Patent ID: 8449261

Claim:
A blade for a multi-stage axial compressor, for use in any one of stages eighteen to twenty one of the axial compressor, comprising: a base; and an airfoil, extending radially from the base, having: a suction face and a pressure face; a second end radially distal from the base; a chord length; a camber line; a thickness defined by a distance, perpendicular to the camber line, between the suction face and the pressure face; a plurality of relative thicknesses, defined as the thickness divided by the chord length; an airfoil height, defined as a distance between the base and the second end; and a relative height, defined as a height point, extending in the radial direction from the base, divided by the airfoil height, wherein: at a first division starting from the base, the relative airfoil height is 0.000000 and a maximum relative thickness at that height is 0.1200; at a second division starting from the base, the relative airfoil height is 0.305181 and a maximum relative thickness at that height is 0.1139; at a third division starting from the base, the relative airfoil height is 0.553382 and a maximum relative thickness at that height is 0.1089; at a fourth division starting from the base, the relative airfoil height is 0.745602 and a maximum relative thickness at that height is 0.1050; at a fifth division starting from the base, the relative airfoil height is 0.884467 and a maximum relative thickness at that height is 0.1023; at a sixth division starting from the base, the relative airfoil height is 0.973731 and a maximum relative thickness at that height is 0.1005; and at a seventh division starting from the base, the relative airfoil height is 1.0000 and a maximum relative thickness at that height is 0.1000, wherein each maximum relative thickness has a tolerance of +/−0.3%, and is carried to four decimal places and wherein each relative height is carried to six decimal places.