一种高精度宽范围流量供给系统设计与实验研究  

Design and experimental research on high-precision and wide-range flow supply system

作　　者：石朝纲 金志光[1] 周航 沈理 SHI Chaogang;JIN Zhiguang;ZHOU Hang;SHEN Li(College of Energy and Power Engineering,Nanjing University of Aeronautics and Astronautics,Nanjing 210016,China)

机构地区：[1]南京航空航天大学能源与动力学院,江苏南京210016

出　　处：《推进技术》2024年第10期277-288,共12页Journal of Propulsion Technology

基　　金：国家自然科学基金重点项目(12332018)。

摘　　要：为了在航空发动机试验中提供稳定精确的流量,实现航空发动机短舱泄漏面积评估,设计了一种基于音速喷嘴的高精度宽范围流量供给系统,对其进行了实验研究并对泄漏孔板模型进行标定。所设计的流量测量台采用音速喷嘴正压法,通过改变音速喷嘴个数及调节喷嘴上游压力实现流量的连续调节,并通过放置蜂窝器、气流冲击滞止消除流向动量等措施改善流场品质,提高流量测量精度。流量测量试验结果表明,测量台能够实现0.04~1.78 kg/s宽范围内的高精度连续测量;随试验流量的增大,试验稳压时间从70 s左右缩短到20 s左右;在前后压比1.5时可以保证音速喷嘴达到壅塞,音速喷嘴组个体之间无相干性。测量台结构简单,操作方便,试验流场均匀,试验重复性较好。In order to provide stable and accurate flow in aero-engine test and evaluate the leakage area of aero-engine nacelle,a high-precision and wide-range flow supply system based on sonic nozzle is designed,and the test research is carried out.Then the leakage mass flow of the orifice plate model is calibrated.The flow supply system designed use the positive pressure method of the sonic nozzle.By changing the number of sonic noz⁃zles and adjusting the upstream pressure of nozzles,the flow rate can be adjusted continuously.The quality of flow field is improved and the accuracy of flow measurement is improved by placing honeycomb and eliminating the streamwise momentum by the air impact stagnation.The flow measurement test results show that the measure⁃ment platform can achieve high-precision continuous measurement in the wide range of 0.04~1.78 kg/s.With the increase of the test flow,the test pressure stabilization time decreases from 70 s to 20 s.When the pressure ratio of front to back is 1.5,the sonic nozzle can reach choking,and there is no coherence between the sonic nozzle groups.The platform is simple in structure,easy to operate,uniform in flow field and good in repeatability.

关 键 词：流量测量台 气体流量计 音速喷嘴 正压法 实验研究 

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]