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Unsteady Cascade Aerodynamic Response Using a Multiphysics Simulation CodeThe multiphysics code Spectrum(TM) is applied to calculate the unsteady aerodynamic pressures of oscillating cascade of airfoils representing a blade row of a turbomachinery component. Multiphysics simulation is based on a single computational framework for the modeling of multiple interacting physical phenomena, in the present case being between fluids and structures. Interaction constraints are enforced in a fully coupled manner using the augmented-Lagrangian method. The arbitrary Lagrangian-Eulerian method is utilized to account for deformable fluid domains resulting from blade motions. Unsteady pressures are calculated for a cascade designated as the tenth standard, and undergoing plunging and pitching oscillations. The predicted unsteady pressures are compared with those obtained from an unsteady Euler co-de refer-red in the literature. The Spectrum(TM) code predictions showed good correlation for the cases considered.
Document ID
20000021221
Document Type
Technical Memorandum (TM)
Authors
Lawrence, C. (NASA Glenn Research Center Cleveland, OH United States)
Reddy, T. S. R. (Toledo Univ. OH United States)
Spyropoulos, E. (ANSYS, Inc. Sunnyvale, CA United States)
Date Acquired
September 7, 2013
Publication Date
January 1, 2000
Subject Category
Aeronautics (General)
Report/Patent Number
NASA/TM-2000-209635
E-11964
NAS 1.15:209635
Funding Number(s)
PROJECT: RTOP 509-10-11
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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