Numerical study on transonic blade-vortex interaction: Flowfield analysis

Numerical investigations of aerodynamic sound generation due to transonic blade-vortex interaction were performed numerically. The numerical method is based on a third-order upwind finite volume scheme in space and a second-order explicit Runge-Kutta scheme in time. A standard transonic blade vortex interaction is presented to demonstrate two dominant sound waves, transonic and compressible waves. The fluctuation dilatation and correlation of the dilatation are presented to identify these two significant sound waves that travel upstream. Three unsteady shock wave motions, types A, B and C identified by Tijdeman, were simulated by changing the physical parameters, such as Mach number, vortex strength, and initial position of the vortex.