Numerical research on the trailing-edge sweep of supersonic/transonic turbines

Although the sweep design used in fans and compressors has been the subject of considerable research and development, its application in turbines is relatively rare. This paper first studies the aerodynamic effects and mechanics of a general backward sweep in supersonic plane cascades. In response to the specific challenge of severe changes in working conditions, a new structure, combined with the characteristics of an unchanged throat and sweep around the trailing-edge, is proposed and studied. After two targeted modifications, the trailing-edge sweep is applied to a turbine stage. The results show that, similar to fans and compressors, the aerodynamic influence of the sweep in the turbine changes the working conditions and spanwise loading in spanwise tubes. Proper trailing-edge sweep design can weaken the strength of the 3D shock wave under similar flow conditions, providing a new approach for shock-weakening treatments. By applying the trailing-edge sweep, the turbine stage achieves an efficiency improvement of nearly 0.4%.