Velocity measurement of blade boundary layer in subsonic compressible flow field with hot wire

被引：0
|
作者：
Zhang Z. [1 ,2 ]
Xiang X. [1 ,2 ]
Wang L. [1 ,2 ]
Tong X. [1 ]
Zhao W. [1 ,2 ]
Zhao Q. [1 ,2 ,3 ]
机构：
[1] Institute of Engineering Thermophysics, Chinese Academy of Sciences, Beijing
[2] School of Aeronautics and Astronautics, University of Chinese Academy of Sciences, Beijing
[3] Key Laboratory of Light-Duty Gas-Turbine, Institute of Engineering Thermophysics, Chinese Academy of Sciences, Beijing
来源：
Tuijin Jishu/Journal of Propulsion Technology | 2024年 / 45卷 / 04期
关键词：
Boundary layer; Cascade; Compressible flow field; Compressor; Hot wire anemometer;
D O I：
10.13675/j.cnki.tjjs.2302056
中图分类号：
学科分类号：
摘要：
In order to develop a simple and effective method for measuring the blade boundary layer velocity in subsonic compressible flow field，then providing useful information for the blade design and numerical simulation，the measurement technology of hot-wire anemometer is focused on in this paper. In view of the influence of density change on the calibration results of hot-wire in compressible flow field，the hot wire calibration method based on the constant pressure control which is suitable for boundary layer velocity measurement was proposed. While for the velocity and density coupling problems that cannot be directly obtained by the hot wire measurement in the compressible flow field，the velocity decoupling method by introducing the steady static pressure on blade surface was also introduced，and the main errors of the proposed methods were analyzed and evaluated. On this basis，the hot wire calibration and boundary layer velocity measurement verification tests were carried out，and the results show that the coefficients of the hot wire calibration mathematical model based on the constant pressure control change linearly with the pressure. At the same time，a correction method based on overheat ratio adjustment was proposed to solve the nonlinear effect of temperature，which can reduce the effect of temperature deviation of about 13 ℃ on the hot wire voltage to less than 1%. So the hot wire calibration processes based on the constant pressure control are simplified furtherly. Combining with the velocity decoupling method based on the steady static pressure on the blade surface，a simple and feasible velocity measurement method with high-frequency response characteristic for the blade boundary layer in the subsonic compressible flow field is provided. © 2024 Journal of Propulsion Technology. All rights reserved.
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