| Increasing turbine inlet temperature is one of important methods to advance the gas turbine engine performance and to enhance the economic capability. As one of the key cooling methods, film cooling has been widely used in gas turbine. In order to increase the film cooling efficiency, it is necessary to investigate the detailed hot-gas flow mechanisms in the turbine.Firstly, the paper investigates a turbine cascade with two rows of slots in leading edge and a turbine cascade with two rows of straight/inclined holes in leading edge based on the experiment through the Fine/Turbo software. The simulation results of blade surface pressure agree well with the experiment data. Based on the work, the paper mainly investigates the 3D flow of cascade passage and characters nearby the holes in high or normal inlet temperature. Then the paper studies the interactive infection between the cooling flow and the main flow. Finally, the influence of some parameters, such as blow ratio, jet angle, the number of rows and different arrange styles of holes to cooling efficiency are also discussed in this paper. |
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