摘要
叶型结冰会改变叶型原有的气动外形,影响气动特性。采用FENSAP-ICE软件对NACA0012翼型的结冰进行数值计算,并与试验结果进行对比验证;对压气机进口导叶叶型进行二维结冰计算,并对数值计算结果进行流场分析。结果表明:明冰对叶型的气动性能影响大于毛冰,叶型气动特性的衰退主要受分离区中上分离涡的影响,叶型前缘上翘的明冰引起叶型尾部分离区域面积增大,强烈的分离涡导致结冰后叶型压力损失增大。
The icing of the blade will change its original aerodynamic shape and affect its aerodynamic characteristics.The FENSAP-ICE software is used to compare and verify the numerical calculation results of icing on NACA0012 airfoil with the experimental results.The two-dimensional icing calculation of the compressor inlet guide vane profile is carried out,and the numerical calculation results of flow field are analyzed.The results show that the aerodynamic effect of glaze ice on the blade profile is greater than that of rime ice,the aerodynamic characteristics of the blade profile are mainly affected by the upper separation vortex in the separation zone,the upturned glaze ice on the leading edge of blade profile causes the tailing separation area to expand,and the strong separation vortex can increase the pressure loss of the icing blade profile.
作者
任永鹏
申连洋
王忠义
王艳华
万雷
王松
REN Yongpeng;SHEN Lianyang;WANG Zhongyi;WANG Yanhua;WAN Lei;WANG Song(College of Power and Energy Engineering,Harbin Engineering University,Harbin 150001,China;The Second Military Representative Office of Shenyang Bureau of Marine Equipment in Harbin,Harbin 150001,China)
出处
《航空工程进展》
CSCD
2020年第5期636-644,共9页
Advances in Aeronautical Science and Engineering
基金
国家自然科学基金(51679051)
国家科技重大专项(2017-I-0007-0008,2017-V-0002-0051,2017-V-0012-0064)
黑龙江省优秀青年基金(YQ2019E015)。
