Inlet design and experimental verification of matching axial supersonic through-flow fan
-
摘要:
针对某轴向超声速通流风扇设计与之匹配的轴对称进气道，提出了一种适用于此类进气道的设计方法，此类进气道无扩张段结构，出口即为喉道，全流场超声速。首先以
Ma 0=2.5为设计点设计初始进气道并探究了半锥角等典型参数对进气道的影响，结果表明：随半锥角增大，进气道出口总压恢复系数σ 增大、长度缩短。经分析，缩短进气道长度对于提升进气道出口σ 较为有效。将内压段中心体型面以曲面形式设计缩短进气道长度并设计试验模型进行风洞试验，此方案进气道长度缩短了约23.3%，数值模拟结果表明，在Ma 0=2.5和2.0下的不同攻角工况，进气道出口σ 提升；数值模拟的中心体沿程压力曲线和外压段纹影与风洞试验吻合较好，验证了本文数值模拟方法和进气道设计方法的正确性。Abstract:Aiming at the axisymmetric inlet designed for an axial supersonic through-flow fan, a design method suitable for this kind of inlet is proposed. This kind of inlet has no expansion section structure, the outlet is the throat, and the whole flow field is supersonic. Firstly, the initial inlet is designed with
Ma 0=2.5 as the design point, and the influence of typical parameters such as half cone angle on the inlet is explored. The results show that with the increase of half cone angle, the total pressure recovery coefficientσ at the outlet of the inlet increases and the length decreases. After analysis, shortening the inlet length is more effective for improving theσ . The central body surface of the internal pressure section is designed in the form of curved surface to shorten the length of the inlet and the test model is designed for wind tunnel test. The length of the inlet is shortened by about 23.3%. The numerical simulation results show that theσ of the inlet increases at different angles of attack atMa 0=2.5 and 2.0. The curve of pressure ratio along the center of the numerical simulation and the schlieren of the external pressure section are in good agreement with the wind tunnel test, which verifies the correctness of the numerical simulation method and the inlet design method in this paper. -
图 1 Fluent计算边界条件和网格无关性验证（2D）
Figure 1. Boundary conditions of Fluent and grid independence verification （2D）
图 2 Fluent计算边界条件和网格无关性验证（3D）
Figure 2. Boundary conditions of Fluent and grid independence verification （3D）
图 3 轴向超声速通流风扇和常规涡扇发动机对比示意图
Figure 3. Comparison of axial supersonic through-flow fan and conventional turbo-fan engine
图 7 Profile 1设计点流场及数值纹影图
Figure 7. Flow field and numerical schlieren diagram of Profile 1 at design point
图 9 不同δ2下进气道出口总压恢复系数
Figure 9. Total pressure recovery coefficient at inlet exit under different δ2
图 10 δ2为0°和4.5°时进气道马赫数云图和数值纹影图
Figure 10. When δ2 is 0° and 4.5°, the Mach number cloud diagram and numerical schlieren diagram of the inlet
图 13 型面控制方案与Profile 2对比
Figure 13. Comparison of the surface control schemes and the Profile 2
图 14 两种典型型面控制方案进气道流场（Ma0=2.5）
Figure 14. Two typical surface control schemes of inlet flow field （Ma0=2.5）
图 15 Profile 3设计点流场及数值纹影
Figure 15. Flow field and numerical schlieren diagram of the Profile 3 at design point
图 16 Profile 2和Profile 3设计点沿程压比（Ma0=2.5）
Figure 16. On-way pressure ratio of the Profile 2 and Profile 3 at design point （Ma0=2.5）
图 17 Profile 2和Profile 3非设计点流场及数值纹影图
Figure 17. Flow field and numerical schlieren diagram of the Profile 2 and the Profile 3 at off-design points
图 18 型面控制前后进气道出口总压比云图（α=0°）
Figure 18. Comparison of the total pressure ratio cloud diagram of outlet before and after optimization （α=0°）
