航空发动机液压管路静压力损失分析及试验验证

液压机械装置(HMU)燃油管路的设计是否合理将直接影响到油液静压力的传递损失和各液压元件的工作特性.为了研究燃油管路内部流动损失机理,验证相关计算方法的置信度,针对典型管路静压力损失,采用锐边节流公式和短管节流公式进行了理论计算,并进行了CFD仿真分析,对计算结果进行了试验验证.计算与试验结果对比分析表明:液流的静压力损失主要出现在进口环腔与管路的交界处,管路下游液流的静压力与出口环腔内一致;锐边节流公式的计算结果相对偏大,而短管节流公式的计算结果更接近于试验值.

Investigation and Experimental Validation on Static Pressure Loss of Aeroengine Hydraulic Pipe

Design of fuel pipe have direct effect on the transmission loss of static pressure and the performance of hydraulic components for aeroengine Hydro-Mechanical Unit (HMU) . In order to investigate the pressure loss mechanism and validate the confidence coefficient of relative numerical methods, the static pressure loss of a typical fuel pipe was calculated with the sharp edge throttle formula, the stub pipe throttle formula and CFD numerical simulation. Finally, experiments were conducted to verify the calculation results. Results indicate that the static pressure loss mainly exits at the junction between inlet cavity and pipe, and downstream of the pipe has the same static pressure with the outlet cavity. The shape edge throttle formula predicts a higher static pressure loss while the results of stub pipe throttle formula have a better agreement with the experiment results.