Analysis of steady-state temperature measurement deviation of thermocouple sensors on aeroengine

被引：0
作者：
Sun H. [1 ]
Mao X. [1 ]
Zhu C. [1 ]
机构：
[1] Shenyang Engine Research Institute, Aero Engine Corporation of China, Shenyang
来源：
Hangkong Dongli Xuebao/Journal of Aerospace Power | 2022年 / 37卷 / 09期
关键词：
convective heat transfer coefficient; hot wind tunnel calibration; radiation correction; temperature measurement deviation; thermocouple sensor;
D O I：
10.13224/j.cnki.jasp.20210417
中图分类号：
学科分类号：
摘要：
In order to meet the application requirements of the aeroengines under harsh working environment of high temperature， high pressure and high incoming Mach number， the hot wind tunnel calibration and temperature measurement accuracy analysis were carried out for the low-pressure turbine rear thermocouple sensor selected for an aeroengine，and the influencing factors of temperature measurement deviation of the thermocouple sensors were identified. A tem- perature measurement deviation correction method based on the derivation formula of convective heat transfer coefficient was used to validate the calibration results. The results showed that the modified method was reasonable and feasible，and the calculation results were in good agreement with the measurement results，the deviation was less than 0. 6% in all test sites. Considering the problem that the hot wind tunnel cannot fully simulate the real operating conditions of aeroen- gines，the modified method was used to correct the calibration results，the deviation between the correction results and the real air temperature was less than 0. 7%， so the low -pressure turbine rear thermocouple sensors can meet the application requirements of this type of aeroengine. © 2022 BUAA Press. All rights reserved.
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页码：2009 / 2016
页数：7
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