论文:2023,Vol:41,Issue(4):740-749
引用本文:
王思维, 王掩刚, 刘汉儒, 陈延俊, 刘淑丽. 升力风扇唇口特征几何与其气动性能关联性分析[J]. 西北工业大学学报
WANG Siwei, WANG Yangang, LIU Hanru, CHEN Yanjun, LIU Shuli. Correlation analysis of lift fan lip feature geometry and aerodynamic performance[J]. Journal of Northwestern Polytechnical University

升力风扇唇口特征几何与其气动性能关联性分析
王思维1, 王掩刚1, 刘汉儒1, 陈延俊1, 刘淑丽2
1. 西北工业大学 动力与能源学院, 陕西 西安 710072;
2. 中国航空工业空气动力研究院, 黑龙江 哈尔滨 150001
摘要:
悬停状态下,唇口可为升力风扇提供接近一半的升力,是垂直起降飞行器动力装置的重要气动部件。以挖掘影响升力风扇唇口性能的几何参数为目标,针对某升力风扇应用需求设计了4种唇口,采用经过试验验证的数值分析方法研究了造成唇口性能差异的流场及几何因素,在此基础上研究了唇口几何参数与气动性能的关联关系并进行了验证。结果表明:10 000 r/min的风扇转速下,双纽线唇口比基于NACA65设计唇口的无量纲升力和无量纲流量分别提高33%与9.5%;对于文中研究对象,当唇口内表面斜率等于2倍双纽线斜率时,唇口的性能参数最优,大于或小于2倍双纽线斜率时,唇口性能均会降低;10 000 r/min的风扇转速下,与双纽线唇口相比,基于2倍双纽线斜率设计的唇口可使升力风扇的总升力提高5.6%。
关键词:    涵道唇口    升力风扇    曲线斜率    流场结构   
Correlation analysis of lift fan lip feature geometry and aerodynamic performance
WANG Siwei1, WANG Yangang1, LIU Hanru1, CHEN Yanjun1, LIU Shuli2
1. School of Power and Energy, Northwestern Polytechnical University, Xi'an 710072, China;
2. AVIC Aerodynamics Research Institute, Harbin 150001, China
Abstract:
In hover, the lip of a lift fan plays a crucial role, contributing to nearly half of the lift for the VTOL aircraft power plant. Thus, investigating the geometric parameters that influence lip performance is of significant importance. In this study, four types of lift fan lips were designed, tailored to meet specific application requirements. Numerical analysis, validated through experimental data, was employed to examine the flow field and the geometric factors that lead to variations in lip performance. Based on the findings, the relationship between lip geometric parameters and aerodynamic performance was thoroughly investigated and confirmed. The results demonstrate that, at a rotational speed of 10 000 r/min, the non-dimensional lift and non-dimensional mass flow of the lemniscate lip exhibit improvements of 33% and 9.5%, respectively, compared to lips designed based on NACA65. Among the various lip configurations, it is found that the performance parameters of the lip are optimal when the slope of the inner surface equaled twice the slope of the lemniscate. On the other hand, when the slope deviated from this optimal value, whether greater or lesser, a reduction in lip performance was observed. Specifically, at a rotational speed of 10 000 r/min, the lip designed based on a lemniscate slope could increase the total lift of the lift fan by 5.6% when compared to the lemniscate lip.
Key words:    duct lip    lift fan    slope    flow field structure   
收稿日期: 2022-09-06     修回日期:
DOI: 10.1051/jnwpu/20234140740
通讯作者: 王掩刚(1976—),西北工业大学教授,主要从事高性能叶轮机械设计技术与内流流动控制研究。e-mail:wyg704@nwpu.edu.cn     Email:wyg704@nwpu.edu.cn
作者简介: 王思维(1997—),西北工业大学博士研究生,主要从事高性能叶轮机械设计技术研究。
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参考文献:
[1] 郭佳豪, 周洲, 李旭. 一种涵道螺旋桨桨叶高效设计方法[J]. 航空学报, 2022, 43(7): 89-99 GUO Jiahao, ZHOU Zhou, LI Xu. An efficient design method for the blade of ducted propeller[J]. Acta Aeronautica et Astronautica Sinica, 2022, 43(7): 89-99 (in Chinese)
[2] PEREIRA J L, CHOPRA I. Hover tests of micro aerial vehicle-scale shrouded rotors, part Ⅰ: performance characteristics[J]. Journal of the American Helicopter Society, 2009, 54(1): 18-45
[3] 李建波, 高正, 唐正飞, 等. 涵道风扇升力系统的升阻特性试验研究[J]. 南京航空航天大学学报, 2004, 36(2): 164-168 LI Jianbo, GAO Zheng, TANG Zhengfei,et al. Experimental investigation on lift and drag of ducted fan system[J]. Journal of Nanjing University of Aeronautics & Astronautics, 2004, 36(2): 164-168 (in Chinese)
