航空燃油离心泵抗汽蚀优化设计及仿真

针对航空燃油离心泵工作时出现的汽蚀问题,采用正交试验法对离心泵叶轮进行优化设计。选取叶轮出口直径D₂、叶轮出口宽度b₂、叶片数Z、叶片厚度H为正交试验的4个因素,完成了正交试验并对试验结果进行极差分析,得到了以泵汽蚀余量为优化指标的影响排序,并最终获得最优参数组合。通过流场仿真对现用离心泵和优化后离心泵的泵汽蚀余量和蒸汽质量分数进行对比,优化后的航空燃油离心泵泵汽蚀余量小于现用离心泵泵汽蚀余量,且蒸汽质量分数降低了19.98%,说明优化后的离心泵抗汽蚀性能显著提高。

Optimization Design and Simulation of Cavitation Resistance of Aviation Fuel Centrifugal Pump

In order to solve the cavitation problem in aviation fuel centrifugal pump,the impeller of centrifugal pump is optimized by orthogonal test.The impeller outlet diameter D₂,the outlet width b₂,the number of blades Z, the blade thickness H are selected as the four factors of the orthogonal experiment.The orthogonal experiment is completed and the range analysis of the test results is carried out.The influence sequence of the pump cavitation allowance as the optimization index is obtained,and the optimal parameter combination is finally obtained.Through flow field simulation to compare the pump cavitation allowance and steam mass fraction of the current centrifugal pump and the optimized centrifugal pump,the optimized jet fuel centrifugal pump's cavitation allowance is less than the current centrifugal pump's cavitation allowance and the steam mass fraction decreases by 19.98%,indicating that the optimized centrifugal pump's cavitation resistance performance is significantly improved.