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TECHNICAL PAPERS

The Investigation of Turbine and Exhaust Interactions in Asymmetric Flows— Blade-Row Models Applied

[+] Author and Article Information
J. J. Liu, T. P. Hynes

Whittle Laboratory, University of Cambridge, Cambridge CB3 0DY, UK

J. Turbomach 125(1), 121-127 (Jan 23, 2003) (7 pages) doi:10.1115/1.1516812 History: Revised October 02, 2001; Online January 23, 2003
Copyright © 2003 by ASME
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References

Figures

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Illustration of actuator disk model
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Streamline and quasi-orthogonal line in the meridional plane
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Diagram for disk boundary condition
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Choking model for a turbine blade passage
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Mesh used for disk-model validation
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Mach number distribution across actuator disks
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Density distribution across actuator disks
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Pressure distribution across actuator disk
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Mesh used for the comparison of disk boundary conditions; two disks are located at i=9 and i=13
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Mach number distributions for low-speed flow, the mass flow error is 0.19% using Eq. (3) (Model A), and it is 0.86% using Eq. (5) (Model B)
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Mach number distributions for high-speed flow, the mass flow error is 0.12% using Eq. (3) (Model A), and it is 6.16% using Eq. (5) (Model B)
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Multiblock mesh used for an exhaust hood
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Stream ribbons starting from four radial lines at the diffuser inlet in the exhaust hood
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Mach contours at a plane of θ=0 deg in the exhaust hood

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