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SUBSONIC STALL FLUTTER ANALYSIS IN 2D BLADE CASCADE USING HYBRID BOUNDARY ELEMENT METHOD

. In this paper study of subsonic stall ﬂutter in the steam turbine blades is carried out. Subsonic stall ﬂutter is one of the dominating and frequently occurring aeroelastic phenomena in large power turbines. The study is carried out by both experimentally and numerically to understand the fundamental physics behind it. Aerodynamics damping (AD) is one of the parameter to analyze the aeroelastic stability of stall ﬂutter in 2D blade cascade. To numerically model the stall ﬂutter in steam turbine a medium ﬁdelity numerical tool is developed. In this research project computationally less expensive potential ﬂow based hybrid boundary element method e.g. panel method, ﬂow model is developed to model the unsteady ﬂow in low pressure turbine blade cascade and to estimate the aeroelastic stability (stall ﬂutter) parameters. A modiﬁed version panel method using viscous-inviscid coupling including discrete vortex particle (DVM) free wake model can be used for the separated ﬂow conditions as it is in stall ﬂutter case. These methods are widely adopted for aeroelastic modeling of wind turbines, helicopter rotors, and aircraft aeroelasticity problem . The AD for different Inter blade phase angle (IBPA) is estimated using newly developed hybrid BEM based ﬂow model. The estimated AD will be compared with experimental data and CFD results to evaluate the efﬁciency and the accuracy of the model.