航空发动机风扇和压气机的设计向着高马赫数、高叶尖切线速度的方向发展。高的叶尖相对马赫数会引发严重的激波附面层干扰,而激波与附面层的相互作用和栅后背压的改变对激波的形状和强度影响很大。
在氧枪喷头设计和制定供氧制度时要减小激波损失。
Loss of shock wave should be decreased when design oxygen lance nozzle and oxygen blowing system.
再应用改进了的端壁损失和激波损失模型，最终算出轴流压气机设计点损失沿叶高的分布规律。
Finally, the total loss distribution along the blade span of the axial flow compressor is estimated according to an improved end wall loss model and a shock loss model.
激波总压损失用正激波关系式通过马赫数法向分量估计。
The shock total pressure was estimated with the normal component of the Mach number using normal shock theory.
应用推荐