Evolution of Upstream Propagating Shock Waves From a Transonic Compressor Rotor

[+] Author and Article Information
Anil Prasad

Aerodynamics Division, Pratt and Whitney Aircraft Engines, East Hartford, CT 06108

J. Turbomach 125(1), 133-140 (Jan 23, 2003) (8 pages) doi:10.1115/1.1516813 History: Received October 28, 2001; Online January 23, 2003
Copyright © 2003 by ASME
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Ferri, A., 1964, “Aerodynamic properties of supersonic compressors,” Aerodynamics of Turbines and Compressors, High Speed Aerodynamics and Jet Propulsion, Vol. X, ed., W. R. Hawthorne, Princeton University Press, Princeton, NJ.
Probasco,  D. P., Leger,  T. J., Wolff,  J. M., Copenhaver,  W. W., and Chriss,  R., 2000, “Variations in Upstream Vane Loading with Changes in Back Pressure in a Transonic Compressor,” ASME J. Turbomach., 122, pp. 433–441.
Giles,  M. B., 1988, “Non-Reflecting Boundary Conditions for Euler Equation Calculations,” AIAA J., 28, pp. 2050–2058.
Kerrebrock,  J. L., and Mikolajczak,  A. A., 1970, “Intra-stator Transport of Rotor Wakes and its Effect on Compressor Performance,” ASME J. Eng. Power, 92, pp. 359–368.
Ni,  R.-H., 1982, “A Multiple-Grid Scheme for Solving Euler Equations,” AIAA J., 20, pp. 1565–1571.
Davis, R. L., Ni, R.-H., and Carter, J. E., 1986, “Cascade Viscous Flow Analysis Using Navier-Stokes Equations,” AIAA Pap., Paper No. 86-0033.
Ni, R.-H., and Bogoian, H., 1989, “Predictions of 3-D Multistage Turbine Flow Fields Using a Multiple-Grid Euler Solver,” AIAA Pap., Paper No. 89-0233.
Ni, R.-H., and Sharma, O. P., 1990, “Using a 3-D Euler Flow Simulation to Assess Effects of Periodic Unsteady Flow Through Turbines,” AIAA Pap., Paper No. 90-2357.
Davis, R. L., Shang, T., Buteau, J., and Ni, R.-H., 1996, “Prediction of 3-D Unsteady Flow in Multi-stage Turbomachinery using an Implicit Dual Time-Step Approach,” AIAA Pap., Paper No. 96-2565.
Wilcox, D. C., 1998, Turbulence Modeling for CFD, DCW Industries, Inc.
Morfey,  C. L., and Fisher,  M. J., 1970, “Shock-wave Radiation from a Supersonic Ducted Rotor,” Aeronaut. J., Royal Aeronautical Society, , 74, pp. 579–585.
Rudnick,  I., 1953, “On the Attenuation of a Repeated Sawtooth Shock Wave,” J. Acoust. Soc. Am., 25, pp. 1012–1013.
Dring,  R. P., and Oates,  G. C., 1990, “Throughflow Theory for Nonaxisymmetric Turbomachinery Flow—Part I: Formulation,” ASME J. Turbomach., 112, pp. 320–327.
van Zante,  D. E., Strasizar,  A. J., Hathaway,  M. D., and Okiishi,  T. H., 2000, “Recommendations for Achieving Accurate Numerical Simulation of Tip Clearance Flows in Transonic Compressor Rotors,” ASME J. Turbomach., 122, pp. 733–742.
Chauvin, J., Sieverding, C., and Griepentrog, H., 1970, “Flow in Cascades with a Transonic Regime,” Flow Research on Blading, ed., L. S. Dzung, pp. 151–189, Elsevier.
Sharma, O. P., and Tan, C. S., 1999, “Impact of Unsteadiness Induced by Adjacent Airfoil Rows on the Performance, Structural Integrity and Stalling Characteristics of Axial Flow Compressors,” Blade Interference Effects in Axial Turbomachinery Stages, von Karman Institute.
Smith, L. H., 1970, “Casing Boundary Layers in Multistage Axial-flow Compressors,” Flow Research on Blading, ed., L. S. Dzung, 275–304, Elsevier.
Mikolajczak, A. A., 1976, “The Practical Importance of Unsteady Flow,” AGARD Conf. Proc., on Unsteady Phenomena in Turbomachinery, 177 .
Hetherington, R., and Moritz, R. R., 1976, “Influence of Unsteady Flow on the Design and Operation of Aero Engines,” AGARD Conf. Proc., on Unsteady Phenomena in Turbomachinery, 177 .
Gorrell, S. E., Okiishi, T. H., and Copenhaver, W. W., 2002. “Stator-Rotor Interactions in a Transonic Compressor: Part 1—Effect of Blade-Row Spacing on Performance,” ASME Paper GT-2002-30494.
Koch,  P. J., Probasco,  D. P., Wolff,  J. M., Copenhaver,  W. W., and Chriss,  R., 2000, “Transonic Compressor Influences on Upstream Surface Pressures with Axial Spacing,” J. Propul. Power, 117, pp. 474–476.
McAlpine, A., and Fisher, M. J., 2000, “On the Prediction of “Buzz-Saw” Noise Generated by an Aeroengine,” AIAA Pap., Paper No. 2000–2095.


Grahic Jump Location
Locus of the passage centerline overlayed on contours of normalized static pressure in (a), and the variation of static pressure along the passage centerline in (b), for the 2-D inviscid computation
Grahic Jump Location
Definition of axial line along which static pressure is interpolated, with contours of unit relative Mach number
Grahic Jump Location
Axial pressure variations from the 2-D inviscid and viscous simulations are shown as solid lines, with the corresponding envelopes predicted from the semi-analytical model being shown with broken lines
Grahic Jump Location
Comparison between measurement and 3-D viscous computation along the passage centerline at 92% span of (a) normalized total velocity, and (b) relative yaw angle. Experimental data are denoted by symbols and the solid lines correspond to the two consecutive computational planes between which the measurements lie.
Grahic Jump Location
Axial pressure variations from the 3-D viscous and inviscid simulations are shown as solid lines, with the corresponding envelopes predicted from the semi-analytical model shown with broken lines
Grahic Jump Location
Axial variation of normalized mass-averaged entropy due to the upstream propagating shock system (–) and the total entropy generated by the rotor ([[dashed_line]]). Results from the 3-D viscous simulation are displayed.
Grahic Jump Location
Upstream variation of normalized circumferential static pressure distortion at four spanwise locations with the indicated inlet relative Mach numbers, from the 3-D viscous simulation
Grahic Jump Location
Circumferential variation of normalized total velocity at (a) 80% span and 5% chord upstream of the leading edge, and (b) 92% span and 38% chord upstream of the leading edge. The solid line is the prediction from the 3-D viscous simulations and the symbols represent experimental data.
Grahic Jump Location
Variation of the induced circumferential pressure distortion from an (steady) isolated rotor calculation compared to the same rotor embedded in a (time-accurate) multi-stage simulation. Results from 3-D viscous simulations are shown.




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