Abstract: Methods and apparatus for inspecting a component are provided. The method includes receiving a plurality of data points that define a shape of the component, fitting the received data points to a curve that defines a predetermined model shape, and comparing the received data points to the curve defining the predetermined model shape to determine a break radius of the component.

Abstract: A method for replacing a portion of a gas turbine engine rotor blade, the rotor blade having a contour defined by a blade first sidewall and a blade second sidewall includes cutting through the rotor blade such that a cut line extends from a leading edge of the blade to a trailing edge of the blade, and between the first sidewall and the second sidewall, removing the portion of the rotor blade that is radially outward of the cut line, and coupling a replacement blade portion to remaining blade portion such that the newly formed rotor blade is formed with a pre-determined aerodynamic contour.

Abstract: A method facilitates repairing a gas turbine engine compressor blade airfoil. The method comprises removing titanium alloy material from along leading and trailing edges of the airfoil, and along a radially outer tip of the airfoil to form respective leading edge, trailing edge, and tip cut-backs which each define cut-back depths, and depositing titanium weld material onto the leading edge, trailing edge, and tip cut-backs. The method also comprises removing at least some of the titanium weld bead material to obtain pre-desired finished dimensions for the leading and trailing edges, and radially outer tip.