Numerical Investigationon GlazeIce Accretionwith Evaporationof WaterFilm

Journal of Propulsion Technology ›› 2018, Vol. 39 ›› Issue (7): 1540-1548.

• Combustion , Heat and Mass Transfer • Previous Articles Next Articles

Numerical Investigationon GlazeIce Accretionwith Evaporationof WaterFilm

College of Energy and Power Engineer，Nanjing University of Aeronautics and Astronautics，Nanjing 210016，China,College of Energy and Power Engineer，Nanjing University of Aeronautics and Astronautics，Nanjing 210016，China,Research Institute of Unmanned Aircraft，Nanjing University of Aeronautics and Astronautics，Nanjing 210016，China and College of Energy and Power Engineer，Nanjing University of Aeronautics and Astronautics，Nanjing 210016，China

Published:2021-08-15

考虑水膜蒸发的三维明冰积冰数值研究 *

苏长明¹,胡娅萍¹,曹广州²,吉洪湖¹

南京航空航天大学能源与动力学院，江苏南京 210016,南京航空航天大学能源与动力学院，江苏南京 210016,南京航空航天大学无人机研究院，江苏南京 210016,南京航空航天大学能源与动力学院，江苏南京 210016

作者简介:苏长明，男，硕士生，研究领域为飞机防冰结冰。
基金资助:
国家自然科学基金( 51506084)；江苏省自然科学基金( BK20150740)。

Abstract

Abstract: In the process of glaze ice accretion，the ice surface will be covered with a thin water film. The water film on the surface of the ice can flow and heat transfer，water film evaporation can cause mass and energy transfer，which has an effect on the ice phase change. In order to study the effects of water evaporation on ice ac. cretion，a three-dimensional mathematical model considering the water film evaporation on the process of glazeice accretion has been established，which is based on the existing three-dimensional ice model，and the corre. sponding icing code has been developed. A typical examples provided by NASA，simulating the ice accretion of NACA0012 airfoil under the glaze ice accretion conditions is selected in this paper，and the results of calculation with NASA test and the simulation results are compared. The results show that the average evaporation of waterfilm is 1.5g/(m2·s)，and that the heat absorbed by evaporation accounts for 35% of the total heat transfer. Com.pared with the calculation results that without considering the water film evaporation，the ice volume and ice shape obtained in this paper are in good agreement with the experimental results. So it is necessary and reason.able to consider water film evaporation in 3D ice accretion simulation.

Key words: Water film evaporation；Glaze ice accretion；Ice model；Ice shape

摘要： 明冰积冰过程中冰层表面会覆盖一层薄水膜，水膜在冰层表面流动和传热，水膜蒸发会引起质量和能量传递，对积冰相变产生影响。为了研究水膜蒸发对积冰的影响，在已有三维积冰模型的基础上，考虑了明冰积冰过程中水膜的蒸发，建立了考虑水膜蒸发的三维积冰数学模型，并开发了相应的积冰计算程序。选取 NASA提供的典型算例，模拟了明冰积冰条件下 NACA0012翼型的积冰过程，并将计算结果与 NASA试验和数值结果进行对比。结果表明水膜的平均蒸发量为 1.5g/(m2·s)，蒸发吸收的热量占总传热的 35%。与不考虑水膜蒸发的计算结果相比，本文得到的积冰量和冰形都与试验结果具有更好的一致性，说明三维明冰计算中考虑水膜蒸发是有必要和合理的。

关键词: 水膜蒸发；明冰积冰；积冰模型；冰形

SU Chang-ming¹,HU Ya-ping¹,CAO Guang-zhou²,JI Hong-hu¹. Numerical Investigationon GlazeIce Accretionwith Evaporationof WaterFilm[J]. Journal of Propulsion Technology, 2018, 39(7): 1540-1548.

苏长明,胡娅萍,曹广州,吉洪湖. 考虑水膜蒸发的三维明冰积冰数值研究 *[J]. 推进技术, 2018, 39(7): 1540-1548.

