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4.3 Turbine Blade Aerodynamics Note that the passage vortex center in both the vector and vorticity plots moves farther away from the endwall (Y/S=0.0 location) as the passage vortex travels from location H to I in figure 12. This is also consistent with the flow visualization in figure 11. The axial vorticity magnitudes of the passage vortex in plane I are somewhat smaller than those in plane H. The flow turns further away from the axial direction in plane I resulting in smaller component of vorticity in the axial direction. However, the axial vorticity of the wall vortex increases in plane I as the intensity of this vortex grows as it is driven along with the passage vortex. The high negative axial vorticity at the bottom left corner in plane I in figure 12 indicates the suction side corner vortex34. The corner vortices are less likely to develop if the blade surface-endwall corner is filleted. The induced wall vortex, corner vortices, and additional vortices due to the trailing edge wake can be clearly identified in the flow downstream of a blade passage as in figure 13. The data are obtained from the same passage flow as in figure 12, but the location of the data is in a pitchwise plane, K, slightly downstream of the passage exit. The projection of the trailing edge at this plane is located at Z/P=0.0 and the axial direction is into the plane of the data. The positive axial vorticity and the negative axial vorticity just above the positive region in figure 13 also indicate the passage vortex and wall vortex, respectively. The locations of these vortices are even higher above the endwall compared to those in figure 12. In figure 13, the negative trailing edge wake vorticities on the left of the passage vortex form due to the wake in the adverse pressure gradient region at the trailing edge (see figure. 3). The corner vortices indicated by the negative vorticities about Z/P=0.0 and just above the endwall are enhanced by the trailing wake flows at this location. Figure 14 shows the influences of the various vortex structures on the flow orientation near the exit plane of a blade passage35. The uniformity of the flow angles near the suction side is severely affected by the vortex flow. Both the pitch and yaw angles in figure 14 are referenced to the axial +X direction. The blade turning angle at this location is about 65 degree. The positive pitch angles in the figure indicate that the flow is directed away from the endwall while the negative pitch angles indicate that the flow is directed toward the endwall. The under-turning of the flow yaw angles, which is less than 59 deg near Y/S=0.20, is very high near the passage vortex center. The high over-turning of the flow yaw angles, which is greater than 69 degree near Y/S=0.25, in the vicinity of the suction side occur because of the wall vortex or suction side leg vortex. The over-turning of the yaw angles also occur in the endwall boundary layer region at Y/S<0.12 where the cross-flow is very strong (see figure.4). Such under- and over-turning of the exit flows affect the blade loading and aerodynamic losses in the next row of blades in the turbine stage. 4.3-5 Pressure Loss The vortex structures are a significant source of pressure or aerodynamic losses across the blade passage. They entrain fluid from the free stream flow and enhance convective turbulent transport in the endwall region as well Fig. 14. Flow turning angles in a plane near exit of a blade passage. Fig. 15. Turbulent kinetic energy (Tke) and total pressure loss coefficient Cpt along a blade passage. SS=suction side, PS=pressure side, and ∆Pt=Pt-Pref. Source: See Note 25 (Saha). 372PDF Image | Turbine Blade Aerodynamics
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