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Sumanta Acharya as on the blade surface. This also results in high local thermal loading on the turbine passage walls. Figure 15 shows the turbulent kinetic energy and total pressure loss generated by the secondary vortices at two axial locations of the blade passage of figure 12. The total pressure loss is determined from the difference of local total pressure and the reference total pressure at the passage inlet. The axial locations of figure 15 correspond to the pitchwise planes H and I in figure 12. At Z/P<-0.30, in plane H, the magnitudes of Tke/V2 larger than 0.020 and Cpt larger than 0.30 can be considered to be located within the secondary vortex flow region. In plane I, the secondary vortex flow region is represented by the contours of Tke/V2 and Cpt for Z/P<-0.50. Turbulent kinetic energy decreases from the axial location H to the location I in the secondary vortex flow region because the flow accelerates as it travels downstream. Because of its size and the magnitude of the vorticity, the passage vortex is primarily responsible for the turbulent kinetic energy and the total pressure losses in the secondary flow region near the suction side. Note that in both the axial locations of figure 15 the high turbulent kinetic energy just above the endwall and outside the secondary flow region occurs because of the boundary layer flow. Also it is important to realize that in the axial location I near the exit plane, the total pressure losses in the passage vortex core region are more than five times the total pressure losses in the free stream region with Cpt<0.20. 4.3-6 Aerodynamics of 2-D Vane Cascade The results presented so far on the flow structure in a blade passage are very typical of other linear blade cascade studies reported36. The magnitudes of the flow quantities are different from one study to the other, but the pattern and arrangement of the secondary flows are similar. The secondary flow patterns in a two-dimensional vane cascade are also expected to be similar to that in a linear blade cascade. This is because the formation of the leading edge horse-shoe vortex is inevitable for the vane passage as well. The horse-shoe vortex is then driven by the endwall cross flow and pressure gradient in the passage forming the suction side leg and pressure side leg vortices. The secondary flows are weaker and smaller in a linear vane passage than in a linear blade passage because of the smaller flow turning and weaker endwall cross flow in the vane passage37. However, the same components of the secondary flows are present in both the vane and blade passages. Due to the weaker secondary flows in the vane passage, the pressure losses are smaller relative to those across a blade passage. Figure 16 presents the data measured in a linear vane cascade38. The pressure side leg vortex (clockwise rotating) and the suction side leg vortex (counter-clockwise rotating) at plane SS-1 in figure 16 are located near the pressure side and adjacent to the suction side of the vane, respectively. At a farther downstream location SS-3, the pressure side leg vortex is driven close to the suction side and pair up with counter- rotating suction side leg vortex to form the passage Fig. 16. Secondary velocity vectors and streamwise velocity contours show- ing vortex flow formations in a linear vane cascade. SS= suction surface and PS= pressure surface. Source: See Note 33. 373 vortex. Like the blade passage flow, the suction side leg Fig. 17. Static pressure and secondary velocity vectors across a plane in a vane passage of annular cascade. PS=pressure side and SS=suction side. Source: See Note 3. (Sieverding)PDF Image | Turbine Blade Aerodynamics
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