This paper deals with a reduced-order model of a multi-stage rotor in which each stage has a different number of blades. In particular, it is shown that a reduced-order model can be developed on the basis of tuned modes of certain bladed disks. The validity of this algorithm is shown for a spring-mass model with three degrees of freedom per sector . In addition, the statistical distributions of the peak maximum amplitude are generated via Monte Carlo simulations , and the impact of mistuning is examined for a two-stage rotor.
|Original language||English (US)|
|Number of pages||9|
|Journal||International Journal of Turbo and Jet Engines|
|State||Published - 2008|
All Science Journal Classification (ASJC) codes
- Aerospace Engineering