To provide a substrate consisting of carbon or non-metallic materials containing carbon with a layer of a metal having a high melting point, first an undercoat layer is applied to the substrate by plasma spraying in an inert atmosphere. The undercoat layer predominantly consists of rhenium, molybdenum, zirconium, titan, chrome, niobium, tantalum, hafnium, vanadium, platinum, rhodium or iridium. Onto that undercoat layer, a covering layer can be applied, by plasma spraying as well. In order to reduce the thermo-mechanical stress and to improve the adhesion of the undercoat layer on the surface of the substrate, the substrate is preheated prior to applying the undercoat layer. By means of such a method, carbon-containing substrates can be provided with an undercoat layer and, if required, with a covering layer quickly and reliably at low costs.

A method for manufacturing and repair wherein a component composed of equiaxed cast or wrought alloys has at least one section joined thereto composed of directionally solidified or single crystal material

A method for preparing a metallic article made of metallic constituent elements includes furnishing a mixture of nonmetallic precursor compounds of the metallic constituent elements. The method further includes chemically reducing the mixture of nonmetallic precursor compounds to produce an initial metallic material, without melting the initial metallic material, and consolidating the initial metallic material to produce a consolidated metallic article, without melting the initial metallic material and without melting the consolidated metallic article. A net macroscopic composition of the consolidated metallic article varies spatially according to a pre-selected pattern

A metallic article and method for producing such an article, having a metallic substrate, at least one metallic layer sprayed onto a laser shock peened surface area of the substrate, and a region having deep compressive residual stresses imparted by laser shock peening extending into the substrate from the laser shock peened surface. The metallic substrate and or layer may be made from an alloy such as a Cobalt or a Nickel based superalloy. The substrate may be made from Nickel Base forgings or Titanium base forgings. An exemplary embodiment of the present invention is a gas turbine engine rotor component such a disk and, more particularly, a turbine disk suitable for use in a hot section of a gas turbine engine. The invention may be used for new or refurbished parts to restore dimensions of the component and, in particular, radial dimensions.

A crack weld repair and method, particularly, for a gas turbine engine blade or other metallic component in the engine, providing a metallic substrate, a metallic filler bonded onto a substrate bond surface on the metallic substrate, and a region having deep compressive residual stresses imparted by laser shock peening extending into the substrate beneath the substrate bond surface. One embodiment provides a laser shock peened surface below the weld material filled void in a damaged area of the component forming a region of deep compressive residual stresses imparted by laser shock peening (LSP) extending from the laser shock peened surface into the component. Optionally, the surface over the repaired area of the weld filled void may also be laser shock peened forming a second region of deep compressive residual stresses imparted by laser shock peening (LSP) extending from the laser shock peened surface into the weld repair. Another embodiment provides a weld buildup tip overlay on a substrate bond surface of an airfoil tip having a laser shock peened region beneath the substrate bond surface.