An annular combustor with evaporation tubes was designed for certain micro-turbojet engine.
为某微型涡喷发动机设计了一个蒸发管环形燃烧室。
The three-dimensional flow field of annular combustor for aero-derivative gas turbine burning gas fuel was numerically simulated.
采用数值模拟方法对燃用天然气的某型航改燃气轮机环形燃烧室进行三维流场分析。
Turbulent reactive flow in a short annular combustor is simulated by changing the number and location of nozzle and swirler in combustor dome.
通过改变燃烧室头部喷嘴、旋流器的数目和位置，对短环形流燃烧室内有较强回流的湍流旋流流动进行了模拟。
The results of calculation show that the numerical procedure is reasonable and can be expended to predict the turbulent reacting flows in the annular combustor.
计算结果表明计算方法合理，这计算程序进一步扩展，可用来预估环形燃烧室反应流流场。
The annular multi-hole radial jets have important effect on combustor liner.
环向径向射流对燃烧室火焰筒内的流场有着重要的影响。
Annular reverse flow zone can be found too in the combustor with the flat-straight slag baffle.
简单环形挡渣板也能产生环形回流区，在旋风燃烧室设计中可取代锥形缩口挡渣板。
Annular reverse flow zone can be found too in the combustor with the flat-straight slag baffle.
简单环形挡渣板也能产生环形回流区，在旋风燃烧室设计中可取代锥形缩口挡渣板。
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