摘要
设计了用于航空发动机压气机级间参数测量的叶型受感部。通过风洞校准试验,得出在不同来流速度条件下,压力叶型受感部的不敏感角范围及总压测量误差和温度叶型受感部的总温测量误差,确定了影响叶型受感部测量准确度的主要因素。在试验结果的基础上,对叶型受感部结构进行了优化。
The airfoil sensing area was designed for an aeroengine compressor interstage parameters measurement. The insensitive angle range and the total pressure measurement error for ai（foil sensing area and the total pressure measurement error of temperature airfoil sensing area were obtained with various inflow velocity by the winel tunnel calibration test. The major factor was also determined, which affected the measurement accuracy of the airfoil sensing area. The structure of the airfoil sensing area was optimized based on the result of the experiment.
出处
《航空发动机》
2010年第2期43-45,21,共4页
Aeroengine
关键词
叶型受感部
测试
压气机
级间参数
探针
航空发动机
airfoil sensing area
measurement
compressor
interstage parameters
probe
aeroengine
