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TECHNICAL PAPERS

Implementation of a Compressor Face Boundary Condition Based on Small Disturbances

[+] Author and Article Information
John W. Slater

John H. Glenn Research Center at Lewis Field, MS 86-7, 21000 Brookpark Road, Cleveland, OH 44135e-mail: john.w.slater@grc.nasa.gov

Gerald C. Paynter

The Boeing Company, MS 67-LF P.O. Box 3707, Seattle, WA 98124e-mail: gerald.c.paynter@boeing.com

J. Turbomach 123(2), 386-391 (Feb 01, 2000) (6 pages) doi:10.1115/1.1344884 History: Received February 01, 2000
Copyright © 2001 by ASME
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References

Mayer,  D. W., and Paynter,  G. C., 1994, “Boundary Conditions for Unsteady Supersonic Inlet Analyses,” AIAA J., 32, No. 6, pp. 1200–1206.
Suresh, A., Townsend, S. E., Cole, G. L., Slater, J. W., and Chima, R., 1999, “Analysis of Inlet-Compressor Acoustic Interactions Using Coupled CFD Codes,” AIAA Paper No. 99-0749.
Chung, J. K., and Cole, G. L., 1995, “Comparison of Compressor Face Boundary Conditions for Unsteady CFD Simulations of Supersonic Inlets,” AIAA Paper No. 95–2627.
Paynter, G. C., 1998, “Modeling the Response From a Cascade to an Upstream Convective Velocity Disturbance,” AIAA Paper No. 98–3570.
Freund, D. D. and Sajben, M., 1997, “Reflection of Large Amplitude Acoustic Pulses from an Axial Flow Compressor,” AIAA Paper No. 97–2879.
Sajben, M., 1999, “Prediction of Acoustic, Vorticity, and Entropy Waves Generated by Short-Duration Acoustic Pulses Incident on a Blade Row,” ASME Paper No. 99-GT-148.
Paynter,  G. C., 1997, “Response of a Two-Dimensional Cascade to an Upstream Disturbance,” AIAA J., 35, No. 3, pp. 434–440.
Paynter,  G. C., Clark,  L. T., and Cole,  G. L., 1998, “Modeling the Response From a Cascade to an Upstream Acoustic Disturbance,” AIAA J., 38, No. 8, pp. 1322–1330.
Chung, J., Slater, J. W., Suresh, A., and Townsend, S. E., 1999, “NPARC v3.1 User’s Guide,” NASA TM-1999-209058.
Wasserbauer, J. F., Shaw, R. J., and Neumann, H. E., 1975, “Design of a Very-Low-Bleed Mach 2.5 Mixed-Compression Inlet With 45 Percent Internal Contraction,” NASA TM X-3135.
Shapiro, A. H., 1954, The Dynamics and Thermodynamics of Compressible Fluid Flow, Ronald Press Company, New York.

Figures

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Flow schematic after the disturbance/blade passage interaction. An acoustic disturbance travels upstream to the left.
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Flow schematic prior to the disturbance blade passage interaction. The disturbance approaches the blade pair from the left.
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Time history of the static pressure for a +10 precent step pressure perturbation in a straight annular duct
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Time history of the static pressure for ±10 percent step circumferential velocity perturbations
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The time histories of the pressure at sensor 1 for the Paynter small-disturbance boundary condition
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The time histories of the pressure at sensor 2 for the Paynter small-disturbance boundary condition
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The time histories of the pressure at sensor 3 for the Paynter small-disturbance boundary condition
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The time histories of the pressure at sensor 2 for the Chung–Cole, Mayer–Paynter, and constant-velocity boundary conditions
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The time histories of the terminal shock position subject to a free-stream pressure disturbance

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