combustor

By using flame propagation theory,2D two-phase turbulent combustion model,EBU-Arrhenius model,PSI-Cell model and ADINA software,the velocity,temperature and pressure fields at different flight conditions are calculated for an aeroengine when lean blowout occurs in the combustor.

应用火焰传播理论、二维两相紊流燃烧的k-ε模型、EBU-Arrhen ius模型、颗粒群轨道模型和AD INA软件,计算出了某型在研航空发动机在不同飞行状态下的主燃烧室贫油熄火时的流场、温度场和压力场;计算值与试验结果比较吻合,证实了数值模拟的合理性和可行性。

Design of main burning furnace and tail gas incinerator are reviewed with a 70 kt/a sulphur recovery unit as an example.

以某70 kt／a硫磺回收装置为例,仅对主燃烧炉和尾气焚烧炉的设计作一回顾,着重介绍设备结构、设计特点、材质选择及耐火衬里的施工要点等。

The effect of main combustible ingredient,amount of flame colouring ingredient and the treatment of candle wick on the generation of coloured flame is discussed.

讨论了主燃剂的种类、发色剂的用量及烛芯的处理对彩焰效果的影响 。