Embodiments of the present disclosure provide surface treatment tools, methodologies, and/or treated turbomachine components. A surface treatment tool according to the present disclosure can include a lathe assembly having a lathe chuck for receiving a component thereon, wherein the lathe chuck rotates the component about a first axis of rotation, and wherein the component includes an exposed axial target surface; and a sander or burnishing tool coupled to the lathe assembly and including a sanding or burnishing surface thereon, coupled to a drive system, wherein the sanding or burnishing surface is oriented along a second axis substantially non-parallel with the first axis of rotation, such that the sanding or burnishing surface selectively contacts the target surface of the component to yield a polished target surface.

A method for preventing corrosion of an impeller-shaft assembly of a turbomachine comprises the steps of assembling an impeller on a shaft in order to define an impeller-shaft assembly; plating the assembly by inserting the assembly into a plating bath; and coating at least a first predefined surface on the impeller and a second predefined surface on the shaft wherein the coating step is performed by spraying the predefined surfaces.

A method applies one or more films of polynuclear aluminum oxide hydroxide and polynuclear chromium hydroxide to a metal substrate. A method thermally treats the metal substrate with the one or more films at a temperature of at least 250 C., the thermal treatment reducing the polynuclear aluminum oxide hydroxides and the polynuclear chromium hydroxides to at least one layer of aluminum-chromium oxide.

The seal assembly can have a support ring having an annular shape defined around a seal axis, and a plurality of strips of a metal material, each strip of the plurality of strips being folded along a length of the strip forming a fold and a pair of segments extending radially inwardly from the fold, relative the seal axis, the fold secured at the support ring, the fold having a bending radius defined around a bending axis, the bending axis oriented parallel to the seal axis, the plurality of strips being arranged circumferentially relative one another, around the seal axis.

A turbine blade of a gas turbine engine is described which includes an airfoil extending away from the hub platform to a blade tip. The airfoil defines a leading edge, a trailing edge, and a span-wise length extending between the platform and the blade tip. A hot-corrosion-resistant coating is located on the leading edge of the airfoil within a radially inner portion thereof, the radially inner portion extending away from the hub platform a desired distance along said span-wise length.

Movable ring assembly for a turbomachine rotor, the movable ring including an outer peripheral toothing, each tooth of the outer peripheral toothing having an inner face intended to be positioned facing a blade root of the rotor, and an outer face opposite to the inner face and intended to be positioned facing an axial retaining hook arranged on the blade root. Furthermore, the movable ring assembly includes at least one protective element arranged on the outer face of at least one tooth of the outer peripheral toothing.

The invention relates to a high temperature protective coating based on MCrAlY coating, with M at least one element out of the group of Ni, Co and Fe, for a component of a turbo machine, especially a gas turbine, the coating containing at least at least 1.75 vol.-% chromium borides and the coating consisting of the following chemical composition (in wt.-%): 10-27 Cr; 3-12 Al; 1-4 Si; 0.1-3 Ta; 0.01-3 Y; 0.1-3 B; 0-7 M, with M being a different element out of said group compared to the remainder, and the remainder being M and inevitable impurities. A preferred embodiment is a coating with the following chemical composition: 10-27 Cr; 3-12 Al; 1-4 Si; 0.1-3 Ta; 0.01-3 Y; 0.1-3 B; 0-7 Co and the remainder being Ni and inevitable impurities.

Disclosed is an austenitic stainless steel alloy that includes, by weight, about 22% to about 28% chromium, about 3.5% to about 6.5% nickel, about 1% to about 6% manganese, about 0.5% to about 2.5% silicon, about 0.3% to about 0.6% carbon, about 0.2% to about 0.8% niobium, about 0.2% to about 0.8% nitrogen, and a balance of iron. Molybdenum and tungsten are excluded. The alloy is suitable for use in turbocharger turbine housing applications for temperature up to about 980 C.

A component includes a diffusion coating comprising an inter-diffusion zone between the diffusion coating and a substrate and a non-metallic inclusions zone adjacent to an outer surface of the diffusion coating. A method of coating a component includes applying an aluminizing slurry to a localized area of a component and applying a chromizing slurry to the localized area of the component subsequent to heat treating the aluminizing slurry.

A method of fabricating a part by selectively melting powder is provided. The method includes: depositing a first layer of a first powder having a first element as its main element; depositing, on the first layer, a second layer of a second powder having a second element as its main element, which second element is different from the first element; and moving a first energy beam over the second layer, the energy delivered by the first beam serving to initiate an exothermic reaction between the first element and the second element, the energy given off by the exothermic reaction acting to locally melt together the first and second layers.