Abstract
Unsteady aerodynamics is the driving phenomenon for HCF failures of advanced design multistage blade rows. Hence, accurate HCF design analysis is dependent on experimentally validated three-dimensional unsteady aerodynamic blade row interaction CFD codes. Of particular interest herein are the blade row interaction phenomena in transonic compressors. Specifically, the unsteady flow through an IGV row generated by the downstream transonic rotor is simulated with TURBO utilized as an inviscid three-dimensional multistage CFD code. The results of this simulation are then correlated with corresponding benchmark experimental data.
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