表面粗糙度对涡轮叶片吸力面边界层的影响

摘要

In order to study the effect of the increased surface roughness on turbine blade due to operation,erosion and corrosion,the effect of surface roughness on the development of suction side boundary layer in the design condition is simulated.The study indicates:The velocity distribution in boundary layer is more plump when roughness on blade surface increases.The aerodynamic loss is induced due to the decreased separation bubble caused by the decreased roughness.The transition is advanced with the enlarged surface roughness,so the boundary layer loss becomes remarkable.%为了研究涡轮叶片烧蚀、腐蚀以及积碳等引起的叶片表面粗糙度增大对吸力面边界层的影响，数值模拟分析了在设计工况下，表面粗糙度对低压涡轮叶片吸力面边界层发展的影响规律。结果表明：增加叶片表面粗糙度使边界层的速度分布趋于饱满；减小粗糙度可减弱边界层的分离，降低分离损失；增大粗糙度可诱发边界层提前发生转捩；粗糙度愈大，边界层的损失愈加显著。