蛇形进气道影响下发动机进口部件水撞击特性的数值研究

推进技术 ›› 2016, Vol. 37 ›› Issue (12): 2251-2260.

蛇形进气道影响下发动机进口部件水撞击特性的数值研究

屈靖国,吉洪湖,胡娅萍,陈宁立

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

发布日期:2021-08-15
作者简介:屈靖国，男，硕士生，研究领域为航空发动机积冰。

Numerical Study on Water Droplets Impingement on Aero-Engine Entry Components with a Serpentine Inlet

College of Energy and Power，Nanjing University of Aeronautics and Astronautics，Nanjing 210016，China,College of Energy and Power，Nanjing University of Aeronautics and Astronautics，Nanjing 210016，China,College of Energy and Power，Nanjing University of Aeronautics and Astronautics，Nanjing 210016，China and College of Energy and Power，Nanjing University of Aeronautics and Astronautics，Nanjing 210016，China

Published:2021-08-15

摘要/Abstract

摘要： 为了了解亚声速蛇形进气道影响下航空发动机进口段迎风表面处的水滴撞击特性，采用欧拉/欧拉法对蛇形进气道和发动机进口段在来流马赫数为0.3及环境温度为266.5K的大气结冰条件下进行了空气/过冷水滴两相流场的计算，再由已获得的水滴流场进行支板表面水撞击特性的计算。整流罩表面水滴的撞击计算时采用插值的方法将原两相流场的计算结果插值到新生成的整流罩的近壁网格处，之后采用新生成的整流罩面网格进行水撞击特性的计算。通过计算获得了发动机进口结冰参数、支板以及整流罩表面水收集系数的分布。计算结果表明整流罩和支板表面水滴撞击的主要区域与进气道的弯曲方向有关且位于其下表面一侧，最大水收集系数达到0.98。与之相对比的整流罩和支板其他区域的水收集系数则显得非常微小，在数值上约等于0。此外，对于与进气道对称面平行的竖直支板，其与机匣相交的区域存在水收集系数为0遮蔽区。

关键词: 蛇形进气道；欧拉/欧拉法；发动机进口；支板；整流罩；水撞击

Abstract: In order to get water droplets impinging characteristic on the up-wind surface of aero-engine entry components under the influence of a serpentine inlet，the Eulerian/Eulerian method was taken to calculate the two phase flow field，which was composed of air and super-cooled water，under an atmospheric icing condition of free stream Mach number 0.3 and environmental temperature 266.5K. And then the calculation of water droplets impingement on the surface of the struts was based on the obtained water droplets flow field. Several layers of new grid，to which the previously calculated two phase flow field was interpolated，were generated on the surface of the spinner and then used for its water droplets impingement calculation. The distribution of icing parameters at the aero-engine entry and water collection efficiency on the surface of struts and the spinner were obtained after the calculation was finished. The results show that the location of the main area of water droplets impingement is related to the bending direction of the serpentine inlet and the main area locates on the lower surface of the struts and the spinner and the maximum water collection efficiency on this area reaches 0.98. By contrast，water collection efficiency in other areas of the struts and the spinner is very low and the value approximately equals to zero. In addition，there is a droplets shadowed zone，whose water collection efficiency is zero，around the intersection part between the spinner and the strut which is parallel with the inlet symmetry plane.

Key words: Serpentine inlet；Eulerian/Eulerian method；Aero-engine entry；Struts；Spinner；Water droplets impingement

屈靖国,吉洪湖,胡娅萍,陈宁立. 蛇形进气道影响下发动机进口部件水撞击特性的数值研究[J]. 推进技术, 2016, 37(12): 2251-2260.

QU Jing-guo,JI Hong-hu,HU Ya-ping,CHEN Ning-li. Numerical Study on Water Droplets Impingement on Aero-Engine Entry Components with a Serpentine Inlet[J]. Journal of Propulsion Technology, 2016, 37(12): 2251-2260.

