亚声速压气机平面叶栅风洞标准模型建立  

Establishment of standard model of linear cascade wind tunnel for subsonic compressor

作　　者：蔡明 高丽敏[1] 李瑞宇[1] 欧阳波 刘波[1] CAI Ming;GAO Limin;LI Ruiyu;OUYANG Bo;LIU Bo(School of Power and Energy,Northwestern Polytechnical University,Xi’an 710129,China;AVIC The First Aircraft Institute,Xi’an 710089,China)

机构地区：[1]西北工业大学动力与能源学院,西安710129 [2]航空工业第一飞机设计研究院,西安710089

出　　处：《航空学报》2025年第2期114-131,共18页Acta Aeronautica et Astronautica Sinica

基　　金：国家自然科学基金(92152301);国家科技重大专项(2017-Ⅱ-0001-0013)。

摘　　要：平面叶栅风洞标模是轴流压气机设计体系建设以及推动平面叶栅试验技术标准化的关键。基于西北工业大学平面叶栅风洞完成了具有典型亚声速可控扩散叶型的压气机标模叶栅的设计和试验。采用自主建立的流场品质综合调控系统保证了标模叶栅的来流准确性、流场周期性以及展向二维性,在此基础上获取了标模叶栅的进气角特性、轴向密流比特性、叶片表面等熵马赫数分布以及叶栅尾迹分布,并与德国宇航院风洞公开的参考叶栅数据进行了对比。研究表明:标模叶栅流场周期性和准确性良好,具有4个连续通道的进口均匀区域和2个连续通道的出口周期性区域;测量通道的进口马赫数偏差不超过0.005,轴向密流比偏差不超过0.02;出口气流的周期性指数不超过2。与参考叶栅数据的对比表明,设计马赫数0.62下,标模叶栅和参考叶栅的损失、出气角、静压比随进气角的变化趋势基本一致。由于出口测量位置差异导致标模叶栅的损失和出气角较参考叶栅偏大,但静压比基本相同;2套叶栅的叶片表面等熵马赫数分布高度一致。总体而言,建立的标模叶栅试验数据全面、可靠性高。The standard model for linear cascade wind tunnel is the key to the construction of axial compressor design system and the standardization of linear cascade testing technique.The standard model of compressor cascade with a typical controlled diffusion airfoil is designed and tested based on the linear cascade wind tunnel of Northwestern Poly technical University.The flow quality of the standard cascade including inflow precision,flow periodicity,and twodimensionality is adjusted by a self-established integrated control system.On the basis of ensuring the flow quality,the performance of the standard cascade is measured,including the features of incidence and axial velocity density ratio,as well as the distributions of surface isentropic Mach number and wake,and is then compared to the reference cascade data published by DLR.The results show that the standard cascade exhibits good flow periodicity and accuracy,including a uniform region over four successive blade passages upstream and a periodicity range over two successive blade passages downstream,and the periodicity index of outflow is less than 2.The deviation of the inlet Mach number and axial velocity density ratio in the measuring blade passage is no more than 0.005 and 0.02,respectively.The comparison with the reference cascade data shows that the variation laws of the loss,exit flow angle and static pressure ratio with the inlet flow angle are essentially the same between the standard cascade and reference cascade at the design inlet Mach number of 0.62.The loss and exit flow angle of the standard cascade are larger than those of the reference cascade due to the difference of measuring position downstream of cascade,but the static pressure ratio is basically the same.The distributions of the surface isentropic Mach numbers for the two sets of cascades are highly consistent.In general,the test data for the established standard cascade are comprehensive and reliable.

关 键 词：平面叶栅 风洞试验 标准模型 压气机叶栅 轴向密流比 周期性 二维性 

分 类 号：V231.1[航空宇航科学与技术—航空宇航推进理论与工程]