结冰风洞中液滴相变效应数值模拟

doi:10.7527/S1000-6893.2017.21586

流体力学与飞行力学

本期目录 | 过刊浏览 | 高级检索

前一篇 | 后一篇

结冰风洞中液滴相变效应数值模拟

郭向东^1,2, 王梓旭², 李明², 刘蓓²

1. 中国空气动力研究与发展中心空气动力学国家重点实验室, 绵阳 621000;
2. 中国空气动力研究与发展中心飞行器结冰与防除冰重点实验室, 绵阳 621000

收稿日期:2017-07-06 修回日期:2017-09-21 出版日期:2018-03-15 发布日期:2017-09-21
通讯作者: 郭向东,E-mail:easterkuo@163.com E-mail:easterkuo@163.com
基金资助:
国家"973"计划（2015CB755800）

Numerical investigation of phase transition effects of droplet in icing wind tunnel

GUO Xiangdong^1,2, WANG Zixu², LI Ming², LIU Bei²

1. State Key Laboratory of Aerodynamics, China Aerodynamics Research and Development Center, Mianyang 621000, China;
2. Key Laboratory of Aircraft Icing and Anti/De-Icing, China Aerodynamics Research and Development Center, Mianyang 621000, China

Received:2017-07-06 Revised:2017-09-21 Online:2018-03-15 Published:2017-09-21
Supported by:
National Basic Research Program of China (2015CB755800)

摘要/Abstract

摘要： 为明晰结冰风洞中液滴相变效应，发展了基于Euler法的气液两相传质传热耦合流动计算方法，探索了3 m×2 m结冰风洞主试验段构型相变效应对液滴传热过程的影响，开展了参数影响研究，评估了试验段内液滴过冷状态。结果表明：构型内液滴经历了先蒸发后凝结两个阶段，蒸发效应促进了准一维传热阶段液滴温度的下降趋势，使液滴温度趋于湿球温度，而凝结效应则抑制了三维收缩阶段液滴温度的下降趋势，进而增大了试验段液气温差，影响液滴过冷状态；增大初始相对湿度和试验段气流速度，会导致蒸发效应减弱而凝结效应增强，进而增强了相对湿度和气流速度对液滴过冷状态的影响程度，与此相反，初始液滴尺寸的增加，则会导致蒸发效应和凝结效应均减弱，进而减弱了液滴尺寸对液滴过冷状态的影响程度；在典型工况下，小尺寸液滴（液滴直径范围为40~100 μm）在高风速时（试验段气流速度大于164 m/s）将偏离过冷状态（液气温差超过3℃）。

关键词: 飞机结冰, 结冰风洞, 液滴相变, 过冷, Euler法

Abstract: To understand the phase transition effects of the droplet in an icing wind tunnel, a method based on the Euler theory is developed to simulate mass and heat transfer of coupling of momentum of gas-droplet mixed flows. Using this method, the droplet phase transition effects on the process of the droplet heat transfer are explored for the main test section configuration of a 3 m×2 m icing wind tunnel. Parametric studies are then conducted to evaluate the supercooling state of the droplet in the test section. Results show that the droplets experience firstly evaporation and then condensation in the configuration. The evaporation effects enhance the trend of decrease in the droplet temperature in the quasi-1D stage, and then make the droplet temperature close to the wet-bulb temperature. However, the condensation effects inhibit the trend of decrease in the droplet temperature in the 3D contraction stage, so that the temperature difference between droplet and gas in the test section is increased. As a result, the droplet phase transition has an effect on the supercooling state of the droplet in the test section. In addition, the increased initial relative humidity and test section velocity reduce the evaporation effects, but enhance the condensation effects. Therefore, the effects of relative humidity and test section velocity on the supercooling state of the droplet are enhanced. On the contrary, effects of both evaporation and condensation are reduced, as the initial sizes of the droplet increases. Therefore, the effect of the droplet size on the droplet supercooling is reduced. In typical test conditions, small droplets (the diameter is bigger than 40 μm and smaller than 100 μm) in the center of the test section deviate from the supercooling state (the temperature difference between droplet and gas is higher than 3℃) at the high velocity (the velocity is higher than 164 m/s).

Key words: aircraft icing, icing wind tunnel, droplet phase transition, supercooling, Euler method

中图分类号:

V221.3

郭向东, 王梓旭, 李明, 刘蓓. 结冰风洞中液滴相变效应数值模拟[J]. 航空学报, 2018, 39(3): 121586-121586.

GUO Xiangdong, WANG Zixu, LI Ming, LIU Bei. Numerical investigation of phase transition effects of droplet in icing wind tunnel[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2018, 39(3): 121586-121586.

