大涵道比风扇/增压级叶尖间隙影响研究

doi:10.7527/S1000-6893.2017.620951

Abstract

Abstract:

An analytical study of tip clearance flows in the high-bypass-ratio fan/booster is presented. The results reveal that for all kinds of corrected rotating speed, the flow and the total pressure ratio predicted by CFD is very close to the experiment result; for the high corrected rotating speed, the efficiency is lower in CFD and stall margin is almost equal to the experiment results; for the decreased corrected rotating speed, the efficiency of the experiment is obviously higher, and stall margin of the experiment is lower. Evaluations are conducted under 1.0, 0.85 and 0.6 corrected rotating speed conditions for multiple fan tip clearance levels to obtain clearance sensitivities. When the tip clearance increases, the shock wave-boundary interaction and tip leakage flow mixing lead to secondary flow loss at high corrected rotating speed, and the performance decreases at the design point. Stall margin will rapidly fall when the tip clearance rises to a certain level. Similar results are obtained at low corrected rotating speed while the decline of efficiency is slower and stall margin rises as tip clearance increases, revealing the reduction of tip sensitivity as the corrected rotating speed reduces. There is little influence of tip clearance on the core flow at all kinds of corrected rotating speed.

Key words: fan/booster, high-bypass-ratio, tip clearance, aerodynamic performance, numerical simulation

CLC Number:

V231.3

CHEN Yunyong, WAN Ke, YANG Xiaohe, DING Jianguo. Influence of tip clearance on high-bypass-ratio fan/booster[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2017, 38(9): 520951-520951.

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Influence of tip clearance on high-bypass-ratio fan/booster

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