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TECHNICAL PAPERS

Variations in Upstream Vane Loading With Changes in Back Pressure in a Transonic Compressor

[+] Author and Article Information
Douglas P. Probasco, Tim J. Leger, J. Mitch Wolff

Department of Mechanical & Materials Engineering, Wright State University, Dayton, OH 45435

William W. Copenhaver

Air Force Research Laboratory, Wright-Patterson Air Force Base, OH 44135

Randall M. Chriss

NASA Glenn Research Center, Cleveland, OH 43210

J. Turbomach 122(3), 433-441 (Feb 01, 1998) (9 pages) doi:10.1115/1.1303074 History: Received February 01, 1998
Copyright © 2000 by ASME
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References

Verdon, J. M., 1992, “Unsteady Aerodynamic Methods for Turbomachinery Aeroelastic and Aeroacoustic Applications,” AIAA Paper No. 92-0011.
Kim, K. H., and Fleeter, S., 1992, “Compressor Blade Row Unsteady Aerodynamic Response to Attached and Separated Flow Forcing Functions,” AIAA Paper No. 92-0147.
Henderson, G. H., and Fleeter, S., 1992, “Airfoil Wake and Linear Theory Gust Response Including Sub and Super-resonant Flow Conditions,” AIAA Paper No. 92-3074.
Johnston, R. T., Feiereisen, J. M., and Fleeter, S., 1994, “Rotor Wake and Potential Forcing Functions, Including Blade Row Interactions,” AIAA Paper No. 94-2975.
Johnston, R. T., and Fleeter, S., 1996, “Time-Resolved Variations of an IGV Flow Field in the Presence of a Rotor Potential Field,” AIAA Paper No. 96-2670.
Johnston, R. T., and Fleeter, S., 1997, “Rotor Blade Pressure Measurement in a High Speed Axial Compressor Using Pressure and Temperature Sensitive Paints,” AIAA Paper No. 97-0162.
Rao, K. V., Delaney, R. A., and Topp, D. A., 1992, “Turbine Vane-Blade Interaction,” Interim Report WL-RT-92-2002.
Law, C. H., 1989, “Two Axial Compressor Designs for a Stage Matching Investigation,” AFWAL-TR-89-2005.
Rao, K., and Delaney, R., 1990, “Investigation of Unsteady Flow Through Transonic Turbine Stage; Part 1: Analysis,” AIAA Paper No. 90-2408.
Benek, J. A., Donegan, T. L., and Suhs, N. E., 1987, “Extended Chimera Grid Embedding Scheme With Application to Viscous Flows,” AIAA Paper No. 87-1126-CP.
Baldwin, B., and Lomax, H., 1978, “Thin Layer Approximation and Algebraic Model for Separated Turbulent Flows,” AIAA Paper No. 78-257.
Pierzga,  M. J., and Wood,  J. R., 1985, “Investigation of the Three-Dimensional Flow Field Within a Transonic Fan Rotor: Experiment and Analysis,” ASME J. Eng. Gas Turbines Power, 107, No. 2, pp. 436–449.

Figures

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Schematic of SMI compressor rig
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Flow path through SMI compressor rig
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Transducer locations on IGV: (a) 95, (b) 89, (c) 83, (d) 70, (e) 50 percent IGV chord
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Actual transducer application on IGV
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Coordinate system used in VBI formulation
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Compressor performance map for: (a) open throttle; (b) above design; (c) peak efficiency; (d) below design; (e) near-stall
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Differenced nondimensionalized pressure time traces for various back pressures at 50 percent span and different chordwise positions on IGV: (a) 70, (b) 83, (c) 89, (d) 95 percent
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Differenced nondimensionalized pressure time traces for various back pressures at 75 percent span and different chordwise positions on IGV: (a) 70, (b) 83, (c) 89, (d) 95 percent
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Sketch of various shock positions
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First harmonic unsteady delta pressure phase results: 50 percent span
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First harmonic unsteady delta pressure phase results 75 percent span
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Comparison of first harmonic magnitude for 50 percent span and 75 percent span near-stall
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FFT of near-stall 95 percent chord experimental data
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Pressure time history for convergence check
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105 percent speed: below design Mach number contours; 50 percent span
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Frequency response comparison: 95 percent chord 50 percent span
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Comparison of computational and experimental pressure for below design (a) 50, (b) 70, (c) 83, (d) 89, (e) 95 percent chord location on IGV  

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