A Modal Interpretation for Aeroelastic Stability Enhancement of Mistuned Bladed Disks

Understanding the mechanism of aeroelastic stability improvement induced by mistuning is essential for design bladed disks in aero-engines. In this paper, a quantitative interpretation given. It starts projecting mistuned modes into space spanned tuned modes. way, damping can be expressed superposition damping. Closed-form expressions are found, providing clear interpretations several frequently reported trends literature. Further, prediction approach proposed, where analysis coupling only needs to performed once, and it decoupled from effect. The advantages two-fold. First, pattern accelerated. Second, allows one introduce more accurate data or models An empirical disk with NASA-ROTOR37 profile used as an example, alternate, wave, random patterns considered.