摘要
To obtain the outlet temperature of combustor,a kind of high-temperature and water cooling thermocouple was designed.The main factors affecting the results of thermocouple measurement were analyzed after numerical simulation.Results showed that the high-temperature water cooling thermocouple can achieve high temperature measurement under the condition of 2 400 K.With the increase of the distance between the water cooling structure and the stagnation cover,the temperature measurement result was more accurate,and the increase in the area ratio of the inlet and outlet of the stagnation cover within a reasonable range can make the measurement results more accurate.The surface emissivity of the measuring point had a great influence on the radiation error.The pressure and flow rate of cooling water can be effectively reduced after adding zirconia coating onto the surface of the rake body.
To obtain the outlet temperature of combustor,a kind of high-temperature and water cooling thermocouple was designed.The main factors affecting the results of thermocouple measurement were analyzed after numerical simulation.Results showed that the high-temperature water cooling thermocouple can achieve high temperature measurement under the condition of 2 400 K.With the increase of the distance between the water cooling structure and the stagnation cover,the temperature measurement result was more accurate,and the increase in the area ratio of the inlet and outlet of the stagnation cover within a reasonable range can make the measurement results more accurate.The surface emissivity of the measuring point had a great influence on the radiation error.The pressure and flow rate of cooling water can be effectively reduced after adding zirconia coating onto the surface of the rake body.
作者
ZHAO Kai
LI Feng
LU Fuguo
ZHOU Tao
YANG Hongyu
ZHAO Kai;LI Feng;L Fuguo;ZHOU Tao;YANG Hongyu(School of Energy and Power Engineering,Beijing University of Aeronautics and Astronautic;School of Aviation Operations and Services,Aviation University of Air Forc)
出处
《航空动力学报》
EI
CAS
CSCD
北大核心
2018年第9期2084-2092,共9页
Journal of Aerospace Power
基金
National Natural Science Foundation(9174110013)
Aviation Power Fund(614B090310)