最大厚度位置对高亚音轴流压气机叶型设计的影响

为了在具有不同负荷的压气机叶栅的初始设计过程中选取最大厚度位置,采用数值方法对在不同折转角的高亚音来流条件下对扩压叶栅进行了大量的系统性研究,分析了最大厚度位置、折转角以及稠度3个叶栅几何参数对叶栅变冲角特性以及对最小损失冲角下的叶栅气动性能的影响规律.基于大量叶栅样本建立数学模型,用来定量描述最小损失冲角,以及最小损...

Effect of Maximum Thickness Location on High Subsonic Axial Compressor Airfoil Design

In order to select the maximum thickness position in the initial design process of compressor cascade at different loads, a large number of systematic studies for compressor cascades with different turning angles under high subsonic inlet flow conditions were carried out by numerical method,the influence rules of three cascade geometric parameters of the maximum thickness position, turning angle and consistency on the characteristics of cascade varying angle of attack and the cascade aerodynamic performance at minimum loss angle of attack were analyzed.Based on lots of cascade samples, the mathematical model was established to quantitatively describe the dependence rule between the aerodynamic performance parameters, such as the minimum loss angle of attack, the total pressure loss coefficient at the minimum loss angle of attack and the diffusion factor, and the geometric parameters of the cascade.Based on the mathematical model,the dependence relationship graphs of performance parameters were drawn, and the loss and gain caused by changing the maximum thickness position were analyzed.The optimal selection maps of the maximum thickness position under different design conditions were given, so as to provide reliable profile reference data for high load cascade design. The results show that the selection of maximum thickness position has significant impact on the blade profile design of high load compressor cascade, the optimal maximum thickness position is located in 20% to 35% relative chord length. With the increase of turning angle and cascade diffusion degree, the optimal position of maximum thickness moves forward, and the induced loss gain is increased significantly.