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.
Application of Model Order Reduction to Compressor Aeroelastic Models
Contributed by the International Gas Turbine Institute (IGTI) of THE AMERICAN SOCIETY OF MECHANICAL ENGINEERS for publication in the ASME JOURNAL OF ENGINEERING FOR GAS TURBINES AND POWER. Paper presented at the International Gas Turbine and Aeroengine Congress and Exhibition, Munich, Germany, May 8–11, 2000; Paper 00-GT-377. Manuscript received by IGTI November 1999; final revision received by ASME Headquarters February 2000. Associate Editor: D. Wisler.
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Willcox , K., Peraire , J., and Paduano, J. D. (March 26, 2002). "Application of Model Order Reduction to Compressor Aeroelastic Models ." ASME. J. Eng. Gas Turbines Power. April 2002; 124(2): 332–339. https://doi.org/10.1115/1.1416152
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