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Sumanta Acharya 385 coolant jets from the pressure side at 30% axial chord seem to dislocate the lift-off line slightly downstream from their positions. The jet traces from the holes located upstream of the passage in figure 37 shows virtually very little or no traces near the pressure side and all jets near the suction side are deflected around the lift-off line. The strong leading edge horse-vortex is either lifting the jets or deflecting the jets even if they are shooting directly toward the leading edge. The jets from the middle holes in the upstream row have low momentum and are aimed toward the pressure side while the cross flow here is directed in the axial direction have low kinetic energy. Thus, these jets have small trajectories and are easily swept in the main flow as soon as they are ejected. The traces of the jets from the holes inside the passage, except those near the pressure side, are swept toward the suction side by the cross flow. Similar behavior of the jets inside a blade passage is also observed72. The 3rd to 5th jet from the pressure side at 30% axial chord and 2nd to 4th jet from the suction side at 60% axial chord are additionally pulled in by the passage vortex (see the lift-off line) and in cases, are entrained into the passage vortex at the hole location itself. The traces nearest the pressure side are almost parallel to the pressure side as the boundary layer is very thin here and flow behaves as inviscid. A single jet from one of the four holes at the pressure side corner interacts with and strengthens the jet downstream and the combined jet trajectory is very long at this location. The jets at 90% axial chord and nearest the suction side in the previous two rows eject with high momentum due to the low wall static pressure. The main flow kinetic energy is also high at these locations because of its high speed. These keep these jet traces narrow and stick to the endwall for a longer distance. Also note that the last row of jets are covering a large area on the endwall as they are swept toward the suction side by the cross flow. These jets affect the cross flow as seen in the surface flow visualization of figure 37 (the top image). The streamlines downstream of the holes at 90% axial chord are parallel to the passage rather than being turned toward the suction side as compared to the streamlines upstream of these holes. Thus, these jets have weakened the cross flow near the passage exit. The effects of the same cooling holes as in figure 37 on the passage vortex structure and total pressure losses at the exit flow are shown in figure 3873. But, the inlet blowing ratio for the data with the endwall coolant injection is now 2.0. The plots with no coolant injection are included in figure 38 for comparison. The dashed lines in the figure indicate the spanwise locations of the passage vortex cores. The passage vortex is identified in the vector plot at the location of the clockwise rotation and in the total pressure loss contour at the location of circular region with high loss magnitudes. As noted in both the vector and contour plots, the passage vortex with coolant flow is located much nearer the endwall than with no coolant flow. The momentum of the ejected coolant adds energy to the boundary layer fluid. Therefore, when the passage vortex entrains these boundary layer fluids, the total pressure losses near the bottom part of the passage vortex are reduced. Coolant jets can be injected from continuous slots located in the upstream endwall/platform of the blade passage inlet. This type of coolant flow is often termed as the slot-bleed injection. The readers are referred to note 74 for information on the secondary flow field behavior with the slot-bleed74. 4.3-9 Notes ______________________________ 1. B. Lakshminarayana, Fluid Mechanics and Heat Transfer of Turbomachinery (New York:John Wiley & Sons Inc., 1996). 2. S. L. Dixon, Fluid Mechanics, Thermodynamics of Turbomachinery, 3rd ed. (Oxford: Butterworth-Heinemann Ltd., 1995). 3. H. E. Gallus, J. Zeschky, and C. Hah, “Endwall and Unsteady Flow Phenomena in an Axial Turbine Stage,” ASME Tran. J. Turbomachinery 117 (1995): 562-570; E. Boletis, “Effects of Tip Endwall Contouring on the Three-Dimensional Flow Field in an Annular Turbine Nozzle Guide Vane: Part 1- Experimental Investigation,” ASME Tran. J. Engr for Gas Turbines and Power 107 (1985): 983-990; C. H. Sieverding, W. Van-Hove, and E. Boletis, “Experimental Study of the Three-Dimensional Flow Field in an Annular Turbine Nozzle Guidevane,” ASME Tran. J. Engr for Gas Turbines and Power 106 (1984): 437-444. 4. A. Duden, I. Raab, and L. Fottner, “Controlling the Secondary Flow in a Turbine Cascade by Three-Dimensional Airfoil Design and Endwall Contouring,” ASME Tran. J. Turbomachinery 121(1999): 191-199; S. P. Harasgama and C. D. Burton, “Film Cooling Research on the Endwall of a Turbine Nozzle Guide Vane in a Short Duration Annular Cascade: Part 1- Experimental Technique and Results,” ASME Tran. J. Turbomachinery, Vol. 114 (1992): 734-740. 5. R. P. Dring and W. H. Heiser, Turbine Aerodynamics, Chap.4 in Aerothermodynamics of Aircraft Engine Components, AIAA education series (New York: AIAA Inc., 1985). 6. L. Fielding, Turbine Design- The Effect of an Axial Flow Turbine Performance of Parameter Variation, (New York: ASME Press, 2000); J.P. Gostelow, Cascade Aerodynamics, (OxfordPergamon Press Ltd., Oxford, U.K., 1984).PDF Image | Turbine Blade Aerodynamics
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