Cooling and infrared radiation characteristics of diversion shielding at exhaust outlet of double-layer mixing duct
-
摘要:
以降低一体化红外抑制器混合管出口导流片温度及其红外辐射强度为目的，设计了双层混合管和带冷却结构的导流器。通过CFD和红外辐射强度空间分布数值仿真，研究了双层混合管强迫冷却进气流量、导流器出口形状和波瓣瓣数对排气喷流和排气混合管红外辐射强度的影响。计算结果表明，双层混合管+导流器结构相较于基准模型（单层混合管，导流片无冷却）可以有效降低导流器可视表面高温区，导流器自身的红外辐射强度降幅可达82.9%；导流器出口的波瓣可以诱导流向涡对，强化冷却气流与混合管出口排气尾流掺混，排气红外辐射强度相对于基准模型最大的降幅可达68.2%，混合管及其排气的总体辐射强度的降幅峰值可达86.4%。排气红外辐射强度以及总体辐射强度均随着波瓣瓣数的减少而逐渐减小，导流器出口过多的波瓣瓣数设计反而不利于流向涡的发展。混合管总体辐射强度随着强迫冷却气流流量的增加而逐渐减小，冷却气流流量与主流流量比值为0.1时，相对于不通冷却气流的情况，总体辐射强度的降幅峰值为68.3%。
Abstract:In order to reduce the temperature and infrared radiation intensity of the diverter at the outlet of the mixing duct of the integrated infrared suppressor, a double mixing duct and a diverter with cooling structure were designed. Through CFD and numerical simulation of the spatial distribution of infrared radiation intensity, the effects of inlet flow rate of forced cooling, outlet shape of deflector and number of valves on the infrared radiation intensity of exhaust jet and exhaust mixing duct were studied. The calculation results showed that compared with the reference model (single-layer mixing duct, no cooling of the deflector), the structure of double-layer mixing duct and deflector can effectively reduce the visible surface high-temperature region of the deflector, and the infrared radiation intensity of the deflector itself can be reduced by 82.9%. The wave disc at the outlet of the deflector can induce streamwise vortex pairs, and the enhanced cooling air can be mixed with the exhaust wake at the outlet of the mixing duct. Compared with the benchmark model, the infrared radiation intensity of the exhaust can drop up to 68.2%, and the overall radiation intensity of the mixing duct and its exhaust can drop up to 86.4%. The exhaust infrared radiation intensity and the overall radiation intensity decreased gradually with the decrease of the number of valves and the excessive number of valves at the outlet of the diverter was not conducive to the development of streamwise vortex. The overall radiation intensity of the mixed duct gradually decreased with the increase of the forced cooling airflow flow rate. When the ratio of the cooling airflow flow rate to the main flow rate was 0.1, the overall radiation intensity decreased by a peak of 68.3% compared with the situation without cooling airflow.
-
图 1 单层混合管+单层导流结构示意图
Figure 1. Schematic diagram of single-layer mixing duct and single-layer diversion structure
图 2 双层混合管强迫冷却进气+导流器结构模型
Figure 2. Structural model of forced cooling inlet and deflector with double mixing duct
图 3 混合管出口段缺口示意图
Figure 3. Schematic diagram of the notch in the outlet section of the mixing duct
图 8 出口温度实验值与数值计算值对比
Figure 8. Comparison between experimental and numerical values of outlet temperature
图 12 混合管出口下游1D截面的温度分布云图
Figure 12. Temperature distribution cloud map of the 1D section downstream of the outlet of the mixing duct
图 13 探测平面3～5 μm波段红外辐射强度（A-0、B-1和C-1模型）
Figure 13. Infrared radiation intensity in 3—5 μm band of detection plane （A-0, B-1 and C-1 models）
图 14 混合管出口下游1D截面的流向涡分布
Figure 14. Streamwise vortex distribution of 1D section downstream of mixing duct outlet
图 15 C-4模型混合管出口下游不同截面的流向涡分布
Figure 15. Streamwise vortex distribution of C-4 model at different sections downstream of the mixing duct outlet
图 16 C-4模型混合管出口下游不同截面的温度分布云图
Figure 16. Temperature distribution of different sections downstream of the C-4 model mixing duct outlet
图 17 混合管出口下游1D截面的温度分布云图
Figure 17. Temperature distribution of the 1D section downstream of the outlet of the mixing duct
