航空发动机进气支板电热防冰试验

Test on electrothermal anti-icing of aero-engine inlet strut

为了研究电加热防冰的效果,开展了小型航空发动机进气支板的电加热防冰试验。结合该型号发动机进气支板的结构特点,设计了3种电热防冰加热布置方式,分别在支板沿轴向的不同位置采用1~3个电加热棒作为防冰热源。通过模拟不同的发动机进气结冰环境参数和电加热功率,在冰风洞中对3种电加热方式进行了防冰试验研究。通过布置在支板外表面的温度测点记录了防冰过程中支板表面的瞬态温度变化,分析了支板防冰过程中表面温度的变化特点。防冰试验研究了热源总功率、热源布置方式、液态水含量以及来流温度对支板防冰性能的影响。试验结果表明,合理的电加热方式可以取得较好的防冰效果,同时避免支板后部的溢流水结冰。

To study the performance of electrothermal anti-icing,a test on the inlet strut of the small aero-engine is carried out.According to the structural features of this type of aero-engine inlet strut,three heating arrangement modes of the electrothermal anti-icing system are designed,which adopt one to three electrical heating rods as the heat sources at different locations along the direction of the strut chord length.The three heating modes are tested in the icing wind tunnel with different icing environment and electrical heating power.The measuring points are set on the strut surface to record the transient temperature change during the anti-icing process.As a result,the characteristics of temperature change on the strut surface during the anti-icing tests can be analyzed.The effect of the electrothermal power,the heating modes,the liquid water content and the oncoming airflow temperature on the anti-icing performance of the strut are all investigated experimentally.The results show that a reasonable electrical heating mode can achieve better anti-icing performance and the runback ice can be also avoided near the strut tailing edge.