图 19 Profile 2和Profile 3不同攻角出口总压恢复系数
Figure 19. Comparison of total pressure recovery coefficient at different α of the Profile 2 and Profile 3
图 20 α=6°时Profile 2 和 Profile 3出口总压比云图对比
Figure 20. α=6°, the total pressure ratio of the inlet Profile 2 and Profile 3 is compared
图 22 试验模型与实际模型流场对比
Figure 22. Comparison of flow field between experimental model and simulation model
图 23 仿真与试验沿程压比对比
Figure 23. Comparison of pressure ratio between simulation and experiment
图 24 数值模拟与试验外压段激波对比
Figure 24. Comparison of shock in external pressure section between simulation and experiment
表 1 不同疏密度网格节点数
Table 1. Number of grid nodes with different density
网格疏密
程度2D 3D 节点数/
104底层网格
尺度/mm节点数/
104底层网格
尺度/mm粗糙 2.8 0.01 186 0.01 适中 7 0.0005 466 0.006 较密 11 0.0005 900 0.006 
下载: 导出CSV
表 2 2D、3D进气道数值模拟气动参数
Table 2. Numerical simulation of inlet aerodynamic parameters of 2D and 3D
空间维度 π σ 2D 1.71 0.927 3D 1.70 0.926
下载: 导出CSV
表 3 两种型面控制方案进气道部分气动参数
Table 3. Partial aerodynamic parameters of inlet under two surface control schemes
方案 Mae σ ϕ A 2.07 0.928 0.998 B 2.17 0.945 0.998
下载: 导出CSV
表 4 Profile 2和Profile 3部分气动参数对比
Table 4. Comparison of partial aerodynamic parameters between the Profile 2 and the Profile 3
Ma0 构型 Mae σ ϕ 2.5 Profile 2 2.19 0.925 0.998 Profile 3 2.17 0.945 0.998 2.0 Profile 2 1.75 0.942 0.955 Profile 3 1.75 0.958 0.955 1.5 Profile 2 1.26 0.959 0.906 Profile 3 1.28 0.966 0.906 0.8 Profile 2 0.77 0.987 0.831 Profile 3 0.77 0.983 0.827
下载: 导出CSV
表 5 风洞来流参数（Ma0=0）
Table 5. Wind tunnel inflow parameters （Ma0=0）
来流静压$p_0 $/Pa 来流总压$p_0^* $/Pa 来流总温T*/K 23520 184031 297
下载: 导出CSV
-
[1] Chesnakas C J, Ng W F. Supersonic through-flow fan blade cascade studies[J]. Journal of Fluids Engineering, 2003, 125(5): 796-805. doi: 10.1115/1.1601257 [2] 马继华, 单鹏, 周盛. 超音通流风扇叶栅流场数值模拟[J]. 北京航空航天大学学报, 1994, 20(3): 271-279. Ma Jihua, Shan Peng, Zhou Sheng. Numerical simulation of supersonic through-flow fan cascade flowfield[J]. Journal of Beijing University of Aeronautics and Astronautics, 1994, 20(3): 271-279. (in ChineseMa Jihua, Shan Peng, Zhou Sheng. Numerical simulation of supersonic through-flow fan cascade flowfield[J]. Journal of Beijing University of Aeronautics and Astronautics, 1994, 20(3): 271-279. (in Chinese) [3] Richard J C. Unsteady quasi-one-dimensional nonlinear dynamic model of supersonic through-flow fan surge[J]. Journal of Propulsion and Power, 2006, 22(1): 188-196. doi: 10.2514/1.14332 [4] 李嘉宾, 季路成. 轴向超音通流转叶风扇级的方案设计分析[J]. 工程热物理学报, 2018, 39(2): 271-276. Li Jiabin, Ji Lucheng. Basic analysis on the design of an fan stage with axial supersonic through-flow rotor[J]. Journal of Engineering Thermophysics, 2018, 39(2): 271-276. (in ChineseLi Jiabin, Ji Lucheng. Basic analysis on the design of an fan stage with axial supersonic through-flow rotor[J]. Journal of Engineering Thermophysics, 2018, 39(2): 271-276. (in Chinese) [5] Sun Shijun, Zhou Ling, Ji Lucheng. Influence of solidity on aerodynamic performance of axial supersonic through-flow fan cascades[J]. Journal of Propulsion and Power, 2022, 38(4): 559-572. doi: 10.2514/1.B38519 [6] 孙士珺, 李晓龙, 刘艳明, 等. 宽速域来流对超声通流风扇叶型气动性能的影响[J]. 