同心圆式主副模分区燃烧组织燃烧室数值研究

推进技术 ›› 2012, Vol. 33 ›› Issue (5): 760-764.

同心圆式主副模分区燃烧组织燃烧室数值研究

常峰,索建秦,梁红侠,武晓欣

西北工业大学动力与能源学院,陕西西安 710072;西北工业大学动力与能源学院,陕西西安 710072;西北工业大学动力与能源学院,陕西西安 710072;西北工业大学动力与能源学院,陕西西安 710072

发布日期:2021-08-15
作者简介:常峰(1987—),男,硕士生,研究领域为航空发动机燃烧室。E-mail:443637284@qq.com
基金资助:
高等学校博士学科点专项科研基金(20106102120031)。

Numerical Study of Co-Axial Pilot and Main Module Combustor

School of Power and Energy, Northwestern Polytechnical University, Xi’an 710072,China;School of Power and Energy, Northwestern Polytechnical University, Xi’an 710072,China;School of Power and Energy, Northwestern Polytechnical University, Xi’an 710072,China;School of Power and Energy, Northwestern Polytechnical University, Xi’an 710072,China

Published:2021-08-15

摘要/Abstract

摘要： 针对新一代高温升燃烧室燃烧组织问题,提出了一种满足高温升燃烧室要求的方案,设计了先进的发散小孔冷却结构和同心圆式主副模分区的头部燃烧组织,采用稳态的压力求解器结合非预混PDF模型,对慢车和设计两个工况进行数值研究。通过数值计算获得了燃烧室速度场和温度场分布特性,结果显示了良好的分区供油分区燃烧组织特性。

关键词: 燃烧室;高温升;发散冷却;燃烧组织;数值仿真

Abstract: For combustion organization problems of the new high temperature rise combustor,a scheme including advanced effusion cooling structure and co-axial pilot and main module dome burning organization is designed. By solving the N-S equations, combined with non-premixed of PDF model, the computation is performed for the idle and design condition. The velocity and temperature field characteristics are obtained by numerical study, and the results show good partition burning organizational characteristics.

Key words: Combustor；High temperature rise；Effusion cooling；Burning organization；Numerical simulation

常峰,索建秦,梁红侠,武晓欣. 同心圆式主副模分区燃烧组织燃烧室数值研究[J]. 推进技术, 2012, 33(5): 760-764.

参考文献

[2] 侯晓春．高性能航空燃气轮机燃烧技术[M].北京:国防工业出版社,2002．
[3] 黎明,吴二平,唐明．高温升蒸发型双腔燃烧室的设计[J]．推进技术,2010,31(4):418-422．(LI Ming,WU Er-ping,TANG Ming.Design of Vaporing Combustor with Double Chambers and High Temperature Rise[J].Journal of Propulsion Technology,0,1(4):418-422.)
[4] 金如山．高温升燃烧室技术[J]．推进技术及产品,9,4(1):34-36．
[5] 林宇震,许全宏,刘高恩．燃气轮机燃烧室[M]．北京:国防工业出版社,2008．
[6] Kress E J,Taylor J R,Dodds W J．Multiple Swirler Dome Combustor for High Temperature Rise Applications[R]．AIAA 90-2159．
[7] 张川,索建秦,金如山．民用飞机低污染燃烧室的技术成熟度划分[J]．航空工程进展,0,1(1)．
[8] 张弛,张荣伟,徐国强,等．直射式双旋流空气雾化喷嘴的雾化效果[J]．航空动力学报,2006,21(5):805-809．
[9] 汪涛, 索建秦, 梁红侠,等．火焰筒切向进气发散小孔冷却数值模拟[J]．航空动力学报,2011,6(5):1052-1058．
[10] SUO Jianqin, LIANG Hongxia, Chin JS．Study on Gas Combustor Cooling Calculation[R]．AIAA 2009-5292．
[11] James S,Zhu J,Anand M S．Simulation of Gas Turbine Combustor Flows Using the Node-Based PDF Transport Method[R]．AIAA 2002-4013．
[12] Dhanuka Sulabh K,Temme Jacob E, Driscoll James F,et al．Unsteady Aspects of Lean Premixed Prevaporized (LPP) Gas Turbine Combustor:Flame-Flame Interactions[R]．AIAA 2010-1148．
[13] Foust Michael J, Doug Thomsen, Rick Stickles, et al．Development of the GE Aviation LowEmission TAPS Combustor for Next Generation Aircraft Engines[R]．AIAA 2012-0936．
[14] Gouldin F C, J S D.Velocity Field Characteristics of a Swirling Flow Combustor[J].AIAA Journal,5,3(1):95-102.