M. Böswald, M. Link, C. Schedlinski

In this paper, an overview and some selected details are given on a general procedure to improve large order structural dynamic models of aero-engines. Because of the complexity of typical whole engine models (WEM) a special model validation strategy is required to account for the large number of finite element (FE) model parameters which may be uncertain in a WEM. A three-step strategy is proposed which is based on three subsequent levels of model validation. In the first step, model validation is carried out on component model level, whereas in the second step, sub-assembly models are validated with emphasis on updating joint parameters, and in the final step, model validation is carried out on the whole engine assembly level where only a few uncertain joint parameters need to be adjusted. Typical problems encountered during computational model updating are addressed, among those, the selection of effective updating parameters. An extension of the classical model updating techniques is presented which aims at extending the prediction capability of the model into the large vibration amplitude regime where non-linear behavior is likely to occur. This is achieved by identifying non-linear joint stiffness and damping parameters by application of a non-linear model updating approach based on measured non-linear frequency response data.

International Forum on Aeroelasticity and Structural Dynamics, 2005, München

Conference Paper

englisch

21,0 x 29,7 cm, 17 Seiten

DGLR-Bericht, 2005, 2005-04, International Forum on Aeroelasticity and Structural Dynamics 2005; S.1-17; 2005; Deutsche Gesellschaft für Luft- und Raumfahrt - Lilienthal-Oberth e.V., Bonn

NA

in getr. Zählung;

models, nonlinearity, validatation

Bibliothek

2005