航空发动机燃烧室喷嘴内燃油传热特性的数值研究  

Numerical investigation of heat transfer characteristics of aero-engine combustor injector

作　　者：苗辉 王慧汝 贾真 扈鹏飞[2] 

机构地区：[1]中航空天发动机研究院有限公司,北京100028 [2]沈阳发动机设计研究所,沈阳110015

出　　处：《燃气涡轮试验与研究》2015年第3期30-32,48,共4页Gas Turbine Experiment and Research

摘　　要：采用数值模拟方法,研究航空发动机燃烧室喷嘴内燃油的传热特性:使用三维建模软件对喷嘴进行精细的几何建模,喷嘴模型包括旋流器叶片和隔热套管等细节特征;采用商业CFD软件对比研究不同喷嘴内燃油的传热特性,确定喷嘴隔热套管的隔热效果。结果表明,在所给工况条件下,隔热套管能减少喷嘴杆部温升约50%,对主油路温升的抑制作用随着主油路流量的增加而逐渐减小,对副油路燃油温升的抑制作用比较明显且基本不随主油路流量变化。工程算法和数值模拟计算的喷嘴出口燃油温度之间相差明显。Numerical study on the heat transfer performance of aero-engine combustor injector was con-ducted. Elaborate geometry models with swirler blades and heat insulation casing （HIC） were presented. Comparative heat transfer researches were performed to estimate the effect of HIC on temperature rise of avi-ation kerosene through the injector. It is found that HIC decrease the temperature rise in bar department of injector by 50%in typical cases. Additionally, HIC has a more obvious effect on thermal protection for sec-ondary fuel channel than for primary fuel channel. Furthermore, with increase in flow rate of primary fuel channel, the thermal protection influence of HIC on primary fuel channel become weaker, and no significant change of that influence on secondary fuel channel were found. Finally, engineering method would get a re-markable lower temperature rise than numerical simulation.

关 键 词：航空发动机 燃烧室 燃油喷嘴 热防护 传热 结焦 数值模拟 

分 类 号：V231.1[航空宇航科学与技术—航空宇航推进理论与工程]