Patent ID: 9102014
Filing Date: 2015-08-11
Classification: B23P,F01D,F05D,Y10T

Abstract:
1. A method of servicing an airfoil assembly for use in a gas turbine engine, the airfoil assembly defined by a base material and comprising an airfoil having a radially inner end which is attached to a platform from which the airfoil extends, the method comprising: removing predetermined amounts of the base material from the airfoil assembly proximate to a fillet area and the radially inner end of the airfoil assembly at leading and trailing edges of the airfoil and at a location between the leading and trailing edges via water jet material removal, the fillet area comprising a junction between the airfoil and the platform and located at an intersection between the airfoil and the platform; wherein a remainder of the base material comprising base material of the airfoil assembly other than proximate to the fillet area is left intact; wherein a radius of curvature at the fillet area of the resulting structure after said removing is at least as large as a radius of curvature at the fillet area before said removing; and wherein the predetermined amounts of the base material that are removed from the airfoil assembly at the leading and trailing edges of the airfoil and at the location between the leading and trailing edges of the airfoil are dependent upon a thickness of the fillet area at these locations so as to remove the predetermined amounts of the base material including any defects in the base material at these locations such that, after the base material is removed, a structural rigidity of the airfoil is maintained at the fillet area.