脉冲爆震驱动下涡轮流场的非定常特征研究

To reveal the influence of the pulse detonation unsteady characteristics on the turbine flow field， a three-dimensional numerical model of the GE-E³ two-stage high pressure turbine was established. The detonation chamber outlet parameters were used as the boundary conditions of the turbine inlet to study the turbine flow driven by detonation. The elementary flow at 50% blade height was analyzed，and then the separation flow on the blade surface and the leakage flow in the tip clearance were studied. The results showed that the gas flow ran at supersonic speeds through the turbine channel，resulting in obvious oblique incision expansion and free expansion outside the cascade. The interaction between the leading shock and the blade changed the airflow attack angle significantly and produced local adverse pressure gradients，resulting in severe flow separation on the blade surface. The leading shock acting on the rotor blade increased the pressure difference on both sides of the tip clearance，and enhanced shearing and mixing between the leakage flow and the mainstream，resulting in a significant increase in entropy in the mainstream area.