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TECHNICAL PAPERS

Recommendations for Achieving Accurate Numerical Simulation of Tip Clearance Flows in Transonic Compressor Rotors

[+] Author and Article Information
Dale E. Van Zante, Anthony J. Strazisar, Jerry R. Wood

NASA Lewis Research Center, Cleveland, OH 44135

Michael D. Hathaway

US Army Vehicle Technology Center, Cleveland, OH 44135

Theodore H. Okiishi

Iowa State University, Ames, IA 50011

J. Turbomach 122(4), 733-742 (Feb 01, 1999) (10 pages) doi:10.1115/1.1314609 History: Received February 01, 1999
Copyright © 2000 by ASME
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References

Figures

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Total temperature excess of the clearance flow at 92 percent rotor chord along the survey line shown
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LDV measurement locations for Rotor 35
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Contours of axial velocity (m/s) on the 92 percent span streamsurface from the LDV measurements. The clearance flow trajectory is marked by the dashed line.
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Contours of tangential velocity (m/s) at 33, 53, 72, and 92 percent rotor chord and midgap from the LDV measurements
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Detail of rotor mesh at 50 percent span (every other grid line is shown)
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Detail of mesh in the blade tip region
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Axial velocity contours (starting at 0 m/s with 20 m/s intervals) for the blade tip grid plane for configurations 1 and 3
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Tangential velocity contours (10 m/s interval) for the outer 20 percent of span on the cross-channel surface at 92 percent rotor chord for configurations 1 and 3
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Visualization of primary and induced clearance vortices
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Axial velocity contours (starting at 0 m/s with 20 m/s intervals) for the blade tip grid plane for configuration 3 with a slip boundary condition applied over the region shown
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Comparison of computed and measured operating range for Rotor 35 at 80 percent speed
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Axial velocity contours (starting at 0 m/s with 20 m/s intervals) for the blade tip plane for design speed with a grid similar to configuration 3
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Comparison of computed and measured operating range for Rotor 35 at design speed
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Relation of the clearance jet velocity and the shroud-wall velocity in the relative reference frame

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