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Research Papers

Time-Linearized and Time-Accurate 3D RANS Methods for Aeroelastic Analysis in Turbomachinery

[+] Author and Article Information
Hans-Peter Kersken1

Christian Frey, Christian Voigt

Graham Ashcroft

 Institute of Propulsion Technology,  German Aerospace Center (DLR),  Linder Höhe, 51147 Cologne, GermanyGraham.Ashcroft@dlr.de

1

Address all correspondence to this author.

J. Turbomach 134(5), 051024 (May 24, 2012) (8 pages) doi:10.1115/1.4004749 History: Received April 08, 2011; Revised July 08, 2011; Published May 24, 2012; Online May 24, 2012

A computational method for performing aeroelastic analysis using either a time-linearized or an unsteady time-accurate solver for the compressible Reynolds averaged Navier--Stokes (RANS) equations is described. The time-linearized solver employs the assumption of small time-harmonic perturbations and is implemented via finite differences of the nonlinear flux routines of the time-accurate solver. The resulting linear system is solved using a parallelized generalized minimal residual (GMRES) method with block-local preconditioning. The time accurate solver uses a dual time stepping algorithm for the solution of the unsteady RANS equations on a periodically moving computational grid. For either solver, and both flutter and forced response problems, a mapping algorithm has been developed to map structural eigenmodes, obtained from finite element structural analysis, from the surface mesh of the finite element structural solver to the surface mesh of the finite volume flow solver. Using the surface displacement data an elliptic mesh deformation algorithm, based on linear elasticity theory, is then used to compute the grid deformation vector field. The developed methods are validated first using standard configuration 10. Finally, for an ultra-high bypass ratio fan, the results of the time-linearized and the unsteady module are compared. The gain in prediction time using the linearized methods is highlighted.

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Copyright © 2012 by American Society of Mechanical Engineers
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Figures

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Figure 1

Welded turbine vane cluster: FE data (right) and CFD mesh with mapped displacements (left)

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Figure 2

Comparison of surface displacements mapped from the FE mesh (right) to the CFD mesh (left)

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Figure 3

Original (yellow) and deformed tip clearence cells at 0 deg (blue) and 180 deg (green)

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Figure 4

Amplitude (top) and phase (bottom) of the pressure perturbation versus chordwise coordinate normalized by the chordlength for STCF10 case 8

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Figure 5

Aerodynamic damping for STCF10

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Figure 6

UHBR fan rig mounted in DLR’s M2VP test facility

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Figure 8

Aerodynamic damping for UHBR

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Figure 9

Real part of the aerodynamic work computed with the nonlinear method (top) and the linear method (bottom)

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