摘要
航空发动机进口帽罩作为发动机重要的进口部件,防冰能力关乎发动机性能甚至影响飞行安全。为了研究航空发动机进口帽罩防冰性能,通过冰风洞对进口帽罩进行结/防冰试验,得到了进口帽罩表面结冰状况随热气流量、来流温度、来流风速的影响规律。试验结果表明:进口帽罩防冰能力从尖锥头部到帽罩后端逐渐增强;帽罩防冰能力随热气流量增加而提升;帽罩表面冰型随来流温度、来流风速变化而发生改变;帽罩表面结冰区域随风速增加而扩大。研究成果可以为进口帽罩防冰系统设计和验证提供重要指导。
Inlet cowl is an important part of aero-engine.Its anti-icing ability relates to engine performance,and even affects flight safety.In order to investigate anti-icing properties of aero-engine inlet cowl,influence of hot-air flow,entrance temperature,entrance velocity on icing condition of inlet cowl was obtained by icing experiment and anti-icing experiment in the icing tunnel.The test results show that the anti-icing capability of the inlet cowl is enhanced from the cone to the end of cowl.The anti-icing effectiveness of the inlet cowl increases with hot-air flow.The inlet cowl s surface ice type varies with entrance temperature and entrance velocity.The icing area of the inlet cowl increases with increasing entrance velocity.The research results have important guidance for the anti-icing system design and verification of aero-engine inlet cowl.
作者
陈竹兵
周澎录
龚欢
王泽宇
宋思泽
CHEN Zhu-bing;ZHOU Peng-lu;GONG Huan;WANG Ze-yu;SONG Si-ze(Department of Strength Test,Shenyang Engineering Research Institute of AECC,Shenyang 110015,China)
出处
《科学技术与工程》
北大核心
2024年第9期3876-3881,共6页
Science Technology and Engineering
基金
国家重大科技专项(J2019-XXXX)。
