A steam turbine member has suppressed adhesion of scale for a long time without deterioration of corrosion resistance and the like of a turbine. A steam turbine member includes a hard layer 2 and a deposited amorphous carbon film 3 on a base material 1, in that order.

A coated article including an article having a surface; an oxidation resistant bond coat layer deposited on the surface, the oxidation resistant bond coat layer comprising a metal silicide phase, a crystalline ceramic phase and an amorphous ceramic phase, wherein the metal silicide phase has an aspect ratio greater than 1:1 but less than 50:1.

An automated system is provided. The system includes: a manipulator coupled to: an opening forming device configured to create an opening having a predefined geometry partially into a multilayer component at a selected location on a surface of the multilayer component, where the multilayer component includes a plurality of material layers including at least a substrate and a bond coat, and where the opening exposes each of the plurality of material layers; and an imaging device configured to create an image of the exposed plurality of material layers in the opening; and a processor configured to calculate at least a thickness of the bond coat of the exposed plurality of material layers from the image and based on the predefined geometry of the opening. Methods of using the system to analyze layer thickness of a multilayer component and repair a multilayer component are also provided.

A coating system for a turbine engine component is disclosed. The coating system includes a substrate, an optional bond coat, a synthetic oxide layer and a top coat. The synthetic oxide layer is formed by atomic layer deposition and includes two or more oxides.

A turbine blade for a gas turbine engine has an airfoil including leading and trailing edges joined by spaced-apart pressure and suction sides to provide an external airfoil surface extending from a platform in a spanwise direction to a tip. The external airfoil surface is formed in substantial conformance with multiple cross-sectional profiles of the airfoil defined by a set of Cartesian coordinates set forth in Table 1, the Cartesian coordinates provided by an axial coordinate scaled by a local axial chord, a circumferential coordinate scaled by a local axial chord, and a span location.

Turbine engine (80) components, such as blades (92), vanes (104, 106), ring segment 110 abradable surfaces 120, or transitions (85), have furcated engineered groove features (EGFs) (403, 404, 418, 509, 511, 512) that cut into the outer surface of the component's thermal barrier coating (TBC). In some embodiments, the EGF planform pattern defines adjoining outer hexagons (560, 640, 670, 690, 710). In some embodiments, the EGF pattern further defines within each outer hexagon (560, 640, 670, 690, 710) a planform pattern of adjoining inner polygons (570, 580, 590, 600, 610, 680, 682, 700, 702, 704, 705, 720). At least three respective groove segments (509, 511, 512) within the EGF pattern (506, 507, 508) converge at each respective outer hexagonal vertex (510, 564) or inner polygonal vertex (574, 564, 604, 614) in a multifurcated pattern, so that crack-inducing stresses are attenuated in cascading fashion, as the stress (σ.sub.A) is furcated (σ.sub.B, σ.sub.C) at each successive vertex juncture.

A coupon for replacing a cutout in a hot gas path component of a turbomachine is provided. The coupon includes a body having an outer surface; a chamber within the body for receiving a flow of a coolant; and a passage extending from the chamber to the outer surface of the body. The passage includes an internal portion within a wall of the body having a first perpendicular, cross-sectional area and an exit portion at the outer surface of the body having a second perpendicular, cross-sectional area that is greater than the first perpendicular, cross-sectional area.

A turbine engine component can include a surface comprising at least one edge and a coating disposed upon the surface that can extend to the edge. A spall break can be disposed along a line upon the surface adjacent the edge to prevent spallation of the coating from spreading from the edge onto the surface beyond the spall break. The spall break can comprise a discontinuity of the coating. A method of coating a turbine component can include preparing a substrate to receive a coating and selecting a fail location along the substrate for a coating. One or more coating can be applied to the substrate and a spall break can be incorporated into the one or more coatings. The spall break can comprise a line of discontinuity in the one or more coatings along the fail location.

In some examples, an article for a high-temperature mechanical system including a substrate and a doped calcia-magnesia-alumina-silicate resistant (doped CMAS-resistant) layer on the substrate. The doped CMAS-resistant layer is a thermal barrier coating or an environmental barrier coating and includes a calcia dopant.

An abradable powder composition is includes a metal component, a lubricant component, and a polymer component. A portion of the metal component is wrapped in the lubricant component to achieve high lubricity and abradability. The abradable powder composition can be used to form an abradable seal coating provided for use in a turbo machinery having a housing and a wheel having multiple blades. The housing houses the wheel which rotates therein. The seal coating is formed on the inner walls of housing adjacent where the wheel blades pass during their rotation. When the wheel is rotated such that, the blades contact the seal coating, it is abraded to form a close fit gap. The abradable seal coating preferably does not produce significant wear of the blade tips or transfer abradable material significantly to the blade tips upon being abraded.