基于收扩喉部结构的非介入式发动机进气流量管设计  

Design of non⁃intrusive engine intake flow pipe based on convergent⁃divergent throat structure

作　　者：杨振 王毅[1] 刘琳琳 YANG Zhen;WANG Yi;LIU Linlin(Changcheng Institute of Metrology&Measurement,Beijing 100095,China)

机构地区：[1]航空工业北京长城计量测试技术研究所,北京100095

出　　处：《计测技术》2023年第2期71-81,共11页Metrology & Measurement Technology

基　　金：国家“十四五”技术基础项目(JSJL2020205A003)。

摘　　要：针对航空发动机进气流量测量不准确的问题,设计了增加收扩喉部结构的新型发动机进气流量管。所设计结构对流场的整流作用,可以通过布置更少的测点获得更高的流量测量准确度;利用直管段与喉部产生的静压差,以非接触的方式获取进气流量,极大简化了试验现场进气流量测试方法。通过仿真与试验验证了设计方案的可行性,研究结果为航空发动机进气流量的准确测量提供了新的解决思路。Aiming at the problem of inaccurate measurement of aero⁃engine intake flow,this paper investigates a new type of aero⁃engine flow pipe with a throat structure.Its advantage is that on the one hand,due to the optimization of the flow field by the throat structure,higher intake flow measurement accuracy can be obtained by arranging fewer measuring probes.On the other hand,the static pressure difference between the straight pipe section and the throat is used to obtain the flow in the pipe in a non⁃contact way,which greatly simplifies the test method of the inlet flow in the test site.The feasibility of the design scheme is verified by simulation and experiment.The research results provide a new solution for the accurate measurement of aero⁃engine intake flow.

关 键 词：航空发动机 进气流量管 收数值仿真 收扩喉部结构 

分 类 号：TB937[一般工业技术—计量学] V23[机械工程—测试计量技术及仪器]