Experimental and numerical investigation of core and bypass flow mixing characteristics in variable-bypass-ratio afterburner/ram combustor
-
摘要:
以变循环发动机可变涵道比加力/冲压燃烧室为研究对象，采用缩比模型流场实验和全尺寸三维数值仿真的方法，揭示不同涵道比、平行混合器出口面积比下的加力燃烧室内部流场特征，定量评价加力燃烧室内速度不均匀度、掺混损失、隔热屏冷却通道外侧机匣壁面温度峰值等参数。研究结果表明：相较于内涵入口均匀流，内涵入口考虑旋流后，旋转的内涵流体与外涵流体增强了剪切混合，严重时引起内涵高温流体部分进入隔热屏冷却通道，致使隔热屏冷却通道外机匣局部温度高达812.97 K。采用平行混合器可有效控制加力/冲压燃烧室总压损失，在3.5%以内。内外涵出口面积比是重要参数，合理的面积分配能够确保外涵道流体有足够的空气进入隔热屏冷却通道，同时有足够的惯性力遏制隔热屏入口段内侧流动分离。小涵道比工况下，增大内外涵出口面积比将导致冷却气量减少约20%，可能造成隔热屏冷却效果变差；同时低动量的外涵流体难以克服逆压梯度，在隔热屏内侧形成回流区，导致火焰稳定器上游径向速度不均匀度恶化至0.10～1.20，对加力燃烧不利。在大涵道比工况下，过小的内外涵出口面积比将导致掺混损失增至3.16%，随着内外涵出口面积比提高，内外涵气流匹配度改善，速度不均匀度范围提升至0.85～1.07，展现出更优的综合性能。
Abstract:The variable-bypass-ratio afterburner/ram combustor of a variable cycle engine was investigated through scaled-model flow experiments and full-scale three-dimensional numerical simulations. The purpose of the research was to reveal the internal flow characteristics under different bypass ratios (BPR) and parallel mixer exit area ratios, while quantitatively evaluating key parameters including velocity non-uniformity, mixing loss, and peak outer casing temperature of the heat shield cooling channel. The results showed that, compared with the uniform flow at the core flow inlet, the introduction of swirl enhanced shear mixing between the rotating core flow and the bypass stream. Under severe conditions, this caused partial ingress of high-temperature core fluid into the heat shield cooling channel, resulting in localized temperatures as high as 812.97 K on the outer casing. The use of a parallel mixer effectively controlled the total pressure loss in the afterburner/ram combustor, maintaining it within 3.5%. The bypass-to-core exit area ratio served as a critical parameter. An appropriate area allocation ensured sufficient bypass airflow entered the cooling passage while providing adequate momentum to suppress flow separation at the inner side of the heat shield inlet. Under small bypass ratio conditions, increasing the bypass-to-core exit area ratio reduced the cooling flow rate by approximately 20%, which can impair the cooling effectiveness of the heat shield. Additionally, the low-momentum bypass flow struggled to overcome the adverse pressure gradient, leading to the formation of a recirculation zone on the inner side of the heat shield and worsening the radial velocity non-uniformity upstream the flame holder to a range of 0.10—1.20, adversely affecting afterburner performance. In contrast, under large bypass ratio conditions, an excessively small bypass-to-core exit area ratio increased the mixing loss to 3.16%. As the bypass-to-core exit area ratio increased, the matching between the core and bypass flows improved, and the velocity non-uniformity narrowed to a range of 0.85—1.07, demonstrating superior overall performance.
