Aiaa 99–1467 Low Order Aerodynamic Models for Aeroelastic Control of Turbomachines

A reduced order aerodynamic model is developed for aeroelastic analysis of turbomachines. The proper orthogonal decompostion technique is used to obtain the modal basis vectors of this model. Two-dimensional frequency domain solutions are used to obtain the basis vectors eeciently, however the model itself is developed in the time domain and is cast in state-space form. The number of states of the model is less than ten per blade passage, making it appropriate for control applications. The aerodynamic model is coupled with a simple structural model that has two degrees of freedom for each blade. Results are presented for unsteady inviscid ow through a single stage rotor that moves in both pitch and plunge. The technique is applicable to viscous and three-dimensional problems as well as multi-stage problems with inlet and exit disturbance ows.