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TECHNICAL PAPERS

Experimental Investigation of Diffuser Hub Injection to Improve Centrifugal Compressor Stability

[+] Author and Article Information
Gary J. Skoch

U. S. Army Research Laboratory, Glenn Research Center, Cleveland, OH 44135

J. Turbomach 127(1), 107-117 (Feb 09, 2005) (11 pages) doi:10.1115/1.1812779 History: Received October 01, 2003; Revised March 01, 2004; Online February 09, 2005
Copyright © 2005 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 hub instrumentation and injector nozzle locations
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Hub-side injector nozzle orientations
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Stage total pressure ratio versus net flow entering the diffuser corrected to inlet conditions at design speed and 2.4% tip clearance with hub suction-side injection
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Stage total pressure ratio versus impeller inlet corrected flow at design speed and 2.4% tip clearance with hub suction-side injection
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Impeller static-total prerssure ratio versus impeller inlet corrected flow at design speed and 2.4% tip clearance with hub suction-side injection
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Impeller total temperature ratio versus impeller inlet corrected flow at design speed and 2.4% tip clearance with hub suction-side injection
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Stage adiabatic efficiency versus impeller inlet corrected flow at design speed and 2.4% tip clearance with hub suction-side injection
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Stage total pressure ratio versus net flow entering the diffuser corrected to inlet conditions at design speed and 2.4% tip clearance with hub vane-bisected injection
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Stage total pressure ratio versus net flow entering the diffuser corrected to inlet conditions at design speed and 2.4% tip clearance with hub pressure-side injection
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Stage total pressure ratio versus net flow entering the diffuser corrected to inlet conditions at design speed and 2.4% tip clearance for the recirculation case of pressure-side injection
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Stage total pressure ratio at design speed and 2.4% tip clearance for the zero injection cases of suction-side, vane-bisected, and pressure side nozzle orientations
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Stage total temperature ratio at design speed and 2.4% tip clearance for the zero injection cases of suction-side, vane-bisected, and pressure-side nozzle orientations
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Impeller static-total pressure ratio versus impeller inlet corrected flow at design speed and 2.4% tip clearance for the zero injection cases of suction-side, vane-bisected, and pressure-side nozzle orientations
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Stage adiabatic efficiency at design speed and 2.4% tip clearance for the zero injection cases of suction-side, vane-bisected, and pressure-side nozzle orientations
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Static pressure rise in the diffuser vaneless space at design speed and 2.4% tip clearance for the zero injection cases of suction-side, vane-bisected, and pressure-side nozzle orientations
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Static pressure rise in the diffuser semivaneless region at design speed and 2.4% tip clearance for the zero injection cases of suction-side, vane-bisected, and pressure-side nozzle orientations
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Diffuser vane leading edge loading on the shroud surface for the zero injection cases of suction-side, vane-bisected, and pressure-side nozzle orientations
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Diffuser vane leading edge loading on the hub surface for the zero injection cases of suction-side, vane-bisected, and pressure-side nozzle orientations
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Static pressure-rise in the diffuser vaneless space at design speed and 2.4% tip clearance produced by range improvement techniques applied to the shroud surface, reproduced from 2
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Cross section of test compressor showing control tube configuration tested in 2
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Control tube immersions previously tested on the shroud surface 2. Two immersions were achieved by placement and removal of a shim.
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Orientations of flat side of nozzle opening relative to the tangential velocity vector of impeller discharge flow within the vaneless region

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