超临界高压动叶栅壁面静压分布的试验研究

EXPERIMENTAL STUDY ON THE SURFACE STATIC PRESSURE DISTRIBUTION IN SUPER-CRITICAL HIGH-PRESSURE ROTOR

在低速风洞上对某型超临界汽轮机高压级动叶栅进行了静态试验。详细测量总压损失由栅前至栅后的发生与发展以及静压系数在不同叶高沿叶型的分布。试验结果表明,具有后部加载叶型的正弯动叶片栅气动特性优良,叶型损失与二次流损失较小,出口气动参数沿叶高分布均匀,并且具有良好的冲角适应性.

Certain supercritical high-pressure stage rotor blade cascade of steam turbine was captive tested in a low speed wind tunnel. The emergence and development of total pressure losing was tested detailedly from the front cascade to back cascade, and static pressure coefficients distribution was tested along the blade at different spanwise. Experiment results indicated the blade that was designed with aft-loading and positive-curving type has even exit aerodynamics parameter distribution along spanwise and favorable incidence adaptability.