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Sumanta Acharya originates at the same location where the passage vortex starts to form (merging point of the counter-rotating vortex legs). The wall vortex stays above the passage vortex and is driven along with the passage vortex. The small corner vortex induced at the junction of blade leading edge and endwall (see figure 8) by the horse-shoe vortex is driven along the pressure side and suction side edge with the two main vortex legs. In Wang, et al., they are identified as the pressure side leading edge vortex and suction side leading edge vortex, respectively29. They remain small as they travel inside the passage and their sense of rotation are opposite to the rotation of the main vortex legs they are associated with. The pressure side leading edge corner vortex sticks along the pressure surface corner near the leading edge as shown in figure 10. When it enters the passage farther downstream, it is also driven toward the suction side of the adjacent blade along with the pressure side leg vortex by the endwall cross-flow and pressure gradient. The suction side leading edge corner vortex on the other hand remains adjacent to the suction side edge until it meets with pressure side leg vortex from the neighboring blade. The corner vortices are not visible in the smoke flow visualization as the large vortex legs entrain most of the smoke in the flow and enough smoke is not available to generate their small patterns clearly. The three- dimensional structures of different vortex flows in a blade passage sketched in figure 11 are adopted directly from Wang, et al.30. The sketch shows two additional small vortex flows located along the pressure surface corner and suction surface corner. They originate about half way downstream in the passage. The existence of such corner vortices is indicated by the high local mass transfer results at the blade surface-endwall corner in Goldstein et al.31. These corner vortices rotate in the same direction as the rotation of the suction side leg vortex. The time-averaged structures of the passage vortex in the same flow as in figure 10 are shown at two axial locations in figure 12. The data presented is measured with a five-hole pressure probe32. The velocity vectors are determined based on the resolved components33. The plane H in figure 12 is located about half way down the passage and the plane I is located near the exit of the passage. Unlike figure 11, the flow is being viewed in the axial direction and therefore, the suction surface is on the left hand side in the plots of figure 12. Thus, the rotation of the passage vortex is in the clockwise direction in the velocity vector plots. The existence of the suction side leg vortex is not apparent in the vector plots as it becomes weak in the downstream locations. In a small region just above the passage vortex and adjacent to suction surface at plane I, the vectors seem to turn counter-clockwise indicating the presence of the wall vortex or suction side leg vortex. However, the vortex is clearly apparent in the vorticity plots in figure 12. The positive axial vorticity indicates the passage vortex while the negative axial vorticity located above the positive region indicates the suction side leg vortex or the wall vortex. The same arrangement of the vortex systems in the downstream locations have been observed in the flow visualization. The vortex center is located at the location of the maximum Fig. 12. Velocity vectors and axial vorticity representing passage vortex at suction side. SS=suction side, Z=pitchwise distance from pressure side, and ωx=axial vorticity. 371 vorticity in congruence with the forced vortex motion. Fig. 13. Axial vorticity downstream of passage exit in a linear blade cas- cade. VP= passage vortex, Vsh=suction side leg vortex, and Vwip= wall vortex. Source: See Note 56 (Acharya).PDF Image | Turbine Blade Aerodynamics
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