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Sumanta Acharya with a five-hole pneumatic probe unlike the magnitudes in figure 15 which are obtained from computations in the same passage with an incoming boundary layer of smaller thickness. The total pressure losses in figure 26 are much lower at the bottom part of the passage vortex with the fillet than without the fillet. This indicates that the Fillet 1 has reduced the passage vortex both in size and strength. Also revealed, the under-turning (yaw angle) of the exit flow with the Fillet 1 occurs over a larger region in the passage vortex core52. Similar results about the passage vortex and associated total pressure losses are observed with other fillet profiles of type (i)53. Figure 27 shows the effectiveness of another fillet profile of type (i) in reducing the passage vortex in a linear vane cascade. The quantities in figure 27 are measured in a plane normal to the vane pressure surface54. The velocity vectors in the figure show the structure of the pressure side vortex near the pressure surface. As can be clearly seen, the pressure side leg vortex is not complete for the filleted vane unlike the vortex for the unfilleted case. The spiral of the vortex is not complete in the same location for the filleted case as the passage vortex is weakened. This will eventually make the passage vortex weaker down the passage for the filleted vane. Also, the location of the passage vortex center appears to shift farther away from the pressure side for the filleted case compared to that for the unfilleted case. The turbulent kinetic energy magnitudes in figure 27 are much smaller for the filleted vane than those for the unfilleted vane. The k-contours indicate a well-defined vortex core for the unfilleted case while the k-contours for the filleted case are much uniform in the y/P direction. The fillet causes the passage vortex in this plane to fluctuate along y/P as the velocity component in this direction has the largest fluctuations with the fillet. On the contrast, the large fluctuations in the w-velocity component cause the passage vortex to fluctuate in the z/S direction for the unfilleted vane. Endwall Profiling: Endwall profiling is achieved in two ways- axial profiling along the passage with no pitchwise variation and non- axisymmetric profiling along the passage with profile variations in both the axial and pitchwise directions. The profiling is aimed either to accelerate the boundary layer fluid at the endwall or to reduce the pitchwise pressure gradient at the endwall. (i) Axial Profiling of the Endwall: Since there is no variation of the profile in the pitch direction, this profiling is also termed as the two dimensional axisymmetric contouring. The profiling is employed on either of the endwalls in the passage, but not on the both endwalls. The height of the profile increases over a smooth curve from the leading edge to the trailing edge such that aspect ratio of the exit plane or the throat area is unaffected as shown in figure 28. This type of endwall profile was studied in linear vane passages55. The axisymmetric profiles of the endwall upstream of the blade/vane passage such as the profile (b) of figure 28 are also studied56. Upstream profiles in the first stage nozzle guide vane are used for the gas path transition from the combustor chamber to the turbine inlet. In any profile shown in figure 28, the inlet velocity to the blade/vane passage decreases (due to increased passage area) and the flow acceleration through the passage increases (due to decreased passage area). This leads to a reduction in the boundary layer thickness and suppresses the growth of secondary flows on the endwalls. Also, the exit flow angle is expected to undergo less under-turning and over-turning due to the higher flow acceleration downstream with the endwall profiling extending through the passage. Fig. 28. Axisymmetric axial profiling of endwall: (a) endwall profile through blade passage, (b) endwall profile upstream of blade passage. Fig. 29. Streamwise velocity and secondary velocity vectors at 0.90Cax in a linear vane passage with endwall profiling through passage aft. Source: See Note 55. (Burd) 379PDF Image | Turbine Blade Aerodynamics
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