| Citation: | ZHANG Guochen, LI Zhipeng, CAO Zhiyuan, et al. Numerical simulation on combination of circumferential groove and tip clearance modification to control tip clearance flow field[J]. Journal of Aerospace Power, 2024, 39（12）：20220895 doi: 10.13224/j.cnki.jasp.20220895
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A parallel dilation tip clearance was designed to inhibit the flow loss at rotor tip clearance. Through numerical simulation, it was found that the modified tip clearance can effectively suppress the wake loss at the trailing edge of the rotor and reduce the size of the corner separation vortex in the region of the casing formed by mixing the spanwise underflow and the leakage flow at the trailing edge of the suction surface. The position of shock waves action on the rotor suction surface moved downstream, which shortened the length of the boundary layer and weakened the separation degree of the boundary layer. The research showed that the peak efficiency of the modified tip clearance increased to 0.374% and the stability margin increased to 3.457% compared with the design tip clearance. To improve the effect of vortex loss suppression by the modified tip clearance, a circumferential single casing groove was added at the leading edge of the rotor tip. The results showed that the combination scheme can reduce the risk of double leakage flow, make the interface between the main stream and the tip leakage flow move into the channel and reduce the entropy, delay the occurrence of spike stall caused by leading edge spillage at low flow rate. Moreover, the stability margin and peak efficiency of the combination scheme increased by 4.105% and 0.164%, respectively, compared with the design tip clearance.
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