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Sumanta Acharya The axial pressure distributions along the blade surface (figure 3) change with the span location. The region below 14% span can be considered to be the boundary layer region in the figure. The difference between the free stream static pressure coefficient and endwall region static pressure coefficient Cp on the pressure surface is small and almost uniform. This suggests that pressure gradient on the pressure surface occurs mostly in the axial direction rather than in the spanwise direction. The differences in the suction surface Cp between the 50% span and below 14% span in figure 3 are significant and occur because of the strong cross flow from the pressure side to the suction side in the endwall boundary layer and the vortex leg along the suction surface13. The locations of the lowest Cp within the boundary layer occurs further downstream of the lowest Cp location in the mid-span free-stream region. The endwall cross flow drives the low momentum boundary layer fluid toward the suction surface-endwall junction and causes these observed differences in the Cp distributions. This is also the reason why the axial location of the lowest Cp in the boundary layer and the lowest Ps on the endwall are different. Also note that Cp magnitude decreases significantly from the endwall (i.e. 4.4% span) to the boundary layer edge (i.e. 13.5% span) all along the axial direction. Such spanwise pressure gradient drives the boundary layer fluid and the endwall region secondary flows toward the mid-span direction near the suction surface. The implications of such migrations are realized in the Heat Transfer Analysis section. The velocity distribution on the blade surface near the endwall is also shown in figure 3. The suction surface velocity in the endwall region is lower compared to the free-stream velocity in mid-span because of the influence of strong secondary flows and higher Cp around the suction side edge (i.e. at 4.4% span). As with the lowest Cp location, the associated peak suction surface velocity in the endwall region also moves down the axial direction relative to the peak velocity location at the mid-span. The difference in velocity distribution on the pressures side is opposite to what is observed on the suction surface between the mid-span location and endwall region. This can be attributed to the smaller pressure surface Cp near endwall as well as the thin boundary layer, which is also skewed and thicker toward the suction surface, downstream of the endwall separation line. Fig. 7. Surface oil-flow visualization on a linear blade surface and end-wall in a linear cascade. LE= leading edge, TE= trailing edge, and BL= boundry layer Source: See Note 14. With the knowledge of velocity and pressure distribution on the blade surface at the mid-span and near endwall, it is now appropriate to discuss the three dimensional flow on the blade surface as a whole. It is apparent by now that the blade suction surface flow near the endwall wall region becomes skewed and three dimensional due to the interaction of the boundary layer and flow separation on the suction surface and endwall. The flow visualization on the suction surface of a two dimensional linear blade in figure 7, as observed in Hodson and Dominy, clearly shows the near surface flow behavior14. The flow on the pressure surface is two dimensional for most part of the span as the oil streaklines indicating the surface streamlines are parallel to the endwall in the upper flow visualization of figure 7. The uniform pressure distribution along the pressure surface span (see figure 3) and very weak interaction of the boundary layers between the pressure surface and endwall are responsible for such flow behavior. However, the laminar boundary layer near the pressure surface leading edge may diffuse with a rise in surface pressure when the incoming flow is at high speed. In this case, the boundary layer separates along the line S6 and re-attaches along the line R6 creating a closed separation bubble along most of the span near the leading edge. The laminar boundary layer accelerates following the re-attachment and continues to grow along the pressure surface 367 toward the trailing edge. The two-dimensional separation bubble has no apparent influence on the secondary flows on the endwall.PDF Image | Turbine Blade Aerodynamics
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