Patent ID: 7887288
Filing Date: 2011-02-15
Classification: B24C,C21D,F01D,Y02T,Y10T

Abstract:
1. A turbine blade or vane, comprising: an airfoil portion; a root portion arranged below the airfoil portion; a dove tail shaped securing portion arranged below the root portion having a surface comprised of sub regions that have locally different compressive residual stresses; a concavely curved sub region having a radius of curvature arranged within the surface regions where the width of the concavely curved portion is three to five times the radius of curvature; and a convexly curved sub region arranged on the surface and adjacent to the concavely curved sub region, wherein the concavely curved region has higher compressive residual stresses than the convexly curved region, and the level of the compressive residual stress in the concavely curved region is al least 30% of the component base material yield strength (R