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Research Papers

Shaping of Tip End-Plate to Control Leakage Vortex Swirl in Axial Flow Fans

[+] Author and Article Information
Alessandro Corsini, Franco Rispoli

Dipartimento di Meccanica e Aeronautica, Università di Roma “La Sapienza,” Via Eudossiana 18, I-00184 Rome, Italy

A. G. Sheard

 Fläkt Woods Limited, Tufnell Way, Colchester CO4 5AR, UK

J. Turbomach 132(3), 031005 (Mar 24, 2010) (9 pages) doi:10.1115/1.3145017 History: Received August 06, 2008; Revised February 25, 2009; Published March 24, 2010; Online March 24, 2010

This paper reports on quantitative tests of passive techniques for rotor-tip noise control in low-speed axial flow fans, based on blade-tip modifications involving the addition of antivortex appendages as end-plates. The end-plate thickness chordwise distribution is determined to control the chordwise evolution of the leakage vortex rotation number. The results confirm that the new end-plate configurations provide a mechanism by which leakage vortex bursting can be avoided. As such, the modified rotors represent an effective means of passive control of vortex breakdown.

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Copyright © 2010 by American Society of Mechanical Engineers
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Figures

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Figure 4

Normalized helicity Hn contours on cross sections and vortex cores at the tip, D operating point: (a) AC90/6/TF rotor and (b) AC90/6 data rotor

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Figure 6

AC90/6TF and AC90/6TFvte end-plate geometries (not to scale) (16)

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Figure 7

Measured total pressure and total pressure efficiency characteristic curves (dashed lines: data fan; solid lines: AC90/6/TF fan; line-circles: AC90/6/TFvte fan)

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Figure 8

Chordwise distributions of tip-leakage vortex rotation Ro number at design operating point (line: AC90/6/TF fan; line-circle: AC90/6/TFvte fan)

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Figure 12

Evolution of total pressure loss coefficient ζ inside the blade passage: (a) data rotor, (b) AC90/6/TF rotor, and (c) AC90/6/TFvte

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Figure 1

Fan rotors: (a) data fan and (b) modified AC90/6/TF fan

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Figure 2

Streamlines in the rotor tip gap at D operating point and vortex bursting visualization

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Figure 3

Streamlines and vortex axial velocity isosurface (waTLV=0) in the rotor tip gap at D operation

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Figure 5

Chordwise distributions of tip-leakage vortex rotation Ro number at design operating point (dashed line: data fan; solid line: AC90/6/TF fan)

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Figure 9

Tip leakage flow velocity and skewing angle distributions through the gap: (a) 0.15 chord, (b) 0.3 chord, (c) 0.55 chord, and (d) 0.75 chord (dashed lines: data fan; solid lines: AC90/6/TF fan; line-circles: AC90/6/TFvte fan)

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Figure 10

Spanwise distributions of axial (φa) and radial (φr) flow coefficients behind the rotor (dashed lines: data fan; solid lines: AC90/6/TF fan; line-circles: AC90/6/TFvte fan)

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Figure 11

Spanwise distributions of swirl flow coefficient behind the rotor (dashed lines: data fan; solid lines: AC90/6/TF fan; line-circles: AC90/6/TFvte fan)

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