旋流杯空气雾化喷嘴套筒出口形状对小型燃烧室点火性能的影响

罗国良; 宋双文; 胡好生; 彭剑勇

旋流杯空气雾化喷嘴套筒出口形状对小型燃烧室点火性能的影响

中国航空工业集团公司中国航空动力机械研究所,湖南株洲 412002

基金项目: 南京航空航天大学基本科研业务费专项科研项目(NS2010053)

计量
- 文章访问数: 1789
- HTML浏览量: 4
- PDF量: 41
- 被引次数: 0
出版历程
- 收稿日期: 2010-07-27
- 修回日期: 2011-03-04
- 刊出日期: 2011-08-28

Influences of the swirl cup flares design on the small combustor ignition performances

China Aviation Powerplant Research Institute, Aviation Industry Corporation of China,Zhuzhou Hunan 412002,China

摘要

摘要: 对平滑和扩张套筒出口形状的旋流杯空气雾化喷嘴燃烧室点火性能进行了研究.这两种旋流杯空气雾化喷嘴中,涡流器是两个旋向相反的径向叶片涡流器,喷嘴为单油路离心喷嘴.采用单头部扇形燃烧室,在燃烧室进口为常温常压空气,燃烧室压力降为0.1%~4.0%的条件下,研究了这两种设计的空气雾化喷嘴燃烧室的点火性能.研究发现,扩张套筒出口形状旋流杯燃烧室点火性能大大优于平滑出口套筒形状的点火性能,其原因是套筒出口形状影响了下游的流场和液雾散布,从而导致了点火性能的差异.
- 航空发动机 /
- 燃烧室 /
- 点火 /
- 空气雾化喷嘴 /
- 旋流杯
Abstract: The small combustor ignition performances were investigated experimentally with arc flare and straight line flare design swirl cup.Both swirl cups have the same primary and secondary radial vane swirler and a simplex pressure atomizer.The ignition experiments were conducted under atmospheric pressure and temperature,and the pressure drop across the flame tube was between 0.1% and 4.0% of inlet total pressure.The ignition results indicate that the ignition performances of swirl cup with straight line flare design are better than those with arc flare design.The flow field and two-phase flow field investigated from previous measurements illuminate the reason of the ignition results.
- aircraft engine /
- combustor /
- ignition /
- airblast atomizer /
- swirl cup

HTML

参考文献(12)

[1]	Sampath P,Verhiel J,McCaldon K.Low emissions technology for small aviation gas turbines.AIAA 2003-2564,2003.
[2]	彭云晖,林宇震,许全宏,等.双旋流空气雾化喷嘴喷雾、流动和燃烧性能[J].航空学报,2008,29(1):1-14. PENG Yunhui,LIN Yuzhen,XU Quanhong,et al.Review of atomization,aerodynamics and combustion performance of swirl cup[J].Acta Aeronautica et Astronaution Sinica,2008,29(1):1-14.(in Chinese)
[3]	方昌德.世界航空发动机手册[M].北京:航空工业出版社,1996.
[4]	Wang H Y,McDonell V G,Samuelsen G S.Influence of hardware design on the flow field structures and the patterns of droplet dispersion Part Ⅰ:mean quantities[J].Journal of Engineering for Gas Turbines and Power,1995,117(2):282-289.
[5]	Lang H J,Huang Y,Guo Z H.The flow fields in a model combustor with primary holes after different swirl cups.ASME GT2006-90489,2006.
[6]	Mongia H C,AI-Roub M,Danis A,et al.Swirl cup modeling Part Ⅰ.AIAA-2001-3576,2001.
[7]	Ateshkadi A,McDonell V G,Samuelsen G S.Effect of mixer geometry on fuel spray distribution,emissions and stability.AIAA 98-0247,1998.
[8]	徐华胜,黄义勇,王秀兰.喷嘴供油特性对双涡流器头部气动雾化效果的影响研究[J].燃气涡轮试验与研究,2004,17(2):14-17. XU Huasheng,HUANG Yiyong,WANG Xiulan.Study on the effect of fuel jet characteristics on airblast atomization performance for device with two stage swirler[J].Gas Turbine Experiment and Research,2004,17(2):14-17.(in Chinese)
[9]	Mongia H C,Gore J P,Grinstein F F,et al.Combustion research needs for helping development of next generation advanced combustors.AIAA 2001-3853,2001.
[10]	袁怡祥,林宇震,刘高恩,等.燃油周向分级对贫油熄火油气比的影响[J].航空动力学报,2003,18(5):639-644. YUAN Yixiang,LIN Yuzhen,LIU Gaoen,et al.The effect of fuel-circumferential staging on lean blowout limit at idle condition[J].Journal of Aerospace Power,2003,18(5):639-644.(in Chinese)
[11]	林宇震,林培华,许全宏,等.套筒空气雾化喷嘴燃烧室点火研究[J].航空动力学报,2007,22(3):342-346. LIN Yuzhen,LIN Peihua,XU Quanhong,et al.Research on ignition performance of a hybrid airblast atomizer combustor with convergent-divergent sleeve[J].Journal of Aerospace Power,2007,22(3):342-346.(in Chinese)
[12]	Lefebvre A H.Gas turbine combustion[M].Phiadelphia,PA,USA:Taylor & Francis Press,1999.