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On-line Access: 2022-08-22

Received: 2021-12-07

Revision Accepted: 2022-03-17

Crosschecked: 2022-08-30

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 ORCID:

Ru-bing LIU

https://orcid.org/0000-0003-1471-0321

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Journal of Zhejiang University SCIENCE A 2022 Vol.23 No.8 P.652-668

http://doi.org/10.1631/jzus.A2100618


Active flow control of S-duct by plasma synthetic jet


Author(s):  Ru-bing LIU, Xiao-yin MEI, Sheng-hui XUE, Yu-wen LU, Zhe-zhe SU, Qi LIN

Affiliation(s):  School of Aerospace Engineering, Xiamen University, Xiamen 361102, China; more

Corresponding email(s):   lrb@xmu.edu.cn, qilin@xmu.edu.cn

Key Words:  S-duct, Flow control, Plasma synthetic jet (PSJ), Flow separation, Pressure distortion


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Ru-bing LIU, Xiao-yin MEI, Sheng-hui XUE, Yu-wen LU, Zhe-zhe SU, Qi LIN. Active flow control of S-duct by plasma synthetic jet[J]. Journal of Zhejiang University Science A, 2022, 23(8): 652-668.

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pages="652-668",
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doi="10.1631/jzus.A2100618"
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Abstract: 
flow separation and secondary flow in the s-duct of an aircraft engine cause severe pressure loss and airflow distortion at the outlet, lowering engine performance. Herein, a serial two-electrode plasma synthetic jet (PSJ) actuator array is used to actively control the flow field in the duct and improve its characteristics. The results show that the PSJ significantly increases the wall pressure recovery coefficient, suppresses flow separation, and improves the outlet pressure distortion. The primary and secondary orders of the influencing factors are as follows: control position>jet momentum coefficient>excitation frequency>jet configuration. The best jet control position is near the separation location, and the best jet configuration is the ‘Λ’ configuration. The higher the jet momentum coefficient and excitation frequency, the better the flow control. The wall pressure coefficient increases by up to 127.8%, and the outlet steady pressure distortion index decreases by 9.15%. The control mechanism is the direct energy injection into the flow boundary layer through a high-speed jet and the indirect control effect of the induced streamwise vortex. On the one hand, the PSJ suppresses flow separation by improving the ability of the boundary layer to resist the inverse pressure gradient. On the other hand, it reduces pressure distortion by decreasing the intensity of the secondary flow and weakening the backflow. This study thus provides a new technology for the active control of the flow-field characteristics in an s-duct and has significance for guiding the application of synthetic jet technology in s-ducts.

基于等离子体合成射流的S形进气道主动流动控制研究

作者:刘汝兵1,2,梅笑隐1,2,薛生辉1,2,卢钰文1,苏哲哲1,林麒1,2
机构:1.厦门大学,航空航天学院,中国厦门,361102;2.福建省等离子体与磁共振研究重点实验室,中国厦门,361102
目的:S形进气道内的流动分离和二次流造成进气道出口压力损失和气流畸变较为严重,严重影响发动机的工作性能。为改善其流场特性,本文采用串联式等离子体合成射流主动控制进气道内的流场,抑制进气道内流动分离和出口压力畸变,提高进气道气动性能。
创新点:1.系统探究等离子体合成射流控制位置、布局形式、动量系数和激励频率对控制效果的作用规律,并采用正交实验法确定上述参数的主次和最优组合。2.从流向和出口截面流场及压力分布出发,厘清等离子体合成射流主动控制S型进气道流动的机理。
方法:1.在低速风洞试验中(图2),利用压力扫描阀采集进气道壁面静压分布和出口总压分布,并通过粒子图像测速(PIV)技术测量进气道壁面沿程和出口流场(图5)。2.在壁面布置等离子体合成射流阵列对进气道内的流动分离进行主动控制,改变等离子体合成射流相关参数(图7和9),探究其作用规律,并利用正交实验法确定各参数的影响主次。3.通过对比分析沿程、出口的流场和压力分布(图13),探究等离子体合成射流控制流动分离的机理(图16)。
结论:1.等离子体合成射流能够显著提高静压恢复系数,抑制流动分离并改善出口压力畸变;射流控制位置在分离点附近最佳,而“Λ”型布局形式是最优的。2.本实验中,壁面静压系数提高最大可达127.8%,而出口稳态畸变指数降低了9.15%。3.控制机理是高速射流的直接能量注入及其产生的流向涡间接控制效应;一方面,可提高边界层抵抗逆压梯度的能力,抑制流动分离;另一方面,可有效降低二次流的强度,减弱出口截面回流,降低压力畸变。

关键词:S形进气道;流动控制;等离子体合成射流;流动分离;总压畸变

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