低动能来流下背负式进气道非定常流动特性分析

刘志敏; 闫盼盼; 张群峰; 黎星佐; 孙超

doi:10.13700/j.bh.1001-5965.2018.0573

低动能来流下背负式进气道非定常流动特性分析

doi: 10.13700/j.bh.1001-5965.2018.0573

1.
北京航空航天大学航空科学与工程学院, 北京 100083
2.
北京交通大学土木建筑工程学院, 北京 100044
3.
中国航空工业集团有限公司沈阳飞机设计研究所, 沈阳 110035

基金项目:

国家自然科学基金 11772314

装备预研领域基金课题 6140206040316JW17001

详细信息

作者简介:
刘志敏男, 博士研究生, 研究员。主要研究方向:飞行器设计

闫盼盼男, 博士。主要研究方向:应用计算流体力学

张群峰男, 博士, 副教授。主要研究方向:应用计算流体力学

黎星佐男, 硕士。主要研究方向:飞行器设计

孙超男, 硕士, 高级工程师。主要研究方向:飞行器设计

通讯作者:
张群峰, E-mail: zhangqunfeng@263.net

中图分类号: V211.3
计量
- 文章访问数: 991
- HTML全文浏览量: 195
- PDF下载量: 403
- 被引次数: 0
出版历程
- 收稿日期: 2018-09-28
- 录用日期: 2018-10-15
- 网络出版日期: 2019-04-20

Unsteady flow characteristics of dorsal inlet under low-energy inflow

1.
School of Aeronautic Science and Engineering, Beihang University, Beijing 100083, China
2.
School of Civil Engineering, Beijing Jiaotong University, Beijing 100044, China
3.
Shenyang Aircraft Design and Research Institute, Aviation Industry Corporation of China, Ltd., Shenyang 110035, China

Funds:

National Natural Science Foundation of China 11772314

National Defense Pre-research Foundation of China 6140206040316JW17001

More Information

Corresponding author: ZHANG Qunfeng, E-mail: zhangqunfeng@263.net

摘要

摘要:
为了改善飞翼布局背负式S弯进气道低动能来流状态下的流动性能，采用改进的延迟分离涡模拟（IDDES）方法对原型及改进型背负式进气道流场进行了数值模拟研究，对比分析了进气道流量特性及内部脉动压力特性。结果表明：低动能来流时背负式进气道上部唇口附近存在很大的气流转折角，导致唇口产生分离涡；原型进气道唇口分离涡强度高，高能量分离涡在进气道顶部破裂产生了大范围旋涡结构，进一步加剧了流动分离，从而引发进气道内产生强烈的压力脉动，声压级最大幅值高达145 dB；改进型进气道唇口分离涡得到了有效控制，强度大幅下降，进气道内部压力脉动幅值也显著降低，声压级降幅达8 dB；改进型进气道分离的抑制使进气道有效流通截面积增大，质量流量增加。同时，流场出口品质提升，进气道出口综合畸变指数降低了9.5%。
- 背负式S弯进气道 /
- 分离流动 /
- 改进的延迟分离涡模拟(IDDES) /
- 压力脉动 /
- 流量
Abstract:
To improve the dorsal S-shaped inlet flow performance of low-energy inflow.The flow fields of both original and improved dorsal inlet were studied by using improved delayed detached-eddy simulation (IDDES) method, and the mass flow and pressure fluctuation characteristics of the two inlets were compared. The results show that, influenced by the fuselage, airflow turning angle near the inlet lip is very large and this will cause the formation of separation bubbles. The intensity of the separation vortex at the lip of the original inlet is very high. When the separation bubbles with high energy break down at the top of the inlet, massive high-strength vortices are created. These high-strength vortices aggravate the separation near the inlet top and cause fierce pressure fluctuations inside the S-shaped inlet. The amplitude of the sound pressure level can reach 145 dB. The strength of separation bubbles inside the improved inlet issuccessfully decreased, which enlarges the effective flow area of the inlet and increases mass flux. The pressure fluctuations inside the S-shaped inlet decrease and the reduction of sound pressure level is up to 8 dB. Meanwhile, the comprehensive distortion coefficient decreased by 9.5% which improves the characteristic of outlet flow field.
- dorsal S-shaped inlet /
- separated flow /
- improved delayed detached-eddy simulation (IDDES) /
- pressure fluctuation /
- flux

HTML全文

图 1 背负式S弯进气道计算模型

Figure 1. Calculation model of dorsal S-shaped inlet

下载: 全尺寸图片幻灯片

图 2 对称面网格分布

Figure 2. Grid distribution on symmetry plane

下载: 全尺寸图片幻灯片

图 3 背负式进气道内Q值等值面分布(Q=1×10⁷ s^-2)

Figure 3. Q iso-surface distribution inside dorsal inlet(Q=1×10⁷ s^-2)

