초록 ▼

A new blading system for controlling the structural vibrations in axial-flow compressors, turbines, or fans, as in aircraft engines and like turbomachines including a stator disc and a rotor disc is presented. The rotor disc defines several radial hubs that retain the rotor blading systems. Each bla

A new blading system for controlling the structural vibrations in axial-flow compressors, turbines, or fans, as in aircraft engines and like turbomachines including a stator disc and a rotor disc is presented. The rotor disc defines several radial hubs that retain the rotor blading systems. Each blading system includes a blade formed of an airfoil, and a root attachment which is dimensioned to fit within, and to engage a corresponding hub. Viscoelastic dampers are selectively applied to the outer surfaces of the root attachment on which compressive or shear forces are likely to develop, intermediate the root attachment and the hub, for compression therebetween upon rotation of the rotor disc, in order to dampen structural vibrations. One advantage presented by the viscoelastic dampers lies in its simplicity, efficiency, cost effectiveness, and its ability to be retrofitted into existing turbomachines with minor surface treatment of the root attachments. Furthermore, since the dampers are not exposed to the inflowing airstream, they do not affect the aerodynamic performance of the turbomachine. Another feature of the damping system is that it provides a significant source of damping to minimize destructive structural vibrations, thereby increasing the durability of the turbomachine, and reducing acoustic noise accompanying high amplitude vibrations.

대표청구항 ▼

[ What is claimed is:] [1.] In a turbomachine including at least one stator disc having a plurality of radial stator vanes, and at least one rotor disc terminating in a plurality of radial hubs to retain a plurality of blading systems, each of the blading systems comprising in combination:a blade fo

[ What is claimed is:] [1.] In a turbomachine including at least one stator disc having a plurality of radial stator vanes, and at least one rotor disc terminating in a plurality of radial hubs to retain a plurality of blading systems, each of the blading systems comprising in combination:a blade formed of an airfoil and a root attachment;said root attachment being dimensioned to fit within and to engage a corresponding one of the hubs, and including at least one outer surface on which a compressive and shear force develops upon rotation of said rotor disc; andat least one viscoelastic damper positioned against said outer surface of said root attachment, intermediate said root attachment and said corresponding one of the hubs, for compression therebetween upon rotation of said rotor disc to dampen vibration energy resulting from the passage of said blade in proximity to the stator vanes, without affecting the aerodynamic performance of the turbomachine.