Patent ID: 8449261
Filing Date: 2013-05-28
Classification: F01D,F04D,F05D

Abstract:
1. 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: 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.