A 3D Euler/Navier-Stokes aeroelastic code for propulsion applications

Abstract

This paper describes the development and verification of an aeroelastic code (TURBO-AE) based on an Euler / Navier-Stokes unsteady aerodynamic code (TURBO). The aeroelastic formulation is described. The modeling of the dynamics of the blade using a modal method is detailed, along with the grid deformation procedure used to model the elastic deformation of the blade. The work-per-cycle method used to evaluate aeroelastic stability is described. Representative results are presented for a helical fan test configuration used to verify the code. Results included are for both zero and non-zero interblade phase angles. Excellent agreement with linear theory is seen in all cases. Some representative results are also presented for a realistic compressor configuration. The paper concludes with an evaluation of the development thus far, and some plans for further development and validation of the TURBO-AE code.