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TECHNICAL PAPERS

Nonuniform Flow in a Compressor Due to Asymmetric Tip Clearance

[+] Author and Article Information
Seung Jin Song, Seung Ho Cho

School of Mechanical and Aerospace Engineering, Seoul National University, Seoul 151-742, Korea

J. Turbomach 122(4), 751-760 (Feb 01, 2000) (10 pages) doi:10.1115/1.1308569 History: Received February 01, 2000
Copyright © 2000 by ASME
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References

Figures

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Blade and radius scale views of a compressor stage
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Schematic of the tip clearance flow model of Martinez-Sanchez 14
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Geometry of compressor tip vortex roll up
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Coordinate system for the model
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Radial distributions of axial velocity, absolute tangential velocity, and relative flow angle at rotor exit predicted by the new RSC model
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Radial distributions of axial velocity, absolute tangential velocity, and absolute flow angle at stator exit predicted by the new RSC model
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Radial distributions of axial velocity, absolute tangential velocity, and relative flow angle at rotor exit predicted by the RC model of Park 12
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Radial distributions of axial velocity, absolute tangential velocity, and absolute flow angle at stator exit predicted by the RC model of Park 12
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Upstream axial velocity perturbation versus azimuthal angle
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Upstream pressure perturbation versus azimuthal angle
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Rotor blade loading perturbation versus azimuthal angle
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Perturbation in the average pressure on rotor hub versus azimuthal angle
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Predicted total and pressure rotordynamic coefficients versus operating flow coefficient
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Predicted cross rotordynamic coefficients due to blade loading perturbation versus operating flow coefficient
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Predicted total and pressure rotordynamic coefficients versus design flow coefficient
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Predicted total and pressure rotordynamic coefficients versus design work coefficient
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Predicted total and pressure rotordynamic coefficients versus design reaction

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