考虑热障涂层及冷却结构影响的某F级燃气轮机火焰筒数值研究

Numerical Study on Combustor Liner of F-class Gas Turbine Considering the Effect of Thermal Barrier Coatings and Cooling Structures

以某F级燃气轮机燃烧室火焰筒为研究对象,考虑热障涂层及冷却结构对火焰筒气动传热影响,基于流热固耦合方法对额定工况下的火焰筒进行了内部流场、温度场和应力场分析,并将数值分析结果与火焰筒实际损伤情况进行对比。结果表明:数值分析结果的火焰筒高应力区域与火焰筒实际损伤区域基本吻合,采用流热固耦合方法可以预测火焰筒实际损伤情况;不同位置的热障涂层陶瓷层隔热效果相近;基体和热障涂层陶瓷层在冷却结构附近的区域均为高应力区域。

Taking the combustor liner of F-class gas turbine as the research object,analysis was carried out on the internal flow field,temperature field and stress field of the combustor liner under rating operation conditions based on fluid-thermal-solid coupling method,considering the effect of thermal barrier coatings and cooling structures on the aerodynamic heat transfer of the combustor liner.The results of numerical analysis were compared with the actual damage situation of the combustor liner.Results show that the high stress areas are basically consistent with the actual damaged regions of the combustor liner,thus the fluid-thermal-solid coupling method can be used to predict the damage situation of the combustor liner.The ceramic layers of the thermal barrier coatings at different locations have similar insulation effect.Both the substrate and the ceramic layers of the thermal barrier coatings in the vicinity of the cooling structures are areas of high stress.