摘要
为了研究离心式航空燃油泵空化流场特性,基于RNG k-ε湍流模型与ZGB空化模型,对某带诱导轮的离心式航空燃油泵三维内流场进行了数值计算,分析了诱导轮与离心叶轮叶片表面的空化区演变、燃油泵内部不同过流部件中的空泡区占比、叶顶泄漏涡空化、回流涡空化等流动现象。结果表明,诱导轮对空化的抑制有积极作用,三种不同工况下的空化余量NPSH值一样;诱导轮叶片表面的空化包括叶顶空化、云空化、叶梢空化等不同类型;空化数σ=0.0953时为临界空化点,诱导轮与叶轮区的空泡体积占5%~10%;回流涡空化首先产生于诱导轮叶顶背面附近,随着空化数的降低,回流涡空化区逐步与云空化融合;无论有无空化,燃油泵进口段始终存在明显的二次流。
In order to study the cavitation flow field characteristics of centrifugal aviation fuel pump,the three-dimensional internal flow field of a centrifugal aviation fuel pump with inducer was numerically calculated by RNG k-εturbulence model and ZGB cavitation model.The flow phenomena such as the evolution of cavitation zone on the blade surface of inducer and centrifugal impeller,the proportion of cavitation zone in different flow passage parts in the fuel pump,tip leakage vortex cavitation and back flow vortex cavitation are analyzed.The results show that the inducer has a positive effect on cavitation suppression,and the NPSH value of cavitation allowance is the same under three different working conditions.The cavitation of inducer blade surface includes tip cavitation,cloud cavitation,tip cavitation and so on.Cavitation numberσ=0.0953 is the critical cavitation point and the cavitation volume in the inducer and impeller area accounts for 5%~10%.The back flow vortex cavitation first occurs near the top and back of the inducer blade.With the decrease of the cavitation number,the back flow vortex cavitation area gradually merges with the cloud cavitation.No matter there is cavitation or not,there is always obvious secondary flow in the inlet section of the fuel pump.
作者
罗丹
王维军
赵鑫
谭向军
吴大转
Dan Luo;Wei-jun Wang;Xin Zhao;Xiang-jun Tan;Da-zhuan Wu(AVIC Chengdu Caic Electronics Co.,Ltd.;College of Energy Engineering,Zhejiang University)
出处
《风机技术》
2022年第6期22-27,共6页
Chinese Journal of Turbomachinery
基金
流体机械及工程四川省重点实验室(西华大学)开放课题资助(szjj2019-029)
航空工业成都凯天电子股份有限公司预研项目(Y2049、Y2173)。
关键词
航空燃油泵
空化
诱导轮
泄漏涡
二次流
Aviation Fuel Pump
Cavitation
Inducer
Leakage Vortex
Secondary Flow
