某型全环燃烧室点火特性试验  

Experiment on ignition performance of a full annular combustor

作　　者：丁国玉 马丹 高雅 陶焰明 刘达兵 DING Guoyu;MA Dan;GAO Ya;TAO Yanming;LIU Dabing(Hunan Aviation Powerplant Research Institute,ero Engine Corporation of China,Zhuzhou Hunan 412002,China;South Industry Company Limited,Aero Engine Corporation of China,Zhuzhou Hunan 412002,China)

机构地区：[1]中国航发湖南动力机械研究所,湖南株洲412002 [2]中国航发南方工业有限公司,湖南株洲412002

出　　处：《航空动力学报》2023年第6期1299-1305,共7页Journal of Aerospace Power

基　　金：国家科技重大专项(2017-Ⅲ-0007-0032)。

摘　　要：对某型全环燃烧室进行了模拟地面起动和高空状态下的点火性能试验,研究表明:着火及联焰油气比均随燃烧室进口马赫数的增大而减小;随着模拟点火高度增加,点火变得越来越困难,特别是在试验工况中的低进口马赫数状态下;着火、联焰边界对应的油气比均随换算参考速度的增加而减小,且符合幂函数的函数形式,通过拟合得到着火、联焰边界对应的油气比与换算参考速度之间的函数关系式,经与试验值对比,着火、联焰边界预估值的误差大多分别不超过10%和15%。Experiments were conducted to study the ignition performance on a full annular combustor by simulating the ground start and high-altitude ignition parameters.The test results showed that the fuel-air ratio of both the stable flame establishment and the flame propagation from the ignition dome to the unburned dome decreased with the increasing inlet airflow Mach number;ignition became more and more difficult with the increase of simulating ignition height,especially at low inlet Mach number condition;the fuel-air ratio of stable flame establishment limit and the light around limit decreased with the increase of corrected reference velocity,and there was a power function relationship between them;the functional relationship was obtained by fitting;if compared with the test values,the errors of the estimated fuel-air ratio of stable flame establishment limit and light around limit were mostly less than 10% and 15%,respectively.

关 键 词：全环燃烧室 着火边界油气比 联焰边界油气比 点火特性 换算参考速度 

分 类 号：V231.3[航空宇航科学与技术—航空宇航推进理论与工程]