参考文献

[1] Ruff G A, Berkowitz B M. User′s Manual for the NASA Lewice Ice Accretion Prediction Code (LEWICE)[R]. NASA-CR-185129, 1990.
[2] Colin S, Pinella D, Garrison P. Ice Accretion Calculations for a Commercial Ttransport Using the LEWCE3D, ICEGRID3D and CMARC Programs[R]. AIAA 99-0250.
[3] Beaugendre H, Morency F, Habashi W G. ICE3D, FENSAP-ICE′S 3D in Flight Ice Accretion Module[R]. AIAA 2002-0385.
[4] Bourgault Y, Boutanios Z, Habashi W G. Three-Dimensional Eulerian Approach to Droplet Impingement Simulation Using FENSAP-ICE, Part1: Model Algorithm, and Validation[J]. Journal of Aircraft, 2000, 37(1): 95-103.
[5] Croce G, Beaugendre H, Habashi W G. CHT3D: FENSAP-ICE Conjugate Heat Transfer Computations with Droplet Impingement and Runback Effects[R]. AIAA 2002-0386.
[6] Caruso S C. Three-Dimensional Unstructured Mesh Procedure for Iced Wing Flow Field and Droplet Trajectory Calculations [R]. AIAA 94-0486.
[7] 姜玉廷, 郑群, 罗铭聪, 等. 叶片前缘两相流冲击冷却的耦合数值模拟[J]. 推进技术, 2015, 36(3): 443-449. (JIANG Yu-ting, ZHENG Qun, LUO Ming-cong, et al. Conjugate Simulation of Two Phase Flow Impingement Cooling on Blade Leading Edge[J]. Journal of Propulsion Technology, 2015, 36(3): 443-449.)
[8] 吴海燕, 王昱, 孙明波, 等. 超声速混合层液滴两相流动的大涡模拟[J]. 推进技术, 2009, 30(1): 24-29. (WU Hai-yan, WANG Yu, SUN Ming-bo, et al. Large Eddy Simulation of Two-Phase Mixing Layer with Droplets[J]. Journal of Propulsion Technology, 2009, 30(1): 24-29.)
[9] Bourgault Y, Habashi W G, Dompierre J. An Eulerian Approach to Supercooled Droplets Impingement Calculations [R]. AIAA 97-0176.
[10] 刘鑫, 邢玉明, 杜佶. 基于欧拉方法的机翼表面水滴撞击特性数值模拟 [J]. 唐山学院学报, 2014, 27(6): 18-21.
[11] 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.
[12] Al-Khalil K, Hitzigrath R, Philippi O, et al. Icing Analysis and Test of a Business Jet Engine Inlet Duct [R]. AIAA 2000-1040.
[13] Papadakis M, Yeong Hsiung-Wei, Wong See-Cheuk, et al. Comparison of Experimental and Computational Ice Shapes for an Engine Inlet[R]. AIAA 2010-7671.
[14] Nathman J K, McComas A. Icing Collection Efficiency from Direct Simulation [R]. AIAA 2007-505.
[15] 杨倩, 常世楠, 袁修干. 发动机进气道水滴撞击特性分析[J]. 北京航空航天大学学报, 2002, 28(3):363-365.
[16] 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[J]. 北京航空航天大学学报, 2011, 37(1): 2-5.
[17] 胡娅萍, 庞黎刚, 吉洪湖, 等. S型进气道沿程结冰参数变化的数值模拟[J]. 航空动力学, 2014, 29(1):23-30.
[18] 庞黎刚. 异型进气道沿程结冰参数变化的数值分析[D]. 南京:南京航空航天大学, 2010.
[19] 王云. 航空发动机原理[M]. 北京: 北京航空航天大学出版社, 2009. 　　　　　　　　　　　　　*　收稿日期:2015-07-05；修订日期:2015-10-27。作者简介:屈靖国,男,硕士生,研究领域为航空发动机积冰。E-mail: qujingguo53880@126.com(编辑:史亚红)