Shock System Model of Highly Loaded Turbine Cascade

Abstract

To support the design of a two-dimensional turbine blade profile with reduced shock loss, an efficient model for shock system with separation shock in highly loaded turbine cascade needed to be established to realize parameterized shock losses prediction and analysis. The discussions on the model demonstrate that the effect of base pressure on shock losses can be achieved by controlling the width of the base region (the region between the pressure surface and suction surface trailing edge separation points). Increasing the trailing-edge wedge angle can increase the base pressure as well as the width of the base region, thus reducing the shock losses. Moreover, the pressure change caused by reducing the suction surface curvature downstream of the throat can reduce the loss caused by the reflected shock.