下载: 全尺寸图片幻灯片

图 4 背负式进气道唇口附近流线图

Figure 4. Streamline near dorsal inlet lip

下载: 全尺寸图片幻灯片

图 5 背负式进气道入口前四阶POD模态

Figure 5. The first four order POD modes of dorsal inlet

下载: 全尺寸图片幻灯片

图 6 改进型背负式进气道内Q值等值面分布(Q=1×10⁷ s^-2)

Figure 6. Q iso-surface distribution inside improved dorsal inlet (Q=1×10⁷ s^-2)

下载: 全尺寸图片幻灯片

图 7 改进型背负式进气道唇口附近流线图

Figure 7. Streamline near improved dorsal inlet lip

下载: 全尺寸图片幻灯片

图 8 改进型背负式进气道入口前四阶POD模态

Figure 8. The first four order POD modes of improved dorsal inlet

下载: 全尺寸图片幻灯片

图 9 背负式进气道内部横截面流向速度分布云图

Figure 9. Streamwise velocity distribution contour of interior sections of dorsal inlet

下载: 全尺寸图片幻灯片

图 10 改进型背负式进气道内部横截面流向速度分布云图

Figure 10. Streamwise velocity distribution contour of interior sections of improved dorsal inlet

下载: 全尺寸图片幻灯片

图 11 背负式进气道质量流量随时间变化曲线

Figure 11. Variation curves of mass flux with time of dorsal inlet

下载: 全尺寸图片幻灯片

图 12 背负式进气道出口截面总压监测点分布

Figure 12. Distribution of total pressure monitor points on outlet section of dorsal inlet

下载: 全尺寸图片幻灯片

图 13 σ_r沿周向分布

Figure 13. Circumferential distribution of σ_r

下载: 全尺寸图片幻灯片

图 14 背负式进气道内部前四阶POD模态

Figure 14. The first four order POD modes of dorsal inlet interior

下载: 全尺寸图片幻灯片

图 15 改进型背负式进气道内部前四阶POD模态

Figure 15. The first four order POD modes of improved dorsal inlet interior

下载: 全尺寸图片幻灯片

图 16 背负式进气道脉动压力功率谱密度分析及快速傅里叶变换分析

Figure 16. Power spectral density and fast Fourier transformation of fluctuating pressure for dorsal inlet

下载: 全尺寸图片幻灯片

图 17 改进型背负式进气道脉动压力功率谱密度分析及快速傅里叶变换分析

Figure 17. Power spectral density and fast Fourier transformation of fluctuating pressure for improved dorsal inlet

下载: 全尺寸图片幻灯片

表 1 畸变指数

Table 1. Distortion coefficient

工况	ε_av	Δσ₀	θ^－/(°)	W
原型	0.034	0.04	135	0.074
改进型	0.031	0.036	128	0.067

下载: 导出CSV

参考文献(19)

