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Title: Shock Wave Spectrum Forming around the Compound Five-Hole Probe and its Influence on Pneumatic Parameters Acquisition during Subsonic to Supersonic Flow
题目：复合型五孔探针的激波图谱及其对获取气动参数的影响研究
Authors: KAN Xiaoxu, SUO Licheng, LEI Haodong, WU Wanyang, ZHONG Jingjun
作者：阚晓旭，锁立城，雷浩东，吴宛洋，钟兢军
单位：上海海事大学
Journal of Thermal Science, 2024, 33(6): 2019-2031.
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摘要
Abstract: Supersonic wind tunnel experiment is one of the important measurements for developing advanced gas turbines, and supersonic multi-hole probes are sophisticated tools to measure pneumatic parameters in such experiments. However, shock waves form around the probe head in supersonic flow, which affect the accuracy of results. In this study, a supersonic five-hole probe is selected as the research object. Firstly, a compound five-hole pressure-temperature probe was designed and produced with 3D-printing technology. Then, the shock wave spectrum was numerically calculated by three methods, which were the Mach number, density gradient, and shock function; in contrast to the other two methods, the shock function could accurately identify the types and ranges of shock and expansion waves. The results show that a strong shock wave is formed at the front section of the probe head, and the shock wave generated around the pressure measuring tube affects the total pressure and Mach number of the flow field, which causes the increase of entropy. The intensity of the shock wave at the head of the pressure measuring tube is the largest, causing a decrease in the total pressure around the flow field. Afterwards, to reduce the calculation errors caused by neglecting the compressibility of gases and the entropy increase, a gas compression factor δs was introduced. It is proved that the error of the calculated pneumatic parameters is less than 5% and 10% in subsonic and supersonic condition, respectively, with the gas compression factor considered. The research results of this paper provide theoretical reference for the design and use of pneumatic probes during subsonic to supersonic flow.
摘要：超声速风洞实验是发展先进燃气轮机的重要手段之一，超声速多孔探针是这类实验中测量气动参数的精密工具。然而，在超声速流动中，探头周围会形成激波，影响测量结果的准确性。本研究选取超声速五孔探针的头部作为研究对象。首先，利用3D打印技术设计并制作了复合式五孔压力-温度探针。然后，采用马赫数、密度梯度和激波函数3种方法对激波谱进行数值计算；与其他两种方法相比，激波函数可以准确地识别激波和膨胀波的类型和范围。结果表明，在探针头部的前段形成了较强的激波，测压管周围产生的激波影响流场的总压和马赫数，引起熵增。测压管头部的激波强度最大，导致流场周围的总压降低。随后，为了减小由于忽略气体的可压缩性和熵增引起的计算误差，引入了气体压缩因子δs。经验证，在考虑气体压缩因子的情况下，计算得到的气动参数在亚声速和超声速条件下的误差分别小于5 %和10 %。本文的研究结果为气动探针在亚声速到超声速流动过程中的设计和使用提供了理论参考。
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引用格式
KAN Xiaoxu, SUO Licheng, LEI Haodong, WU Wanyang, ZHONG Jingjun, Shock Wave Spectrum Forming around the Compound Five-Hole Probe and its Influence on Pneumatic Parameters Acquisition during Subsonic to Supersonic Flow, Journal of Thermal Science, 2024, 33(4): Journal of Thermal Science, 2024, 33(6): 2019-2031..
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