Abstract:
PROBLEM TO BE SOLVED: To provide a repairing method of a turbine engine part. SOLUTION: This repairing method of the turbine engine part such as a vane and a blade having air foil comprises to remove an oxide deposit from respective parts of a part indicating damage by crushing or oxidation of heat insulating coating, to remove a ceramic heat insulating layer from the part, and to blend a surface of the part generating nicks, dents and cracks. When the part has a deteriorated aluminum area, the deteriorated area is removed or replenished. A tip part of the part is also recovered when the part is damaged, and cutting capacity of the part is restored by applying polishing to the tip part. Afterwards, ceramic coating is applied to the part. COPYRIGHT: (C)2003,JPO
Abstract:
PROBLEM TO BE SOLVED: To provide the coating film of an aluminum compd. capable of being easily applied on the selected part of a metallic article and highly resistant to oxidation and thermal fatigue. SOLUTION: The local coating film of a low-activity aluminum for a metallic article is formed by arranging a tape coating film material on a part of the article. The coating film material contains a binder, a halide activator, an aluminum source and an inert ceramic material. The coating film material and article are heated at 1800 deg.F (982 deg.C) to 2050 deg.F (1121 deg.C) for 4 to 7hr in an inert atmosphere. Consequently, the local coating film of a low-activity aluminum compd. having an aluminum coating film microstructure including two different regions, i.e., an inner diffusion region and an outer region contg. 20-28wt.% aluminum, is formed.
Abstract:
A repair coating for superalloy articles, such as gas turbine engine components, includes a volatile organic carrier or water-based carrier, a fluxing agent, a thickening agent, balance a filler mix. The filler mix consists of at least two distinct particulate components. The mix includes a first particulate component having a composition which approximates that of the article being repaired. The mix also includes a second particulate component having a composition approximating that of the article and a melting point depressant, such as boron. This melting point depressant is substantially in excess of that in the article and sufficient to provide melting of a portion of the mix at a processing temperature below the melting temperature of the article. The above filler mix is blended with the other constituents to form the repair coating which is applied to an article.
Abstract:
A method for forming or remanufacturing a component (22; 200) to have an internal space (50). A refractory metal blocking element is formed, in situ, with at least a portion to be within the internal space (50). A material (90; 232) is added by at least one of welding, laser cladding, and diffusion brazing, the blocking element at least partially blocking entry of the material (90; 232) to the internal space (50). The blocking element is removed.
Abstract:
The invention relates to a low activity localised aluminide coating for a metallic article made by positioning a coating material, preferably in the form of a tape, on a portion of the article. The coating material comprises a binder, a halide activator, an aluminum source, and an inert ceramic material. The coating material and the article are heated in an inert atmosphere between about 1800 DEG F (982 DEG C) and about 2050 DEG F (1121 DEG C) for between about four and about seven hours thereby producing a low activity localized aluminide coating having an outward diffusion aluminide coating microstructure characterized by two distinct zones, an inner diffusion zone and an outer zone including between about 20-28 percent, by weight, aluminum.
Abstract:
A method for forming or remanufacturing a component (22; 200) to have an internal space (50). A refractory metal blocking element is formed, in situ, with at least a portion to be within the internal space (50). A material (90; 232) is added by at least one of welding, laser cladding, and diffusion brazing, the blocking element at least partially blocking entry of the material (90; 232) to the internal space (50). The blocking element is removed.
Abstract:
A nickel base repair alloy comprises a blend of about 40 to 60 wt% of a first nickel based braze alloy containing boron, about 15 to 35 wt% of a first nickel based filler material, and the remainder consisting of a blend of a second nickel based filler material and a low melting eutectic braze nickel based alloy.
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.