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TECHNICAL PAPERS

Vortex Transport and Blade Interactions in High Pressure Turbines

[+] Author and Article Information
V. S. P. Chaluvadi, A. I. Kalfas, H. P. Hodson

Whittle Laboratory, Cambridge University Engineering Department, Madingley Road, Cambridge CB3 0DY, UK

J. Turbomach 126(3), 395-405 (Sep 03, 2004) (11 pages) doi:10.1115/1.1773849 History: Received December 01, 2002; Revised March 01, 2003; Online September 03, 2004
Copyright © 2004 by ASME
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References

Figures

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Schematic diagram of the test configuration
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(a) Large-scale rotating delta wing in the turbine rig, (b) stator vane, (c) rotor blade
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Schematic of the three-axis hot-wire probe
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Secondary velocity vectors at delta-wing exit (plane 0)
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Flow field at stator exit (8.7% Cx downstream of stator TE, plane 1); (a) Y contours for datum configuration, (b) Y contours for Δ-wing configuration, (c) Y contours from steady simulations with Δ-wings, (d) average turbulence intensity contours with Δ-wings
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Pitchwise averaged spanwise variations of Y stator exit (plane 1)
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Flow field at stator exit (plane 1); (a) yaw angle, (b) secondary velocity vectors
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Pitchwise averaged spanwise variations of yaw angle at stator exit (plane 1)
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Unsteady Tu contours at stator exit (plane 1)
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Computed contours of entropy function at stator exit (8.4% Cx downstream of the stator TE)
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Computed contours of the entropy function at rotor inlet in one stator wake passing period (25.2% Cx downstream of stator TE/10% upstream of rotor LE)
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Power spectral density inside the stator hub passage vortex; (a) datum configuration, (b) delta-wing configuration
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Flow field at rotor exit (10% Cx downstream of rotor TE, plane 3); (a) Y contours for datum configuration, (b) Y contours for delta wing configuration, (c) TU contours for delta-wing configuration
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Pitchwise averaged spanwise variations at rotor exit
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Unsteady Tu contours at rotor exit (plane 3)
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Comparison of the steady and unsteady numerical simulations: entropy function

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