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TECHNICAL PAPERS

The Impact of Forward Swept Rotors on Tip Clearance Flows in Subsonic Axial Compressors

[+] Author and Article Information
G. Scott McNulty, John J. Decker, Brent F. Beacher

GE Aircraft Engines, One Neumann Way, MD A411, Cincinnati, OH 45215

S. Arif Khalid

Streamline, Inc., Indianapolis, IN

J. Turbomach 126(4), 445-454 (Dec 29, 2004) (10 pages) doi:10.1115/1.1773852 History: Received December 01, 2002; Revised March 01, 2003; Online December 29, 2004
Copyright © 2004 by ASME
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References

Figures

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Comparison of aerodynamic sweep distributions
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Configuration 1 radial and forward swept rotors
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Comparison of design point static pressure coefficient distributions
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Characteristics data for configuration 1 at nominal and open clearance levels: (a) static pressure coefficient and (b) torque efficiency
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Configuration 1 forward swept rotor surface static pressure data at various throttle settings at nominal clearance
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Characteristics data for configuration 2 at nominal and open clearance levels: (a) static pressure coefficient and (b) torque efficiency
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Measured rotor tip-clearance sensitivities: (a) maximum tip static pressure coefficient, (b) throttle margin, and (c) peak efficiency
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Comparison of forward swept and radial rotor surface static pressure data for configuration 1 at open clearances
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Comparison of surface static pressure data at nominal and open clearances for the forward swept rotor of configuration 1
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Comparison of surface static pressure data to CFD analysis for configuration 1 forward swept rotor at throttle 16 with nominal clearance
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Comparison of flow measurements to CFD analysis for configuration 1 swept rotor at throttle 16 with nominal clearance: (a) inlet relative flow angle, (b) exit relative flow angle, (c) inlet axial velocity, (d) exit axial velocity, (e) exit absolute total pressure. (Radial rotor CFD shown for reference.)
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Comparison of rotor trailing-edge contours for configuration 1 CFD analyses at throttle 16 with nominal clearance: (a) axial velocity (ft/s), (b) loss coefficient.
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Comparison of blade-to-blade axial velocity contours at mid-clearance gap for configuration 1 CFD analyses at throttle 16 with nominal clearance
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Comparison of blade-to-blade relative velocity contours at blade tip for configuration 1 CFD analyses at throttle 16 with nominal clearance
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Comparison of nondimensional tip-leakage flow blockage versus tip loading parameter using the method of Khalid 1516

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