航空学报2026，Vol.47Issue(11)：102-114,13.DOI:10.7527/S1000-6893.2026.33004
发动机进气道直流喷嘴防冰系统换热特性
Heat transfer characteristics of engine inlet swirl nozzle anti-icing system
摘要
Abstract
To investigate the heat transfer characteristics of impinging jet and annular flow in the aero-engine inlet swirl nozzle anti-icing system,a numerical simulation method is conducted to analyze the coupled internal-external flow and heat transfer within the inlet anti-icing cavity.Dimensionless characteristic parameters are established for evaluating the swirl nozzle anti-icing system performance.The influence of Nozzle Jet Angle(NJA),Nozzle Position(NP),and Nozzle Area Ratio(NAR)on surface temperature distribution and uniformity at the inlet lip are investigated.The regu-lar relationship formula between the average Reynolds number and the Nusselt number was obtained for swirl nozzle anti-icing flow and heat transfer.Results show that:Increasing the hot air jet distance enhances the swirl nozzle anti-icing system performance;changing NJA and NP slightly offset toward the internal flow channel side of the inlet signifi-cantly improves temperature uniformity of the lip.Increasing the area of the orifice which is adjacent to the inlet,im-proves temperature uniformity of the lip but simultaneously raises the risk of overheating of the inlet lip.关键词
发动机进气道/直流喷嘴/防冰系统/换热特性/冲击射流/环形流动Key words
engine inlet/swirl nozzle/anti-icing system/heat transfer characteristics/impinging jet/annular flow分类
航空航天引用本文复制引用
尹金鸽,冯丽娟,邓阳..发动机进气道直流喷嘴防冰系统换热特性[J].航空学报,2026,47(11):102-114,13.基金项目
国家科技重大专项(J2019-Ⅲ-0010-0054) National Science and Technology Major Project of China(J2019-Ⅲ-0010-0054) （J2019-Ⅲ-0010-0054）
