基于分流叶片技术的离心式航空燃油泵优化设计

Optimum design of centrifugal aviation fuel pump based on splitter blades technology

为了优化提升离心式航空燃油泵空化性能,在原有常规设计叶片的基础上,采用分流叶片技术与叶片前伸设计2种叶轮模型,分别为叶片前伸头部后掠与叶片前伸头部直线。基于RNG k-ε湍流模型与ZGB空化模型分别数值计算了1800~10400 L/h流量范围下6个工况的离心式航空燃油泵单相定常与空化流场。结果表明,采用大包角长叶片的分流叶片可提高离心式航空燃油泵全流量范围内扬程,且性能曲线较平坦;1800 L/h小流量工况下3种模型效率分别为32.85%、29.52%和31.86%,7600 L/h小流量及10400 L/h额定流量工况下叶片前伸头部后掠效率比其他2种模型效率低4%;叶片前伸头部后掠与叶片前伸头部直线性能优于常规叶片空化性能。分析结果为离心式航空燃油泵的空化流动控制、效率提升提供了理论依据。

To optimize the cavitation performance of centrifugal aviation fuel pump,splitter blades and forward blades technologies were adopted to design two different impellers based on the conventional designed blades.The two optimized impellers with forward blades were sweepback and straight line respectively.The single phase steady and cavitation flows of 6 points between 1800 L/h and 10400 L/h were simulated with RNG k-εturbulence model and ZGB cavitation model.The results show that the new impellers with splitter blades can improve the head in the full flow range of centrifugal aviation fuel pump and make the performance curve flat.Under the small flow rate of 1800 L/h,the efficiency values of the three models are 32.85%,29.52%and 31.86%respectively.The efficiency value of blade forward extension and head sweep of 7600 L/h low flow rate and rated conditions of 10400 L/h is 4%lower than that of the other two models.The cavitation performances of the optimized models are better than that of the conventional blades.The paper can provide a theoretical basis for cavitation flow control and efficiency improvement of centrifugal pump.