摘要 针对高压涡轮导叶叶背侧出现的鼓包开裂现象,采用气热耦合数值计算方法研究了导叶后腔流动和换热。研究发现:后腔冲击结构的冷气分配不合理,造成叶背侧靠近下游区域冷却不充分,形成了较大的温度梯度,进而产生大的热应力导致叶背侧出现鼓包开裂现象。通过调整冲击孔几何参数,提出了两种改进方案。分析了两种改进方案的流动与换热情况,并与原型冷却结构的计算结果进行比较,发现改进方案2的冷却结构冲击孔的冷气流动更有序,冷气流量分配更合理,形成的冷却效果最好,有效降低了叶背侧的最高温度和温度梯度。 Aiming at the bulge and crack phenomenon on the pressure side in the high pressure turbine guide vane,the flow and heat transfer in the aft-cavity of vane were analyzed using the numerical calcula⁃tion method of conjugate heat transfer.Results showed that the distribution of cool-air in the rear cavity im⁃pact structure was not reasonable,which lead to insufficient cooling of the fault site and a large temperature gradient was generated after a long period of work.The thermal stress finally caused the bulge and crack.Two cooling schemes,the improved model 1 and the improved model 2,were obtained by adjusting the geo⁃metric parameters of the impinge holes.The flow and heat transfer conditions of the two schemes were ana⁃lyzed and compared with the calculated results of the initial model.It was found that in the cooling structure of the improved model 2 scheme,the cool air flow of impinge holes were more orderly and the cool air flow distribution were more reasonable,so that the maximum temperature and temperature gradient on the back of the vane was well reduced and the cooling effect was the best.
机构地区 中国航发四川燃气涡轮研究院
出处 《燃气涡轮试验与研究》 北大核心 2021年第1期34-40,共7页 Gas Turbine Experiment and Research
关键词 航空发动机 高压涡轮 导向叶片 冲击冷却 气热耦合分析 鼓包 裂纹 aero-engine high pressure turbine guide vane impingement cooling numerical simulation conjugate heat transfer analysis bulge crack
