论文部分内容阅读
在设计超声叶型时,为使得叶栅进口马赫数和气流角等于给定值,提出一种新的叶型参数化方法。该方法以经典唯一进气角计算方法为基础,将超声叶栅的唯一进气角和叶型几何形状关联起来,由进口马赫数和气流角确定吸力面进口段叶型;根据喉部面积、前后缘小圆半径、最大挠度和最大厚度等特征参数确定其他部分叶型。用此参数化方法设计了6个超声叶型,并用Fluent对设计结果进行了验证。结果表明,来流马赫数及进气角的设计值与Fluent求解结果基本一致,进气角最大误差仅为0.7°,进口马赫数最大误差仅为0.01;并且实现了多激波增压和减小激波损失等效果。
In the design of ultrasonic blade, a new parameterization method of blade was proposed in order to make the inlet Mach number and air flow angle equal to a given value. Based on the classical calculation method of single inlet angle, this method correlates the unique inlet angle and the blade geometry of the ultrasonic cascade, and determines the inlet profile of the suction surface by the Mach number and air flow angle. According to the throat area, Before and after the edge of a small radius, maximum deflection and maximum thickness and other characteristics of the parameters to determine the other part of the leaf type. Six ultrasonic blades were designed by this parameterization method, and the design results were verified by Fluent. The results show that the design values of Mach number and inlet angle are basically consistent with the results of Fluent, the maximum error of intake angle is only 0.7 °, the maximum error of inlet Mach number is only 0.01, and the multiple shock pressurization and subtraction Small shock loss and other effects.