整体叶盘对涡轮叶盘间传热强化的数值研究

Numerical Simulation on the Enhanced Heat Transfer Effects of the Blisk to the Blades and Disk in the Turbine

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。

Two turbine stages with different linking structures between blades and disk are studied by u- sing a CFD code. One of them is a turbine with tenoning structure, the other is a turbine with blisk struc- ture. The distribution of velocity, pressure, temperature in the mainstream channels and the temperature distribution of the blades and disk are analyzed in order to confirm the rationality of the numerical simula- tion. Then the temperature distributions of blades and disk belonging to the different structures are com- pared to show the difference of heat transfer between blades and disk. The results show that the tempera- ture of blades in the blisk turbine is declining, especially at the blade root, the declining range is from 10K to 2OK, the temperature of the disk in the blisk turbine is increasing obviously relative to the conven- tional turbine with tenonning structure. Although the blisk structure is simpler than tenoning, structure, the thermal stress of the blade for the blisk turbine is heavily increasing. Therefore, the blisk turbine is adapted to the short-life missile engine.