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TECHNICAL PAPERS

A Transport Model for the Deterministic Stresses Associated With Turbomachinery Blade Row Interactions

[+] Author and Article Information
Allan G. van de Wall, Jaikrishnan R. Kadambi

Department of Mechanical and Aerospace Engineering, Case Western Reserve University, Cleveland, OH 44106  

John J. Adamczyk

NASA Glenn Research Center, Cleveland, OH 44135

J. Turbomach 122(4), 593-603 (Feb 01, 2000) (11 pages) doi:10.1115/1.1312802 History: Received February 01, 2000
Copyright © 2000 by ASME
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References

Figures

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Change in efficiency for a four stage axial compressor operating at two axial gaps 1
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Change in peak overall efficiency for a reaction turbine from data of WRIGHT AERONAUTICAL CORP 3
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Illustration of how a wake stretching in a diffusing duct simulates compressor flows
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Illustration of how a wake compressing in an accelerating duct simulates turbine flows
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Pitchwise average normalized Kexit for the 45 deg turning duct (no viscosity)
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Mixing loss benefit for several inlet wake defects
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Pitchwise average Kexit versus inlet wake angle for the 40 deg turbine, no viscosity
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Distribution of normalized Kexit for the 40 deg turbine (no viscosity)
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Transport of disturbances through GE-LSRC with θw=−49.7 deg
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Deterministic stresses versus pitch for GE-LSRC, no viscosity
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Audit of normalized Kexit versus pitch for GE-LSRC
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Transport of disturbances through PW-LPT with θw=60 deg
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Deterministic stresses versus pitch for PW-LPT, no viscosity
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Audit of normalized Kexit versus pitch for PW-LPT.

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