一种可变弯度叶片式旋流畸变发生器设计技术  

Design technology of a variable curvature blade type swirl distortion generator

作　　者：张新雨 屠宝锋[1] 方锐 杨光[1] ZHANG Xinyu;TU Baofeng;FANG Rui;YANG Guang(College of Energy and Power Engineering,Nanjing University of Aeronautics and Astronautics,Nanjing 210016,China)

机构地区：[1]南京航空航天大学能源与动力学院,南京210016

出　　处：《航空动力学报》2022年第9期1957-1969,共13页Journal of Aerospace Power

基　　金：国家科技重大专项(J2019-Ⅴ-0017-0112)。

摘　　要：为了研究进气旋流畸变对压气机性能和稳定性的影响,设计了一种能够产生典型对涡与整体涡可变弯度叶片式旋流畸变发生器。结合正交仿真试验设计方法,分别以对涡旋流强度为优化目标和以对涡旋流强度、整体涡旋流强度和整体涡总压恢复系数为综合优化目标对旋流畸变发生器的几何参数,包括叶片稠度、叶片数量以及轮毂比等进行气动优化设计,并采用CFD数值模拟仿真研究了旋流畸变发生器生成旋流特征。经过单指标优化分析,旋流畸变发生器生成对涡旋流强度最高可达24.60°,整体涡旋流强度最高可达38.73°。经过多指标综合优化,旋流畸变发生器生成对涡和整体涡的总压恢复系数分别提高了4.26%和3.57%。叶片式旋流畸变发生器设计具有结构简单、操作方便、试验周期短等优点,并具有较好的工程应用性。In order to study the effect of inlet swirl distortion on the performance and stability of a compressor, a variable curvature blade type swirl distortion generator capable of producing typical twin swirls and bulk swirls was designed. In combination with the design method of orthogonal simulation test, the geometric parameters of the swirl distortion generator, including blade solidity, number of blades and hub ratio, were optimized with twin swirl intensity as the optimization objective and twin swirl intensity, bulk swirl intensity and bulk swirl total pressure recovery coefficient as the comprehensive optimization objectives,and the CFD numerical simulation was used to study the characteristics of the swirl produced by the generator. Under the single object optimization, the maximum twin swirl intensity was 24. 60°, and the maximum bulk swirl intensity was 38. 73°. After multi-index optimization design,the total pressure recovery coefficient of the twin swirl and the bulk swirl was improved by 4. 26%and 3. 57%, respectively.The design of the variable curvature blade type distortion generator has the advantages of simple structure, convenient operation, short testing time, presenting a favorable engineering application prospect.

关 键 词：旋流畸变 稳定性 正交试验设计 整体涡 对涡 

分 类 号：V231.3[航空宇航科学与技术—航空宇航推进理论与工程]