Blade Film Cooling Within The Cold Flow Characteristics Of The Channel

To satisfy the practical need of film cooling in turbine blades of aeroengine, some detailed experimental measurements on the flow field in the channel with the holes on the wall and in the holes had been completed within a wide range of aerodynamic parameters. And the interrelated numerical simulated compute had also been implemented.The measurements including the jet and the suction needed to be carried out under different Reynolds number and different velocity ratio. In course of experiments, a lot of experimental data and figures had been obtained and the distributions of the flow field had been revealed detailedly. Furthermore, the discharge coefficients in hole had been measured.It was discovered in experiment that the change of Reynolds number influenced the distribution trend of flow field unobviously regardless in the channel and in the holes but the value of the velocity in the holes. Contrarily, the effect of the velocity ratio was very obvious. And the velocity ratio was the bigger, the effect was the more obvious.This paper used commerce software FLUENTS to implement numerical simulated compute because it could in more detail and comprehensive open out the distribution laws of the flow field in the channel and in the holes and the experimental results had been consummately enlarged. At last, the experimental results were contrasted and analyzed with the computational ones.