发动机进气道短舱前缘结冰三维模拟研究
收稿日期: 2012-04-09
修回日期: 2012-06-12
网络出版日期: 2013-03-29
基金资助
"凡舟"青年科研基金(20110503)
Three-dimensional Simulation Research on Ice Shape at Engine Inlet Nacelle Front
Received date: 2012-04-09
Revised date: 2012-06-12
Online published: 2013-03-29
Supported by
"FanZhou" Youth Scientific Funds (20110503)
为计算发动机进气道短舱前缘的结冰冰形,在Messinger结冰热力学模型的基础上发展了一套纯三维的表面溢流水流动结冰模型。考虑空气摩擦力为表面溢流水流动的主要驱动力,用空气对进气道表面的剪切力来确定溢流水的流动方向及流量分配。为求解溢流水结冰模型,发展了一套重复查找表面控制体状态的方法,能够快速完成整个三维表面的计算。用该方法对某三维发动机进气道进行计算,得到了三维结冰冰形,并将计算结果与FENSAP-ICE计算结果进行了对比,结果显示两者的冰形轮廓基本一致,仅在冰角处存在差异,表明本文三维发动机结冰计算模型与计算方法是有效的,其计算精度与FENSAP-ICE结果相当。
申晓斌 , 林贵平 , 卜雪琴 , 郁嘉 , 侯盼雪 . 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 . DOI: 10.7527/S1000-6893.2013.0087
To simulate the ice shape at an engine inlet nacelle front, a pure three-dimensional ice accretion model based on Messinger's thermodynamic model is established, which took the surface runback water stream into consideration. Regarding the air friction as the main factor to drive the surface runback water stream, the shear force of the inlet surface is used to determine the direction and flow distribution of the runback water. To solve the ice accretion model of the water film, an approach of repeatedly searching the surface control volume condition is developed, which could achieve the calculation of the whole three-dimensional surface. Ice accretion calculation of a certain three-dimensional engine inlet is carried out, and the three-dimensional ice shapes are obtained. Comparison between the computational results and FESAP-ICE results indicates that the ice profiles of both methods are coincident approximately except for the difference at the ice horn location. The comparison results confirm the validity of the three-dimensional engine ice accretion model and the computational method, and the precision of the results is almost the same as that of the FENSAP-ICE software.
Key words： engine; three-dimensional simulation; ice shape; runback water; thermodynamic model
[1] Qiu X G, Han F H. Aircraft anti-icing system. Beijing: Compilation and Examination Group of Aero Specialized Teaching Materials, 1985. (in Chinese) 裘燮纲, 韩凤华. 飞机防冰系统. 北京: 航空专业教材编审组, 1985.
[2] Al-Khalil K M, Keith T G, Jr, De Witt K J. Icing calculations on a typical commercial jet engine inlet nacelle. Journal of Aircraft, 1997, 34(1): 87-93.
[3] Bidwell C S, Mohler S R. Collection efficiency and ice accretion calculations for a sphere, a swept MS(1)-317 wing, a swept NACA-0012 wing tip, an axisymmetric inlet, and a Boeing 737-300 inlet. AIAA-1995-755, 1995.
[4] Al-Khalil K, Hitzigratht R, Philippit O, et al. Icing analysis and test of a business jet engine inlet duct. AIAA-2000-1040, 2000.
[5] Schuster E P, Gambill J M, Fisher M S. Computational icing analysis of aircraft inlets. AIAA-1992-3178, 1992.
[6] Bidwell C S, Potapczuk M G. Users manual for the NASA lewis three-dimensional ice accretion code (LEWICE3D). NASA TM-105974, 1993.
[7] Beaugendre H, Morency F, Habashi W G. ICE3D, FENSAP-ICE'S 3D in-flight ice accretion module. AIAA-2002-0385, 2002.
[8] Papadakis M. Comparison of experimental and computational ice shapes for an engine inlet. AIAA-2010-7671, 2010.
[9] Newmerical Technologies Int. FENSAP-ICE 2011 manual. Canada: Newmerical Technologies Int., 2011.
[10] Yi X, Gui Y W, Zhu G L. Numerical method of a three-dimensional ice accretion model of aircraft. Acta Aeronautica et Astronautica Sinica, 2010, 31(11): 2152-2158. (in Chinese) 易贤, 桂业伟, 朱国林. 飞机三维结冰模型及其数值求解方法. 航空学报, 2010, 31(11): 2152-2158.
[11] Chang S N, Su X M, Qiu Y F. Ice accretion simulation on three dimensional wings. Acta Aeronautica et Astronautica Sinica, 2011, 32(2): 212-222. (in Chinese) 常士楠, 苏新明, 邱义芬.三维机翼结冰模拟. 航空学报, 2011, 32(2): 212-222.
[12] Hu Y P. Numerical simulation of ice accretion on aero-engine entry components. Nanjing: College of Energy and Power Engineering, Nanjing University of Aeronautics and Astronautics, 2008. (in Chinese) 胡娅萍. 航空发动机进口部件积冰的数值模拟研究. 南京: 南京航空航天大学能源与动力学院, 2008.
[13] Yang S H, Lin G P. Numerical simulation of ice accretion on airfoils. Journal of Aerospace Power, 2011, 26(2): 323-330. (in Chinese) 杨胜华, 林贵平. 机翼结冰过程的数值模拟. 航空动力学报, 2011, 26(2): 323-330.
[14] Yang S H. Two-dimensional in-flight ice accretion simulation. Beijing: School of Aeronautic Science and Engineering, Beihang University, 2010. (in Chinese) 杨胜华. 二维飞机结冰过程仿真. 北京: 北京航空航天大学航空科学与工程学院, 2010.
[15] ANSYS Inc. ANSYS fluent 12.0 UDF manual. New Hapmpshire: ANSYS Inc., 2009.
[16] Shen X B, Lin G P, Yang S H. Analysis on three dimensional water droplets impingement characteristics of engine inlet. Journal of Beijing University of Aeronautics and Astronautics, 2011, 31(1): 1-5.(in Chinese) 申晓斌, 林贵平, 杨胜华. 三维发动机进气道水滴撞击特性分析. 北京航空航天大学学报, 2011, 31(1): 1-5.
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