A Research on Large Deflexion Supersonic Turbine Blade Rows

Abstract

Though supersonic gas dynamics has already been introduced in the design of supersonic turbine blades, many problems are left unsolved, which were made clear by our preliminary experiment of conventional blades. The problems are summarized as follows. (1) The shock boundary layer interaction around the leading edges.(2) The introduction of the effect of boundary layer displacement in the blade design.(3) The behavior of the supersonic flow around the trailing edges of turbine blades. Special model tests concerning these problems are performed to obtain new design data, which are applicable to improve the design method. A new design method to realize given velocity triangles is proposed. Using this method a new blade is designed, manufactured and tested to confirm the superior performances.