某型发动机燃烧室工作稳定性的数值计算

The numerical calculation on the stability of aeroengine combustor

概述了某型航空发动机燃烧室工作稳定性的数值模拟结果。采用修正的k-ε双方程紊流模型计算了燃烧室在慢车、最大、中间、最大热负荷和高空小平飞下的三维流场、温度场和熄火特性。模拟结果表明,某型机燃烧室熄火的余气系数α随压力增加有一定的增加,熄火速度亦提高;主燃区温场热区决定出口温场热区,其位置具有一定游动性;从慢车加速至各工作状态,热点指标δa变差,且由余气系数α决定,因此过急地推油门会造成火焰筒某些扇面热点过高,并产生故障。

The results of numerical calculation on the stability of a type of the aeroengine combustor are presented in this paper. The calculation on the 3 - D flow field, temperature field and blowout characteristic of the combustor for the ground idling, the peak, the middling, the peak head load, and the altitude - small lever flying conditions adopts the modified - two - equation turbulence combustion model. The numerical results have shown that, with the increasing of the pressure, both the blowout rest air coefficient of this combustor and the blowout velocity will increase. The thermal zones of the temperature field at primary combustion zone determine the thermal zones of the exit temperature field, its position have some floatings. From the ground idling to other conditions, the hot spot index will become worse, and the value is determined by . So sharp pushing thrust lever will cause higher hot spot in some sector of the burner, the ending is create failure.