A blade outer airseal has a body comprising: an inner diameter (ID) surface; an outer diameter (OD) surface; a leading end; and a trailing end. The airseal body has a metallic substrate and a coating system atop the substrate along at least a portion of the inner diameter surface. At least over a first area of the inner diameter surface, the coating system comprises an abradable layer comprising a metallic matrix and a solid lubricant; and the metallic matrix comprises, by weight, 35% copper, 30.0-45.0% combined nickel, cobalt, and iron with combined iron and cobalt content at most one-third of the nickel content, 2.0-8.0% aluminum, and 5.0-15.0% chromium.

An insulated seal seat assembly comprises a shaft configured and arranged to rotate about an axial axis, a seal seat that is secured to the shaft, and a thermal insulator configured and arranged radially between the shaft and the seal seat.

A thermal and environmental barrier coating composed of ceramic hollow microspheres sintered together. In one embodiment the microspheres are sintered together with a powder of another material that acts as a binder, or with a powder of a material that may be the same as the material of the hollow microspheres, forming a matrix in which the hollow microspheres are embedded. The hollow microspheres may be composed of a material with a high temperature capability, and with a low coefficient of thermal expansion.

A method of filling an internal cavity of a component for a machine with viscoelastic damping medium and/or insulating medium comprises pumping a plurality of capsules into the internal cavity using a peristaltic pump. Each capsule comprises a flexible skin encapsulating a viscoelastic damping medium, one or more viscoelastic damping medium precursors, an insulating medium, or one or more insulating medium precursors.

A method of making a light weight housing for an internal component is provided. The method including the steps of: forming a first metallic foam core into a desired configuration; forming a second metallic foam core into a desired configuration; inserting an internal component into the first metallic foam core; placing the second metallic foam core adjacent to the first metallic core in order to secure the internal component between the first metallic foam core and the second metallic foam core; applying an external metallic shell to an exterior surface of the first metallic foam core and the second metallic foam core; and securing an inlet fitting and an outlet fitting to the housing, wherein a thermal management fluid path for the internal component into and out of the housing is provided by the inlet fitting and the outlet fitting.

An apparatus and method for cooling an engine component such as a turbine engine airfoil, including a wall bounding an interior extending axially between a leading edge and a trailing edge and radially between a root and a tip. A cooling circuit it located within the interior of the airfoil can include a porous section having a porosity permitting a volume of fluid, such as air, to pass through the porous section.

Provided is an arrangement for discharging current due to a lightning stroke at a tip add-on of a rotor blade of a wind turbine, the arrangement including a conductor adapted to conduct the current due to the lightning stroke; an insulation arranged around the conductor, the insulation with the conductor being arrangeable within the tip add-on.

A method is provided in one example embodiment and may include positioning at least one nozzle within a hollow portion of a rotor blade at a distance associated with a span of the rotor blade and providing, via the at least one nozzle, a liquid foam mixture in the hollow portion, wherein the liquid foam expands and becomes a solid foam material that fills the hollow portion of the rotor blade. Another method is provided in another example embodiment and may include providing a plurality of openings for a rotor blade that are positioned proximate to a hollow portion of the rotor blade and providing a liquid foam mixture in the hollow portion of the rotor blade through at least one opening of the rotor blade, wherein the liquid foam mixture expands and becomes a solid foam material that fills the hollow portion of the rotor blade.

A fragmenting nozzle system includes a first nozzle at least partially disposed within a second nozzle. The first nozzle includes an ablative shell, a syntactic foam support disposed between the ablative shell and the second nozzle, and an ignition system disposed at least partially within the syntactic foam support. For example, the ignition system is operable to generate a controlled-energy deflagration pressure wave that fragments the first nozzle but not the second nozzle.

An airfoil assembly and a method of manufacturing the same are provided, the airfoil assembly defining a span axis, a root end, and a tip end. The airfoil assembly includes a reinforcement structure comprising a first helical support structure wrapped around the span axis between the root end and the tip end and a second helical support structure wrapped around the span axis between the root end and the tip end; a polymeric matrix material positioned at least partially around the reinforcement structure; and an outer skin positioned around the reinforcement structure and the polymeric matrix material.