A 3D linearized Euler analysis for blade rows part 1: Aerodynamic and numerical formulations

A three-dimensional, linearized, unsteady, Euler analysis is being developed to efficiently predict the aeroelastic and aeroacoustic behaviors of axial-flow turbomachinery blading. The aerodynamic and numerical formulations are presented in Part 1 of this paper. In particular, the field equations and boundary conditions governing nonlinear and linearized, unsteady, inviscid flows through blade rows in cylindrical annular ducts are derived. A linearized numerical formulation, coupling a near-field, wave-split, finite-volume analysis to far-field eigenanalyses, is also described. The linearized aerodynamic and numerical models have been implemented into a three-dimensional, unsteady flow code, LINFLUX. This code is applied in Part 2 to benchmark, unsteady, subsonic flows to demonstrate its accuracy and prediction capabilities.