Design and experimental research of Mach number range 0—4 2D mixed parallel-type curved compression inlet
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摘要:
采用内外压缩型面可控的弯曲压缩进气道反设计方法，设计了一种新型混合并联式二元弯曲压缩进气道，重点针对进气道模态转换过程及冲压单独工作条件下进行了数值仿真及试验研究，获得了进气道宽速域性能，结果也表明新型混合并联式弯曲压缩进气道具有较高的综合气动特性，冲压工作状态马赫数为4、攻角为3°时总压恢复0.5以上，马赫数为3、攻角为3°时总压恢复0.75以上，涡轮工作状态马赫数为2、攻角为3°时总压恢复0.88以上，综合畸变指数小于5%，满足宽速域进发匹配需求。
Abstract:Based on the internal and external compression surface controllable curved compression inlet reverse design method, a mixed parallel-type curved compression inlet was designed, numerical simulation and experiment research were conducted focusing on inlet model transition process and ramjet work alone, and wide speed performance of inlet was obtained. The result showed that, the new type parallel curved compression inlet had high comprehensive aerodynamic characteristics, at ramjet work alone state Mach number 4、Angle of attack 3° total pressure recovery coefficient was above 0.5, at Mach number 3、Angle of attack 3° total pressure recovery coefficient was above 0.75, at turbine work state Mach number 2、Angle of attack 3° total pressure recovery coefficient was above 0.88, composite distortion factor was under 5%, meeting the matching requirements of wide speed domain.
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图 1 传统外并联型式组合进气道
Figure 1. Traditional configuration of external parallel-type combined inlet
图 4 进气道出口测量段测耙位置示意图
Figure 4. Schematic diagram of rake position at inlet outlet measuring section
图 6 Ma=2，α=3°涡轮进气道匹配状态流场结构
Figure 6. Matching flowfield structure of Ma=2，α=3° at turbine inlet operation state
图 7 Ma=2，α=3°试验条件下涡轮进气道节流特性
Figure 7. Throttling performance of turbine inlet at Ma=2，α=3° experiment condition
图 8 Ma=2，α=3°试验条件下冲压进气道节流特性
Figure 8. Throttling performance of ramjet inlet at Ma=2，α=3° experiment condition
图 9 Ma=3，α=3°冲压进气道单独工作匹配点流场结构
Figure 9. Flowfield structure of Ma=3，α=3° at ramjet inlet operation state alone
图 10 Ma=3试验条件下冲压进气道节流特性
Figure 10. Throttling performance of ramjet inlet at Ma=3 experiment condition
图 11 Ma=4，α=3°冲压进气道单独工作匹配点流场结构
Figure 11. Flowfield structure of Ma=4，α=3° at ramjet inlet operation state alone
图 12 Ma=4试验条件下冲压进气道节流特性
Figure 12. Throttling performance of ramjet inlet at Ma=4 experiment condition
图 13 Ma=3，α=3°，δ2=6.7°时共同工作流场结构
Figure 13. Flowfield structure of Ma=3，α=3°，δ2=6.7° at combined operating condition
图 14 Ma=3，α=3°不同调板角度下涡轮进气道节流特性
Figure 14. Throttling performance of turbine inlet at Ma=3, α=3° with different actuator plate angles
图 15 Ma=3，α=3°不同调板角度下冲压通道特性
Figure 15. Tperformance of ramjet inlet at Ma=3, α=3° with different actuator plate angles
表 1 冲压进气道唇口调节位置
Table 1. Ramjet inlet cowl-lip adjustment position
马赫数 唇口位置 内收缩比 4 前 1.32 3 前/后 1.32/1.04 
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表 2 涡轮进气道调板板位
Table 2. Turbine inlet actuator plate adjustment position
马赫数 可调二级压缩面相对角度δ2/（°） 1.2 13.5 2 11.5 2.5 9 3 6.7
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表 3 风洞来流参数
Table 3. Parameters of wind tunnel
马赫数 风洞单位雷诺数/107 m−1 来流静压/Pa 来流总温/K 2 1.78 23574 288 3 2.91 9610 288 4 3.09 3981 288
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[1] BULMAN M J, SIEBENHAAR A. Combined cycle propulsion: aerojet innovations for practical hypersonic vehicles[R]. AIAA 2011-2397, 2011. [2] 张华军,郭荣伟,李博. TBCC进气道研究现状及其关键技术[J]. 空气动力学学报,2010,28(5): 613-620. doi: 10.3969/j.issn.0258-1825.2010.05.022ZHANG Huajun,GUO Rongwei,LI Bo. Research status of TBCC inlet and its key technologies[J]. Acta Aerodynamica Sinica,2010,28(5): 613-620. (in Chinese) doi: 10.3969/j.issn.0258-1825.2010.05.022 [3] 向先宏,钱战森,张铁军. TBCC进气道模态转换气动技术研究综述[J]. 航空科学技术,2017,28(1): 10-18.XIANG Xianhong,QIAN Zhansen,ZHANG Tiejun. An overview of turbine-based combined cycle (TBCC) inlet mode transition aerodynamic technology[J]. Aeronautical Science & Technology,2017,28(1): 10-18. (in Chinese) [4] WEIDNER J P. Conceptual study of a turbjet ramjet inlet[R]. NASA TM-80141, 1979. [5] 孙波,邵庆龄,倪凯捷,等. 并联TBCC可调进气道并联方案[J]. 