Patent ID: 8678757

Claim:
A compressor stator vane or compressor rotor blade for an axial flow compressor wherein the axial flow compressor includes an axial direction, a radial direction, a compressor hub, and a compressor casing, the stator vane or rotor blade comprising: an airfoil with a plurality of airfoil sections including a span, a camber line and a leading edge at which the camber line includes a leading edge blade angle with the axial direction of the compressor and a trailing edge at which the chamber line includes a trailing edge blade angle with the axial direction of the compressor, wherein the plurality of airfoil sections are stacked at the leading edge on a straight line extending along the radial direction of the compressor from the compressor hub towards a compressor casing, and wherein the leading edge blade angle of the plurality of airfoil sections varies along the span and the leading edge blade angle is larger for the plurality of airfoil sections close to the compressor hub and close to the casing than for mid-span airfoil sections, wherein the trailing edge blade angle of the plurality of airfoil sections varies along the span and the trailing edge blade angle is larger for airfoil sections close to the compressor hub and/or close to the casing than for mid-span airfoil section, and wherein a first variation in the trailing edge blade angle of the airfoil sections is smaller than a second variation in the leading edge blade angle of the airfoil sections.