燃烧室电火花点火模型

Spark ignition model for combustor

为了准确掌握影响航空发动机燃烧室点火边界的关键因素,并建立燃烧室点火边界预测模型,对单头部燃烧室的点火过程及点火边界进行了试验与理论研究。获取了燃烧室点火过程的火核生成与传播特性曲线,形成了拓宽燃烧室点火边界的优化方法,基于点火恢复时间建立了燃烧室点火边界预测模型,并对预测模型的精度进行验证。结果表明:提高喷嘴雾化性能是提升点火性能的最有效途径,点火模型预测结果与试验结果相符度较好,模型的最大误差小于20%,满足燃烧室工程设计需要。

With an aim to develop an ignition model and obtain the key factors influencing the ignition limits in aero-engine combustor, testing and theoretical investigations were conducted based on the ignition process inside a single dome gas turbine combustor. The characteristic curve of ignition process was obtained, and a method to optimize the ignition performance was also proposed. An ignition model to predict the ignition limits was developed based on the concept of recovery time, and the accuracy of the prediction model was validated. It is found that the significant improvement in ignition performance can be obtained by decreasing the atmozation performance of nozzle. A very satisfactory agreement is demonstrated between the predictions based on the prediction model and the actual measured values. The maximum error of the prediction model is less than 20%, which is qualified to meet the requirements of the combustor design.