Coating systems for a cooled turbine blade tip, such as a metal turbine blade tip, are provided. The coating system includes an abrasive layer overlying the surface of the turbine blade tip. One or more buffer layers may additionally be disposed between an outer surface of the blade tip and the abrasive layer. The coated blade tip can be used with a ceramic matrix composite (CMC) shroud coated with an environmental barrier coating (EBC) to provide improved cooling to the tip so as to lengthen oxidation time of the abrasive layer and reduce blade tip wear. Methods are also provided for forming the cooled blade tip and applying the coating system onto the cooled turbine blade tip.

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 method for joining engine components includes positioning a first plurality of thermal protection structures across a thermal protection space between a first thermal protection surface and a second thermal protection surface. The first and second engine components are locally joined by forming a first plurality of transient liquid phase (TLP) or partial transient liquid phase (PTLP) bonds along corresponding ones of the first plurality of thermal protection structures between the first thermal protection surface and the second thermal protection surface. The second thermal protection surface is formed from a second surface material different from a first surface material of the first thermal protection surface.

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.

An anti-ice arrangement for a gas turbine engine may comprise an engine static structure, a fan blade housed for rotation within the engine static structure, and a magnetic field source mounted in close proximity to the fan blade and configured for inducing eddy currents in the fan blade to increase a surface temperature of the fan blade.

A first stage turbine nozzle includes a first stage hub portion extending axially along a central axis, a first stage disk portion attached to the first stage hub portion and centered on the central axis, and a plurality of first stage vanes positioned radially around and attached to the first stage disk portion. Each vane extends a vane height H away from the first stage disk portion and each vane has a first end positioned at a diameter D away from the central axis. The first stage turbine nozzle also includes a plurality of first stage throats defined between radially adjacent first stage vanes. Each first stage throat has a throat width W between radially adjacent first stage vanes. The first stage turbine nozzle also includes a coating on a sidewall of each first stage vane, wherein a surface roughness of the sidewall is between 125 and 200 microinches Ra.

A coating for an article includes a seal coat comprising self-healing particles disposed in a seal coat matrix and a bond coat disposed on the seal coat. The bond coat includes a matrix, diffusive particles disposed in the matrix, and gettering particles disposed in the matrix. A coating for an article and a method of applying a coating to an article are also disclosed.

In an implementation, a rotor blade (alternatively referred to herein as blade) for a helicopter or other aircraft may include an outer layer. The outer layer may define a cavity. The outer layer may at least partially correspond to an airfoil, e.g., a wing. One or more inserts may be included within the cavity and be encompassed thereby. The first insert may have a density of at least 0.6 pounds per cubic inch.

A composite bond coat may include a matrix and a reinforcing component. The matrix may be formed from silicon-based particles, and the reinforcing component includes silicon-based ceramic particles. The composite bond coat may be formed by introducing a precursor composition into a plume generated by a thermal spray gun to generate a thermal spray stream. The thermal spray stream may be directed at a major surface defined by a substrate of the component to form the composite bond coat. The precursor composition includes the matrix component and the reinforcing component.

A bearing for a turbomachine variable pitch stator vane pivot mounted in a bore of a casing of the turbomachine and including a bushing integral with the bore and allowing rotation of a pivot rod within the casing, and additionally a ring mounted so as to be integral with the pivot rod inside the bushing and including an outer part providing the stiffening of the ring and an inner part integral with the outer part and providing a damping function.