[1]	李大伟, 张云飞, 马东立.背负式S形进气道设计及数值分析[J].推进技术, 2006, 27(1):61-65. doi: 10.3321/j.issn:1001-4055.2006.01.015 LI D W, ZHANG Y F, MA D L.Design and numerical investigation of dorsal S-shaped inlet[J].Journal of Propulsion Technology, 2006, 27(1):61-65(in Chinese). doi: 10.3321/j.issn:1001-4055.2006.01.015
[2]	李大伟, 马东立.背负式S形进气道流场控制技术[J].北京航空航天大学学报, 2008, 34(12):1456-1459. http://d.old.wanfangdata.com.cn/Periodical/bjhkhtdxxb200812021 LI D W, MA D L.Improving dorsal S-shaped inlet performance by vortex flow control[J].Journal of Beijing University of Aeronautics and Astronautics, 2008, 34(12):1456-1459(in Chinese). http://d.old.wanfangdata.com.cn/Periodical/bjhkhtdxxb200812021
[3]	郁新华, 刘斌, 陶于金, 等.背负式进气道设计及其气动性能研究[J].西北工业大学学报, 2007, 25(2):270-273. doi: 10.3969/j.issn.1000-2758.2007.02.024 YU X H, LIU B, TAO Y J, et al.Top-mounted inlet design and its aerodynamic performance[J].Journal of Northwestern Polytechnical University, 2007, 25(2):270-273(in Chinese). doi: 10.3969/j.issn.1000-2758.2007.02.024
[4]	谭慧俊, 郭荣伟.一种背负式无附面层隔道进气道的数值模拟研究与实验验证[J].航空学报, 2004, 25(6):540-545. doi: 10.3321/j.issn:1000-6893.2004.06.003 TAN H J, GUO R W.Numerical simulation investigation and experimental validation of a top-mounted diverterless inlet and its validation[J].Acta Aeronautica et Astronautica Sinica, 2004, 25(6):540-545(in Chinese). doi: 10.3321/j.issn:1000-6893.2004.06.003
[5]	TAN H J, GUO R W.Design and wind tunnel study of a top-mounted diverterless inlet[J].Chinese Journal of Aeronautics, 2004, 17(2):72-78. doi: 10.1016/S1000-9361(11)60217-3
[6]	SHI L, GUO R W.Serpentine inlet design and analysis: AIAA-2012-0839[R].Reston: AIAA, 2012.
[7]	ZHANG Z, XU Q, HOU A.Numerical simulation on aerodynamic performance of dorsal S-shaped inlet[C]//3rd International Symposium on Systems and Control in Aeronautics and Astronautics.Piscataway, NJ: IEEE Press, 2010: 5632898.
[8]	MURAKAMI Y W A U.Design of top mounted supersonic inlet for silent supersonic technology demonstrator S3TD[C]//27th International Congress of the Aeronautical Sciences, 2010: 1-9.
[9]	张乐, 周洲, 许晓平, 等.飞翼无人机3种保形进气口进气道气动与隐身综合特性对比[J].航空动力学报, 2015, 30(7):1651-1660. http://d.old.wanfangdata.com.cn/Periodical/hkdlxb201507017 ZHANG L, ZHOU Z, XU X P, et al.Comparison on aerodynamic and stealthy performance of flying wing unmanned aerial vehicle with three conformal intake inlets[J].Journal of Aerospace Power, 2015, 30(7):1651-1660(in Chinese). http://d.old.wanfangdata.com.cn/Periodical/hkdlxb201507017
[10]	孔德英, 邓文剑, 方力.一种背负式S弯进气道辅助进气门设计[J].航空科学技术, 2016, 27(12):1-7. doi: 10.3969/j.issn.1007-5453.2016.12.001 KONG D Y, DENG W J, FANG L.Design of an auxiliary air intake for the dorsal S-shaped inlet[J].Aeronautical Science & Technology, 2016, 27(12):1-7(in Chinese). doi: 10.3969/j.issn.1007-5453.2016.12.001
[11]	徐诸霖, 达兴亚, 范召林.基于五孔探针的大S弯进气道旋流畸变评估[J].航空学报, 2017, 38(12):53-62. http://d.old.wanfangdata.com.cn/Periodical/hkxb201712005 XU Z L, DA X Y, FAN Z L.Assessment of swirl distortion of serpentine inlet based on five-hole probe[J].Acta Aeronautica et Astronautica Sinica, 2017, 38(12):53-62(in Chinese). http://d.old.wanfangdata.com.cn/Periodical/hkxb201712005
[12]	张航, 谭慧俊, 李湘萍.类X-47狭缝式进气道的流动特征与工作性能[J].航空学报, 2009, 30(12):2243-2249. doi: 10.3321/j.issn:1000-6893.2009.12.001 ZHANG H, TAN H J, LI X P.Flowstructure and performance characteristics of X-47-like slot-shaped inlet[J].Acta Aeronautica et Astronautica Sinica, 2009, 30(12):2243-2249(in Chinese). doi: 10.3321/j.issn:1000-6893.2009.12.001
[13]	SHUR M L, SPALART P R, STRELETS M K, et al.A hybrid RANS-LES approach with delayed-DES and wall-modelled LES capabilities[J].International Journal of Heat and Fluid Flow, 2008, 29(6):1638-1649. doi: 10.1016/j.ijheatfluidflow.2008.07.001
[14]	SPALART P R, DECK S, SHUR M L, et al.A new version of detached-eddy simulation, resistant to ambiguous grid densities[J].Theoretical and Computational Fluid Dynamics, 2006, 20(3):181-195. doi: 10.1007/s00162-006-0015-0
[15]	SPALART P, JOU W, STRELETS M, et al.Comments on the feasibility of LES for wings, and on a hybrid RANS/LES approach[C]//First AFOSR International Conference on DNS/LES, 1997: 137-147.
[16]	VENKATAKRISHNAN V.On the accuracy of limiters and convergence to steady state solutions[C]//31st Aerospace Sciences Meeting and Exhibit.Reston: AIAA, 1994: 1-12.
[17]	JAMESON A.Time dependent calculations using multigrid, with applications to unsteady flows past airfoils and wings[C]//10th Computational Fluid Dynamics Conference.Reston: AIAA, 1991: 1586-1599.
[18]	SIROVICH L.Turbulence and the dynamics of coherent structures Ⅰ-Ⅲ[J].Quarterly of Applied Mathematics, 1987, 45(3):561-590. doi: 10.1090/qam/1987-45-03
[19]	刘大响, 叶培梁, 胡骏, 等.航空燃气涡轮发动机稳定性设计与评定技术[M].北京:航空工业出版社, 2004. LIU D X, YE P L, HU J, et al.Stability design and assessment technology of aeronautical turbine engine[M].Beijing:Aviation Industry Press, 2004(in Chinese).