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TECHNICAL PAPERS

Recommendations for Achieving Accurate Numerical Simulation of Tip Clearance Flows in Transonic Compressor Rotors

[+] Author and Article Information
Dale E. Van Zante, Anthony J. Strazisar, Jerry R. Wood

NASA Lewis Research Center, Cleveland, OH 44135

Michael D. Hathaway

US Army Vehicle Technology Center, Cleveland, OH 44135

Theodore H. Okiishi

Iowa State University, Ames, IA 50011

J. Turbomach 122(4), 733-742 (Feb 01, 1999) (10 pages) doi:10.1115/1.1314609 History: Received February 01, 1999
Copyright © 2000 by ASME
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References

Wisler,  D. C., 1985, “Loss Reduction in Axial Flow Compressors Through Low-Speed Model Testing,” ASME J. Turbomach., 107, pp. 354–363.
Adamczyk,  J. J., Celestina,  M. L., and Greitzer,  E. M., 1993, “The Role of Tip Clearance in High-Speed Fan Stall,” ASME J. Turbomach., 115, pp. 28–38.
Hoying,  D. A., Tan,  C. S., Vo,  H. D., and Greitzer,  E. M., 1999, “Role of Blade Passage Flow Structures in Axial Compressor Rotating Stall Inception,” ASME J. Turbomach., 121, pp. 735–742.
Denton, J. D., 1996, “Lessons Learned From Rotor 37,” presented at the 3rd International Symposium on Experimental and Computational Aerothermodynamics of International Flows (ISAIF), Beijing, China, Sept. 1–6.
Dunham, J., and Meauze, G., 1998, “An AGARD Working Group Study of 3D Navier–Stokes Codes Applied to Single Turbomachinery Blade Rows,” ASME Paper No. 98-GT-50.
AGARD, 1998, “CFD Validation for Propulsion System Components,” J. Dunham, ed., AGARD-AR-355.
Suder,  K. L., and Celestina,  M. L., 1996, “Experimental and Computational Investigation of the Tip Clearance Flow in a Transonic Axial Compressor Rotor,” ASME J. Turbomach., 118, pp. 218–229.
Chima,  R. V., 1998, “Calculation of Tip Clearance Effects in a Transonic Compressor Rotor,” ASME J. Turbomach., 120, pp. 131–140.
Gerolymos,  G. A., and Vallet,  I., 1999, “Tip-Clearance and Secondary Flows in a Transonic Compressor Rotor,” ASME J. Turbomach., 121, pp. 751–762.
Kirtley, K. R., Beach, T. A., and Adamczyk, J. J., 1990, “Numerical Analysis of Secondary Flow in a Two-Stage Turbine,” Paper No. AIAA-90-2356.
Dawes,  W. N., 1987, “A Numerical Analysis of the Three-Dimensional Viscous Flow in a Transonic Compressor Rotor and Comparison With Experiment,” ASME J. Turbomach., 109, pp. 83–90.
Reid, L, and Moore, R. D., 1978, “Performance of Single-Stage Axial-Flow Transonic Compressor With Rotor and Stator Aspect Ratios of 1.19 and 1.26, Respectively, and With Design Pressure Ratio of 1.82,” NASA TP 1338.
Van Zante, D. E., Adamczyk, J. A., Strazisar, A. J., and Okiishi, T. H., 1997, “Wake Recovery Benefit in a High-Speed Axial Compressor,” ASME Paper No. 97-GT-535.
Strazisar, A. J., Wood, J. R., Hathaway, M. D., and Suder, K. L., 1989, “Laser Anemometer Measurements in a Transonic Axial-Flow Fan Rotor,” NASA TP 2879.
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. Turbomach., 112, pp. 370–376.
Shabbir, A., Zhu, J., and Celestina, M. L., 1996, “Assessment of Three Turbulence Models in a Compressor Rotor,” ASME Paper No. 96-GT-198.
Shabbir, A., Celestina, M. L., Adamczyk, J. J., and Strazisar, A. J., 1997, “The Effect of Hub Leakage Flow on Two High Speed Axial Compressor Rotors,” ASME Paper No. 97-GT-346.
Dean, R. C., Jr., 1954, “The Influence of Tip Clearance on Boundary-Layer Flow in a Rectilinear Cascade,” MIT Gas Turbine Laboratory Report No. 27-3.
Storer,  J. A., and Cumpsty,  N. A., 1991, “Tip Leakage Flow in Axial Compressors,” ASME J. Turbomach., 113, pp. 252–259.
Chen,  G. T., Greitzer,  E. M., Tan,  C. S., and Marble,  F. E., 1991, “Similarity Analysis of Compressor Tip Clearance Flow Structure,” ASME J. Turbomach., 113, pp. 260–271.
Van Zante, Dale E., Strazisar, Anthony J., Wood, Jerry R., Hathaway, Michael D., and Okiishi, Theodore H., 2000, “Recommendations for Achieving Accurate Numerical Simulation of Tip Clearance Flows in Transonic Compressor Rotors,” NASA TM 210347.
Barankiewicz, W. S., and Hathaway, M. D., 1998, “Impact of Variable-Geometry Stator Hub Leakage in a Low Speed Axial Compressor,” ASME Paper No. 98-GT-194.
Khalsa, A. S., 1996, “Endwall Blockage in Axial Compressors,” PhD. Dissertation, Massachusetts Institute of Technology, June.

Figures

Grahic Jump Location
LDV measurement locations for Rotor 35
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Contours of axial velocity (m/s) on the 92 percent span streamsurface from the LDV measurements. The clearance flow trajectory is marked by the dashed line.
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Contours of tangential velocity (m/s) at 33, 53, 72, and 92 percent rotor chord and midgap from the LDV measurements
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Detail of rotor mesh at 50 percent span (every other grid line is shown)
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Detail of mesh in the blade tip region
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Axial velocity contours (starting at 0 m/s with 20 m/s intervals) for the blade tip grid plane for configurations 1 and 3
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Tangential velocity contours (10 m/s interval) for the outer 20 percent of span on the cross-channel surface at 92 percent rotor chord for configurations 1 and 3
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Visualization of primary and induced clearance vortices
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Axial velocity contours (starting at 0 m/s with 20 m/s intervals) for the blade tip grid plane for configuration 3 with a slip boundary condition applied over the region shown
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Comparison of computed and measured operating range for Rotor 35 at 80 percent speed
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Axial velocity contours (starting at 0 m/s with 20 m/s intervals) for the blade tip plane for design speed with a grid similar to configuration 3
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Comparison of computed and measured operating range for Rotor 35 at design speed
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Relation of the clearance jet velocity and the shroud-wall velocity in the relative reference frame
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Total temperature excess of the clearance flow at 92 percent rotor chord along the survey line shown

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