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TECHNICAL PAPERS

Optimum Strain Gage Application to Bladed Assemblies

[+] Author and Article Information
J. Szwedowicz

Thermal Machinery Lab, ABB Turbo Systems Ltd., CH-5401 Baden, Switzerlande-mail: jaroslaw.szwedowicz@ch.abb.com

S. M. Senn, R. S. Abhari

Turbomachinery Lab, Swiss Federal Institute of Technology, Zurich, Switzerland

J. Turbomach 124(4), 606-613 (Nov 07, 2002) (8 pages) doi:10.1115/1.1506957 History: Received October 30, 2001; Online November 07, 2002
Copyright © 2002 by ASME
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References

Figures

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The rotational periodic structure of N=9 cyclic sectors (a) and its cyclic finite element representation (b), where n is a nodal diameter number and l indicates a number of a cyclic sector
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FE mesh on the airfoil contour with the indicated nodal local reference system xyz, where the bigger and smaller circles denote the corner and mid-nodes, respectively
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Illustration of nodal complex dynamic strain components of the cyclic FE system in the complex domain
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Orientation of the ‘measurement’ axis of the strain gage in the nodal local reference system xyz
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Example of the impeller instrumented with strain gages (a) and illustration of the strain variation along the gage (b)
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Optimization function Ψ of a single node for different orientations φ (where values Ψ are multiplied by 1×103)—(a) values Ψ in the linear scale, (b) values Ψ in the logarithmic scale
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The spatially curved pressure side of the impeller vane with the eight calculated optimal strain gage placements (nodes on the surface indicated with a dashed line are used in the optimization)
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Values of population’s for the maximum (upper figure) and average (bottom figure) fitness from the GA process
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Comparison of the gage positions obtained from the GA procedure and qualitative technique (upper figure), where the lower figure presents the maximum and average fitness for the optimized gage locations

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