-
图 7 混合器下游切面仿真与实验数据对比
Figure 7. Comparison of CFD and experimental data at the mixer downstream cross-section
图 8 火焰稳定器前切面仿真与实验数据对比
Figure 8. Comparison of CFD and experimental data at the flame holder upstream plane
图 9 内涵进气面速度和温度云图
Figure 9. Contour plots of velocity and temperature at the core duct inlet plane
图 10 中心对称截面速度云图（内涵有无旋流对比）
Figure 10. Contours of velocity on the central symmetric plane （with/without swirl in the core flow）
图 11 中心对称截面温度云图（内涵有无旋流对比）
Figure 11. Contours of temperature on the central symmetric plane （with/without swirl in the core flow）
图 12 火焰稳定器上游截面速度云图（内涵有无旋流对比）
Figure 12. Velocity contours on the upstream cross-section of the flame holder （with/without swirl in the core flow）
图 13 外/内涵入口压比随混合器出口面积分配的变化曲线
Figure 13. Curve of bypass/core inlet pressure ratio versus mixer exit area allocation
图 14 小涵道比条件下中心对称截面速度云图（不同混合器出口面积分配对比）
Figure 14. Contours of velocity on the central symmetric plane under low bypass ratio （with different mixer exit area allocations）
图 15 小涵道比条件下中心对称截面温度云图（不同混合器出口面积分配对比）
Figure 15. Contours of temperature on the central symmetric plane under low bypass ratio （with different mixer exit area allocations）
图 16 小涵道比条件下火焰稳定器上游横截面速度云图（不同混合器出口面积分配对比）
Figure 16. Velocity contours at flame holder upstream cross-section under low bypass ratio （with different mixer exit area allocations）
图 17 大涵道比条件下中心对称截面速度云图（不同混合器出口面积分配对比）
Figure 17. Contours of velocity on the central symmetric plane under high bypass ratio （with different mixer exit area allocations）
图 18 大涵道比条件下中心对称截面温度云图（不同混合器出口面积分配对比）
Figure 18. Contours of temperature on the central symmetric plane under high bypass ratio （with different mixer exit area allocations）
图 19 大涵道比条件下火焰稳定器上游横截面速度云图（不同混合器出口面积分配对比）
Figure 19. Velocity contours at Flame Holder upstream cross-section under high bypass ratio （with different mixer exit area allocations）
表 1 实验工况下模型进口和出口参数
Table 1. Inlet and outlet parameters for the experimental model
工况 外涵入口 内涵入口 pb/kPa qm,inl/（kg/s） Tin1/K pin1/kPa qm,in2/（kg/s） Tin2/K pin2/kPa 小涵道比 0.56 313.15 376.94 1.76 731.15 378.51 367.5 大涵道比 0.90 313.15 356.51 1.47 653.15 349.24 336.6 
下载: 导出CSV
表 2 仿真与实验参数对比
Table 2. Comparison of CFD and experimental parameters
工况 $ {\sigma _{\text{p}}} $ $ \Delta {C_{\theta ,{\text{h}}}} $ $ \Delta {C_{r,{\text{h}}}} $ CFD EXP CFD EXP CFD EXP 小涵道比 0.0153 0.0151 0.90～1.17 0.80～1.24 0.74～1.25 0.79～1.24 大涵道比 0.0284 0.0254 0.89～1.04 0.77～1.23 0.70～1.22 0.78～1.15
下载: 导出CSV
表 3 内涵旋流对加力燃烧室性能的影响
Table 3. Impact of core flow swirl on afterburner performance
参数 无旋流 有旋流 $ {\sigma _{\text{p}}} $ 0.0011 0.0041 $ \phi $ 0.060 0.073 $ {T_{{\text{l}} - {\text{max}}}}{\text{/K}} $ 484.20 812.97 $ \Delta {C_{\theta ,{\text{h}}}} $ 0.99～1.01 0.79～1.13 $ \Delta {C_{r,{\text{h}}}} $ 0.10～1.20 0.93～1.19
下载: 导出CSV
表 4 混合器出口面积影响的参数对比表
Table 4. Parameter comparison table of mixer exit area effects