航空学报, 2023, 44(21): 528523. Sun Shijun, Li Xiaolong, Liu Yanming, et al. Influence of wide-speed-range inflow on aerodynamic performance of supersonic through-flow fan cascade[J]. Acta Aeronautica et Astronautica Sinica, 2023, 44(21): 528523. (in Chinese doi: 10.7527/S1000-6893.2023.28523Sun Shijun, Li Xiaolong, Liu Yanming, et al. Influence of wide-speed-range inflow on aerodynamic performance of supersonic through-flow fan cascade[J]. Acta Aeronautica et Astronautica Sinica, 2023, 44(21): 528523. (in Chinese) doi: 10.7527/S1000-6893.2023.28523 [7] 单鹏, 陶德平. 超音通流风扇发动机循环分析[J]. 推进技术, 1991, 12(2): 31-39. Shan Peng, Tao Deping. Cycle analysis for a supersonic through flow fan engine[J]. Journal of Propulsion Technology, 1991, 12(2): 31-39. (in ChineseShan Peng, Tao Deping. Cycle analysis for a supersonic through flow fan engine[J]. Journal of Propulsion Technology, 1991, 12(2): 31-39. (in Chinese) [8] 杨玉东, 马继华, 陶德平. 超音通流风扇气动设计问题初探[C]//中国航空学会第八届叶轮机学术讨论会论文集. 北京: 中国航空学会, 1996: 15-25. Yang Yudong, Ma Jihua, Tao Deping. Aerodynamic design of supersonic through-flow fan[C]//Proceedings of the 8th Turbomachinery Symposium of China Aeronauti-cal Society. Beijing: Chinese society of aeronautics and astronautics, 1996: 15-25. (in ChineseYang Yudong, Ma Jihua, Tao Deping. Aerodynamic design of supersonic through-flow fan[C]//Proceedings of the 8th Turbomachinery Symposium of China Aeronauti-cal Society. Beijing: Chinese society of aeronautics and astronautics, 1996: 15-25. (in Chinese) [9] 何中伟, 张世英. 轴对称超音速进气道附面层控制实验研究[J]. 南京航空航天大学学报, 1985(2): 91-100. He Zhong Wei, Zhang Shi Ying. Experimental study on boundary layer control of axisymmetric supersonic inlet[J]. Journal of Nanjing University of Aeronautics and Astronautics, 1985(2): 91-100. (in ChineseHe Zhong Wei, Zhang Shi Ying. Experimental study on boundary layer control of axisymmetric supersonic inlet[J]. Journal of Nanjing University of Aeronautics and Astronautics, 1985(2): 91-100. (in Chinese) [10] 谢旅荣, 郭荣伟. 定几何混压式轴对称超声速进气道气动特性数值仿真和实验验证[J]. 航空学报, 2007, 28(1): 78-83. Xie Lurong, Guo Rongwei. Numerical simulation and experimental verification of aerodynamic characteristics of fixed-geometry mixed-compression axisymmetric supersonic inlet[J]. Acta Aeronautica et Astronautica Sinica, 2007, 28(1): 78-83. (in ChineseXie Lurong, Guo Rongwei. Numerical simulation and experimental verification of aerodynamic characteristics of fixed-geometry mixed-compression axisymmetric supersonic inlet[J]. Acta Aeronautica et Astronautica Sinica, 2007, 28(1): 78-83. (in Chinese) [11] 高文智. 鼻锥钝化轴对称高超声速进气道流动特性研究[D]. 合肥: 中国科学技术大学, 2015. Gao Wenzhi. Study on flow characteristics of axisymmetric hypersonic inlet with nose bluntness[D]. Hefei: University of Science and Technology of China, 2015. (in ChineseGao Wenzhi. Study on flow characteristics of axisymmetric hypersonic inlet with nose bluntness[D]. Hefei: University of Science and Technology of China, 2015. (in Chinese) [12] 王卫星, 郭荣伟. 基于边界层转捩的高超声速进气道特性研究[J]. 航空学报, 2012, 33(10): 1772-1780. Wang Weixing, Guo Rongwei. Research on characteristics of hypersonic inlet based on boundary layer transition[J]. Acta Aeronautica et Astronautica Sinica, 2012, 33(10): 1772-1780. (in ChineseWang Weixing, Guo Rongwei. Research on characteristics of hypersonic inlet based on boundary layer transition[J]. Acta Aeronautica et Astronautica Sinica, 2012, 33(10): 1772-1780. (in Chinese) [13] 张辉, 伊卫林, 岳连捷, 等. 