Investigation of film cooling on the leading edge of turbine blade based on detached eddy simulation

In order to assess the influences of curved hole passage on cooling effectiveness and flow structure of turbine blade leading edge, the detached eddy simulation is applied to numerically investigate the AGTB turbine cascade under the condition of global blowing ratio M=0.7. The straight or curved cooling holes are located at either the pressure or suction side near the leading edge. The analysis and discussion focus on the local turbulence structure; influence of pressure gradient on the structure, and distribution of cooling effectiveness on the blade surface. The numerical results show that cooling hole with curved passage could bring positive impact on the increase of the local cooling effectiveness. On the suction side, the increased cooling effectiveness could be about 82% and about 77% on the pressure side, compared to the conventional straight hole.