设计工况下非轴对称端壁造型方法对涡轮动叶性能的影响

To reveal the physical mechanism of non-axisymmetric end-wall control of secondary flow for turbine blades, a numerical study of the first stage rotor blade of a gas turbine under design conditions was carried out by using trigonometric function modeling method. Results show that good aerodynamic benefits can be obtained only when the appropriate non-axisymmetric end-wall radius perturbation is applied. The performance will be improved for a disturbance radius ranges from 5% to 10% of the blade height. Compared to the non-axisymmetric end-wall shape amplitude, the aerodynamic performance is more sensitive to the non-axisymmetric end-wall geometric location. This method can reduce reasonably the transverse pressure gradient and delay the development of passage vortex, and thus result in the weakening of intensity and dimension of channel vortex, and then the flow loss is reduced.