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4.3 Turbine Blade Aerodynamics Blade surface pressure distributions on the pressure surface are about the same for the annular cascade and linear cascade44. The radial pressure gradient on the pressure surface (annular cascade) is present only near at the hub side. On the contrary, the radial pressure gradient is present along the entire span on the blade surface and is larger in the first one- third of the surface in axial direction compared to the rest of the surface. When compared at the same corresponding radial location, the magnitudes of static pressure coefficient on the suction surface are always higher in the annular cascade than in the linear cascade due to the radial pressure gradient. However, the suction surface pressure coefficient distributions in the axial direction follow similar patterns in both types of cascade employing same blade geometry. Thus, the two dimensional local separation bubbles also appear on the blade suction surface in an annular passage. The vane suction surface flow pattern in an annular cascade is presented in figure 2145. The visualization reveals the asymmetric surface streamlines relative to the spanwise meridian unlike the streamline patterns on the suction surface in a linear cascade. In figure 21 also, the separation lines divide the near surface flow behavior into three regions as has been observed in case of a linear passage. The first region is the two dimensional laminar region extending from the leading edge to the inclined separation line (spanwise) between passage vortex separation lines. In the radial/spanwise direction this region is limited between the separation lines for passage vortex. Near surface flow simply follows the suction surface in the first region. The second region is the turbulent flow region that extends behind the inclined re-attachment line to the trailing edge in figure 21. Unlike that in the linear cascade (figure 7), the suction surface separation bubble formed here (figure 21) by these inclined separation and re-attachment lines is asymmetric. The third flow region, which is the three dimensional boundary layer region in figure 21 limited by the passage vortex separation line and endwall, is larger on the casing side than on the hub side. The separation lines extend all the way to the trailing edge. The separation line for the passage vortex at the casing is farther away from the casing than the separation line for the hub-end passage vortex line is from the hub wall. This is in accordance with the passage vortex movement observed in figure 18 for the annular cascade and as described, is caused by the radial imbalance of the radial forces. The inclination of the surface streamlines in the third region caused by the passage vortex funneling and entrapping fluid is an indication of the vortex strength. The three dimensional vortex flows near the hub and casing walls are enhanced in an annular rotor passage where the blades rotate relative to a stator passage. In the blade stage, there is a gap between the blade tip and casing to allow for rotation. Due to the pressure gradient from the blade pressure side to the suction side there is a leakage flow from the pressure side to the suction side in the tip gap. The tip- gap flows generate an additional vortex flows near the casing wall which develop and grow along with the casing side passage vortex in the rotor passage. The tip vortex influences the passage vortex from the casing wall. Figure 22 shows the tip-clearance vortex and passage vortex structures near Fig. 22. Measured secondary velocity vectors at rotor exit in an an- nular passage. Source: See Note 3. (Gallus) Fig. 23. Relative total pressure contours in an annular rotor passage showing vortex flows. PS= pressure side and SS= suction side. Source: See Note 47. 376PDF Image | Turbine Blade Aerodynamics
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