反应机理对燃烧室出口温度分布仿真结果的影响  

Effects of reaction mechanism on the combustor outlet temperature distribution

作　　者：范珍涔[1] 程波[1] 曹宗华[1] 陈振辉[1] FAN Zhen-cen;CHEN Bo;CAO Zong-hua;CHEN Zhen-hui(China Gas Turbine Establishment,Chengdu 610500 China)

机构地区：[1]中国燃气涡轮研究院,成都610500

出　　处：《燃气涡轮试验与研究》2016年第4期17-21,共5页Gas Turbine Experiment and Research

摘　　要：为考察不同反应机理对航空发动机燃烧室出口温度分布数值模拟的影响,基于小火焰模型,采用6种不同的航空煤油化学反应机理,对航空发动机燃烧室的三维两相燃烧流场进行了数值模拟。比较了各机理所预测的出口温度场和燃烧效率结果的异同,并结合试验数据进行分析,考察了各机理模拟燃烧室出口温度分布及效率的准确性。结果表明:23步反应机理和30步反应机理预测的出口温度分布及燃烧效率有较高的可信度,单步、2步、11步反应机理预测结果则与试验结果相差较大;H-O反应在反应机理中的作用非常关键,只考虑NO而不考虑其他NOx生成对模拟结果影响很小。To investigate the effects of different chemical reaction mechanism on the numerical simulationof aero-engine main combustor outlet temperature distribution, three dimensional two phase combustionflow fields of a certain aero-engine main combustor were simulated with six different chemical reactionmechanism of aviation kerosene, based on the flamelet model. Similarities and differences of simulation re?sults on outlet temperature distribution and combustion efficiency were compared and analyzed with experi?mental data. The results show that temperature distribution and combustion efficiency were accurately pre?dicted with 23 step mechanism and 30 step mechanisms, while the prediction varies a lot with experimentalresults by the single step, 2 step and 11 step mechanisms. And it is indicated that H-O reaction was impor?tant in simulation and nitrogen oxides besides NO had little effect on simulation results.

关 键 词：航空发动机 燃烧室 出口温度分布 小火焰模型 航空煤油 化学反应机理 数值模拟 

分 类 号：V231.15[航空宇航科学与技术—航空宇航推进理论与工程]