[4] TOBIAS E, HORN J. Simulation analysis of the controllability of a tandem ducted fan aircraft[C]//AIAA Atmospheric Flight Mechanics Conference and Exhibit, 2008
[5] KRUGER W. On wind tunnel tests and computations concerning the problem of shrouded propellers[R]. NACA-TM-1202, 1949
[6] PLATT R J. Static tests of a shrouded and an unshrouded propeller[R]. NACA-RM-L7H25, 1948
[7] 张阳, 周洲, 郭佳豪. 分布式涵道风扇喷流对后置机翼的气动性能影响[J]. 航空学报, 2021, 42(9): 431-444 ZHANG Yang, ZHOU Zhou, GUO Jiahao. Effects of distributed electric propulsion jet on aerodynamic performance of rear wing[J]. Acta Aeronautica et Astronautica Sinica, 2021, 42(9): 431-444 (in Chinese)
[8] 刘凯, 叶赋晨. 垂直起降飞行器的发展动态和趋势分析[J]. 航空工程进展, 2015, 6(2): 127-138 LIU Kai, YE Fuchen. Review and analysis of recent developments for VTO vehicles[J]. Advances in Aeronautical Science and Engineering, 2015, 6(2): 127-138 (in Chinese)
[9] 昌敏, 周洲, 郑志成. 升力风扇垂直起降飞机过渡态总体参数分析[J]. 西北工业大学学报, 2013, 31(3): 406-412 CHANG Min, ZHOU Zhou, ZHENG Zhicheng. Analysis of conceptual parameters of lift-fan VTOL aircraft in transition[J]. Journal of Northwestern Polytechnical University, 2013, 31(3): 406-412 (in Chinese)
[10] WANG H T, WANG Y G, WANG S W, et al. Optimization strategy for performance improvement of a lift fan cowl lip based on panel method[J]. Journal of Mechanical Science and Technology, 2021, 35(7): 2961-2970
[11] MARTIN P, BOXWELL D, NYGAARD T, et al. Design, analysis, and experiments on a 10-inch ducted rotor VTOL UAV[C]//American Helicopter Society 2005 Forum, 2005
[12] 邓阳平, 米百刚, 张言. 涵道风扇气动特性影响因素数值计算研究[J]. 西北工业大学学报, 2018, 36(6): 1045-1051 DENG Yangping, MI Baigang, ZHANG Yan. Research on numerical calculation for aerodynamic characteristics analysis of ducted fan[J]. Journal of Northwestern Polytechnical University, 2018, 36(6): 1045-1051 (in Chinese)
[13] 王海童, 王掩刚, 周芳, 等. 基于面元法的分布式涵道推进系统进气道优化设计[J]. 推进技术, 2021, 42(11): 2465-2473 WANG Haitong, WANG Yangang,ZHOU Fang,et al. Optimization design of inlet for distributed ducted fan propulsion system based on panel method[J]. Journal of Propulsion Technology, 2021, 42(11): 2465-2473 (in Chinese)
[14] 王春阳, 周洲, 王睿, 等. 涵道式垂直起降固定翼无人机纵向稳定性研究[J]. 西北工业大学学报, 2021, 39(4): 712-720 WANG Chunyang, ZHOU Zhou, WANG Rui, et al. Study on longitudinal stability of ducted vertical take-off and landing fixed-wing UAV[J]. Journal of Northwestern Polytechnical University, 2021, 39(4): 712-720 (in Chinese)
[15] STIPA L. Experiments with intubed propellers[R]. NASA-TM-655, 1932
[16] ZHANG T, BARAKOS G N. Review on ducted fans for compound rotorcraft[J]. Aeronautical Journal, 2020, 124(1277): 941-974
[17] TAYLOR R T. Experimental investigation of the effects of some shroud design variables on the static thrust characteristics of a small-scale shrouded propeller submerged in a wing[R]. NASA-TM-4126, 1958
[18] GRAF W, FLEMING J, NG W. Improving ducted fan UAV aerodynamics in forward flight[C]//AIAA Aerospace Sciences Meeting & Exhibit, 2013
[19] DENG S H, WANG S W, ZHANG Z. Aerodynamic performance assessment of a ducted fan UAV for VTOL applications[J]. Aerospace Science and Technology, 2020, 103: 105895
[20] 张阳, 周洲, 王科雷, 等. 分布式动力系统参数对翼身融合布局无人机气动特性的影响[J]. 西北工业大学学报, 2021, 39(1): 17-26 ZHANG Yang, ZHOU Zhou, WANG Kelei, et al. Influences of distributed propulsion system parameters on aerodynamic characteristics of a BLI-BWB UAV[J]. Journal of Northwestern Polytechnical University, 2021, 39(1): 17-26 (in Chinese)
[21] 叶坤, 叶正寅, 屈展. 涵道气动优化设计方法[J]. 航空动力学报, 2013, 28(8): 1828-1835 YE Kun, YE Zhengyin, QU Zhan. Aerodynamic optimization method for duct design [J]. Journal of Aerospace Power, 2013, 28(8): 1828-1835 (in Chinese)