图 18 探测平面3～5 μm波段红外辐射强度（C-1、C-2、C-3和C-4模型）
Figure 18. Infrared radiation intensity in the 3—5 μm band of detection plane （C-1, C-2, C-3 and C-4 models）
图 19 不同冷却气流流量下的混合管壁面温度分布
Figure 19. Temperature distribution of mixing duct wall under different cooling airflow
图 20 不同冷却气流流量下的3～5 μm波段红外辐射强度
Figure 20. Infrared radiation intensity in 3—5 μm band at different cooling flow rate
表 1 计算模型特征及其命名
Table 1. Computational model features and naming
模型编号 模型特点 A-0 单层混合管，单层导流（基准模型） B-1 双层混合管，导流器矩形出口 C-1 双层混合管，导流器出口波瓣n=3 C-2 双层混合管，导流器出口波瓣n=5 C-3 双层混合管，导流器出口波瓣n=7 C-4 双层混合管，导流器出口波瓣n=9 
下载: 导出CSV
表 2 不同出口波瓣瓣数的模型引射系数对比
Table 2. Comparison of ejection coefficients of models with different numbers of outlet wave
模型编号 引射系数 C-1 0.864 C-2 0.867 C-3 0.869 C-4 0.871
下载: 导出CSV
-
[1] HEISER W H. Ejector thrust augmentation[J]. Journal of Propulsion and Power,2010,26(6): 1325-1330. doi: 10.2514/1.50144 [2] PATERSON J. Overview of low observable technology and its effects on combat aircraft survivability[J]. Journal of Aircraft,1999,36(2): 380-388. doi: 10.2514/2.2468 [3] RAO G A,MAHULIKAR S P. New criterion for aircraft susceptibility to infrared guided missiles[J]. Aerospace Science and Technology,2005,9(8): 701-712. doi: 10.1016/j.ast.2005.07.005 [4] LI Cui,LI Yanzhong,WANG Lei. Configuration dependence and optimization of the entrainment performance for gas-gas and gas-liquid ejectors[J]. Applied Thermal Engineering,2012,48: 237-248. doi: 10.1016/j.applthermaleng.2011.11.041 [5] HAKKAKI-FARD A,AIDOUN Z,OUZZANE M. A computational methodology for ejector design and performance maximisation[J]. Energy Conversion and Management,2015,105: 1291-1302. doi: 10.1016/j.enconman.2015.08.070 [6] WU Yifei,ZHAO Hongxia,ZHANG Cunquan,et al. Optimization analysis of structure parameters of steam ejector based on CFD and orthogonal test[J]. Energy,2018,151: 79-93. doi: 10.1016/j.energy.2018.03.041 [7] PRESZ W M Jr,MORIN B L,GOUSY R G. Forced mixer lobes in ejector designs[J]. Journal of Propulsion and Power,1988,4(4): 350-355. doi: 10.2514/3.23073 [8] YODER D A,GEORGIADIS N J,WOLTER J D. Quadrant analysis of a mixer-ejector nozzle for supersonic transport applications[J]. Journal of Propulsion and Power,2007,23(1): 250-253. doi: 10.2514/1.25258 [9] BARIK A K,DASH S K,GUHA A. Experimental and numerical investigation of air entrainment into an infrared suppression device[J]. Applied Thermal Engineering,2015,75: 33-44. doi: 10.1016/j.applthermaleng.2014.05.042 [10] LIU Youhong. Experimental and numerical research on high pumping performance mechanism of lobed exhauster-ejector mixer[J]. International Communications in Heat and Mass Transfer,2007,34(2): 197-209. doi: 10.1016/j.icheatmasstransfer.2006.10.003 [11] SHAN Yong,PAN Chengxiong,ZHANG Jingzhou. Investigation on incompressible lobed mixer–ejector performance[J]. Journal of Propulsion and Power,2015,31(1): 265-277. doi: 10.2514/1.B35279 [12] ZHANG Jingzhou,PAN Chengxiong,SHAN Yong. Progress in helicopter infrared signature suppression[J]. Chinese Journal of Aeronautics,2014,27(2): 189-199. doi: 10.1016/j.cja.2014.02.007 [13] PASZKO M. Infrared signature suppression systems in modern military helicopters[J]. Transactions on Aerospace Research,2017,2017(3): 63-83. doi: 10.2478/tar-2017-0022 [14] 单勇,张靖周. 弯曲混合管引射系统引射-混合特性数值研究[J]. 