Approach to Unidirectional Coupled CFD–FEM Analysis of Axial Turbocharger Turbine Blades

[+] Author and Article Information
D. Filsinger, J. Szwedowicz, O. Schäfer

R & D Turbochargers, ABB Turbo Systems Ltd., 5401 Baden, Switzerland

J. Turbomach 124(1), 125-131 (Feb 01, 2001) (7 pages) doi:10.1115/1.1415035 History: Received February 01, 2001
Copyright © 2002 by ASME
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Unidirectional coupled numerical procedure
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Identical meshes to define complex bladed disk oscillations in the real domain
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Measured Campbell diagram of turbocharger disk with lacing wire in service
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Comparison of relative change in output power for different turbine configurations
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Unsteady pressure p (upper) and temperature T (lower diagram) inlet boundary conditions
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Power excitation spectrum of the blade rotating with speed nTC; upper diagram: full spectrum, lower diagram: zoomed spectrum for the sixth engine order
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Resulting blade force versus time
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Pressure distribution in the midsection of the turbine stage for a single time step (upper plot) and qualitative loading of the turbine blades (lower diagram)
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Nodal diameter diagram of the bladed disk rotating with constant speed nTC=Ω (compare Eq. (7))
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Comparison among the resonance amplitudes of the lowest blade modes excited by the sixth engine order for two damping ratios ξ
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Calculated blade amplitudes at the trailing edge versus exciting frequency (left); and contour plot of qualitative stress distribution in the turbine blade with the damping wire (right)
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Results of strain gage measurements around the sixth turbocharger order



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