参考文献

[1] 杜雁霞, 李明, 桂业伟, 等. 飞机结冰热力学行为研究综述[J]. 航空学报, 2017, 38(2):520706. DU Y X,LI M, GUI Y W, et al. Review of thermodynamic behaviors in aircraft icing process[J]. Acta Aeronautica et Astronautica Sinica, 2017, 38(2):520706(in Chinese).
[2] 桂业伟, 周志宏, 李颖晖, 等. 关于飞机结冰的多重安全边界问题[J]. 航空学报, 2017, 38(2):520723. GUI Y W, ZHOU Z H, LI Y H, et al. Multiple safety boundaries protection on aircraft icing[J]. Acta Aeronautica et Astronautica Sinica, 2017, 38(2):520723(in Chinese).
[3] 易贤, 王斌, 李伟斌, 等. 飞机结冰冰形测量方法研究进展[J]. 航空学报, 2017, 38(2):520700. YI X, WANG B, LI W B, et al. Research progress on ice shape measurement approaches for aircraft icing[J]. Acta Aeronautica et Astronautica Sinica, 2017, 38(2):520700(in Chinese).
[4] RAGNI A, ESPOSITO B, MARRAZZO M, et al. Calibration of the CIRA IWT in the high speed configuration[C]//43th AIAA Aerospace Science Meeting and Exhibit. Reston, VA:AIAA, 2005.
[5] STEEN L E, IDE R F, van ZANTE J F, et al. NASA Glenn icing research tunnel:2014 and 2015 cloud calibration procedures and results:NASA/TM-2015-218758[R]. Washington, D. C.:NASA, 2015.
[6] WILLBANKS C E, SCHULZT R J. Analytical study of icing simulation for turbine engines in altitude test cells[J]. Journal of Aircraft, 1975, 12(12):960-967.
[7] MILLER D R, ADDY H E, IDE R F. A study of large droplet ice accretions in the nasa glenn irt at near-freezing conditions:NASA TM-1996-107142-REV1[R]. Washington, D. C.:NASA, 1996.
[8] BELLUCCI M, ESPOSITO B M, MARRAZZO M, et al. Calibration of the CIRA IWT in the low speed configuration[C]//45th AIAA Aerospace Science Meeting and Exhibit. Reston, VA:AIAA,2007.
[9] 易贤, 马洪林, 王开春, 等. 结冰风洞液滴运动及传质传热特性分析[J]. 四川大学学报, 2012, 44(2):132-135. YI X, MA H L, WANG K C, et al. Analysis of water droplet movement and heat/mass transfer in an icing wind tunnel[J]. Journal of Sichuan University, 2012, 44(2):132-135(in Chinese).
[10] 郭向东,王梓旭,李明,等.结冰风洞中液滴过冷特性数值研究[J].航空学报, 2018, 39(1):121254. GUO X D, WANG Z X, LI M, et al. Numerical study of droplet supercooling in an icing wind tunnel[J]. Acta Aeronautica et Astronautica Sinica, 2018, 39(1):121254(in Chinese).
[11] HILL P G. Condensation of water vapor during supersonic expansion in nozzles[J]. Journal of Fluid Mechanics, 1966, 25(3):593-620.
[12] CHENG W, LUO X S, van DONGEN M E H. On condensation-induced waves[J]. Journal of Fluid Mechanics, 2010, 651(1):145-164.
[13] 郭向东, 黄生洪, 吴颖川, 等. 氢燃料燃烧加热风洞中水蒸气相变效应的数值研究[J]. 推进技术, 2017, 38(4):932-941. GUO X D, HUANG S H, WU Y C, et al. Numerical evaluation of water vapor phase transition effects in a hydrogen-fueled combustion-heated wind tunnel[J]. Journal of Propulsion Technology, 2017, 38(4):932-941(in Chinese).
[14] CAO Y, LUO X S. Numerical study on Homogeneous condensation in a vortex[J]. Procedia Engineering, 2015, 126:607-611.
[15] LUO X S, WANG G, OLIVIER H. Parametric investigation of particle acceleration in high enthalpy conical nozzle flows for coating applications[J]. Shock Waves, 2008, 17(5):351-362.
[16] KERSEY J, LOTH E, LANKFORD D. Effects of Evaporating Droplets on Shock Waves[J]. AIAA Journal, 2010, 48(9):1975-1986.
[17] RUSSO E, KUERTEN J G M, van der Geld C W M, et al. Water droplet condensation and evaporation in turbulent channel flow[J]. Journal of Fluid Mechanics, 2014, 749:666-700.
[18] SAITO T. Numerical analysis of dusty-gas flows[J]. Journal of Computational Physics, 2002, 176(1):129-144.
[19] FUJITA A, KUROSE R, KOMORI S. Experimental study on effect of relative humidity on heat transfer of an evaporating water droplet in air flow[J]. International Journal of Heat and Mass Transfer, 2010, 36(3):244-247.
[20] MILLER R S, HARSTAD K, BELLAN J. Evaluation of equilibrium and non-equilibrium evaporation models for many-droplet gas-liquid flow simulations[J]. International Journal of Multiphase Flow, 1998, 24(6):1025-1055.
[21] HINDMARSH J P, RUSSEL A B, CHEN X D. Experimental and numerical analysis of the temperature transition of a suspended freezing water droplet[J]. International Journal of Heat and Mass Transfer, 2003, 46(7):1199-1213.
[22] COBER S, BERNSTEIN B, JECK R, et al. Data and analysis for the development of an engineering standard for supercooled large drop conditions:DOT/FAA/AR-09/10[R]. Washington, D. C.:FAA, 2009.
[23] KUROSE R, FUJITA A, KOMORI S. Effect of relative humidity on heat transfer across the surface of an evaporating water droplet in air flow[J]. Journal of Fluid Mechanics, 2009, 624:57-67.
[24] LUXFORD G. Experimental and modelling investigation of the deformation, drag and break-up of drizzle droplets subjected to strong aerodynamic forces in relation to SLD aircraft icing[D]. Bedfordshire:Cranfield University, 2005:5-7.

