航空发动机燃烧室出口高温热电偶校准技术

杨灿; 吴伟力; 熊义彬; 姚峥嵘

doi:10.13224/j.cnki.jasp.2016.04.001

航空发动机燃烧室出口高温热电偶校准技术

doi: 10.13224/j.cnki.jasp.2016.04.001

中国航空工业集团公司中国航空动力机械研究所, 湖南株洲 412002

详细信息

作者简介:
杨灿(1968-),女,湖南株洲人,研究员,硕士,主要从事航空发动机测试技术研究.

中图分类号: V231
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- 被引次数: 0
出版历程
- 收稿日期: 2014-09-02
- 刊出日期: 2016-04-28

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

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

摘要

摘要: 在高温校准风洞上,对测量航空发动机燃烧室出口温度气冷式和非气冷式这两种形式的高温热电偶进行校准,确定了高温热电偶的辐射修正系数.校准实验结果表明:高温热电偶的辐射误差随气流速度和压力的增加而降低,而且气流温度与航空发动机机匣壁面温度的温差越大,辐射误差也越大.比较两种结构形式的高温热电偶,非冷却式高温热电偶的测量误差比气冷式高温热电偶的相对较小.
- 高温热电偶 /
- 校准 /
- 辐射修正系数 /
- 误差 /
- 燃烧室出口温度 /
- 航空发动机
Abstract: 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.
- high-temperature thermocouple /
- calibration /
- radiation correction coefficient /
- error /
- combustor exit temperature /
- aero-engine

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参考文献(18)

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