Unsteady pressure mapping in forced response of a turbomachinery
I am currently studying on mode superposition harmonic analysis of a fan blade. An early discussion I mentioned that I am applying unsteady pressure mapping (by APDL commands) on fan blade which comes from CFX transient analysis by .csv file.
Although I apply mapping on blades, there is no change in total deformation or max. equivalent stress comparing to regular pre-structural results.
Do I apply something wrong or the values are so small that doesn't even effect decimal digits of results?