E-mail：hkxb@buaa.edu.cn

关于我们

期刊社服务

专业学科

封面文章

友情链接

主管单位：中国科学技术协会主办单位：中国航空学会北京航空航天大学

结冰风洞中液滴相变效应数值模拟

Numerical investigation of phase transition effects of droplet in icing wind tunnel

PDF (PC)

可视化

摘要/Abstract

引用本文

使用本文

参考文献

相关文章 15

编辑推荐

Metrics

本文评价

[1]	熊华杰, 安怡竞, 吴主龙, 周志宏. 欧拉壁膜模型在结冰模拟中的扩展[J]. 航空学报, 2023, 44(S2): 729287-729287.
[2]	杨映麟, 常士楠, 石奇玉, 齐海峰. 气流剪切作用下的水膜实验[J]. 航空学报, 2023, 44(S2): 729290-729290.
[3]	石达志, 桑为民, 李世杰, 安博. 基于LBM的结冰表面水滴撞击特性数值模拟[J]. 航空学报, 2023, 44(S2): 729192-729192.
[4]	许岭松, 吴渊, 朱东宇, 张付昆, 刘昱. FL⁃61结冰风洞翼型俯仰振荡机构研制[J]. 航空学报, 2023, 44(S2): 729296-729296.
[5]	何磊, 钱炜祺, 董康生, 易贤, 柴聪聪. 基于卷积神经网络的结冰翼型气动特性建模[J]. 航空学报, 2023, 44(5): 126434-126434.
[6]	任靖豪, 王强, 李维浩, 刘宇, 易贤. 基于梯度下降的水滴收集率计算方法[J]. 航空学报, 2023, 44(4): 126381-126381.
[7]	陈勇, 孔维梁, 刘洪. 飞机过冷大水滴结冰气象条件运行设计挑战[J]. 航空学报, 2023, 44(1): 626973-626973.
[8]	束珺, 徐东光, 韩志熔, 李斯, 黄雄. 结冰风洞过冷大水滴试验中混合翼设计[J]. 航空学报, 2023, 44(1): 627182-627182.
[9]	牛俊杰, 桑为民, 李栋, 郝莲, 王泽林. 一种基于水滴收集量代理模型的结冰试飞空域确定方法[J]. 航空学报, 2023, 44(1): 627697-627697.
[10]	李浩然, 段玉宇, 张宇飞, 陈海昕. 结冰模拟软件AERO-ICE中的关键数值方法[J]. 航空学报, 2021, 42(S1): 726371-726371.
[11]	郭向东, 柳庆林, 刘森云, 王梓旭, 李明. 结冰风洞中过冷大水滴云雾演化特性数值研究[J]. 航空学报, 2020, 41(8): 123655-123655.
[12]	郭向东, 张平涛, 赵照, 赖庆仁, 郭龙. 大型结冰风洞云雾场适航应用符合性验证[J]. 航空学报, 2020, 41(10): 123879-123879.
[13]	杜雁霞, 肖光明, 张楠, 李伟斌, 王梓旭, 易贤, 桂业伟. 过冷水滴凝固机理及凝固组织特征[J]. 航空学报, 2019, 40(7): 122627-122627.
[14]	魏扬, 徐浩军, 薛源, 郑无计, 李哲, 裴彬彬. 基于神经网络自适应动态逆的结冰飞机飞行安全边界保护方法[J]. 航空学报, 2019, 40(5): 122488-122488.
[15]	雷梦龙, 常士楠, 杨波. 基于Myers模型的三维结冰数值仿真[J]. 航空学报, 2018, 39(9): 121952-121962.