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On decoupled and fully-coupled methods for blade forced response prediction.

Moffatt, S. and He, L. (2005) 'On decoupled and fully-coupled methods for blade forced response prediction.', Journal of fluids and structures., 20 (2). pp. 217-234.

Abstract

Two highly efficient fully-coupled methods of predicting the resonant forced response of turbomachinery blades have been developed with the intention of increased computational efficiency over a decoupled method. The flow and structural equations are solved simultaneously, based on the frequency-domain nonlinear harmonic method and the modal reduction technique. By combining the aerodynamic forcing and damping calculations into a single analysis, the coupled solution at a single excitation frequency is approximately half that of the decoupled method. Significant flow–structure coupling effects were discovered, leading to a study into the impact of frequency shift on the fully-coupled solution. A case study on the NASA Rotor 67 transonic aero fan rotor shows a significant reduction in vibration amplitude for the fully-coupled solution due to the resonant frequency shift, caused by the aerodynamic added mass effect. Prompting the development of a novel resonance-tracking algorithm to solve the additional degree-of-freedom in resonant frequency, the increase in computational efficiency in the fully-coupled method is lost due to the need for multiple solutions. A study into the added mass effect and the implications on the coupled solution is undertaken and an evaluation is made between the use of decoupled and fully-coupled forced response systems. It is shown that the decoupled method can accurately predict the resonant vibration level from a single calculation at the natural frequency and is insensitive to frequency shift for lightly damped cases.

Item Type:Article
Keywords:Turbomachinery, Flows.
Full text:Full text not available from this repository.
Publisher Web site:http://dx.doi.org/10.1016/j.jfluidstructs.2004.10.012
Record Created:16 Feb 2007
Last Modified:08 Apr 2009 16:21

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