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TECHNICAL PAPERS

Simulations of the Unsteady Flow Through the Fastrac Supersonic Turbine

[+] Author and Article Information
Lisa W. Griffin

Fluid Dynamics Analysis Branch, National Aeronautics and Space Administration, George C. Marshall Space Flight Center, Marshall Space Flight Center, AL 35802

Daniel J. Dorney

Department of Mechanical Engineering, Virginia Commonwealth University, Richmond, VA 23113

J. Turbomach 122(2), 225-233 (Feb 01, 1999) (9 pages) doi:10.1115/1.555453 History: Received February 01, 1999
Copyright © 2000 by ASME
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References

Figures

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Total pressure profiles: (a) blade inlet; (b) blade exit
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Circumferential angle profiles: (a) blade inlet; (b) blade exit
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Blade pressure envelopes, large gap, uncoupled: (a) hub; (b) midspan; (c) tip
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Pressure trace for blade leading edge, midspan, large gap
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Fourier decomposition of pressure for blade, large gap: (a) leading edge; (b) 20 percent axial chord
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Blade pressure envelopes, large gap: (a) hub; (b) midspan; (c) tip
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Pressure trace for blade leading edge, midspan, small gap
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Fourier decomposition of pressures for blade: (a) leading edge; (b) 20 percent axial chord
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Blade pressure envelopes, small gap: (a) hub; (b) midspan; (c) tip
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Total velocity contours between nozzle exit and blade leading edge
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Instantaneous entropy contours at midspan
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Instantaneous Mach numbers at midspan: (a) turbine; (b) blade alone
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Computational geometry: (a) cross-sectional view (every third point plotted); (b) axial view of the nozzle ring exit
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Fastrac turbine blade Campbell diagram with most responsive modes and excitations (chart by Don Harris)
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Cross section of the Fastrac turbopump

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