摘要
针对航空发动机润滑系统喷油嘴喷射方向的偏离问题进行研究.首先分析了喷油嘴喷射方向发生偏离的机理,然后通过计算流体动力学(CFD)的方法与软件,建立了喷油嘴喷油过程的三维数值计算模型,对不同入口速度和喷油嘴长径比条件下的喷射方向进行了多组计算与比较,得到了影响喷射方向偏离的因素及其影响规律.研究发现:喷油嘴入口处的径向速度分量导致了喷射方向的偏离,径向速度分量与法向速度分量之比越大,喷油嘴长径比越大,喷射方向偏离程度越大;对已定的喷油嘴入口速度或长径比,能够找到与之匹配的长径比或入口速度,使得喷油方向无偏离.
The jet flow deflection of aero-engine lubrication system was researc deflection mechanism was analyzed firstly. Then a three-dimensional numeric mo nozzle was established based on the method and application of computational fluid hed. The del of the dynamics（CFD）. Then the spray direction with different inlet velocities and nozzle slenderness ratios was computed. Finally, the influential factor of the deflection and its rule were obtained through the comparison of the results. The study found that the radial velocity causeed the deflection of the spray direction. The greater ratios of radial velocity to normal velocity as well as length to diameter, the higher level the deflection. The results also show that the suitable match of inlet velocity and ratio of length to diameter result in no deflection.
出处
《航空动力学报》
EI
CAS
CSCD
北大核心
2012年第7期1665-1670,共6页
Journal of Aerospace Power
基金
航空科学基金(20090451008)
(20090451009)
关键词
喷油嘴
喷射方向
计算流体动力学
入口速度
长径比
oil nozzle
spray direction
computational fluid dynamics
inlet velocity
ratio of length to diameter
