In a manufacturing method of a turbine rotor blade using an Ni-based forged alloy, provided is a turbine rotor blade and a member of a turbine rotor blade having an excellent workability and a high degree of freedom in the design of a cooling structure. The turbine rotor blade includes at least two members, including a first member and a second member, and each member is provided with cooling structural parts acting as cooling flow passages. The turbine rotor blade has a joint that integrates the first member and the second member, wherein the joint has a forged structure and the whole turbine rotor blade including the joint has a uniform forged structure.

An insert fixture for use in the manufacture of a single crystal component by a hot isostatic pressing process. The insert fixture comprising: at least a lower plate separated from an upper plate by interconnecting members. The upper plate comprises at least a slot for the insertion of the single crystal component. The lower plate features a related engagement feature for engaging with the single crystal component. The insert fixture may be cast from a ceramic material. The insert fixture may be cast from an alumina ceramic or molybdenum alloy. The interconnecting members may be made from a molybdenum alloy.

A certain material irregularly expressed in an observation area is effectively observed. An observing apparatus includes a first observing unit performing a time lapse shooting of a predetermined observation area, a first discriminating unit discriminating whether or not a first material is expressed in the observation area based on an image obtained by the first observing unit, and a second observing unit starting a time lapse shooting relating to a part where the first material is expressed at a timing when the first material is expressed in the observation area, in which a shooting frequency of the time lapse shooting by the second observing unit is higher than a shooting frequency of the time lapse shooting by the first observing unit.

Disclosed herein is a method of coating, comprising providing an article having an internal passage therein to be coated; electrolytically applying a first layer that comprises chromium or a chromium alloy onto a surface of the internal passage; electrolytically applying a second layer comprising aluminum or an aluminum alloy onto the first layer; and heat treating the article to promote interdiffusion between the first layer and the second layer.

The present invention relates to a component of a turbomachine with a repair layer and a method for repairing wear-damaged components (1, 10) of a turbomachine, in particular of elements of a flow duct boundary, having the following method steps: preparing the area to be repaired, in order to provide a smooth and clean surface (4), applying an Ni-based braze (7) with a proportion of hard material particles (8) to the surface (4) to form a repair layer (15), wherein the hard material particles comprise hard alloys based on cobalt or nickel, heat treating the component to braze the repair layer onto the component under vacuum conditions.

Disclosed herein is a method of coating, comprising providing an article having an internal passage therein to be coated; electrolytically applying a first layer that comprises chromium or a chromium alloy onto a surface of the internal passage; electrolytically applying a second layer comprising aluminum or an aluminum alloy onto the first layer; and heat treating the article to promote interdiffusion between the first layer and the second layer.

A certain material irregularly expressed in an observation area is effectively observed. An observing apparatus includes a first observing unit performing a time lapse shooting of a predetermined observation area, a first discriminating unit discriminating whether or not a first material is expressed in the observation area based on an image obtained by the first observing unit, and a second observing unit starting a time lapse shooting relating to a part where the first material is expressed at a timing when the first material is expressed in the observation area, in which a shooting frequency of the time lapse shooting by the second observing unit is higher than a shooting frequency of the time lapse shooting by the first observing unit.

A coated component and a method of preparing a coated component are provided. The method comprises providing a substrate; and applying a dual coating system to the substrate. The applying of the dual coating system includes applying a diffusion barrier coating; and applying a corrosion-resistant coating. The corrosion-resistant coating comprises a greater concentration of silicon and aluminum than the diffusion barrier coating, and the dual layer coating system includes an aluminide interdiffusion zone.

The present disclosure relates to building very large gas turbines without changing rotor materials. The gas turbine part can include a structure composed of a metal and a ternary ceramic called MAX phase, having a formula Mn+1AXn, where n=1, 2, or 3, M is an early transition metal such as Ti, V, Cr, Zr, Nb, Mo, Hf, Sc, Ta, and A is an A-group element such as Al, Si, P, S, Ga, Ge, As, Cd, In, Sn, Tl, Pb, and X is C and/or N.

In some examples, a method may include depositing, from a slurry comprising particles including silicon metal, a bond coat precursor layer including the particles comprising silicon metal directly on a ceramic matrix composite substrate. The method also may include locally heating the bond coat precursor layer to form a bond coat comprising silicon metal. Additionally, the method may include forming a protective coating on the bond coat. In some examples, an article may include a ceramic matrix composite substrate, a bond coat directly on the substrate, and a protective coating on the bond coat. The bond coat may include silicon metal and a metal comprising at least one of Zr, Y, Yb, Hf, Ti, Al, Cr, Mo, Nb, Ta, or a rare earth metal.