Design and performance of serpentine inlet with bypass
-
摘要:
针对一种带旁通的双S弯进气道开展了气动设计和性能仿真研究。探索了改变第一S弯长度对进气道的影响,通过流场流动和砂粒轨迹的分析,对初始设计的模型进行修正,然后在修正后的基准模型的基础上,采用数值模拟方法,重点研究了不同扫气比和过渡截面面积比对进气道管道内流动特性和排砂效率的影响。结果表明:第一S弯的长度过小则气动性能好但不利于排砂,过大则气动性能差但排砂效果好。过渡截面面积比在减小的过程中,进气道气动性能略微下降。当形成分离涡后,总压损失迅速增大,但出口总压畸变指数降低。面积比过大或者过小都不利于进气道排砂。随着扫气比增大,排砂性能提高,进气道出口总压恢复基本稳定,畸变增大。
Abstract:The aerodynamic design and performance simulation of a serpentine inlet with bypass were studied. The influence of alternating the first S-bend length on the inlet was explored. Through the analysis of the flow field and sand particles trajectories, the protype was modified. Then, on the basis of the modified benchmark model, the influences of different scavenge flow ratios and transition section area ratios on flow characteristics and sand separation efficiency in the inlet duct were emphatically studied by means of numerical simulation. The results showed that if the length of the first S-bend was too small, the aerodynamic performance was better but not favorable for sand separation; if the length was too large, the aerodynamic performance was worse but the sand separation effect was better. In the process of decreasing transition area ratio, the aerodynamic performance of inlet decreased slightly. When separation vortices were formed, the total pressure loss increased rapidly, but the outlet total pressure distortion coefficient decreased. And too large or too small area ratio was not conducive to the sand separation of inlet. With the increase of scavenge flow ratio, the performance of sand separation efficiency was improved, the total pressure recovery at the outlet was basically stable and the distortion was increased.
-
Key words:
- inlet /
- bypass /
- turboprop engine /
- aerodynamic performance /
- sand separation /
- area ratio
-
表 1 短半轴变化后的无量纲面积比和偏距比
Table 1. Dimensionless area ratio and offset ratio after the alteration of semiminor axis
短半轴改变长度/mm $\alpha $ $\xi $ −10 0.478 1.100 −5 0.525 1.075 0 0.573 1.050 5 0.621 1.025 10 0.669 1.000 表 2 仿真与实验所得性能参数对比表
Table 2. Performance parameters obtained from simulation and experiment
参数 实验[21] 仿真 总压恢复系数 0.9910 0.9909 AC砂分离效率/% 77.7 83.7 C砂分离效率/% 91.4 98.2 表 3 进气道主要设计参数
Table 3. Main design parameters of the inet
参数 数值 进气道入口直径D1/mm 200 进气道出口直径D2/mm 153 旁通出口直径D3/mm 60 表 4 不同扫气比下的出口参数变化
Table 4. Variatioans of outlet parameters under different scavenge flow ratios
扫气比/% 旁通质量
流量/(kg/s)主流道出口
压力/Pa旁通出口
压力/Pa10 0.1279 91278.6 96560.2 12 0.1583 91296.4 94648.7 14 0.1827 91347.7 92251.0 16 0.2058 91258.5 90326.8 18 0.2292 91295.8 86864.8 -
[1] 时磊,岳剑飞. 沙尘对直升机的危害及预防[J]. 科技资讯,2014,12(13): 122-124. doi: 10.3969/j.issn.1672-3791.2014.13.084SHI Lei,YUE Jianfei. Harm and prevention of dust on helicopters[J]. Science and Technology Information,2014,12(13): 122-124. (in Chinese) doi: 10.3969/j.issn.1672-3791.2014.13.084 [2] LEE C C, BOEKICKER C. Subsonic diffuser design and performance for advanced fighter aircraft[R]. AIAA 85-3073, 1985. [3] 王庆林. 超椭圆进气道的设计[J]. 洪都科技,1990(4): 1-6.WANG Qinglin. Design of super elliptical inlet[J]. Hongdu Science and Technology,1990(4): 1-6. (in Chinese) [4] 李岳锋,杨青真,孙志强. 超椭圆S形进气道的设计及气动性能研究[J]. 计算机仿真,2011,28(3): 82-85. doi: 10.3969/j.issn.1006-9348.2011.03.020LI Yuefeng,YANG Qingzhen,SUN Zhiqiang. Design of super elliptical S-shaped inlet and analysis of aerodynamic performance[J]. Computer Simulation,2011,28(3): 82-85. (in Chinese) doi: 10.3969/j.issn.1006-9348.2011.03.020 [5] 黄晨,谢文忠,靖建朋. 