<p>The accurate predication of aerodynamic flutter margin continues to be an area of growing importance in the design of rotating turbomachinery, especially when considering the ongoing industry objectives for increased operating efficiency, higher power output, and reduced fuel consumption. Improvements in these areas are commonly achieved through incremental design changes to existing hardware, and often trend with higher pressure ratios and mass flow rates through the machine. In many cases, the extent of these flow improvements become constrained by the stability margins of flutter limiting components such as front stage compressor blades and last stage turbine blades. In such cases, designers are left with the difficult task of mitigating the flutter risk, but without limiting the performance of the machine.</p><p>The tip shroud characteristics of a typical last stage turbine blade can significantly influence the overall flutter response of the blade. It is this reason that underlines the importance for understanding the sensitivity of shroud design parameters when attempting to achieve a flutter free design, especially if the aerodynamic qualities of the airfoil need to be preserved. This paper evaluates the flutter performance of a last stage industrial gas turbine blade with multiple tip shroud configurations and demonstrates the influence of the selected design parameters with respect to the aerodynamic damping behavior of the blade.</p>

Numerical Investigation on the Influence of Tip Shroud Design Characteristics on the Aerodynamic Damping of a Last Stage Blade

Paper Proceedings: https://asmedigitalcollection.asme.org/GT/GT2021/volume/84898

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