Study on the influence of pneumatic probe on the wake flow field of transonic turbine cascade  

气动探针对跨音速涡轮叶栅尾流场的影响研究

作　　者：Qingdian Zhang Hongwei Ma Anqi Xiao Yingcun Liu Junde Guo 张庆典;马宏伟;肖安琪;刘英存;郭君德(School of Energy and Power Engineering,Beihang University,Beijing 102206,China)

机构地区：[1]School of Energy and Power Engineering,Beihang University,Beijing 102206,China

出　　处：《Acta Mechanica Sinica》2024年第7期43-54,共12页力学学报（英文版）

基　　金：supported by the National Science and Technology Major Project(Grant Nos.2017-V-0016-0068,and J2019-V-0017-0112);the National Natural Science Foundation of China(Grant No.51776011).

摘　　要：The pneumatic probe is widely used for contact measurements in turbomachinery flow field research.However,it inevitably interferes with the original flow field,leading to additional errors,particularly in wake flow fields or transonic regions with significant pressure gradients.This study employed Reynolds-Averaged Navier-Stokes delete and high-fidelity numerical simulation to investigate the impact of an inserted pneumatic probe on the wake flow field of a transonic turbine blade and compared it to the baseline flow field.Results indicate that the probe causes the shock waves premature occurrence in the high subsonic wake region near the turbine blade trailing edge.These shock waves affect vortex shedding by thickening the boundary layer near the trailing edge and changing the shedding pattern from high-frequency-low-energy to low-frequencyhigh-energy.In addition,the extra flow loss is incurred,and the blade's heat transfer characteristic is changed.This research provides a reference for testing experiments in complex transonic flow fields,guiding experimental researchers to minimize instrument interference with the original flow field.气动探针被广泛用于叶轮机械的接触式流场测量研究中.然而,气动探针不可避免地会干扰原始流场,导致额外误差,尤其是当探针置于尾迹区或压力梯度较大的跨音速流场区域中.本研究采用雷诺时均的纳维-斯托克斯(RANS)结合高保真数值模拟来研究插入式气动探针对跨音速涡轮叶栅尾流场的影响,并与原始叶栅流场进行比较.结果表明,探针的插入导致涡轮叶片尾缘附近的高亚音尾迹区域过早出现激波.激波通过增加尾缘附近的边界层的厚度来影响尾迹处涡流的脱落,并将尾迹涡的脱落模式从高频-低能转变为低频-高能.此外,探针的插入还产生了额外的流动损失,并改变叶片的传热特性.这项研究为跨音速叶栅的气动测试实验提供了参考,并建议实验研究人员尽量减少测试仪器对原始流场的干扰.

关 键 词：Pneumatic probe Wake flow field Transonic turbine cascade Shock wave High-fidelity numerical simulation 

分 类 号：O35[理学—流体力学]