Calibration technology of high-temperature thermocouple for combustor exit of an aero-engine

被引：0

作者：

Yang C. ^{[1
]}

Wu W.-L. ^{[1
]}

Xiong Y.-B. ^{[1
]}

Yao Z.-R. ^{[1
]}

机构：

[1] China Aviation Powerplant Research Institute, Aviation Industry Corporation of China, Zhuzhou, 412002, Hunan

来源：

Hangkong Dongli Xuebao/Journal of Aerospace Power | 2016年 / 31卷 / 04期

关键词：

Aero-engine; Calibration; Combustor exit temperature; Error; High-temperature thermocouple; Radiation correction coefficient;

D O I：

10.13224/j.cnki.jasp.2016.04.001

中图分类号：

学科分类号：

摘要：

The high-temperature thermocouple for measuring aero-engine combustor exit temperature were calibrated in the high-temperature wind tunnel, and radiation correction coefficients were experimentally determined for two types of non-cooled and air-cooled thermocouples. Results of the calibration experiment presented that the radiation errors decreased with increasing airflow velocity and pressure, and it became greater when the temperature difference increased between the airflow temperature and aero-engine case wall temperature. Comparing the two types of thermocouple, the measurement errors of the non-cooled high-temperature thermocouple were smaller than the air-cooled high-temperature thermocouple. © 2016, Editorial Department of Journal of Aerospace Power. All right reserved.

引用

页码：769 / 774

页数：5

共 8 条

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