| 摘要 |
A damping arrangement for a blade ( 20 ) of an axial turbine, in particular a gas turbine, includes a damping element ( 17 ) which is arranged in a recess ( 16 ) in the blade aerofoil ( 10 ) of the blade ( 20 ) and frictionally dampens the vibrations of the blade ( 20 ). In such a damping arrangement, simplified manufacture and assembly and a reliable and effective function are achieved by the recess being configured as a cavity ( 16 ) extending in the radial direction through the inside of the blade aerofoil ( 10 ), the damping element ( 17 ) being inserted in the radial direction into said cavity ( 16 ).
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