摘要
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。
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. Comparison between calculation and test resuits shows good agreement and verifies the rationality and feasibility of this numerical simulation.
出处
《航空发动机》
2006年第2期38-42,共5页
Aeroengine
