Aerodynamic Investigation Of Flow Fields In The Channel With Ejection/Injection Through The Holes On The Wall

To satisfy the practical need of cooling design in turbine blades of aeroengine, aerodynamic investigation of flow fields in the channel with ejection/injection through the holes on the wall and in the holes has been completed. Aerodynamic parameters,pressure coefficient and discharge coefficient in the internal cooling passage of turbine blades had been measured.Aerodynamic investigations of flow fields were carried out under conditions of different Reynolds number,different velocity ratio for the cases of ejection and injection, moreover detailed turbulent boundary layer measurements and flow visualization on the wall of the passage had been accomplished at the same time. The results show that the velocity ratio plays more important role than Reynolds number to influence the aerodynamic parameters of internal cooling passage. The Reynolds number has different influence on the pressure coefficient and discharge coefficient under different velocity ratio.Commercial software FLUENT6.0 was used in the numerical simulations of flow fields. More detailed flow fields in the channel and holes,pressure coefficients and discharge coefficients of the hole were calculated. The calculated results have been compared with the experiented data.Better understanding of the flow field behavior has been achieved by the comparions.And the experimental results had been consummately enlarged and enriched.