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Content Provider | The American Society of Mechanical Engineers (ASME) Digital Collection |
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Author | Doi, Hirofumi Juan, J. Alonso |
Copyright Year | 2002 |
Abstract | The present study demonstrates the capabilities of a fluid/structure coupled computational approach which consists of an unsteady three-dimensional Navier-Stokes flow solver, TFLO, and a finite element structural analysis package, MSC/NASTRAN. The parallelized flow solver relies on a multi-block cell-centered finite volume discretization and the dual time stepping time integration scheme with multigrid for convergence acceleration. High accuracy is pursued with respect to load transfer, deformation tracking and synchronization between the two disciplines. As a result, the program successfully predicts the aeroelastic responses of a high performance fan, NASA Rotor 67, over a range of operational conditions. The results show that the unsteady pressure generated at the shock may act to damp or excite the blade motion mainly depending on the inter-blade phase angle. It is concluded that the level of sophistication in the individually sophisticated disciplines together with an accurate coupling interface will allow for accurate prediction of flutter boundaries of turbomachinery components. |
Sponsorship | International Gas Turbine Institute |
Starting Page | 787 |
Ending Page | 794 |
Page Count | 8 |
File Format | |
ISBN | 0791836096 |
DOI | 10.1115/GT2002-30313 |
e-ISBN | 0791836010 |
Volume Number | Volume 4: Turbo Expo 2002, Parts A and B |
Conference Proceedings | ASME Turbo Expo 2002: Power for Land, Sea, and Air |
Language | English |
Publisher Date | 2002-06-03 |
Publisher Place | Amsterdam, The Netherlands |
Access Restriction | Subscribed |
Subject Keyword | Transonic flow Deformation Blades Nasa Rotors Turbomachinery Synchronization Flow (dynamics) Pressure Stress Fluids Computation Flutter (aerodynamics) Engineering disciplines Finite element analysis Shock (mechanics) Structural analysis |
Content Type | Text |
Resource Type | Article |
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