Patent ID: 7530792
Filing Date: 2009-05-12
Classification: B23P,B24B,C21D,F01D,F05D,Y10T

Abstract:
1. An airfoil for a gas turbine engine, comprising: a root spaced apart from a tip, spaced-apart leading and trailing edges, a suction side extending from the leading edge to the trailing edge, and an opposed pressure side extending from the leading edge and the trailing edge, wherein a thickness of the airfoil is defined between the pressure side and the suction side; and a first region of residual compressive stress extending inward from a first area of a selected one of the pressure side and the suction side, the thickness of the airfoil varying within the first area; wherein the first region is surrounded by a first interior boundary, and a second region of residual compressive stress extending inward from a second area of the other one of the pressure side and the suction side, the thickness of the airfoil varying within the second area, wherein the second region is surrounded by a second interior boundary, and substantially all of the first and second interior boundaries are blended together with each other; and wherein at least a portion of the interior boundaries are coincident with a midplane of the airfoil.