Abstract: A turbine blade (18) for a gas turbine engine includes a machining datum and support tool interface (52). The datum and interface feature is a frustoconical depression residing in a blade outer shroud (36) and ideally aligned with an airfoil stacking line (40). The blade has a prefinished state in which the depression has a prefinished depth and a finished state in which the depression has a finished depth. The finished depth is smaller than the prefinished depth, but is nevertheless sufficient to act as a support feature during manufacturing operations. The utility of the depression, as both a datum and as a support feature, survives the original manufacturing operations so that the depression is useful for post-manufacturing inspection and repair.

Abstract: A turbine blade (18) for a gas turbine engine includes a machining datum (60) that extends radially from a pocket (54) in the outer shroud (36) of the blade. The datum is spaced from a sidewall (64) of the pocket so that the datum is peripherally continuous irrespective of whether the blade is in a prefinished state or in a completely finished state. Because the datum's peripheral continuity survives the original manufacturing process, the datum is available for use in post-manufacturing inspection and repair operations.

Abstract: A method for refurbishing or restoring a turbine vane or other airfoil to restore a desired flow area includes the steps of: providing a plate to be used to restore the flow area on the airfoil; cutting the plate into a desired shape; machining a series of tapers into the cut plate so that the cut plate has a single region with a substantially uniform thickness; overlaying a surface of the airfoil with the pre-cut, pre-shaped plate so that the substantially uniform thickness region is positioned over that part of the airfoil where the flow area is to be restored; and attaching the pre-cut, pre-shaped plate to the airfoil. The refurbishment or restoration method further includes heat treating the pre-cut, pre-shaped plate so that the plate softens and conforms to the shape of the airfoil surface.

Abstract: A fuel nozzle assembly 32 which extends into a flow path 18 for working medium gases is disclosed. Various construction details which decrease the amount of heat transfer to the fuel are developed. The assembly includes an external heat shield 50 and an internal heat shield 98 which provide longitudinally overlapping insulating gaps 52, 102 between the fuel and the hot working medium gases. In particular, the insulating gap 52 extends to the inlet 94 of the fuel nozzle support.