航空动力学报,2017,32(12): 2988-2996.SUN Bo,SHAO Qingling,NI Kaijie,et al. Parallel plans for TBCC variable geometry inlet[J]. Journal of Aerospace Power,2017,32(12): 2988-2996. (in Chinese) [6] SIPPEL M. Research on tbcc propulsion for a Mach 4.5 supersonic cruise airliner[R]. AIAA 2006-7996, 2006. [7] SLATER J W, SAUNDERS J D. CFD simulation of hypersonic TBCC inlet mode transition[R]. AIAA 2009-7349, 2009. [8] FOSTER L E, SAUNDERS J D, Jr. , SANDERS B W, et al. Highlights from a Mach 4 experimental demonstration of inlet mode transition for turbine-based combined cycle hypersonic propulsion[R]. AIAA 2012-4143, 2012. [9] LE D K, VRNAK D R, SLATER J W, et al. A framework for simulating turbine-based combined-cycle inlet mode-transition[R]. AIAA 2012-4144, 2012. [10] CSANK J T, STUEBER T J. Advanced shock position control for mode transition in a turbine based combinedcycle engine inlet model[R]. NASA/TM 2013-216515, 2013. [11] 张明阳,王占学,刘增文,等. Ma4一级内并联式TBCC发动机模态转换性能分析[J]. 推进技术,2017,38(2): 315-322.ZHANG Mingyang,WANG Zhanxue,LIU Zengwen,et al. Analysis of mode transition performance for a Mach 4 over-under TBCC engine[J]. Journal of Propulsion Technology,2017,38(2): 315-322. (in Chinese) [12] 尹朝林. 外并联式TBCC组合发动机的建模与特性分析[D]. 哈尔滨: 哈尔滨工业大学, 2016.YIN Chaolin. The modeling and characteristics analisis of over/under TBCC[D]. Harbin: Harbin Institute of Technology, 2016. (in Chinese) [13] 李龙,李博,梁德旺,等. 涡轮基组合循环发动机并联式进气道的气动特性[J]. 推进技术,2008,29(6): 667-672.LI Long,LI Bo,LIANG Dewang,et al. Aerodynamic characteristics of over/under inlet for turbine based combined cycle engine[J]. Journal of Propulsion Technology,2008,29(6): 667-672. (in Chinese) [14] 赵亮. 内并联式TBCC进气道气动设计与分析[D]. 南京: 南京航空航天大学, 2010.ZHAO Liang. Aerodynamic design and analysis of an inner shunt-wound inlet used in turbine based combined cycle engine[D]. Nanjing: Nanjing University of Aeronautics and Astronautics, 2010. (in Chinese) [15] 唐伟员. 用于内并联TBCC 的变几何二元式进气道设计及气动研究[D]. 南京: 南京航空航天大学, 2016.TANG Weiyuan. Aerodynamic design and study of a variable geometry two-dimensional inlet used in inner shunt-wound turbine based combined cycle[D]. Nanjing: Nanjing University of Aeronautics and Astronautics, 2016. (in Chinese) [16] 左逢源,黄国平,陈杰,等. 基于内乘波概念的TBCC进气道过渡模态研究[J]. 工程热物理学报,2015,36(2): 274-278.ZUO Fengyuan,HUANG Guoping,CHEN Jie,et al. Based on the concept of waverider TBCC inlet mode transition study[J]. Journal of Engineering Thermophysics,2015,36(2): 274-278. (in Chinese) [17] 刘愿,钱战森,向先宏. 外并联式TBCC进气道模态转换风洞试验及模型典型影响因素分析[J]. 实验流体力学,2019,33(5): 19-28.LIU Yuan,QIAN Zhansen,XIANG Xianhong. An analysis on typical influencing factors of wind tunnel experimental model of over-under TBCC inlet mode transition[J]. Journal of Experiments in Fluid Mechanics,2019,33(5): 19-28. (in Chinese) [18] 张堃元. 基于弯曲激波压缩系统的高超声速进气道反设计研究进展[J]. 航空学报,2015,36(1): 274-288.ZHANG Kunyuan. Research progress of hypersonic inlet reverse design based on curved shock compression system[J]. Acta Aeronautica et Astronautica Sinica,2015,36(1): 274-288. (in Chinese) [19] 王磊,张堃元,向有志,等. 高超声速二元弯曲激波压缩面反设计方法的参数化研究[J]. 南京航空航天大学学报,2013,45(4): 441-446. doi: 10.3969/j.issn.1005-2615.2013.04.001WANG Lei,ZHANG Kunyuan,XIANG Youzhi,et al. Parameter analysis of reverse design method of 2-D hypersonic curved shock compression surface[J]. Journal of Nanjing University of Aeronautics & Astronautics,2013,45(4): 441-446. (in Chinese) doi: 10.3969/j.issn.1005-2615.2013.04.001 [20] 朱伟,张堃元,南向军. 壁面马赫数分布规律可控的新型内收缩基准流场设计方法[J]. 推进技术,2013,34(4): 433-438.ZHU Wei,ZHANG Kunyuan,NAN Xiangjun. Investigation on basic flowfield with controlled Mach number gradient for hypersonic inward turning inlets[J]. Journal of Propulsion Technology,2013,34(4): 433-438. (in Chinese) [21] 朱伟,华正旭,王霄,等. 二元弯曲压缩进气道变攻角起动试验[J]. 航空动力学报,2020,35(5): 992-999.ZHU Wei,HUA Zhengxu,WANG Xiao,et al. Variable angle of attack start experiment of 2D curved compression inlet[J]. Journal of Aerospace Power,2020,35(5): 992-999. (in Chinese) -
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