Abstract

A model order reduction technique that yields low-order models of blade row unsteady aerodynamics is introduced. The technique is applied to linearized unsteady Euler CFD solutions in such a way that the resulting blade row models can be linked to their surroundings through their boundary conditions. The technique is applied to a transonic compressor aeroelastic analysis, in which the high-fidelity CFD forced-response results are better captured than with models that use single-frequency influence coefficients. A low-speed compressor stage is also modeled to demonstrate the multistage capability of the method. These examples demonstrate how model order reduction can be used to systematically improve the versatility, fidelity, and range of applicability of the low-order aerodynamic models typically used for incorporation of CFD results into aeroelastic analyses.

Issue Section:
Gas Turbines: Structures and Dynamics
Keywords:
gas turbines, compressors, vibrations, aerodynamics, computational fluid dynamics
Topics:
Blades, Compressors, Computational fluid dynamics, Rotors, Aerodynamics, Flow (Dynamics), Boundary-value problems, Eigenvalues
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 by ASME
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