基于Nurbs曲线的涡控蛇形进气道设计[J]. 航空动力学报,2013,28(10): 2355-2363. doi: 10.13224/j.cnki.jasp.2013.10.025HUANG Chen,XIE Wenzhong,JING Jianpeng. Design of vortex controlled serpentine inlet based on NURBS curve[J]. Journal of Aerospace Power,2013,28(10): 2355-2363. (in Chinese) doi: 10.13224/j.cnki.jasp.2013.10.025 [6] 周慧晨,谭慧俊,李湘萍. 复杂变截面进气道的一种设计方法[J]. 航空动力学报,2009,24(6): 1357-1363. doi: 10.13224/j.cnki.jasp.2009.06.019ZHOU Huichen,TAN Huijun,LI Xiangping. Unique design method of subsonic inlet with complex cross-sectional shape[J]. Journal of Aerospace Power,2009,24(6): 1357-1363. (in Chinese) doi: 10.13224/j.cnki.jasp.2009.06.019 [7] SUN S,TAN H J. Flow characteristics of an ultracompact serpentine inlet with an internal bump[J]. Journal of Aerospace Engineering,2018,31(2): 04017089.1-04017089.11. [8] 谢文忠,郭荣伟. 蛇形进气道涡控设计研究[J]. 航空学报,2011,32(10): 1806-1814.XIE Wenzhong,GUO Rongwei. Vortex-controlled design research for serpentine inlet[J]. Acta Aeronautica et Astronautica Sinica,2011,32(10): 1806-1814. (in Chinese) [9] 宋国磊. 飞翼布局无人机双S弯进气道设计及流动控制技术应用研究[D]. 南京: 南京航空航天大学, 2016.SONG Guolei. Double S-shaped inlet design and flow control investigation for all-wing aircraft[D]. Nanjing: Nanjing University of Aeronautics and Astronautics, 2016. (in Chinese) [10] 李立国, 王锁芳. 直升机发动机的进气防护[M]. 北京: 国防工业出版社, 2009. [11] 付焱晶. 直升机发动机进气防护装置研究[D]. 沈阳: 东北大学, 2011.FU Yanjing. Research on intake protection device of helicopter engine[D]. Shenyang: Northeastern University, 2011. (in Chinese) [12] BARTA A B, BENNETT W A, VITTAL B R, et al. Design and development of a compact bifurcated turboprop inlet[R]. AIAA 91-2017, 1991. [13] 陈晓,李潞龙,马若龙. 带有腔室旁通道的进气道气动性能试验研究[J]. 航空动力学报,1994,9(3): 42-45,107-108. doi: 10.13224/j.cnki.jasp.1994.03.010CHEN Xiao,LI Lulong,MA Ruolong. Experimental experimental study on gasdynamic performance of intake with plenum bypass[J]. Journal of Aerospace Power,1994,9(3): 42-45,107-108. (in Chinese) doi: 10.13224/j.cnki.jasp.1994.03.010 [14] 周诗睿. 螺旋桨与进气道的气动干扰研究[D]. 南京: 南京航空航天大学, 2019.ZHOU Shirui. Research on aerodynamic interference of propeller and inlet[D]. Nanjing: Nanjing University of Aeronautics and Astronautics, 2019. (in Chinese) [15] 王利敏,张彦军,米百刚,等. 涡桨飞机发动机进气道排除异物特性数值研究[J]. 航空工程进展,2020,11(2): 264-271, 278. doi: 10.16615/j.cnki.1674-8190.2020.02.017WANG Limin,ZHANG Yanjun,MI Baigang,et al. Numerical simulation on excluding foreign objects from engine inlet of turboprop aircraft[J]. Advances in Aeronautical Engineering,2020,11(2): 264-271, 278. (in Chinese) doi: 10.16615/j.cnki.1674-8190.2020.02.017 [16] MI Baigang, ZHAN Hao. Numerical simulation on rigid foreign object exclusion in the turboprop engine intake system with a bypass duct[J]. IEEE Access, 2019, 7: 61920-61933. [17] 车得福, 李会雄. 多相流及其应用[M]. 1版. 西安: 西安交通大学出版社, 2007: 505-517. [18] 胡霄乐. 细弯管内多粒径颗粒的气固两相流动规律分析[D]. 杭州: 浙江工业大学, 2015.HU Xiaole. Analysis of gas-solid two-phase flow with multi-sized particles in a thin elbows[D]. Hangzhou: Zhejiang University of Technology, 2015. (in Chinese) [19] WAKEMAN T, TABAKOFF W. Measured particle rebound characteristics useful for erosion prediction[C]//Proceedings of Gas Turbine Conference. London: ASME, 1982: 83-95. [20] STEVEN R, THEODORE H. A study of the compressible flow through a diffusing S-duct[R]. NASA Technical Memorandum 106411, 1994. [21] DUFFY R J, SHATTUCK B F. Integral engine inlet particle separator: Volume Ⅱ design guide[R]. USAAMRDL-TR-75-31B, 1975