内转式进气道进出口宽高比对流动特性的影响

推进技术 ›› 2018, Vol. 39 ›› Issue (12): 2679-2684.

内转式进气道进出口宽高比对流动特性的影响

周航,金志光,张堃元

南京航空航天大学能源与动力学院，江苏南京 210016,南京航空航天大学能源与动力学院，江苏南京 210016,南京航空航天大学能源与动力学院，江苏南京 210016

发布日期:2021-08-15
作者简介:周航，男，博士生，研究领域为高超声速内流气体动力学。E-mail: nuaa_zhouhang@qq.com 通讯作者:金志光，男，博士，副教授，研究领域为高超声速内流气体动力学。

Effects of Entrance and Exit Aspect Ratios on Flow Characteristics of Inward Turning Inlets

College of Energy and Power Engineering，Nanjing University of Aeronautics and Astronautics，Nanjing 210016，China,College of Energy and Power Engineering，Nanjing University of Aeronautics and Astronautics，Nanjing 210016，China and College of Energy and Power Engineering，Nanjing University of Aeronautics and Astronautics，Nanjing 210016，China

Published:2021-08-15

摘要/Abstract

摘要： 为研究内转式进气道进出口宽高比对流动特性的影响规律，通过设置宽高比不等的矩形进出口形状，对不同进出口宽高比组合方式下的进气道性能进行了数值模拟。在Ma6设计点对多个模型的计算结果表明:出口与进口宽高比的比值是影响进气道性能的关键参数，该比值在1～1.5内进气道总压恢复系数较高，最大增幅达25.3%；该比值为1时进气道出口气流畸变最大，通过设置合理的进出口比值可有效减小出口气流畸变，且最大降幅达40.5%；此外，进出口宽高比在0.8～2.4内，增大进出口宽高比可最多缩短25%的进气道长度。

关键词: 内转式进气道；宽高比；数值模拟；截面渐变

Abstract: To study the effects of the entrance and exit aspect ratios on flow characteristic of the inward turning inlet， the performance of inlets with different compound modes of entrance and exit aspect ratios is simulated by setting entrance and exit shape with different aspect ratios. Multiple models are numerically simulated at the design point of Ma6. The results indicate that the ratio of the exit and entrance aspect ratios is an important parameter of the inlet performance. The total pressure recovery coefficient is high when the ratio is between 1 and 1.5. The maximum increase reaches 25.3%. The distortion index is highest when the ratio is 1. Setting different exit and entrance aspect ratios can decrease the distortion index. The maximum decline reaches 40.5%. In addition， when the entrance and exit aspect ratios are between 0.8 and 2.4， increasing the aspect ratios can reduce 25% of the inlet length at most.

Key words: Inward turning inlets；Aspect ratio；Numerical simulation；Shape transition

周航,金志光,张堃元. 内转式进气道进出口宽高比对流动特性的影响[J]. 推进技术, 2018, 39(12): 2679-2684.

ZHOU Hang,JIN Zhi-guang,ZHANG Kun-yuan. Effects of Entrance and Exit Aspect Ratios on Flow Characteristics of Inward Turning Inlets[J]. Journal of Propulsion Technology, 2018, 39(12): 2679-2684.

参考文献

[1] Tam C J, Baurle R A. Inviscid CFD Analysis of Streamline Traced Hypersonic Inlets at Off-Design Conditions[R]. AIAA 2001-0675.
[2] Tam C J, Baurle R A, Streby G D. Numerical Analysis of Stream-Traced Hypersonic Inlets[R]. AIAA 2003-13.
[3] Smart M K. Design of Three-Dimensional Hypersonic Inlets with Rectangular-to-Elliptical Shape Transition[J]. Journal of Power and Propulsion, 1999, 15(3): 408-416.
[4] Taylor T, Vanwie D. Performance Analysis of Hypersonic Shape-Changing Inlets Derived from Morphing Streamline Traced Flowpaths[R]. AIAA 2008-2635.
[5] Malo-Molina F J, Gaitonde D V, Kutschenreuter P H. Numerical Investigation of an Innovative inward Turning Inlet[R]. AIAA 2005-4871.
[6] 尤延铖, 梁德旺, 黄国平. 一种新型内乘波式进气道初步研究[J]. 推进技术, 2006, 27(3): 252-256. (YOU Yan-cheng, LIANG De-wang, HUANG Guo-ping. Investigation of Internal Waverider Derived Hypersonic Inlet[J]. Journal of Propulsion Technology, 2006, 27(3): 252-256.)
[7] 尤延铖, 梁德旺. 基于内乘波概念的三维变截面高超声速进气道[J]. 中国科学E缉:技术科学, 2009, 39(8): 1483-1494.
[8] 南向军, 张堃元, 金志光, 等. 压升规律可控的高超声速内收缩进气道设计[J]. 航空动力学报, 2011, 26(3): 518-523.
[9] 李永洲, 张堃元, 南向军. 基于马赫数分布规律可控概念的高超声速内收缩进气道设计[J]. 航空动力学报, 2012, 27(11): 2484-2491.
[10] 李永洲, 张堃元, 张留欢. 抽吸对高超声速内收缩进气道涡流区及起动性能的影响[J]. 航空动力学报, 2016, 31(7): 1630-1637.
[11] 朱呈祥, 黄国平, 尤延铖, 等. 内乘波式进气道与典型侧压式进气道的性能对比[J]. 推进技术, 2011, 32(2): 151-158. (ZHU Cheng-xiang, HUANG Guo-ping, YOU Yan-cheng, et al. Performance Comparison Between Internal Waverider Inlet and Typical Sidewall Compression Inlet[J]. Journal of Propulsion Technology, 2011: 32(2): 151-158.)
[12] 王德鹏, 田方超, 张启帆, 等. 进口形状对内转式进气道的起动特性影响[J]. 航空动力学报, 2015, 30(6): 1400-1406.
[13] 李永洲. 马赫数分布可控的高超声速内收缩进气道及其一体化设计研究[D]. 南京:南京航空航天大学, 2014.
[14] 南向军. 压升规律可控的高超声速内收缩进气道设计方法研究[D]. 南京:南京航空航天大学, 2014.
[15] Travis W Drayna, Ioannis Nompelis, Graham V Cabdler. Hypersonic Inward Turning Inlets: Design and Optimization[R]. AIAA 2006-297.
[16] 南向军, 张堃元, 金志光, 等. 矩形转圆形高超声速内收缩进气道数值及试验研究[J]. 航空学报, 2011, 32(6): 988-996.
[17] 李永洲, 张堃元, 孙迪. 马赫数分布可控的方转圆高超声速内收缩进气道实验研究[J]. 航空学报, 2016, 37(10): 2970-2979.
[18] Bagaveyev N T, Engbom W A, Bhagwandin V A. Parametric Investigation of Racetrack-to-Circular Cross Section Transition of a Dual-Mode Ramjet Isolator[R]. AIAA 2010-0942.　　　　　　　　　　　　　　收稿日期:2017-10-24；修订日期:2017-12-21。作者简介:周航,男,博士生,研究领域为高超声速内流气体动力学。E-mail: nuaa_zhouhang@qq.com通讯作者:金志光,男,博士,副教授,研究领域为高超声速内流气体动力学。E-mail: nuaa_jzg@nuaa.edu.cn(编辑:史亚红)