涡轮动叶变冲角气动负荷试验研究  

Experimental Investigation on Aerodynamic Load of a Turbine Rotor Blade Under Different Incidences

作　　者：鞠凤鸣[1,2] 韩万金[2] 

机构地区：[1]哈尔滨汽轮机厂有限责任公司,哈尔滨150040 [2]哈尔滨工业大学能源科学与工程学院,哈尔滨150001

出　　处：《汽轮机技术》2011年第6期441-443,共3页Turbine Technology

摘　　要：在环形涡轮叶栅低速风洞上,对某型采用后部加载及正弯曲设计的高负荷动叶进行了静态吹风试验。应用五孔球型测针,详细测量了在3个冲角下由栅前至栅后7个横截面内气流参数沿叶高和节距的分布,同时对各冲角下9个不同叶高截面静压系数也进行了测量。试验结果表明,采用沿叶高改变吸力面最低压力点的后部加载叶型并结合叶片的正弯,能够在保持静压沿叶高分布均匀的条件下,显著降低端部横向压力梯度,增大主流区叶型的气动负荷。In a low-speed annular cascade wind tunnel, static aerodynamic tests were performed on an aft-loaded and positively curved rotor blade cascade with high loading. With the application of five-hole pin ball, the flow parameters in seven cross sections along the blade height and pitch at three incidences were measured in detail from the front to the back of the blade cascade. In the mean time, the profile static pressure coefficients along blade height were also measured under the three incidences. The results showed that, with the application of the aft-loaded profiles with variable minimum pressure points along blade height and the blade positive curving to the design of rotor blade, the endwall transverse pressure gradient was reduced greatly and the aerodynamic loading on the blade profile in main stream region was increased, which not only decreased the secondary loss, but also enhanced the load bearing capacity of the blade cascade.

关 键 词：涡轮叶栅 高负荷 正弯叶片 后部加载 试验研究 

分 类 号：V211.7[航空宇航科学与技术—航空宇航推进理论与工程]