航空发动机支板热滑油防冰性能试验

在冰风洞内开展了结冰条件下涡轴发动机进气支板的热滑油防冰系统的防冰性能试验研究。试验设计加工了滑油电加热系统，采用可编程逻辑控制器（PLC）监控滑油的温度和流量。在冰风洞中采用全尺寸模型开展滑油防冰性能试验，所开展的涡轴发动机支板热滑油防冰试验参数包括：来流温度为-10，-5℃，来流速度为40 m/s，液态水含量为0.5，1.0 g/m³，过冷水滴平均体积直径为20 μm。试验开展了不同结冰气候条件下、不同滑油通道位置滑油防冰进气支板防冰效果的研究，记录了支板表面温度的变化和结冰情况。试验同时得到了支板防冰能力不足时支板表面的结冰冰型和结冰环境下发动机支板热滑油防冰的特点。

Test on Performance of an Aero-engine Strut Hot Lubrication Oil Anti-icing System

An test study on the performance of a hot lubrication oil anti-icing system of an aero-engine strut in an icing tunnel is conducted. The test model is a full-scale inlet strut of a turboshaft engine. In the test, the hot lubrication oil is heated by an electric heater. The temperature and mass flow of the lubrication oil are controlled by a programmable logic controller (PLC) system. The temperature distributions on the strut surface are measured by thermocouples. The icing environment parameters in the icing tunnel for the turboshaft engine strut are: the total temperatures of the free stream are -5℃ and -10℃, the velocity of the free stream is 40 m/s; the liquid water content is 0.5 g/m³ and 1.0 g/m³; the median volumetric diameter of the super-cooled water droplet is 20 μm. The surface temperatures of the strut and the ice shapes accreted on the strut are measured and photographed. The ice shapes are obtained when the capacity of the anti-icing system is insufficient. The characteristics of the hot lubrication oil anti-icing system are also studied under icing conditions.