Numerical simulation for aeroelasticity in turbomachines with vortex method

A new method for quantitatively predicting the interaction between the unsteady aerodynamics and structural dynamics was developed. The unsteady flow with large scale separation is simulated numerically with the developed Discrete Vortex Method. In this calculation process, the instantaneous unsteady force and moment of force acting on the blades can be obtained at each time step. On other hand, the cascade is considered as an elasticity system with damping including the effects of the interblade phase angle. The blades are excited to vibrate by the unsteady force and moment. To deal with the above two respects, the resulting code consists of two basic subprograms which exchange their data between each other at every computational time step and the non-linear problem is then solved in a time-marching discrete continuation fashion. A series of numerical tests are presented including the parameters studies, such as: effects of the damping, incidence etc. For each case, a large number of computational steps is intended to provide sufficient information about the non-linear behavior of the stall flutter. The applicability of the method is demonstrated numerically.