Patent ID: 8911215

Claim:
A compressor rotor blade for an axial compressor, comprising: a curved blade airfoil which includes a pressure-side wall and a suction-side wall which in one direction, extend in each case from a common leading edge to a common trailing edge and, and in another direction extend from a fastening-side blade airfoil end to a blade airfoil tip, forming a span, wherein for each blade airfoil height which exists along the span the blade airfoil includes: a profile with a suction-side contour and a pressure-side contour, an at least partially curved camber line, and a rectilinear profile chord, wherein the suction-side contour and the pressure-side contour, camber line and profile chord extend in each case from a leading edge point to a trailing edge point, wherein at least some of the camber lines of the blade tip-side profiles includes at least two inflection points.