摘要
介绍了航空发动机燃烧室温度场测量所用的燃气取样器和燃气分析系统,并对系统简化所引起的误差进行了分析.阐述了"点"燃烧温度的计算方法以及利用"点"燃烧效率、油气比和燃烧温度计算总平均值的方法.数据显示利用热电偶测量温度获得的燃烧效率比燃气分析法燃烧效率约低4%,在燃气温度约为1 500℃时,热电偶测得的燃气平均温度比燃气分析法平均温度低55℃左右,同时表明燃气分析方法在测量航空发动机燃烧室温度场具有可测温度高、影响因素少、数据准确的优势.
Sampler and gas analysis system were introduced for temperature field of aeroengine combustor, and error was analyzed as a result of gas system simplification. Method of computing combustion temperature was expounded, the average of combustion efficiency and combustion temperature and fuel-air ratio was computed. The temperature field for combustor with five nozzles by gas analysis and thermocouple was analyzed, indicating that combustion efficiency by thermocouple was 4; less than that by gas analysis, and combustion temperature was 55 ℃ lower at 1 500 ℃. Gas analysis was proven to be dominant in measuring high temperature gas from aeroengine combustor. High quality data can be gained by gas analysis, which is hardly influenced by environment.
出处
《航空动力学报》
EI
CAS
CSCD
北大核心
2016年第9期2049-2054,共6页
Journal of Aerospace Power
关键词
燃气分析
取样
五头部燃烧室
温度场
摆动装置
gas analysis
sampling
five nozzles combustor
temperature field
pendulous device
