分级燃烧室预燃级旋流组织对点熄火性能影响的试验研究

为了有效拓宽多级旋流分级燃烧室的稳定工作边界,在模型燃烧室上开展了分级燃烧室点火和熄火特性试验研究,采用平面激光测量技术获得了燃烧室冷态流场结构和燃油浓度分布,分析了双级旋流预膜式空气雾化预燃级设计参数(两级旋流旋向、旋流强度)对流场结构、燃油浓度分布和燃烧稳定性的影响,并阐明了燃烧室点火和熄火特性与流场结构和燃油浓度分布的内在关联机制。结果表明,预燃级两级旋流反旋、适当减小内级旋流强度和增大外级旋流强度有利于改善这类分级燃烧室的点火和熄火特性。相关研究结论能够应用于分级燃烧室预膜式空气雾化预燃级设计。     

同轴分区高温升燃烧室点火性能试验研究

为获取关键特征参数及工作条件对燃烧室点火性能的影响规律,对同轴分区高温升燃烧室进行了点火试验研究.在进口压力分别为96,80,60,45kPa,进口温度为288K的条件下,试验研究了不同头部特征结构、不同火焰筒直径共四种研究方案在不同火焰筒压降(1.5％～5.5％)下的贫油点火性能,获得了其点火边界曲线.试验结果表明:...     

污染效应对超声速燃烧室贫油熄火极限影响实验研究

针对污染效应对超声速燃烧室熄火性能影响问题,采用甲烷燃烧和电阻加热的燃烧室直连式对比实验方法,开展了污染效应对燃烧室贫油熄火极限影响研究.基于超声速燃烧室实验模型,研究了煤油喷嘴结构对贫油熄火极限的影响;采用高速摄像仪和平面激光诱导荧光技术(PLIF),研究了加热方式对贫油熄火极限的影响,获得了光学测量结果和壁面压力分...     

飞机大修精益管理实施方案

本文借鉴同行维修业的管理方法并结合南航A320飞机主维修基地自身的特点,利用精益生产管理的先进理念,创建了一套精益拉动式的生产管理体系.实践证明该管理体系适合企业自身特点,飞机大修工作的质量、周期、成本和生产效率等得到明显改善.     

Effects of swirler position on flame response and combustion instabilities

This study is concerned with the experimental and theoretical investigation of the combustion instabilities in a premixed swirl combustor. It is focused on the effects of the swirl mixing distance on the intrinsic thermoacoustic mode. The swirler as an origin of the swirling flow is also the source of the flow disturbance, which has effects on the flame response. The location of the swirler is varied in the experiment to study the effect on combustion instabilities and flame transfer functions. ...     

An FV-EE model to predict lean blowout limits for gas turbine combustors with different structures and sprays

The occurrence of Lean Blowout(LBO) is a disadvantage that endangers a stable operation of gas turbines. A determination of LBO limits is essential in the design of gas turbine combustors. A semiempirical model is one of the most widely used methods to predict LBO limits.Among the existing semiempirical models for predicting LBO limits, Lefebvre’s LBO model and the Flame Volume(FV) model are particularly suitable for gas turbine combustors. On the basis of Lefebvre’s and FV models, the concept o...     

Experimental investigation of a gliding discharge plasma jet igniter

Relight of jet engines at high altitude is difficult due to the relatively low pressure and temperature of inlet air. The penetration of initial flame kernel affects the ignition probability in the turbine engine combustor greatly. In order to achieve successful ignition at high altitude, a deeper penetration of initial flame kernel should be generated. In this study, a Gliding Arc Plasma Jet Igniter(GAPJI) is designed to induce initial flame kernel with deeper penetration to achieve successful ...