Development of a turbomachinery aeroelastic code based on a 3D linearized Euler solver

This paper describes the development of LINFLUXAE, a turbomachinery aeroelastic code based on the linearized unsteady 3D Euler solver, LINFLUX. The steady solution, required by LINFLUX is obtained from the nonlinear Euler/Navier Stokes solver TURBO-AE. The paper briefly describes the salient features of TURBO-AE, LINFLUX and the details of the aeroelastic extension. The aeroelastic formulation is based on a modal approach. The unsteady aerodynamic forces required for flutter and forced response are obtained by running LINFLUX for each mode for each interblade phase angle and for a given frequency. An eigenvalue formulation is used for flutter analysis. The forced response is calculated from the modal summation of the generalized displacements. The NASA / GE Energy Efficient Engine (Ecubed) fan configuration is chosen as a test case and the results are compared with those obtained from TURBO-AE and ASTROP2.

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