欠频响压力探针测量压气机动态流场的结果分析  

Analysis of Measured Unsteady Flow Field Using a Quasi Fast Response Pressure Probe

作　　者：马宏伟[1,2] 魏巍[1,2] 张良[1,2] 官辉[1,2] 

机构地区：[1]北京航空航天大学能源与动力工程学院,北京100191 [2]先进航空发动机协同创新中心,北京100191

出　　处：《航空发动机》2016年第2期67-72,共6页Aeroengine

基　　金：国家自然科学基金(51136003)资助

摘　　要：压气机内部流动具有很强的非定常特征,尤其是小尺寸发动机叶片通过频率高达30~80 k Hz,而动态压力探针的响应频率只能与叶片通过频率相当,采用其测量不易获得具体的高频流场结构。为了研究这种欠频响情况下测得流场与真实流场的差异,以某低速压气机为对象进行了模拟研究。采用频响为420 Hz的动态压力探针及频响大于33 k Hz的单斜丝热线探针,测量了叶片通过频率为303 Hz的转子出口流场。修正了动态压力探针的容腔效应对测得流场的影响,校验了在测试系统响应频率较低时,修正后流场与热线测得的参考流场之间的差异。对比结果表明：原始流场压力信号的部分频率成分产生了较大偏差,出口截面流场的周向位置有较大误差。经修正后,周向位置较为准确,泄漏堵塞区域形态以及强度都与参考流场的更为接近,但由于尾迹区存在部分高频,修正后结果与参考流场的差异仍较明显。It is well known that the flow filed inside a compressor has strong dynamic characteristic, especially in the small-scale ones whose blade passing frequency could reach 30~80 k Hz. In most circumstances, because the Fast Response Aerodynamic Probe（FRAP） can only meet the blade passing frequency, the dynamic characteristic of the probe can not satisfy the requirement of reproducing a detailed high-frequency flow structure. In order to investigate the difference between measured flow field and real flow field using this quasi FRAP, a dynamic pressure probe with a response frequency of 420 Hz and a slanted single hot wire probe with a response frequency more than 33 k Hz was utilized to measure the unsteady flow filed at the outlet of an isolated compressor rotor which had a blade passing frequency of 303 Hz. The frequency response of the probe was measured to correct the influence of square-cavity effect on the measured flow field. The corresponding corrected ones were compared with the reference flow field measured with hot wire probe as the response frequency of measurement system was low. The comparison shows that some frequency components of the original signals were amplified. After correction, the circumferential position of the unsteady field, the blockage and pattern of the tip leakage area are obviously more close to the reference flow field. Nevertheless, due to the high frequency component in the wake, the correction still cannot get a good result.

关 键 词：欠频响压力探针 动态测量 管传递函数 动态修正 压气机 航空发动机 

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]