工况 $ {A_{16}}/{A_6} $ $ {\sigma _{\text{p}}} $ $ \phi $ $ {T_{{\text{l}} - {\text{max}}}}{\text{/K}} $ $ \Delta {C_{\theta ,{\text{h}}}} $ $ \Delta {C_{r,{\text{h}}}} $ 小涵道比 0.14 0.0043 0.254 676.31 0.99～1.00 0.75～1.08 0.20 0.0015 0.156 543.46 0.98～1.01 0.32～1.11 0.22 0.0010 0.115 506.67 0.99～1.01 0.21～1.16 0.26 0.0007 0.060 484.20 0.99～1.01 0.10～1.20 大涵道比 0.14 0.0316 0.438 708.73 0.97～1.02 0.75～1.27 0.20 0.0108 0.368 667.69 0.99～1.01 0.78～1.17 0.22 0.0073 0.339 630.05 0.99～1.01 0.80～1.13 0.26 0.0185 0.283 593.98 0.99～1.01 0.85～1.07
下载: 导出CSV
-
[1] CHEN Haoying, ZHANG Haibo, WANG Yong, et al. Installation characteristics of variable cycle engine based on inlet flow matching[J]. International Journal of Turbo & Jet-Engines, 2021, 38(3): 319-329. [2] AYGUN H, CILGIN M E, EKMEKCI I, et al. Energy and performance optimization of an adaptive cycle engine for next generation combat aircraft[J]. Energy, 2020, 209: 118261. doi: 10.1016/j.energy.2020.118261 [3] 刘治呈. 变循环发动机发展综述[J]. 现代制造技术与装备, 2019, 55(1): 177-179. LIU Zhicheng. Summary of the development of variable cycle engines[J]. Modern Manufacturing Technology and Equipment, 2019, 55(1): 177-179. (in ChineseLIU Zhicheng. Summary of the development of variable cycle engines[J]. Modern Manufacturing Technology and Equipment, 2019, 55(1): 177-179. (in Chinese) [4] 方昌德. 变循环发动机[J]. 燃气涡轮试验与研究, 2004, 17(3): 1-5. FANG Changde. Variable cycle engines[J]. Gas Turbine Experiment and Research, 2004, 17(3): 1-5. (in ChineseFANG Changde. Variable cycle engines[J]. Gas Turbine Experiment and Research, 2004, 17(3): 1-5. (in Chinese) [5] 吴涛, 骆广琦, 胡砷纛, 等. 配装变循环/常规发动机的飞机航程比较研究[J]. 计算机仿真, 2015, 32(10): 89-93. WU Tao, LUO Guangqi, HU Shendao, et al. Comparison of range of aircraft equipped with variable cycle engine versus turbofan engine[J]. Computer Simulation, 2015, 32(10): 89-93. (in ChineseWU Tao, LUO Guangqi, HU Shendao, et al. Comparison of range of aircraft equipped with variable cycle engine versus turbofan engine[J]. Computer Simulation, 2015, 32(10): 89-93. (in Chinese) [6] OBAID Y, MARK V A, RICHARD M M, et al. Military jet engine acquisition: technology basis and cost-estimating methodology[M]. Santa Monica, US: RAND Corporation, 2002. [7] 周红, 王占学, 刘增文, 等. 可变面积涵道引射器对变循环发动机性能影响[J]. 航空动力学报, 2016, 31(12): 2842-2850. ZHOU Hong, WANG Zhanxue, LIU Zengwen, et al. Impact of variable area bypass injector on variable cycle engine performance[J]. Journal of Aerospace Power, 2016, 31(12): 2842-2850. (in ChineseZHOU Hong, WANG Zhanxue, LIU Zengwen, et al. Impact of variable area bypass injector on variable cycle engine performance[J]. Journal of Aerospace Power, 2016, 31(12): 2842-2850. (in Chinese) [8] YAN Wei, HU Jun, ZHANG Huan, et al. Effects of complicated rotating inlet distortion on compressor aerodynamic stability: AIAA2014-3732 [R]. Reston, US: AIAA, 2014. [9] 李浪浪. 航空发动机加力燃烧室性能数值研究[D]. 哈尔滨: 哈尔滨工程大学, 2023. LI Langlang. Numerical study of afterburner performance of aero engine[D]. Harbin: Harbin Engineering University, 2023. (in ChineseLI Langlang. Numerical study of afterburner performance of aero engine[D]. Harbin: Harbin Engineering University, 2023. (in Chinese) [10] 武渊, 田维平, 乐发仁, 等. 双模态冲压发动机燃烧室流场数值模拟研究[J]. 