| Trailing-edge shock loss control with self-sustaining synthetic jet in a supersonic compressor cascade |
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| 作者姓名： | Yinxin ZHU Wenqiang PENG Zhenbing LUO Qiang LIU Wei XIE Pan CHENG Yan ZHOU |
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| 作者单位： | College of Aerospace Science and Engineering, National University of Defense Technology |
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| 基金项目： | co-supported by the National Natural Science Foundation of China (No. 52075538)；;the National Science and Technology Major Project, China (No. J2019-II-00160037)；;the Natural Science Foundation of Hunan Province, China (No. 2020 JJ2030)； |
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| 摘 要： | To effectively reduce the loss of strong shock wave at the trailing edge of the supersonic cascade under high backpressure, a shock wave control method based on self-sustaining synthetic jet was proposed. The self-sustaining synthetic jet was applied on the pressure side of the blade with the blow slot and the bleed slot arranged upstream and downstream of the trailing-edge shock,respectively. The flow control mechanism and effects of parameters were investigated by numerical simulation. The res...
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| 收稿时间： | 8 June 2022 |
Trailing-edge shock loss control with self-sustaining synthetic jet in a supersonic compressor cascade |
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| Yinxin ZHU,Wenqiang PENG,Zhenbing LUO,Qiang LIU,Wei XIE,Pan CHENG,Yan ZHOU.Trailing-edge shock loss control with self-sustaining synthetic jet in a supersonic compressor cascade[J].Chinese Journal of Aeronautics,2023,36(7):366-377. |
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| Institution: | College of Aerospace Science and Engineering, National University of Defense Technology, Changsha 410073, China |
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| Abstract: | To effectively reduce the loss of strong shock wave at the trailing edge of the supersonic cascade under high backpressure, a shock wave control method based on self-sustaining synthetic jet was proposed. The self-sustaining synthetic jet was applied on the pressure side of the blade with the blow slot and the bleed slot arranged upstream and downstream of the trailing-edge shock, respectively. The flow control mechanism and effects of parameters were investigated by numerical simulation. The results show that the self-sustaining synthetic jet forms an oblique shock wave in the cascade passage which slows down and pressurizes the airflow, and the expansion wave downstream of the blow slot weakens the shock strength which can effectively change the Mach reflection to regular reflection and thus weaken the shock loss. And the suction effect can reduce loss near blade surface. Compared with the baseline cascade, the self-sustaining jet actuator can reduce flow losses by 6.73% with proper location design and vibration of diaphragm. |
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| Keywords: | Compressors Flow control Mach reflection Trailing-edge shock Self-sustaining synthetic jet Shock waves Supersonic cascades |
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