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Sumanta Acharya Fig. 3. Pressure and velocity distribution on blade surface at different spanwise locations. Source: See Note 56 (Acharya). boundary layer separation can occur earlier leading to increased profile losses for the highly loaded blade. Refer to notes 5 and 8 for discussion on the limiting pressure and velocity distributions on the blade surfaces and provide guidelines to limit the wake region over a very small region at the trailing edge in the blade design8. 4.3-3 Flow Field in the Endwall Region The flow field near the hub endwall region of the blade passage is dominated by the boundary layer, strong pressure gradients, and cross flow in the pitchwise direction from the pressure side to the suction side. The resulting near-wall flow field is complex and consists of strong secondary flows and vortex roll-up9. When the endwall boundary layer approaches the blade row, a vortex is formed near the junction of the blade leading edge and the endwall. This vortex is termed as the leading edge horse- shoe vortex. The horse-shoe vortex splits at the leading edge, and propagates downstream into the passage on both the pressure side and the suction side of the blade passage forming two legs of the early passage vortex flows. Corner vortices are also induced in the corner formed by the blade and the hub endwall. The streamlines slightly above the endwall in figure 4 show some distinct features of the endwall boundary layer flow. These features are identified by the separation lines in the figure. The streamlines along the blade leading edge bifurcate as they approach the saddle point. The saddle point is the location on the endwall where the zero degree incidence line meets the separation line and corresponds to the lowest friction velocity. The incoming endwall boundary layer detaches along the separation line, and secondary vortical flows are formed in the regions immediately downstream and adjacent to the separation line. This is indicated by the high concentration of the streamlines adjacent to the separation line. The strong reverse flow in the vortex regions counter the boundary layer streamlines causing them to be concentrated more densely near the separation line. The leading edge horse-shoe vortex immediately downstream of the saddle point is clearly evident in figure 4. The region between the separation line and the blade suction side in figure 4 represents the suction-side leg of the horse shoe vortex10. The region along the separation line directed from the pressure side to the suction side represents the pressure-side leg of the horse-shoe vortex11, and is driven by the passage pressure gradients. The suction side leg vortex and pressure side leg vortex meet together in the mid-passage region where the two separation lines in the passage merge. This location occurs close to the suction surface, and the merger of the two vortices forms a stronger vortex known as the passage vortex. The passage vortex then travels along the blade suction surface toward the passage exit. The axial development and structures of these vortex flows will be analyzed further in Section 4.3-4. Downstream of the pressure side separation line, the endwall boundary layer region is very thin and skewed toward the suction side. This is evidenced by the streamline concentration being sparse in this region as they turn from the pressure side to the suction side. The strong vortical motions of the pressure side leg vortex entrain most of the fluid from the incoming boundary layer and a new boundary layer forms downstream. Comparing the streamlines in figure 4 with those in the mid-span regions in figure 1, it is clear that the turning of the streamlines inside the blade passage and around the leading edge is much greater near the Fig. 4. Streamlines showing separation lines in a near endwall plane of a linear blade passage. 365 Source: See Note 56 (Acharya).PDF Image | Turbine Blade Aerodynamics
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