非轴对称端壁造型在大径向落差长度比压气机中介机匣中的应用  

Application of non-axisymmetric endwall contouring in compressor intermediate duct with a large radius change to length ratio

作　　者：茅晓晨[1,2] 李敏 高丽敏 吴瑜[1,2] MAO Xiaochen;LI Min;GAO Limin;WU Yu(School of Power and Energy,Northwestern Polytechnical University,Xi'an 710072,China;National Key Laboratory of Aerodynamic Design and Research,Northwestern Polytechnical University,Xi'an 710072,China)

机构地区：[1]西北工业大学动力与能源学院,西安710072 [2]西北工业大学翼型、叶栅空气动力学国家级重点实验室,西安710072

出　　处：《空气动力学学报》2024年第11期33-42,I0001,共11页Acta Aerodynamica Sinica

基　　金：国家自然科学基金青年项目(52106057);引智计划(B17037);中央高校基本科研业务费(D5000210483);翼型、叶栅空气动力学国家级重点实验室基金(D5150210006,D5050210015)。

摘　　要：为探索非轴对称端壁造型在大径向落差长度比压气机中介机匣中的应用潜力,采用数值仿真方法研究了该类中介机匣的气动特性,以及轮毂非轴对称端壁造型对中介机匣流动特性和节流特性的影响。结果表明:中介机匣内部流动损失和出口流场畸变主要源于支板角区分离,且均随流体流量的增大而变强,而支板角区分离范围的变化趋势则相反,即随流量的增大而减小。由此,提出一种基于三角函数的非轴对称端壁造型方法,通过改变支板附近轮毂型线的曲率和轴向压力梯度,有效削弱支板角区分离强度,显著改善了中介机匣大流量工作范围内(相对流量不低于0.6)出口流场的畸变强度,使中介机匣总压损失系数降低约6.4%。In order to explore the application potential of non-axisymmetric endwall contouring in the compressor intermediate duct with a large radius change to length ratio,the aerodynamic characteristic of this type of compressor intermediate duct has been numerically studied in the present work,and the effect of the nonaxisymmetric endwall contouring on the hub of the compressor intermediate duct has been investigated in terms of flow and throttle characteristics.The results show that,the flow loss and outlet flow distortion of the compressor intermediate duct are mainly originated from the corner separation of the strut.With the increase of the flow rate,the flow loss and outlet flow distortion are enhanced,which is opposite to the change of the strut corner separation.On this basis,this study has proposed a novel approach for non-axisymmetric endwall contouring using trigonometric functions.By adjusting the curvature of the hub contour near the strut and modifying the axial pressure gradient,this method can effectively reduce the intensity of the corner separation around the strut.Moreover,the implementation of such a non-axisymmetric endwall contouring does not compromise the decreasing trend of the total pressure recovery coefficient with increasing flow rate.Within a wide range of large flow rates(with the relative flow rate not lower than 0.6)in the compressor intermediate duct,this method can successfully attenuate the intensity of secondary flows within the compressor intermediate duct,and reduce the total pressure loss coefficient of the intermediate duct by about 6.4%.

关 键 词：压气机 中介机匣 角区分离 端壁造型 节流特性 

分 类 号：V232[航空宇航科学与技术—航空宇航推进理论与工程]