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TECHNICAL PAPERS

Backward Traveling Rotating Stall Waves in Centrifugal Compressors

[+] Author and Article Information
Z. S. Spakovszky

Gas Turbine Laboratory Department of Aeronautics and Astronautics, Massachusetts Institute of Technology, Cambridge, MA 02139

J. Turbomach 126(1), 1-12 (Mar 26, 2004) (12 pages) doi:10.1115/1.1643382 History: Received December 01, 2001; Revised March 01, 2002; Online March 26, 2004
Copyright © 2004 by ASME
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References

Figures

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Cross section and front view of NASA CC3 centrifugal compressor
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Implementation of modular, low-order dynamic system model for NASA CC3 centrifugal compressor
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1st through 6th harmonic system resonances of NASA CC3 centrifugal compressor for an operating point close to stall
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Energy function 1st through 4th harmonic resonances marked as diamonds in Fig. 3
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Motion of system modes when compressor is throttled into stall
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Motion of third harmonic (n=3) resonances of interacting rotor-stator system for variable interblade row spacing Δx=0[[ellipsis]]1
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Wave system for interacting rotor and stator blade-rows
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Unsteady pressure traces in the vaneless space during a stall ramp at 80% corrected design speed
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Unsteady pressure traces in the vaneless space during a stall ramp at 100% corrected design speed
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Pressure traces at impeller inlet, in the vaneless space, at the diffuser throat and in the diffuser passage along the path into instability at 80% corrected design speed
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“Classic Surge”: pressure traces in the vaneless space at 80% corrected design speed
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Velocity triangles at the impeller exit near the diffuser shroud (solid) and near the diffuser hub (dash). The air jet from the tangential injector nozzle is sketched as the dotted line. The vaneless space is not to scale.
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Speed lines at 80% and 100% corrected design speed: baseline (circles) and with flow control (pluses)
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Pressure traces in the vaneless space during a stall ramp with air injection at 100% corrected design speed
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Impeller total-to-static pressure ratio (left) and diffuser subcomponent pressure rise at the hub (center) and at the shroud (right) for no injection (white symbols) and injected mass flow of 0.7% (gray symbols) and 1.6% of compressor design mass flow (black symbols) at 100% corrected design speed
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Effect of impeller exit tip-clearance on surgemargin and on stability enhancement at 80% and at 100% corrected design speed
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Stability enhancement at 80% and at 100% corrected design speed with different numbers of injectors

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