| Citation: | GU Meng, XIE Gang, ZHOU Zhiyu, et al. Analysis on film cooling hole arrangement effect for rotating blade leading edge[J]. Journal of Aerospace Power, 2023, 38（6）：1340-1349 doi: 10.13224/j.cnki.jasp.20210652
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The effects of hole arrangement of two rows of film holes on the film cooling performance at each side of rotating blade leading edge were investigated. The film cooling performance and flow filed were obtained by using numerical simulation method. The first row of film holes was fixed at ±10° downstream stagnation line and was followed by the second row of holes. The span-wise position and the stream-wise location of the second row of holes were adjusted to achieve different hole arrangement. The results indicated that the effects of hole arrangement of two rows on film cooling were different at two sides of the leading edge. At the leading edge suction side, the relative position between two rows of holes significantly affected the interaction between the adjacent jets from two rows. At the pressure side, closer distance between two adjacent holes in two rows produced better film cooling performance. Meanwhile, the effect of relative position between two rows of holes was mainly located in the near hole region. The film cooling effectiveness at the suction side and pressure side increased by 0.07 and 0.02, respectively.
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