US Patent 10344711 System and method of alleviating blade flutter

A modified inlet region of a turbofan engine for reducing or eliminating turbofan flutter. The modified inlet region is defined by annular inside surface and a fan. The modified inlet region is upstream and co-axial with the fan. A plurality of fins are disposed circumferentially around the annular inside surface and extend radially into the modified inlet region. Each fin may be attached normal to the annular inside surface or at an angle. The plurality of fins serve to disrupt the propagation of acoustic reflections leading to turbofan flutter.