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TECHNICAL PAPERS

Experimental Investigation of Centrifugal Compressor Stabilization Techniques

[+] Author and Article Information
Gary J. Skoch

U.S. Army Research Laboratory, National Aeronautics and Space Administration, Glenn Research Center, Cleveland, OH 44135

J. Turbomach 125(4), 704-713 (Dec 01, 2003) (10 pages) doi:10.1115/1.1624846 History: Received December 01, 2002; Revised March 01, 2003; Online December 01, 2003
Copyright © 2003 by ASME
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References

Figures

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Cross section of test compressor and air injection apparatus
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Diffuser shroud instrumentation and injector locations
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Shroud side injector orientations
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Cross section of test compressor and control tube
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Total pressure ratio characteristics at design speed and 2.4% tip clearance
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X-T diagram of diffuser passage pressures through one surge cycle
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Static pressure rise in the diffuser vaneless space at design speed and 2.4% tip clearance
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Static pressure rise in the diffuser semivaneless region at design speed and 2.4% tip clearance
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Static pressure rise in the diffuser vaned passage at design speed and 2.4% tip clearance
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Diffuser total pressure loss coefficient at design speed and 2.4% tip clearance
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Diffuser vane leading edge loading on the hub surface at design speed and 2.4% tip clearance
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Diffuser vane leading edge loading on the shroud surface at design speed and 2.4% tip clearance
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Stage total temperature ratio at design speed and 2.4% tip clearance
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Impeller static pressure ratio for the baseline and extended range configurations at design speed and 2.4% tip clearance
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Stage adiabatic efficiency at design speed and 2.4% tip clearance
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Recovery from surge using reverse-tangent injectors 4 and 5 at 100% of design speed and 2.4% tip clearance

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