摘要
采用数值方法对某发动机预旋系统展开三维模拟,研究了叶片供气通道转角处不同几何结构对供气通道气体流动和压力损失的影响。结果表明:预旋系统腔内叶片供气通道转角处结构对压力损失的影响非常大。其中转角处结构为倒圆时压力损失最小,倒角时压力损失次之,直角时压力损失最大。可见改善供气通道结构可增大有效流通面积,使气流更容易流过叶片供气通道。
In order to study the effects of various geometric parameters of the air supply passage on the flow and pressure loss in the passage, three-dimensional numerical simulations were carried out by varying geo- metric parameters on corners of the air supply passage to investigate the pre-swirl system of an engine. Re- sults show that geometric parameters of the blade air supply passage significantly affect pressure loss within the cavity. By increasing effective flow area of the air supply passage, air flows more easily through the pas- sage. Among three kinds of structures of air supply passage corners, round corner has least effect on pres- sure loss, square corner has greatest effect on pressure loss, and the effect of chamfer corner lies between them.
出处
《燃气涡轮试验与研究》
北大核心
2013年第2期50-53,共4页
Gas Turbine Experiment and Research
关键词
航空发动机
涡轮
叶片供气通道
压力损失
流量系数
数值模拟
预旋降温
aero-engine
turbine
blade air supply passage
pressure loss
discharge coefficient
numerical simulation
pre-swirled cooling
