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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

Figures

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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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Flow schematic after the disturbance/blade passage interaction. An acoustic disturbance travels upstream to 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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