Patent ID: 7156622
Filing Date: 2007-01-02
Classification: B23P,B64C,F01D,F04D,F05D,Y02T

Abstract:
1. A compressor blade for an aircraft engine, comprising: an airfoil having a blade core made of a fiber compound material and a metallic enclosing structure, wherein the metallic enclosing structure is of a multi-part design and includes a blank on a suction side of the airfoil and a blank on a pressure side of the airfoil which are connected in an area of a leading edge of the airfoil to a leading-edge former constructed of a solid metal, the leading-edge former being thicker on the pressure side than on the suction side and including an attaching rib facing towards the blade core and which protrudes into the fiber compound material, the blank on the pressure-side being thicker than the blank on the suction side.