| 摘要 |
A compressor blade for an aircraft engine includes a blade core made of a fiber compound material and a metallic enclosing structure. The enclosing structure is of a multi-part design and includes blanks ( 4, 5 ) attached to the blade core by a metallic weave ( 6 ) on the suction side and on the pressure side, with the two blanks being firmly connected at the aerodynamically shaped leading edge of the compressor blade by to a leading-edge former ( 3 ). Depending on the specific loads applied on the pressure side and on the suction side, welds attaching the blanks to the leading-edge former ( 8, 9 ) are offset relative to each other and the material thicknesses of the components of the enveloping structure are matched to each other.
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