maximum temperature and volume-average temperature could be reduced without reducing the blade aerodynamic performance, respectively. It is proved that blade maximum temperature and volume-average temperature could be greatly reduced by the combination of this two new designs. Finally, the new combined cooling passage structure was optimized with better heat transfer performance.