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通过对两种不同叶盘连接结构的涡轮级进行气热耦合数值模拟,一是整体叶盘连接结构,二是榫接叶盘连接结构,研究了整体叶盘与榫接叶盘在叶片和轮盘之间传热效果方面的差异。对主流通道的流场、温度场、压力场,以及转子叶片、涡轮盘的温度分布进行分析,验证了数值模拟的合理性。在此基础上,对比分析了两种结构下涡轮转子叶片和涡轮盘的整体温度分布。结果表明:与常规榫接结构相比,整体叶盘结构中叶片温度下降,且主要集中在叶根处,降温幅度约为10~20K,涡轮盘温度有明显提高;在相同的工作条件下,整体叶盘在显著简化结构的同时,热应力显著增加,因此适用于短寿命的弹用发动机。
Through the numerical simulation of the air-heat coupling of the turbine stages with two different leaf disk connections, one is the overall leaf disk connection structure and the other is the tenon leaf disk connection structure. The effects of the integral leaf disk and the tenon leaf disk on the blades and wheels Difference in heat transfer between discs. The flow field, temperature field, pressure field and the temperature distribution of the rotor blades and turbine disk in the mainstream are analyzed to verify the rationality of the numerical simulation. On this basis, the overall temperature distribution of turbine rotor blades and turbine disks under two kinds of structures is comparatively analyzed. The results showed that the temperature of the blade in the leaf disc structure decreased compared with the conventional mortise-tenon structure, and the temperature was mainly concentrated at the root of the leaf. The cooling rate was about 10 ~ 20K and the temperature of the turbine disk was obviously increased. Under the same working conditions, Overall leaf disc significantly simplifies the structure at the same time, thermal stress increased significantly, it is suitable for short-lived bomb engine.