高负荷平面叶栅风洞流场品质改进措施数值研究  

Numerical Study on Flow Field Quality Improvement in a Highly Loaded Linear Cascade Wind Tunnel

作　　者：傅文广 杨昭 张益智 孙鹏 郭重佳 韩吉昂 FU Wen-guang;YANG Zhao;ZHANG Yi-zhi;SUN Peng;GUO Chong-jia;HAN Ji-ang(College of Safety Science and Engineering,Civil Aviation University of China,Tianjin 300300,China;Shaanxi Qian Shan Avionics Company Ltd.,Xi’an 710000,China;Naval Architecture and Ocean Engineering College,Dalian Maritime University,Dalian 116026,China)

机构地区：[1]中国民航大学安全科学与工程学院,天津300300 [2]陕西千山航空电子有限责任公司,陕西西安710000 [3]大连海事大学船舶与海洋工程学院,辽宁大连116026

出　　处：《推进技术》2023年第7期164-175,共12页Journal of Propulsion Technology

基　　金：天津市教委科研计划项目(2021KJ060);中国民航大学科研启动基金项目(2020KYQD34)。

摘　　要：为研究不同改进措施对平面叶栅风洞流场品质的改进效果与机理,以高负荷扩压叶栅为研究对象,利用数值模拟方法研究了试验器进口段上下侧壁抽吸措施、出口导流尾板措施、抽吸与尾板组合措施对叶栅风洞流场品质的改进效果。研究结果表明:上下侧壁抽吸减小了进口段的静压梯度,减弱了上下侧壁附面层对进口流体流向的影响;导流尾板减弱了外界大气对上侧壁附近通道的影响;抽吸与尾板组合措施结合了侧壁抽吸与导流尾板的优点,使得进口静压分布均匀,通道间压差阻力差异减小,对叶栅试验段流场品质的改进效果优于其他方案。在当前马赫数工况下可使叶栅进口64%的通道范围马赫数误差<0.01,冲角误差<0.5°,有三个连续通道出口周期性较好,并且轴向密流比<1.15。In order to study the effects and mechanism of different improvement measures on flow field qual⁃ity of compressor cascade wind tunnel,the highly loaded compressor cascade was studied by numerical methods.The improvement measures included upper and lower side wall suction schemes,the guide tailboard schemes,and the combined suction and tailboard schemes.The results show that the suction of the upper and lower side⁃walls reduces the static pressure gradient in the inlet section and weakens the influence of the upper and lower sidewall boundary layer on the inlet fluid flow direction.The guide tailboard weakens the influence of the external atmosphere on the passages near the upper sidewall.The combination of suction and tailboard scheme combines the advantages of sidewall suction and guide tailboard.This combined application makes the inlet static pressure distribution uniform and reduces the difference in differential pressure resistance between passages.At the same time,the combined scheme is better than other schemes in improving the flow field quality of compressor cascade test section.Under the current Mach condition,the 64%of the compressor cascade inlet passages simultaneously meet the Mach number deviation less than 0.01 and the error of incidence angle less than 0.5°,in which there are three continuous passages having periodicity,and the axial velocity density ratio is less than 1.15.

关 键 词：平面叶栅 流场品质 抽吸 尾板 轴向密流比 数值模拟 风洞 

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]