ENDWALL CONTOURING FOR A CONICAL ENDWALL

摘要

A turbine stage (100) includes an array of airfoils (10) spaced apart circumferentially to define a flow passage (50) therebetween for channeling a working medium. The airfoils (10) extend radially outward from an inner endwall (20) located at a hub side thereof. The inner endwall (20) is inclined at an angle (α1) to an engine axis (40) such that the flow passage (50) is divergent from an upstream side (60) to a downstream side (70). The inner endwall (20) is non-axisymmetric about the engine axis (40), having a mid-passage bulge (22) located between circumferentially adjacent first (10a) and second (10b) airfoils. The bulge (22) has a peak at a position between 20-60% CaxID and at a position between 30-70% pitchID.