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.