References

[1] Lynch F T,Khodadoust A.Effects of Ice Accretions on Aircraft Aerodynamics[J].Progress in Aerospace Sci.ence,2001,37(8): 669-767.
[2] Cole J A,Sand W R.Statistical Study of Aircraft Icing Accidents[R].AIAA 91-0558.
[3] Brumby R E.The Effect of Wing Ice Contamination onEssential Flight Characteristics[R].AGARD-CP-496.1991.
[4] 胡娅萍 .航空发动机进口部件积冰的数值模拟研究[D].南京:南京航空航天大学, 2009.
[5] 易贤 .飞机积冰的数值计算与积冰试验相似准则研究[ D].绵阳:中国空气动力学研究与发展中心, 2007.
[6] 裘燮刚,韩凤华 .飞机防冰系统[ M].北京:航空专业教材编审组, 1996.
[7] Messinger B L.Equilibrium Temperature of an Unheat.ed Icing Surface as a Function of Airspeed[J].Journal of Aeronautical Science,1953,20(1): 29-42.
[8] Ruff G A,Berkowitz B M.User's Manual for the NASA Lewice Ice Accretion Prediction Code(LEWICE)[ R].NASA-CR-185129,1990.
[9] Wright W B,Gent R W,Guffond D.DRA/NASA/ONE.RA Collaboration on Icing Research Part Ⅱ -Prediction of Airfoil Ice Accretion[R].NASA-CR-202349,1997.
[10] Hedde T,Guffond D.Development of a Three-Dimen.sional Icing Code, Comparison with Experimental Shapes[R].AIAA 92-0041.
[11] Bourgault Y,Habashi W G,Beaugendre H.Develop.ment of a Shallow Water Icing Model in FENSAP-ICE[R].AIAA 99-0246.
[12] Beaugendre H, Morency F, Habashi W G.ICE3D, FENSAP -ICE's 3D In -Flight Ice Acccretion Moduler[R].AIAA 2002-0385.
[13] 易贤,桂业伟,朱国林 .飞机三维结冰模型及其数值求解方法[ J].航空学报, 2010,31(11).
[14] 常士楠,苏新明,邱义芬 .三维机翼结冰模拟[ J].航空学报, 2011,32(2).
[15] 申晓斌,林贵平,卜雪琴,等 .发动机进气道短舱前缘结冰三维模拟研究[ J].航空学报, 2013,34(3): 517-524.
[16] 曹广州 .迎风表面三维积冰的数学模型与计算方法研究[ D].南京:南京航空航天大学, 2011.
[17] 曹广州,吉洪湖 .模拟飞机迎风面三维积冰的数学模型[ J].航空动力学报, 2011,26(9): 1953-1963.
[18] 曹广州,吉洪湖,斯仁 .迎风面三维积冰过程中水膜流动的计算方法[ J].航空动力学报, 2015,30(3): 0677-0685.
[19] 张丽芬,刘振侠,张斐,等 .航空发动机旋转帽罩结冰表面换热系数研究[ J].推进技术, 2017,38(4).(ZHANG Li -fen,LIU Zhen-xia,ZHANG Fei,et al.Numerical Simulation of Heat Transfer Coefficient on Ic.ing Surface of Rotating Cone in Aero-Engine[J].Jour.nal of Propulsion Technology,2017,38(4).)
[20] 屈靖国,吉洪湖,胡娅萍,等 .蛇形进气道影响下发动机进口部件[ J].推进技术, 2016,37(12).(QU Jing-guo,JI Hong-hu,HU Ya-ping,et.al.Numeri.cal Study on Water Droplets Impingement on Aero-En.gine Entry Components with a Serpentine Inlet[J].Jour.nal of Propulsion Technology,2016,37(12).)
[21] 卜雪琴,林贵平 .基于 CFD的水收集系数及防冰表面温度预测[ J].北京航空航天大学学报, 2007,33(10): 3810-3813.
[22] 王福军 .计算流体动力学分析[ M].北京:清华大学出版社, 2004.
[23] Versteeg H K, Malalasekera W.An Introduction to Computational Fluid Dynamics: The Finite Volume Method[M].New York: Wiley,1995.
[24] Shin J,Bond T H.Results of an Icing Test on a NA.CA0012 Airfoil in the NASA Lewis Icing Research Tun.nel[R].AIAA 92-0647.
[25] Shin J,Bond T H.Experimental and Computational IceShapes and Resulting Drag Increase for a NACA0012Airfoil[R].NASA-TM-105743,1992.* 收稿日期: 2017-06-21；修订日期: 2017-07-07。基金项目:国家自然科学基金( 51506084)；江苏省自然科学基金( BK20150740)。作者简介:苏长明,男,硕士生,研究领域为飞机防冰结冰。 E-mail:sucm235@126.com (编辑:梅瑛)

Numerical Investigationon GlazeIce Accretionwith Evaporationof WaterFilm

考虑水膜蒸发的三维明冰积冰数值研究 *

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