تحلیل فلاتر کلاسیک یک ردیف‌پره توربین‌گاز با مدل رتبه‌کاسته مبتنی بر روش ریتز

The development of gas turbine design has increased the importance of aeroelasticity in turbomachinery, especially as the development of aircraft engines has led to a reduction in the flutter speed of blade rows. In this study, a reduced-order model based on the Ritz method is introduced, using the classical continuous beam-shaft model for the blade row structure and the Whitehead model developed with strip theory. It takes into account the effect of varying flow velocity distribution along the blade span. Using this model, flutter onset is revealed through the extraction of Vg diagrams, offering a more accurate alternative to the conventional typical section approach in the early stages of gas turbine design, which requires reasonable accuracy and low computational cost. The modal and aerodynamic results are validated by comparison with previous studies, and classical flutter is analyzed on a tuned blade row. It is ultimately shown that with low computational cost, results such as soft flutter onset detection and tracking of more critical modes (including higher modes of the structure) can be achieved, which is a potentially hazardous and controversial phenomenon.