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TECHNICAL PAPERS

A Transport Model for the Deterministic Stresses Associated With Turbomachinery Blade Row Interactions

[+] Author and Article Information
Allan G. van de Wall, Jaikrishnan R. Kadambi

Department of Mechanical and Aerospace Engineering, Case Western Reserve University, Cleveland, OH 44106  

John J. Adamczyk

NASA Glenn Research Center, Cleveland, OH 44135

J. Turbomach 122(4), 593-603 (Feb 01, 2000) (11 pages) doi:10.1115/1.1312802 History: Received February 01, 2000
Copyright © 2000 by ASME
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References

Smith, L. H., Jr., 1970, “Casing Boundary Layers in Multistage Axial-Flow Compressors,” Flow Research in Blading, L. S. Dzung, ed., Elsevier Publishing Company, Amsterdam.
Mikolajczak, A. A., 1977, “The Practical Importance of Unsteady Flow” in: Unsteady Phenomena in Turbomach. AGARD CP-144, North Atlantic Treaty Organization.
Wu, C. H., 1952, “A General Theory of Three-Dimensional Flow in Subsonic and Supersonic Turbomachines of Axial-, Radial-, and Mixed-Flow Types,” NACA TN 2604.
Sharma, O. P., Stetson, G. M., Daniels, W. A., Greitzer, E. M., Blair, M. F., and Dring, R. P., 1996, “Impact of Periodic Unsteadiness and Heat Load in Axial Flow Turbomachines,” Final report from United Technologies Corporation, Pratt & Whitney for NASA Lewis Research Center.
Smith,  L. H.1966, “Wake Dispersion in Turbomachines,” ASME J. Basic Eng., 88, pp. 688–690.
Adamczyk,  J. J., 2000, “Aerodynamic Analysis of Multistage Turbomachinery Flows in Support of Aerodynamic Design,” ASME J. Turbomach., 122, pp. 189–217.
Adamczyk, J. J., 1996, “Wake Mixing in Axial Flow Compressors,” ASME Paper No. 96-GT-29.
Smith, L. H., Jr., 1996, “Discussion of ASME Paper No. 96-GT-029: Wake Mixing in Axial Flow Compressors,” ASME Turbo Expo, Birmingham, England, June 10–13.
van de Wall, A. G., 1999, “A Transport Model for the Deterministic Stresses Associated With Turbomachinery Blade Row Interactions,” Ph.D. Thesis, Department of Mechanical and Aerospace Engineering, Case Western Reserve University.
Adamczyk, J. J., 1985, “Model Equation for Simulating Flows in Multistage Turbomachinery,” ASME Paper No. 85-GT-226.
Hill,  P. G., Schaub,  U. W., and Senoo,  Y., 1963, “Turbulent Wakes in Pressure Gradients,” ASME J. Appl. Mech., 30, pp. 518–524.
McFarland,  E. R., 1984, “A Rapid Blade-to-Blade Solution for Use in Turbomachinery Design,” ASME J. Eng. Gas Turbines Power, 106, pp. 376–382.
Hoyniak, D., and Verdon, J. M., 1994, “Steady and Linearized Unsteady Transonic Analyses of Turbomachinery Blade Rows,” presented at the Seventh International Symposium on Unsteady Aerodynamics and Aeroelasticity of Turbomachines, Fukuoka, Japan, Sept. 25–29.
Verdon, J. M., Barnett, M., Hall, K. C., and Ayer, T. C., 1991, “Development of Unsteady Aerodynamic Analyses for Turbomachinery Aeroelastic and Aeroacoustic Applications,” NASA CR 4405.
Celestina,  M. L., Mulac,  R. A., and Adamczyk,  J. J., 1986, “A Numerical Simulation of the Inviscid Flow Through a Counterrotating Propeller,” ASME J. Eng. Gas Turbines Power, 108, pp. 187–193.
Adamczyk,  J. J., Celestina,  M. L., Beach,  T. A., and Barnett,  M., 1990, “Simulation of Three-Dimensional Viscous Flow Within a Multistage Turbine,” ASME J. Biomech. Eng., 112, pp. 370–376.
Wisler, D. C., 1977, “Core Compressor Exit Stage Study, Vol. I—Blading Design,” NASA CR-135391.
Valkov, T., 1997, “The Effect of Upstream Rotor Vortical Disturbances on the Time-Average Performance of Axial Compressor Stators,” Gas Turbine Laboratory Report No. 227, MIT.
Sharma, O. P., 1997, personal communications.
Barankiewicz, W. S., and Hathaway, M. D., 1997, “Effects of Stator Indexing on Performance in a Low Speed Multistage Axial Compressor,” ASME Paper No. 97-GT-496.
Van Zante, D. E., Adamczyk, J. J., Strazisar, A. J., Okiishi, T. H., 1997, “Wake Recovery Performance Benefit in a High-Speed Axial Compressor,” ASME Paper No. 97-GT-535.

Figures

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Change in efficiency for a four stage axial compressor operating at two axial gaps 1
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Change in peak overall efficiency for a reaction turbine from data of WRIGHT AERONAUTICAL CORP 3
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Illustration of how a wake stretching in a diffusing duct simulates compressor flows
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Illustration of how a wake compressing in an accelerating duct simulates turbine flows
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Pitchwise average normalized Kexit for the 45 deg turning duct (no viscosity)
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Mixing loss benefit for several inlet wake defects
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Pitchwise average Kexit versus inlet wake angle for the 40 deg turbine, no viscosity
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Distribution of normalized Kexit for the 40 deg turbine (no viscosity)
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Transport of disturbances through GE-LSRC with θw=−49.7 deg
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Deterministic stresses versus pitch for GE-LSRC, no viscosity
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Audit of normalized Kexit versus pitch for GE-LSRC
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Transport of disturbances through PW-LPT with θw=60 deg
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Deterministic stresses versus pitch for PW-LPT, no viscosity
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Audit of normalized Kexit versus pitch for PW-LPT.

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