固体火箭技术, 2003, 26(4): 41-44. WU Yuan, TIAN Weiping, LE Faren, et al. Study on numerical simulation of the dual-mode scramjet combustor[J]. Journal of Solid Rocket Technology, 2003, 26(4): 41-44. (in ChineseWU Yuan, TIAN Weiping, LE Faren, et al. Study on numerical simulation of the dual-mode scramjet combustor[J]. Journal of Solid Rocket Technology, 2003, 26(4): 41-44. (in Chinese) [11] 窦健. 变循环发动机后涵道引射器设计与气动性能研究[D]. 南京: 南京航空航天大学, 2019. DOU Jian. Research on design and aerodynamic performance for variable cycle engine rear bypass injector[D]. Nanjing: Nanjing University of Aeronautics and Astronautics, 2019. (in ChineseDOU Jian. Research on design and aerodynamic performance for variable cycle engine rear bypass injector[D]. Nanjing: Nanjing University of Aeronautics and Astronautics, 2019. (in Chinese) [12] 黄光辉. 变循环发动机前涵道引射器设计与气动性能研究[D]. 南京: 南京航空航天大学, 2020. HUANG Guanghui. Design and aerodynamic performance research of front variable area bypass injector of variable cycle engine[D]. Nanjing: Nanjing University of Aeronautics and Astronautics, 2020. (in ChineseHUANG Guanghui. Design and aerodynamic performance research of front variable area bypass injector of variable cycle engine[D]. Nanjing: Nanjing University of Aeronautics and Astronautics, 2020. (in Chinese) [13] 山旭. 一种基于TBCC多模态工作条件的掺混器性能研究[D]. 南京: 南京航空航天大学, 2022. SHAN Xu. Research on performance of a mixer based on multi-modal working conditions of TBCC[D]. Nanjing: Nanjing University of Aeronautics and Astronautics, 2022. (in ChineseSHAN Xu. Research on performance of a mixer based on multi-modal working conditions of TBCC[D]. Nanjing: Nanjing University of Aeronautics and Astronautics, 2022. (in Chinese) [14] AOKI S, LEE J, MASUYA G, et al. Aerodynamic experiment on an ejector-jet[J]. Journal of Propulsion and Power, 2005, 21(3): 496-503. doi: 10.2514/1.6736 [15] HUANG Yakun, HE Xiaomin, JIN Yi, et al. Effect of non-uniform inlet profile on the combustion performance of an afterburner with bluff body[J]. Energy, 2021, 216: 119142. doi: 10.1016/j.energy.2020.119142 [16] FADILAH P A, ERAWAN D F. Effect of applying screen and honeycomb to the flow characteristic in wind tunnel based on CFD simulation[J]. Journal of Physics: Conference Series, 2018, 1130: 012008. doi: 10.1088/1742-6596/1130/1/012008 [17] BARTOSIEWICZ Y, AIDOUN Z, DESEVAUX P, et al. Numerical and experimental investigations on supersonic ejectors[J]. International Journal of Heat and Fluid Flow, 2004, 26(1): 56-70. [18] 黄兴, 陈玉春, 王晓东, 等. 超燃冲压发动机流量匹配机理[J]. 航空动力学报, 2014, 29(4): 852-857. HUANG Xing, CHEN Yuchun, WANG Xiaodong, et al. Mechanism of mass flow matching in scramjet[J]. Journal of Aerospace Power, 2014, 29(4): 852-857. (in ChineseHUANG Xing, CHEN Yuchun, WANG Xiaodong, et al. Mechanism of mass flow matching in scramjet[J]. Journal of Aerospace Power, 2014, 29(4): 852-857. (in Chinese) [19] 陈玉春, 刘小勇, 黄兴, 等. 基于集总参数方程的超燃冲压发动机性能计算模型[J]. 