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TECHNICAL PAPERS

The Fluid Dynamics of LPT Blade Separation Control Using Pulsed Jets

[+] Author and Article Information
Jeffrey P. Bons

Air Force Institute of Technology, Wright-Patterson AFB, OH 45433

Rolf Sondergaard, Richard B. Rivir

Air Force Research Laboratory, Wright-Patterson AFB, OH 45433

J. Turbomach 124(1), 77-85 (Feb 01, 2001) (9 pages) doi:10.1115/1.1425392 History: Received February 01, 2001
Copyright © 2002 by ASME
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References

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Matsunuma, T., Abe, H., Tsutsui, Y., and Murata, K., 1998, “Characteristics of an Annular Turbine Cascade at Low Reynolds Numbers,” presented at IGTI 1998 in Stockholm, Sweden, June 1998. Paper No. 98-GT-518.
Matsunuma, T., Abe, H., and Tsutsui, Y., 1999, “Influence of Turbulence Intensity on Annular Turbine Stator Aerodynamics at Low Reynolds Numbers,” presented at IGTI 1999 in Indianapolis, Indiana, June 1999, Paper No. 99-GT-151.
Helton, D., 1997, private communication.
Lin, J. C., Howard, F. G., Bushnell, D. M., and Selby, G. V., 1990, “Investigation of Several Passive and Active Methods of Turbulent Flow Separation Control,” AIAA Paper No. 90-1598.
Compton, D. A., and Johnston, J. P., 1992, “Streamwise Vortex Production by Pitched and Skewed Jets in a Turbulent Boundary Layer,” AIAA J., 30 , No. 3.
Henry, F. S., and Pearcey, H. H., 1994, “Numerical Model of Boundary-Layer Control Using Air-Jet Generated Vortices,” AIAA J., 32 , No. 12.
Chang,  R., Hsiao,  F. B., and Shyu,  R. N., 1992, “Forcing Level Effects of Internal Acoustic Excitation on the Improvement of Airfoil Performance,” J. Aircr., 29, No. 5, pp. 823–829.
Amitay, M., Kibens, V., Parekh, D., and Glezer, A., 1999, “The Dynamics of Flow Reattachment over a Thick Airfoil Controlled by Synthetic Jet Actuators,” AIAA Paper No. 99-1001.
Weaver, D., McAlister, K., and Tso, J., 1998, “Suppression of Dynamic Stall by Steady and Pulsed Upper-Surface Blowing,” AIAA Paper No. 98-2413.
Wu,  J., Lu,  X., Denny,  A., Fan,  M., and Wu,  J., 1998, “Post-stall flow control on an airfoil by local unsteady forcing,” J. Fluid Mech., 371, pp. 21–58.
Seifert,  A., Bachar,  T., Koss,  D., Shepshelovich,  M., and Wygnanski,  I., 1993, “Oscillatory Blowing: A Tool to Delay Boundary-Layer Separation,” AIAA J., 31, No. 11, pp. 2052–2060.
Kwong, A., and Dowling, A., 1994, “Active Boundary-Layer Control in Diffusers,” AIAA J., 32 , No. 12.
McManus, K., Legner, H., and Davis, S., 1994, “Pulsed Vortex Generator Jets for Active Control of Flow Separation,” AIAA Paper No. 94-2218.
Raghunathan, S., Watterson, J., Cooper, R., and Lee, S., 1999, “Short Wide Angle Diffuser with Pulse Jet Control,” AIAA paper No. 99-0280.
Bons,  J., Sondergaard,  R., and Rivir,  R., 2000, “Turbine Separation Control Using Pulsed Vortex Generator Jets,” ASME J. Turbomach., 123, pp. 198–206.
Sondergaard, R., Bons, J., and Rivir, R., 2000, “Control of Low-Pressure Turbine Separation Using Vortex Generator Jets,” accepted for publication in AIAA Power and Propulsion.
Bons, J., Sondergaard, R., and Rivir, R., 1999, “Control of Low-Pressure Turbine Separation Using Vortex Generator Jets,” AIAA Paper No. 99-0367.
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Figures

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Snapshots of flow over blade suction surface for F+=0.012 and 4 percent duty cycle (mean B=0.05); boundary layer profile positions indicated in Fig. 10; jet exit time history shown at top
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Low-speed linear cascade test facility
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Pulsed VGJ blade geometry, inset showing VGJ configuration (freestream into page)
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Loss coefficient γint versus inlet Reynolds number; Tuin=1 percent,Tuin=4 percent, and VBI prediction
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Integrated wake loss coefficient (γint) profiles normalized by loss coefficient for B=0 versus mean blowing ratio (B); data for pulsed blowing at 10 Hz (F+=0.31) and 50 percent duty cycle versus steady blowing at Re=25k and 63 percent Cx
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Instantaneous jet exit blowing ratios for various duty cycles all at 10 Hz (F+=0.31); data taken with subminiature hotfilm probe in VGJ exit at 63 percent Cx; Re=25k
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Normalized integrated wake loss coefficient (γintint0) versus pulsing duty cycle for constant maximum blowing ratio (B2max, see Fig. 5); data for pulsed blowing at 10 Hz (F+=0.31); Re=25k
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Normalized integrated wake loss coefficient (γintint0) versus dimensionless forcing frequency (F+) for two duty cycles and at constant mean blowing ratio (B=0.2 for 10 percent duty cycle and B=0.75 for 50 percent duty cycle); Re=25k
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Each figure includes a streamwise velocity (m/s) raster plot (y versus t) of wakes 5 and 6 over one VGJ pulse period (on the right) and a time history of jet exit velocity (with added time offset) and θdef (on the left); green lines indicate B=0 and B=2 limits; data for F+=0.012 (a), 0.031 (b), F+=0.12 (c), and 0.31 (d), 50 percent duty cycle, and mean B=0.75
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Each figure includes a streamwise velocity (m/s) raster plot (y versus t) of wakes 5 and 6 over one VGJ pulse period (on the right) and a time history of jet exit velocity (with added time offset) and θdef (on the left); green lines indicate B=0 & 2 limits; data for (a) F+=0.012, 4 percent duty cycle, and mean B=0.05 and (b) F+=0.031, 10 percent duty cycle, and mean B=0.2
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Boundary layer measurement stations on Blade 5

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