燃气涡轮无气膜冷却动叶参数化设计系统应用  

Application of Parameterized Design System for Gas Turbine Rotor Blades without Film Cooling

作　　者：罗磊[1] 陈朔[1] 温风波[1] 王松涛[1] 

机构地区：[1]哈尔滨工业大学能源科学与工程学院,黑龙江哈尔滨150001

出　　处：《推进技术》2015年第6期864-875,共12页Journal of Propulsion Technology

基　　金：国家自然科学基金委创新研究群体(51121004)

摘　　要：为进行燃气涡轮冷却结构的设计,在考虑总的温度分布系数(OTDF)及不考虑OTDF两种情况下,采用一套设计方法,完成了燃气涡轮第一级动叶冷却结构的整体设计。通过设计表明:采用管网计算,并通过三维导热计算进行热分析,最后通过气热耦合计算能够快速地设计出较佳的冷却结构;不考虑OTDF设计时,第一腔流量为16.9g/s,第二腔流量为40.8g/s,最大无量纲温度0.700,采用双进口蛇形通道,换热效果较佳,且结构设计较为简单;考虑OTDF时,为达到设计要求,第一腔流量为18.2g/s,第二腔流量为25.4g/s,第三腔流量为5.3g/s,最大无量纲温度0.752。通过多方案设计,得出在无气膜情况下,采用三个冷气进口多回转通道能够达到较好的冷却效果。Whether taking OTDF （Overall Temperature Distribution Factor） into account or not, a set of design system was used to accomplish the cooling structure design of the gas turbine first stage rotor blades. It shows that the optimal cooling structure can be fast obtained with pipe-net calculation, three-dimensional temperature field calculation performing thermal analysis and aero-thermal conjugated calculation. Moreover, without consid- eration of OTDF, flow rate of the first chamber is 16.9g/s, the second is 40.8g/s, and the highest dimensionless temperature is 0.700. Double inlet with serpentine channel has good effect on heat transfer and simple structure. To meet temperature requirement while taking the OTDF into consideration, flow rate of the first chamber is 18.2 g/s, the second is 25.4g/s, the third is 5.3g/s, and the highest dimensionless temperature is 0.752. Through multiprogram design, a better cooling effect has been achieved by using three cooling air inlets and multi-turn channel under no film cooling condition.

关 键 词：涡轮 冷却 管网计算 三维温度场计算 气热耦合计算 

分 类 号：V235.1[航空宇航科学与技术—航空宇航推进理论与工程]