推进技术, 2012, 33(6): 840-846. CHEN Yuchun, LIU Xiaoyong, HUANG Xing, et al. A model based on lumped parameter method for scramjet performance computation[J]. Journal of Propulsion Technology, 2012, 33(6): 840-846. (in ChineseCHEN Yuchun, LIU Xiaoyong, HUANG Xing, et al. A model based on lumped parameter method for scramjet performance computation[J]. Journal of Propulsion Technology, 2012, 33(6): 840-846. (in Chinese) [20] 黄兴, 陈玉春, 李洁, 等. 双模态超燃冲压发动机流量匹配的临界面积法[J]. 航空动力学报, 2013, 28(6): 1305-1312. HUANG Xing, CHEN Yuchun, LI Jie, et al. Critical area method for mass flow matching of dual-mode scramjet[J]. Journal of Aerospace Power, 2013, 28(6): 1305-1312. (in ChineseHUANG Xing, CHEN Yuchun, LI Jie, et al. Critical area method for mass flow matching of dual-mode scramjet[J]. Journal of Aerospace Power, 2013, 28(6): 1305-1312. (in Chinese) [21] 张荣, 叶志锋, 薛益春. 变循环发动机模式转换调节计划仿真研究[J]. 测控技术, 2011, 30(2): 47-50. ZHANG Rong, YE Zhifeng, XUE Yichun. Simulation research on adjustment plan to mode transition of variable cycle engine[J]. Measurement & Control Technology, 2011, 30(2): 47-50. (in ChineseZHANG Rong, YE Zhifeng, XUE Yichun. Simulation research on adjustment plan to mode transition of variable cycle engine[J]. Measurement & Control Technology, 2011, 30(2): 47-50. (in Chinese) [22] 刘润富, 黄玥, 李臻曜, 等. 波瓣结构后可变面积涵道引射器掺混特性[J]. 航空动力学报, 2024, 39(8): 20220594. LIU Runfu, HUANG Yue, LI Zhenyao, et al. Numerical simulation of mixing characteristic of rear variable area bypass injector with lobed structure[J]. Journal of Aerospace Power, 2024, 39(8): 20220594. (in ChineseLIU Runfu, HUANG Yue, LI Zhenyao, et al. Numerical simulation of mixing characteristic of rear variable area bypass injector with lobed structure[J]. Journal of Aerospace Power, 2024, 39(8): 20220594. (in Chinese) [23] 王靖宇, 张怀宝, 黄国平, 等. 采用射流掺混增强的前可调面积涵道引射器数值模拟[J]. 国防科技大学学报, 2019, 41(2): 69-74, 81. WANG Jingyu, ZHANG Huaibao, HUANG Guoping, et al. Numerical investigation of front variable area bypass injector with jet mixing enhancement[J]. Journal of National University of Defense Technology, 2019, 41(2): 69-74, 81. (in ChineseWANG Jingyu, ZHANG Huaibao, HUANG Guoping, et al. Numerical investigation of front variable area bypass injector with jet mixing enhancement[J]. Journal of National University of Defense Technology, 2019, 41(2): 69-74, 81. (in Chinese) [24] 陈佳, 胡文兵, 陈晓文, 等. 前可变面积涵道引射器特性的试验与数值模拟[J]. 航空动力学报, 2020, 35(2): 263-271. CHEN Jia, HU Wenbing, CHEN Xiaowen, et al. Experiment and numerical simulation on characteristic of front variable area bypass injector[J]. Journal of Aerospace Power, 2020, 35(2): 263-271. (in ChineseCHEN Jia, HU Wenbing, CHEN Xiaowen, et al. Experiment and numerical simulation on characteristic of front variable area bypass injector[J]. Journal of Aerospace Power, 2020, 35(2): 263-271. (in Chinese) [25] 雷晗. 带旁路引气的混合扩压器气动特性研究[D]. 南京: 南京航空航天大学, 2019. LEI Han. Study on aerodynamic characteristics of mixer-diffuser with bypass flow[D]. Nanjing: Nanjing University of Aeronautics and Astronautics, 2019. (in ChineseLEI Han. Study on aerodynamic characteristics of mixer-diffuser with bypass flow[D]. Nanjing: Nanjing University of Aeronautics and Astronautics, 2019. (in Chinese) -
点击查看大图
计量
- 文章访问数: 290
- HTML浏览量: 161
- PDF量: 25
- 被引次数: 0