在实验中，主要通过调整一次空气系数和引射器喷口的大小，达到稳定燃烧的运行工况。
In experiment, steady operating point of combustion can be obtained mainly by setting primary air factor and the size of spout.
在实验结果的基础上利用火焰稳定理论，论证了在不同一次空气系数时获得最佳燃烧器参数的可能性。
Based on the experimental result and flame stability theory, the possibility to obtain the optimum parameters of the burners are discussed under different primary air coefficient.
采用FLUENT软件对大气式燃气燃烧器的引射器进行数值模拟，得出喷嘴位置与一次空气系数的关系。
The numerical simulation of the injector of atmospheric gas burner is carried out using software FLUENT, and the relationship between nozzle position and primary air coefficient is obtained.
航空喷气发动机燃烧室中广泛采用叶片涡流器来控制火焰筒的一次空气流量，并建立强回流区。
The blade-type swirlers have been used in many air engine combustors to control the primary airflow of flame tube and establish a strong recirculation zone.
航空喷气发动机燃烧室中广泛采用叶片涡流器来控制火焰筒的一次空气流量，并建立强回流区。
The blade-type swirlers have been used in many air engine combustors to control the primary airflow of flame tube and establish a strong recirculation zone.
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