| 摘要 |
PURPOSE: To provide a rotor blade that does not receive undesired vibration and limits a damping effect in a particular area of the structure. CONSTITUTION: A vibration damper (damping member) for blades of a gas turbine engine has a shaft 48 and a contact head 50 connected with the shaft. The shaft 48 is slidably inserted in a cylindrical recess 34 arranged in a blade base 14. During rotation of a rotor disk 18, the shaft of the damping member slides along the axis of the shaft, therefore, the damping member is moved at least in the radial direction and circumferential direction by centrifugal forces. The contact head of the damping member of one blade 10 finally abuts with the blade base of the adjacent blade 10' to be useful in vibration damping of the two blades 10 and 10'. |
