Abstract: A bearing system including a first member having an outer surface wherein at least a portion of the outer surface includes a plurality of plateaus and a plurality of indentations, a dry-film lubricant at least partially filling at least one of the plurality of indentations, and a second member having a mating surface to the outer surface of the first member wherein the second member configured to move past the first member.

Abstract: A bearing system including a first member having an outer surface wherein at least a portion of the outer surface includes a plurality of plateaus and a plurality of indentations, a dry-film lubricant at least partially filling at least one of the plurality of indentations, and a second member having a mating surface to the outer surface of the first member wherein the second member configured to move past the first member.

Abstract: 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.

Abstract: A gear pump for a gas turbine engine including a first gear having a plurality of gear teeth supported for rotation on a gear shaft relative to a second gear, wherein the gear teeth are formed from a steel base material and surfaces of the gear teeth are coated with a cavitation resistant coating material, and a journal bearing for carrying a gear shaft load through a fluid film pressure between a surface of the gear shaft and a surface of the journal bearing, wherein at least a portion of the journal bearing is formed from a cavitation resistant base material.

Abstract: An example embodiment of an air bearing assembly includes a first member and a shaft with a flange configured to rotate with respect to the first member. The first member has a first coating on at least one first surface facing at least one second surface on the flange or the shaft. The first coating includes tungsten carbide, a nonpolymeric self-lubricating coating, or a combination thereof. At least one of the second surfaces has a second coating on a surface facing the first coating.

Abstract: A disclosed method of hard coating a wear surface of a valve of an aircraft air management system is performed by depositing a hardface alloy powder onto the wear surface, heating the wear surface and the hardface alloy powder to transform the hardface alloy powder into a molten liquid mass, and subsequently cooling the molten liquid hardface alloy mass to solidify the hardface alloy onto the wear surface. The disclosed process provides for localized application and subsequent bonding of the hardface alloy to discrete portions of the wear surface. The solidified hardface alloy coating may then be machined to obtain specific wear surface geometries.

Abstract: An example embodiment of an air bearing assembly includes at least a first member and a shaft with a flange configured to rotate with respect to the first member. The first member has a coating on at least one surface facing at least one of the shaft and the flange. The coating includes tungsten carbide, a nonpolymeric self-lubricating coating, or a combination thereof.

Abstract: An example embodiment of an air bearing assembly includes a first member and a shaft with a flange configured to rotate with respect to the first member. The first member has a first coating on at least one first surface facing at least one second surface on the flange or the shaft. The first coating includes tungsten carbide, a nonpolymeric self-lubricating coating, or a combination thereof. At least one of the second surfaces has a second coating on a surface facing the first coating.

Abstract: An air bearing according to an example of the present disclosure includes a stationary member and a shaft with a flange configured to rotate with respect to the stationary member, and at least one of the flange and the shaft have a tungsten-carbide-based coating. An alternative air bearing and a method of making an air bearing are also disclosed.

Abstract: 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.

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

Abstract: A non-line-of-sight (NLOS) coating process is provided for a substrate having first and second transverse surfaces where the second surface lacks a LOS for depositional processing. The NLOS coating process includes electroplating or electroless plating a crack-resistant interlayer coating to at least the second surface and applying a wear-resistant coating to the crack-resistant interlayer coating by electrolytic or electroless plating.

Abstract: A component is provided including a body formed at least partially from a composite material. At least a portion of the composite material is covered by a plating. The plating includes a layer of electroless copper, a layer of electrolytic copper, a layer of nickel strike, and a finishing layer.

Abstract: A disclosed method of hard coating a wear surface of a valve of an aircraft air management system is performed by depositing a hardface alloy powder onto the wear surface, heating the wear surface and the hardface alloy powder to transform the hardface alloy powder into a molten liquid mass, and subsequently cooling the molten liquid hardface alloy mass to solidify the hardface alloy onto the wear surface. The disclosed process provides for localized application and subsequent bonding of the hardface alloy to discrete portions of the wear surface. The solidified hardface alloy coating may then be machined to obtain specific wear surface geometries.

Abstract: A vane for a variable diffuser includes a body with an inlet end and an outlet end, a leading surface extending from the inlet end to the outlet end, a trailing surface opposite the leading surface and extending from the inlet end to the outlet end, a first surface extending from the inlet end to the outlet end, and a second surface opposite the first surface and extending from the inlet end to the outlet end. The vane further includes a first cavity on the first surface of the vane adjacent the inlet end, a second cavity on the first surface of the vane adjacent the outlet end, a third cavity on the second surface of the vane adjacent the inlet end, and a fourth cavity on the second surface of the vane adjacent the outlet end.

Abstract: A thrust plate for a butterfly valve includes a thrust plate body that defines a recess that extends between a bottom thrust surface, side walls, and an open top. There is a nickel-based or cobalt-based wear-resistant coating located on the bottom thrust surface. The wear-resistant coating is harder than the thrust plate body.

Abstract: A thrust plate for a butterfly valve includes a thrust plate body that defines a recess. The recess extends between a bottom thrust surface, side walls and an open top. A wear-resistant coating is located on the bottom thrust surface.

Abstract: A valve is provided and includes a component including a surface and a wear plate including a surface disposed in sliding engagement with the surface of the component. The surface of the wear plate includes a corrosion resistant substrate, a secondary layer disposed on a surface of the corrosion resistant substrate, a noble metal layer disposed on a surface of the secondary layer and a tertiary layer disposed on a surface of the noble metal layer.

Abstract: A disclosed method of hard coating a wear surface of a valve of an aircraft air management system is performed by depositing a hardface alloy powder onto the wear surface, heating the wear surface and the hardface alloy powder to transform the hardface alloy powder into a molten liquid mass, and subsequently cooling the molten liquid hardface alloy mass to solidify the hardface alloy onto the wear surface. The disclosed process provides for localized application and subsequent bonding of the hardface alloy to discrete portions of the wear surface. The solidified hardface alloy coating may then be machined to obtain specific wear surface geometries.

Abstract: A rotary metering valve assembly includes a stationary body plate having a first contact surface. Also included is a valve plate having a second contact surface disposed in contact with the first contact surface of the stationary body plate, wherein the valve plate is configured to rotate relative to the stationary body plate. At least one of the first contact surface and the second contact surface comprises a surface flatness of less than about 2.4 ?m (about 93 ?in) and a surface roughness of at least about 0.2 ?m (about 8 ?in).