| タイトル | Rapid Aeroelastic Analysis of Blade Flutter in Turbomachines |
| 本文（外部サイト） | http://hdl.handle.net/2060/20110013059 |
| 著者（英） | Mehmed, O.; Trudell, J. J.; Reddy, T. S. R.; Montgomery, M.; Bakhle, M. A.; Verdon, J.; Stefko, G. L. |
| 著者所属（英） | NASA Glenn Research Center |
| 発行日 | 2006-09-01 |
| 言語 | eng |
| 内容記述 | The LINFLUX-AE computer code predicts flutter and forced responses of blades and vanes in turbomachines under subsonic, transonic, and supersonic flow conditions. The code solves the Euler equations of unsteady flow in a blade passage under the assumption that the blades vibrate harmonically at small amplitudes. The steady-state nonlinear Euler equations are solved by a separate program, then equations for unsteady flow components are obtained through linearization around the steady-state solution. A structural-dynamics analysis (see figure) is performed to determine the frequencies and mode shapes of blade vibrations, a preprocessor interpolates mode shapes from the structural-dynamics mesh onto the LINFLUX computational-fluid-dynamics mesh, and an interface code is used to convert the steady-state flow solution to a form required by LINFLUX. Then LINFLUX solves the linearized equations in the frequency domain to calculate the unsteady aerodynamic pressure distribution for a given vibration mode, frequency, and interblade phase angle. A post-processor uses the unsteady pressures to calculate generalized aerodynamic forces, response amplitudes, and eigenvalues (which determine the flutter frequency and damping). In comparison with the TURBO-AE aeroelastic-analysis code, which solves the equations in the time domain, LINFLUX-AE is 6 to 7 times faster. |
| NASA分類 | Man/System Technology and Life Support |
| レポートNO | LEW-17880-1 |
| 権利 | Copyright, Distribution as joint owner in the copyright |
| URI | https://repository.exst.jaxa.jp/dspace/handle/a-is/499437 |
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