A method for forming a coated turbine component and a coated turbine component is provided. The method includes a step of providing a component having a substrate including a trailing edge face. The method further includes a step of applying a thermal barrier coating or environmental barrier coating selectively to the substrate to form a discontinuous transition from a hot gas path surface at the trailing edge face to discourage hot gas flow along the trailing edge face.

An assembly comprising a vent tube intended to be mounted inside a turbine shaft of a turbomachine. The vent tube has a radially inner annular part from which at least one annular centering part extends radially outwards. The centering part has a groove and a sealing part of a sealing member is mounted in the groove. The sealing part is designed to come into sealing abutment against an inner surface of the turbine shaft. The sealing member has a protective part covering at least one area of the centering part situated upstream and/or downstream of the groove.

A nickel-chromium (NiCr) alloy and a method for electrodepositing the NiCr alloy on a turbine engine component for dimensionally restoring the engine component are described. The engine component is restored by rebuilding wall thickness with the NiCr alloy including from 2 to 50 wt % chromium balanced with nickel. The turbine component coated with the NiCr alloy is heat-treated at a high temperature to homogenize composition of the alloy to mimic the base alloy and to restore materials lost during repair of the turbine component.

Protective coatings on an aerospace component are provided. An aerospace component includes a surface containing nickel, nickel superalloy, aluminum, chromium, iron, titanium, hafnium, alloys thereof, or any combination thereof, and a coating disposed on the surface, where the coating contains a nanolaminate film stack having two or more pairs of a first deposited layer and a second deposited layer. The first deposited layer contains chromium oxide, chromium nitride, aluminum oxide, aluminum nitride, or any combination thereof, the second deposited layer contains aluminum oxide, aluminum nitride, silicon oxide, silicon nitride, silicon carbide, yttrium oxide, yttrium nitride, yttrium silicon nitride, hafnium oxide, hafnium nitride, hafnium silicide, hafnium silicate, titanium oxide, titanium nitride, titanium silicide, titanium silicate, or any combination thereof, and the first deposited layer and the second deposited layer have different compositions from each other.

An article of manufacture includes a rotor blade configured for use with a turbomachine. The blade is configured for attachment to a rotor wheel. The blade is configured to substantially reduce the possibility of attachment with an undesired rotor wheel by modification of at least one characteristic of the blade, so that the modification of the characteristic is matched by a complementary characteristic of the rotor wheel. The characteristic of the blade is, neck width, platform length, platform angle, platform height, tang height, or circumferential width. The blade and the wheel comprise a first stage of the turbomachine. The undesired rotor wheel is in a second stage of the turbomachine, where the first stage is different from the second stage. The complementary characteristic of the wheel is, slot opening width, platform opening depth, slot neck width, slot neck angle, slot tang depth, or slot tang width.

A turbine ring sector made of ceramic matrix composite material has a portion forming an annular base with an inner face for defining the inner face of a turbine ring when the ring sector is mounted on a ring support structure and an outer face from which there extends an attachment portion for attaching the ring sector to the ring support structure, the ring sector further including inter-sector faces, each for facing a neighboring ring sector when the ring sector is mounted on the ring support structure; wherein the inter-sector faces are coated in an environmental barrier that is doped with an electrically-conductive compound and that presents at least one slot.

A corrosion maintenance scheduling and implementation system and method measure one or more characteristics of corrosion in equipment before and after implementation of a corrosion remediation action, determine one or more of a change in the one or more characteristics of the corrosion between before and after implementation of the corrosion remediation action, one or more historical operational characteristics of the equipment, or one or more forthcoming operational characteristics of the equipment, and modify a schedule of the corrosion remediation action for the equipment based on one or more of the one or more characteristics of corrosion that are measured, the change in the one or more characteristics of the corrosion, the one or more historical operational characteristics of the equipment, and/or the one or more forthcoming operational characteristics of the equipment.

A nickel-chromium (NiCr) alloy and a method for electrodepositing the NiCr alloy on a turbine engine component for dimensionally restoring the engine component are described. The engine component is restored by re-building wall thickness with the NiCr alloy including from 2 to 50 wt % chromium balanced with nickel. The turbine component coated with the NiCr alloy is heat-treated at a high temperature to homogenize composition of the alloy to mimic the base alloy and to restore materials lost during repair of the turbine component.

A compressor assembly may include a compressor housing and a compressor impeller disposed within the compressor housing. The compressor housing may have an internal aerodynamic surface that defines a circumferentially extending volute, and the compressor impeller may have an external aerodynamic surface that faces toward at least a portion of the internal aerodynamic surface of the compressor housing. A nonstick coating may be formed on the internal aerodynamic surface of the compressor housing or on the external aerodynamic surface of the compressor impeller. The nonstick coating may prevent foreign material introduced into the compressor assembly from collecting on the internal aerodynamic surface of the compressor housing or on the external aerodynamic surface of the compressor impeller.

Protective coatings on an aerospace component and methods for depositing the protective coatings are provided. A method for depositing a coating on an aerospace component includes exposing an aerospace component to a first precursor and a first reactant to form a first deposited layer on a surface of the aerospace component by a chemical vapor deposition (CVD) process or a first atomic layer deposition (ALD) process and exposing the aerospace component to a second precursor and a second reactant to form a second deposited layer on the first deposited layer by a second ALD process, where the first deposited layer and the second deposited layer have different compositions from each other.