A Correlation for Tip Leakage Blockage in Compressor Blade Passages

[+] Author and Article Information
M. Hoeger, M. Lahmer, M. Dupslaff, G. Fritsch

DaimlerChrysler Aerospace, MTU Motoren- und Turbinen-Union München GmbH, Dachauer Straße 665, München, Germany 80995

J. Turbomach 122(3), 426-432 (Feb 01, 1999) (7 pages) doi:10.1115/1.1303707 History: Received February 01, 1999
Copyright © 2000 by ASME
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Three-dimensional Navier-Stokes simulation of the tip leakage vortex for the TU-Darmstadt transonic compressor rig: strong and weak parts of the tip leakage vortex (left) and the resulting displacement by axial flow reversal (right); see 14
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Average displacement by leakage in the meridional plane (operating point close to stall)
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Typical velocity profile in the reversed flow region with a relative maximum in wax
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Displacement definitions within the blade passage at the outer casing
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Tip gap influence function Fh
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Average tip leakage flow vector at the blade tip
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Stagger angle influence function Fb
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Corrected preshock Mach number and normal shock pressure ratio
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Location x/cax of the maximum additional displacement thickness from tip leakage
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Maximum additional displacement Δδ*s in percent cax: (right) original data; (left) correlation in Eq. (8)
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Transition function for the corrected additional displacement thickness Δδ*scorr(x/cax)
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Displacement thickness δ*1/cax at the rotor inlet (top) and additional displacement thickness Δδ*m/cax (bottom) as a function of the displacement thickness at the throat; TU-Darmstadt compressor rig
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Application of the present correlation to the TU-Darmstadt transonic compressor; design conditions




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