可变几何轴对称进气道初步设计[J]. 燃气轮机技术, 2008, 21(3): 21-24, 28. Zhang Hui, Yi Weilin, Yue Lianjie, et al. Preliminary design on variable- geometry axisymmetric inlet duct[J]. Gas Turbine Technology, 2008, 21(3): 21-24, 28. (in Chinese doi: 10.3969/j.issn.1009-2889.2008.03.006Zhang Hui, Yi Weilin, Yue Lianjie, et al. Preliminary design on variable- geometry axisymmetric inlet duct[J]. Gas Turbine Technology, 2008, 21(3): 21-24, 28. (in Chinese) doi: 10.3969/j.issn.1009-2889.2008.03.006 [14] 郭程伟. 宽范围轴对称变几何进气道设计方法与调节规律研究[D]. 南京: 南京航空航天大学, 2014. Guo Chengwei. Research on the design and regulation of variable axisymmetric inlet working under wide Mach number[D]. Nanjing: Nanjing University of Aeronautics and Astronautics, 2014. (in ChineseGuo Chengwei. Research on the design and regulation of variable axisymmetric inlet working under wide Mach number[D]. Nanjing: Nanjing University of Aeronautics and Astronautics, 2014. (in Chinese) [15] 牛雨鹏, 武志文, 张智慧, 等. 抽吸位置对固冲发动机进气道性能的影响[J]. 航空动力学报, 2024, 39(8): 20220507. Niu Yupeng, Wu Zhiwen, Zhang Zhihui, et al. Effect of suction position on inlet performance of solid rocket ramjet[J]. Journal of Aerospace Power, 2024, 39(8): 20220507. (in ChineseNiu Yupeng, Wu Zhiwen, Zhang Zhihui, et al. Effect of suction position on inlet performance of solid rocket ramjet[J]. Journal of Aerospace Power, 2024, 39(8): 20220507. (in Chinese) [16] 岳连捷, 叶青, 徐显坤, 等. 三面压缩高超进气道附面层抽吸研究[J]. 航空动力学报, 2012, 27(2): 372-378. Yue Lianjie, Ye Qing, Xu Xiankun, et al. Boundary layer bleeding of three-dimensional compression hypersonic inlet[J]. Journal of Aerospace Power, 2012, 27(2): 372-378. (in Chinese doi: 10.13224/j.cnki.jasp.2012.02.023Yue Lianjie, Ye Qing, Xu Xiankun, et al. Boundary layer bleeding of three-dimensional compression hypersonic inlet[J]. Journal of Aerospace Power, 2012, 27(2): 372-378. (in Chinese) doi: 10.13224/j.cnki.jasp.2012.02.023 [17] 张堃元. 高超声速进气道曲面压缩技术综述[J]. 推进技术, 2018, 39(10): 2227-2235. Zhang Kunyuan. Review on curved surface compression technology of hypersonic inlet[J]. Journal of Propulsion Technology, 2018, 39(10): 2227-2235. (in Chinese doi: 10.13675/j.cnki.tjjs.2018.10.008Zhang Kunyuan. Review on curved surface compression technology of hypersonic inlet[J]. Journal of Propulsion Technology, 2018, 39(10): 2227-2235. (in Chinese) doi: 10.13675/j.cnki.tjjs.2018.10.008 [18] 王鑫, 袁化成, 刘甫州, 等. 一种曲面压缩高超声速进气道的设计及流场快速求解方法[J]. 固体火箭技术, 2022, 45(4): 522-531. Wang Xin, Yuan Huacheng, Liu Fuzhou, et al. Rapid design and flow field solution method of curved compression hypersonic inlet[J]. Journal of Solid Rocket Technology, 2022, 45(4): 522-531. (in Chinese doi: 10.7673/j.issn.1006⁃2793.2022.04.005Wang Xin, Yuan Huacheng, Liu Fuzhou, et al. Rapid design and flow field solution method of curved compression hypersonic inlet[J]. Journal of Solid Rocket Technology, 2022, 45(4): 522-531. (in Chinese) doi: 10.7673/j.issn.1006⁃2793.2022.04.005 -
点击查看大图
计量
- 文章访问数: 241
- HTML浏览量: 168
- PDF量: 23
- 被引次数: 0