| 摘要 |
In the rotor of a turbomachine, especially the turbine of a gas turbine engine, each rotor blade is mounted in the rotor disk rim by a blade root having a serrated profile that engages a correspondingly formed axial groove in the rotor disk rim. A shroud band is constructed so that at a predetermined operating point of the turbine, adjacent blades are supported against one another so as to damp vibrations. Light weight and heavy weight rotor blades are mounted alternatingly around the circumference of the rotor disk. The blade root and corresponding axial groove associated with each light weight or heavy weight blade are differently dimensioned or shaped to correspond to the differing loads associated with the heavy weight blades and the light weight blades respectively. Different materials, having different densities, are used for the heavy weight blades and the light weight blades.
|
