推进式螺旋桨飞行中桨叶温度测量与尾气防冰性能评估

为研究某推进式布局螺旋桨表面温度分布特性，评估发动机尾气防冰功能，对螺旋桨进行了飞行中的温度测量试验，在桨叶上布置了Pt100热电阻和K型热电偶，通过无线近距遥测系统实现信号传输，测量螺旋桨在不同高度和发动机状态飞行时的表面温度，结果表明桨叶前缘尾气显著影响区温度随半径增加先升高后降低，桨叶最大厚度处温度则随半径增大呈先降低后升高趋势；飞行高度增加会导致桨叶温度显著下降，在同一高度内增大燃气发生器转速可引起桨叶温度小幅升高。根据相关标准和文献得到桨叶表面临界结冰判据，表明在5km螺旋桨防冰功能有效，在7km部分位置存在结冰风险，在8.5km防冰功能完全失效。

In-Flight Blade Temperature Measurement and Exhaust Gas Anti-Icing Performance Evaluation of Pusher Propeller

The blade temperature of a pusher propeller was measured in flight test to acquire temperature distribution characteristics and evaluate the exhaust gas anti-icing performance. Several Pt100 RTD and K-type thermal-couple were placed on the surface of the blade. The sensor signal was transmitted through wireless telemetry system. The surface temperature of the propeller blade was measured under different altitude and engine state during the flight test. The result shows that the temperature of the leading edge area affected significantly by the exhaust gas increases with the increase of radius and then decreases, and the temperature at the maximum thickness of the blade behaves just the opposite. The increase of flight altitude leads to a significant decrease in the temperature of the blade. Increasing the speed of the gas generator at the same altitude results in a slightly temperature rise of the propeller blade. According to the relevant standard and literature, the evaluation principle of critical anti-icing condition was obtained. The assessment shows a complete anti-icing function of at 5km, a partial freezing risk at 7km and a completely failure at 8.5km.