Modern aircraft engine design challenges are focused on increasing aircraft safety, lowering weight, optimizing manufacturing costs, and raising aircraft performance by expanding engine operating ranges. Within this frame, even though the design of thinner, lighter and highly loaded blades is an efficient solution to meet such requirements, new blade structures are more flexible and thus, are much more sensitive to unsteady physical phenomena such as fluid-structure or blade row interactions. Vibrations of high amplitudes might endanger the blade aeroelastic stability as well as its structural integrity. One of the main goal of aeroelastic investigations in turbomachinery is therefore:
- Improve the comprehension of the physical mechanisms of unsteady aerodynamic excitations.
- Improve the procedures and tools dedicated to the prediction of flutter limits and forced response amplitudes.
The Institute of Aeroelasticity’s studies are focused on four main topics:
- Experimental and numerical investigations dedicated to flutter phenomena.
- Experimental and numerical investigations dedicated to forced response phenomena.
- Experimental investigations dedicated to mistuning effects.
- Experimental investigations dedicated to turbine and compressor blade aerodynamics.