The aim of this paper is to study the effects of
mistuning on fan flutter. The computations are based
on a three-dimensional, whole assembly, timeaccurate,
viscous, finite-volume compressible flow
solver. The unsteady flow cases are computed as
Reynolds-averaged Navier–Stokes, with the basic
assumption that the frequencies of interest are
sufficiently far away from the frequencies of
turbulent flow structures. The overall solution
method is implicit, with second-order accuracy in
space and time. A rig wide-chord fan blade, typical of
modern civil designs, was used as the benchmark
geometry for this study. There are 20 blades in the
fan assembly. A random pattern frequency mistuning
was used in most of analysis undertaken in this
paper. The 1F mode shapes are the same for all
mistuned blades. The objectives of this work are:
1. To check if the introduction of mistuning would
bring the experimental and computed flutter
boundaries closer
2. To explain how mistuning provide stability
3. Establish a relationship between mistuning and
damping
4. Provide a data base which can be used in future
for testing simple mistuning models