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应用数值计算的方法,对采用气膜冷却的涡轮叶片在静止和旋转状态下的流场进行数值模拟,研究涡轮叶片在静止和旋转状态下冷却射流和主流的掺混流场结构.结果表明:涡轮叶片压力面极限流线在静止和旋转两种工况下的区别比较明显.旋转使得马蹄涡的尺度有所加强.压力面和吸力面侧都存在明显的反向涡对结构;在吸力面,反向涡对的对称性比压力面的好;反向涡对随着下游距离的增大逐渐减弱,同时旋转使得掺混流场的轨迹有向叶片径向偏转的趋势.旋转工况下涡轮压力面侧反向涡对的衰减速度和程度变化明显,吸力面侧涡对的涡心位置更靠近叶片壁面,涡的影响区域也较小.
Numerical simulation is used to simulate the flow fields of the turbine blades cooled by gas film under static and rotating conditions and to study the structure of cooling jet flow and mainstream flow field of turbine blades under static and rotating conditions.The results show that: Turbine blade pressure surface limit streamline static and rotation in the two conditions is more obvious difference.Coupled with the rotation of the horseshoe vortex has been strengthened.Special reverse vortex pairs structure exists on the pressure and suction side; , The symmetry of the reverse vortex pairs is better than that of the pressure surface; the reverse vortex pairs weaken with the increase of the downstream distance, and meanwhile the rotation makes the radial flow of the directional vanes of the mixed flow field tend to be deflected. The velocity and degree of decay of the reverse vortex pair on the turbine pressure surface side are obviously changed. The vortex center on the suction side vortex pair is closer to the blade wall surface, and the influence area of the vortex is also smaller.