摘要
介绍了高空模拟试验中,发动机推力统计需要的进气冲量的测量方法,以及不确定度构成因素。提出了进气冲量测量存在受雷诺数影响的流量系数测定误差和附面层速度损失造成的进气速度计算误差;并对这两项误差的不确定度进行了理论分析。以涡扇发动机飞行包线上的典型工况点为例,开展了数值仿真和试验测量,获得了相应的进气冲量测量不确定度。结果表明:推力测量中进气冲量的不确定度为1.2%~1.4%,由雷诺数偏差引起的流量系数误差以及进气速度的计算误差不可忽视,有必要在校准方法或修正方法中予以考虑。
In the high altitude simulation test,the measurement method of intake momentum required for engine thrust statistics and the components of measurement uncertainty were introduced.The measurement error of flow coefficient affected by Reynolds number and the calculation error of inlet velocity caused by boundary layer velocity loss were given.The uncertainty of these two errors was analyzed theoretically.Taking the typical flight condition of a turbofan engine as an example,numerical simulation and test measurement were carried out,and the corresponding uncertainty of intake momentum measurement was obtained.The results showed that the uncertainty of intake momentum in thrust measurement was about 1.2%—1.4%.The error of flow coefficient caused by Reynolds number deviation and the calculation error of intake velocity cannot be ignored,and should be taken into account in the calibration method or correction method.
作者
杨桥
吴锋
王靖元
徐全勇
李红莉
YANG Qiao;WU Feng;WANG Jingyuan;XU Quanyong;LI Hongli(Sichuan Gas Turbine Establishment,Aero Engine Corporation of China,Mianyang Sichuan 621000,China;Institute for Aero Engine,Tsinghua University,Beijing 100084,China;School of Instrument Science and Opto-electronics Engineering,Hefei University of Technology,Hefei 230009,China)
出处
《航空动力学报》
EI
CAS
CSCD
北大核心
2024年第10期329-336,共8页
Journal of Aerospace Power
基金
中国航发四川燃气涡轮研究院外委课题。
关键词
进气冲量
雷诺数指数
流量系数
不确定度评定
高空模拟试验
intake momentum
Reynolds number index
flow coefficient
uncertainty assessment
altitude simulation test
