A FAST EULER-SOLVER FOR THE SOLUTION OF 3-DIMENSIONAL ROTATIONAL COMPRESSIBLE FLOWS

Presents a finite element/volume method for non-linear aeroelasticity analyses of turbomachinery blades. The method uses an Arbitrary Lagran gian-Eulerian (ALE) kinematical description of the fluid domain, in wh ich the grid points can be displaced independently of the fluid motion . In addition, it employs an iterative implicit formulation similar to that of the Implicit-continuous Eulerian (ICE) technique, making it a pplicable to flows at all speeds. A deforming mesh capability that can move the grid to conform continuously to the instantaneous shape of a n aeroelastically deforming body without excessive distortion is also included in the algorithm. The unsteady aerodynamic loads are obtained using inviscid Euler equations. The model for the solid is general an d can accommodate any spatial or modal representation of the structure . Determines the flutter stability of the system by studying the aeroe lastic time response histories which are obtained by integration of th e coupled equations of motion for both the fluid and the structure. De velops and demonstrates in 2D the formulation, which includes several corrections for better numerical stability. The cases studied include NACA64A006 and NACA0012 aerofoils and the EPFL Configuration 4 cascade . Finds the results from the numerical indicate good overall agreement with other published work and hence demonstrates the suitability of a n ICED-ALE formulation for turbomachinery applications.