Analysis of a Rotor-Stator Stage using a Two Dimensional Euler Aeroelastic Solver

摘要

A two dimensional cascade aeroelastic solver for analyzing a multi blade row configuration (for example, a multistage turbomachine) is being developed. The solver can be used for the analysis of single or multiple row of cascades having unequal number of blades in the cascade. The required unsteady aerodynamic forces are obtained from an Euler solver based on a flux differencing scheme. The aerodynamic solver is coupled with a typical section structural model for each blade of the cascade in each row. The flutter and forced response characteristics are analyzed in the time domain, by sequentially solving the structural and aerodynamic equations for each time step. Numerical calculations for a supersonic flow cascade with unstaggered blade rows showed the expected behavior. Results are also shown for the first stage of the Space Shuttle Main Engine (SSME) high pressure fuel turbopump in subsonic flow.