| 摘要 |
On a compressor blade ( 1 ) for gas turbine engines which is made of a fiber-composite core ( 4 ) with metallic enclosure ( 5 ) and which comprises a blade root ( 3 ) connected to an airfoil ( 2 ) and held in a recess ( 9 ) of a compressor disk ( 10 ), the fiber-composite core is made of transversely compressed fibers with subsequent matrix infiltration and is intimately connected via a surface enlargement by a micro-structure ( 7 ) to inner surfaces of the enclosure ( 5 ). Thus, the forces are introduced into the blade root ( 3 ) directly via the fiber material. Opposite side faces of the longitudinally straight blade root ( 3 ) each feature circularly arched bearing faces ( 8 ) with different centers (M 1 , M 2 ) which mate with similarly arched bearing areas ( 11 ) provided in the recess ( 9 ) to provide for a limited, dampened pendular movement for the absorption of the bending forces acting upon the fiber-composite core.
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