叶片进口边后掠对螺旋离心式航空燃油泵空化性能的影响OA

In order to investigate the influence of blade sweep angle on the cavitation performance of a fuel pump,a specific type of spiral centrifugal fuel pump was taken as the research object,and five impeller models with different sweep angles(θi=20°,40°,60°,80°,100°)were designed.Based on the RANS two-equation model and Zwart cavitation model,the internal flow field simulation was carried out by ANSYS CFX software,and the reliability of the numerical calculation method was veri-fied by comparing the numerical calculation results with the experimental results.The results show that the sweep angle and the relative cavitation coefficient NPSHr*have a cubic function relationship.Fur-thermore,NPSHr* shows a trend of decreasing and then increasing as the sweep angle increases.Under the premise that other design parameters remain unchanged,when the blade inlet edge sweep angle coefficient θ*is 0.32,the NPSHr*of the fuel pump is the minimum at 0.79,and the spiral cen-trifugal fuel pump exhibits the best anti-cavitation performance.To sum up,the blade sweep design can suppress the generation and development of cavitation bubbles of spiral centrifugal aviation fuel pumps.The research results provide a theoretical basis for the optimization of the design of the spiral centrifugal fuel pump.