Single-Passage Analysis of Unsteady Flows Around Vibrating Blades of a Transonic Fan Under Inlet Distortion

[+] Author and Article Information
H. D. Li, L. He

School of Engineering, University of Durham, U.K. DH1 3LE Durham

J. Turbomach 124(2), 285-292 (Apr 09, 2002) (8 pages) doi:10.1115/1.1450567 History: Received February 01, 2001; Revised October 15, 2001; Online April 09, 2002
Copyright © 2002 by ASME
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Mesh (on pitchwise and spanwise section) of NASA rotor 67
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Predicted (upper) and measured (lower) relative Mach number contours
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Pressure jump coefficients (σ=180 deg)—(a) hub section, (b) tip section
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Instantaneous total pressure contours at near inlet section—(a) 11-node mode, (b) 2-node mode, (c) 1-node mode
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Time-space pressure trace on the suction side at 90 percent span section (T: time period; X/C: nondimensional streamwise mesh line distance measured from blade leading edge)—(a) 11-node mode, (b) 2-node mode, (c) 1-node mode
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First harmonic pressure coefficient distribution of torsion mode (clean inflow with different torsion amplitude)
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Pressure jump and unsteady forces history (torsion and inlet distortion, SP: single passage solution, MP-11 passage solution)
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First harmonic pressure coefficient distribution (torsion with different inlet distortion modes)
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First harmonic pressure coefficient distribution (1-node inlet distortion with different torsion amplitude)
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Time-averaged and steady pressure distributions—(a) torsion, (b) torsion and 2-node inlet distortion



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