南京航空航天大学学报,2008,40(2): 137-141. SHAN Yong,ZHANG Jingzhou. Numerical computation for pumping and mixing performance on mixer-ejector with curved mixing duct[J]. Journal of Nanjing University of Aeronautics and Astronautics,2008,40(2): 137-141. (in ChineseSHAN Yong, ZHANG Jingzhou. Numerical computation for pumping and mixing performance on mixer-ejector with curved mixing duct[J]. Journal of Nanjing University of Aeronautics and Astronautics, 2008, 40(2): 137-141. (in Chinese) [15] MAQSOOD A,BIRK A M. Improving the performance of a bent ejector with inlet swirl[J]. Journal of Engineering for Gas Turbines and Power,2008,130(6): 061201.1-061201.9. [16] PAN Chengxiong,SHAN Yong,ZHANG Jingzhou. Parametric effects on internal aerodynamics of lobed mixer-ejector with curved mixing duct[J]. Journal of Engineering for Gas Turbines and Power,2014,136(6): 061504.1-061504.10. [17] ZHOU Zeyang,HUANG Jun,WANG Jinjun. Radar/infrared integrated stealth optimization design of helicopter engine intake and exhaust system[J]. Aerospace Science and Technology,2019,95: 105483.1-105483.13. [18] 唐正府,张靖周,单勇. 波瓣喷管-狭长出口弯曲混合管引射混合特性分析[J]. 航空动力学报,2005,20(6): 978-982. TANG Zhengfu,ZHANG Jingzhou,SHAN Yong. Investigation on ejecting and mixing characteristics of lobed nozzle with curved mixing duct and slot exit[J]. Journal of Aerospace Power,2005,20(6): 978-982. (in ChineseTANG Zhengfu, ZHANG Jingzhou, SHAN Yong. Investigation on ejecting and mixing characteristics of lobed nozzle with curved mixing duct and slot exit[J]. Journal of Aerospace Power, 2005, 20(6): 978-982. (in Chinese) [19] 蒋坤宏,张靖周,单勇,等. 一体化红外抑制器遮挡和出口修型对后机身表面温度和红外辐射特性的影响[J]. 航空学报,2020,41(2): 123497. JIANG Kunhong,ZHANG Jingzhou,SHAN Yong,et al. Effects of sheltering and outlet shaping on surface temperature and infrared radiation characteristics of rear airframe with an integrating infrared suppressor[J]. Acta Aeronautica et Astronautica Sinica,2020,41(2): 123497. (in ChineseJIANG Kunhong, ZHANG Jingzhou, SHAN Yong, et al. Effects of sheltering and outlet shaping on surface temperature and infrared radiation characteristics of rear airframe with an integrating infrared suppressor[J]. Acta Aeronautica et Astronautica Sinica, 2020, 41(2): 123497. (in Chinese) [20] 郑禛,张靖周. 导流片对大形状比出口弯曲混合管引射性能影响的数值研究[J]. 南京航空航天大学学报,2020,52(4): 540-547. ZHENG Zhen,ZHANG Jingzhou. Numerical study on effects of guide baffles on pumping performance of curved mixing duct with a large-aspect-ratio outlet[J]. Journal of Nanjing University of Aeronautics and Astronautics,2020,52(4): 540-547. (in ChineseZHENG Zhen, ZHANG Jingzhou. Numerical study on effects of guide baffles on pumping performance of curved mixing duct with a large-aspect-ratio outlet[J]. Journal of Nanjing University of Aeronautics and Astronautics, 2020, 52(4): 540-547. (in Chinese) [21] 任利锋,张靖周,王先炜,等. 直升机后机身内埋式红外抑制器隐身性能分析[J]. 红外与激光工程,2011,40(11): 2091-2097. REN Lifeng,ZHANG Jingzhou,WANG Xianwei,et al. Analysis of stealth properties on IR radiation suppressor embed inside helicopter rear airframe[J]. Infrared and Laser Engineering,2011,40(11): 2091-2097. (in ChineseREN Lifeng, ZHANG Jingzhou, WANG Xianwei, et al. Analysis of stealth properties on IR radiation suppressor embed inside helicopter rear airframe[J]. Infrared and Laser Engineering, 2011, 40(11): 2091-2097. (in Chinese) [22] YANG Zongyao,ZHANG Jingzhou,SHAN Yong. Effects of forward-flight speed on plume flow and infrared radiation of IRS-integrating helicopter[J]. Chinese Journal of Aeronautics,2022,35(3): 155-168. doi: 10.1016/j.cja.2021.07.037 [23] YANG Zongyao,ZHANG Jingzhou,SHAN Yong. Research on the influence of integrated infrared suppressor exhaust angle on exhaust plume and helicopter infrared radiation[J]. Aerospace Science and Technology,2021,118: 107013.1-107013.23. -
点击查看大图
计量
- 文章访问数: 51
- HTML浏览量: 38
- PDF量: 15
- 被引次数: 0