摘要
以旋流燃烧室为研究对象,通过数值模拟提取火焰体积数据,将仅用于描述贫熄实验数据规律的火焰体积法发展为预测贫熄特性的方法。该方法以临熄火时的火焰体积代替传统预测方法中的火焰筒体积,提高了贫熄预测的精度与通用性。在保证预测精度的前提下,基于流动相似原理,将改进的火焰体积法推广到高温高压工况。分析了旋流器、主燃孔等的流通面积对贫熄特性的影响,发现旋流器空气流量对贫熄特性具有十分重要的影响。不论是改变旋流器流通面积,还是改变主燃孔流通面积,只要导致旋流器空气流量比例增大,贫熄油气比就增大;反之则减小。在研究的基准工况下,贫熄油气比的预测误差在±24%以内,远小于相同工况下传统模型-90%以上的预测误差。
Taking swirl combustor as the study object, flame volume data was acquired by numerical simulation to develop flame volume method. The flame volume method was used to describe lean burn test data rule and now can predict lean flameout characteristics. The flame volume method took flame volume near flameout to replace liner volume in conventional prediction method to improve accuracy and versatility. Based on flow similarity principle, the developed flame volume method was extended to high pressure and high temperature conditions while the prediction accuracy was acceptable. The influence of swirler and primary hole flow areas on lean flameout characteristics was studied. The result indicated that the swirler flow rate had important effects on lean flameout characteristics. The lean flameout fuel-air ratio increased as long as the ratio of the swirler flow increased, whether the swirler flow area or the primary hole flow area changed or not. Under the basic operation condition in this study, the prediction error of the lean flameout characteristics is less than ±24%, while the error of the classical model is more than -90%.
作者
黄夏
王慧汝
HUANG Xia;WANG Hui-ru(Basic and Applied Research Center,Aero Engine Academy of China,Beijing 101304,China)
出处
《燃气涡轮试验与研究》
北大核心
2018年第6期8-13,35,共7页
Gas Turbine Experiment and Research
基金
航空动力基金(6141B090311)
关键词
航空发动机
燃烧室
贫油熄火特性预测
火焰体积法
火焰筒结构
高温高压
aero-engine
combustor
lean flameout characteristic prediction
flame volume method
liner structure
high temperature and high pressure
