航空发动机进口帽罩结/防冰特性试验研究  

Experimental Research on Icing/Anti-icing Properties 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)

机构地区：[1]中国航发沈阳发动机研究所强度试验研究室,沈阳110015

出　　处：《科学技术与工程》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)。

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.

关 键 词：航空发动机 进口帽罩 冰风洞 结冰 防冰 

分 类 号：V231[航空宇航科学与技术—航空宇航推进理论与工程]