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TECHNICAL PAPERS

The Impact of Viscous Effects on the Aerodynamic Damping of Vibrating Transonic Compressor Blades—A Numerical Study

[+] Author and Article Information
Björn Grüber

Daimler Chrysler Aerospace, MTU Munich, Munich, Germanyemail: bjoern.grueber@muc.mtu.dasa.de

Volker Carstens

Institute of Aeroelasticity, DLR, Göttingen, Germanyemail: volker.carstens@dlr.de

J. Turbomach 123(2), 409-417 (Feb 01, 2000) (9 pages) doi:10.1115/1.1354139 History: Received February 01, 2000
Copyright © 2001 by ASME
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References

Figures

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Aerodynamic work coefficient, Euler results, ω* =0.3, Ma1=0.85, σ=+90 deg
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Aerodynamic work coefficient, Navier-Stokes results, ω* =0.3, Ma1=0.85,Re1=5⋅105, σ=+90 deg
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Aerodynamic work coefficient, Euler results, ω* =0.1, Ma1=0.85, σ=+90 deg
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Aerodynamic work coefficient, Navier-Stokes results, ω* =0.1, Ma1=0.85,Re1=5.0⋅105, σ=+90 deg
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Mach contours for different timesteps, Navier-Stokes results, α=2.0 deg, ω* =0.3, Ma1=0.85,Re1=5⋅105, σ=+90 deg, —=sonic line
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Composition of grids near the blade’s surface
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Computed and measured time history of static pressure in the midplane between profile and wall (the absolute phase is arbitrary)
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Mach contours for Cwk=0.25 and 0.46, —=sonic line
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Compressor cascade geometry and operating data
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Isentropic Mach number distribution for subsonic and transonic steady-state flow (Re1=5⋅105)
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Wall friction coefficient for subsonic and transonic steady-state flow (Re1=5⋅105)
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Aerodynamic damping as function of IBPA, Euler results, Ma1=0.85, α=0.5 deg
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Aerodynamic damping as function of inflow Mach number, ω* =0.3, σ=+90 deg
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Aerodynamic damping as function of reduced frequency, Ma1=0.85, σ=+90 deg

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