Abstract: A compositionally graded gas turbine disk is made by preparing a rotationally symmetric radially inner segment of a gas turbine disk preform, rotating the inner segment about a central axis, spray applying a radially outer-segment material onto the radially inner segment as it rotates about the central axis, preferably achieving a gradual transition in composition, and thereafter further processing the gas turbine disk preform to produce the compositionally graded gas turbine disk.

Abstract: An article is prepared by furnishing a plurality of powder particle substrates made of a substrate metal, providing a nonmetallic precursor of a metallic coating material, wherein the metallic coating material comprises an alloying element that is thermophysically melt incompatible with the substrate metal, contacting the powder particle substrates with the nonmetallic precursor, chemically reducing the nonmetallic precursor to form coated powder particles comprising the powder particle substrates having a surface-enriched layer of the metallic coating material thereon without melting the powder particle substrates, and processing the coated powder particles to form the article, without melting the powder particle substrates.

Abstract: A process for protecting a thermal barrier coating (TBC) on a component used in a high-temperature environment, such as the hot section of a gas turbine engine. The process applies a protective film on the surface of the TBC to resist infiltration of contaminants such as CMAS that can melt and infiltrate the TBC to cause spallation. The process generally entails applying to the TBC surface a metal composition containing at least one metal whose oxide resists infiltration of CMAS into the TBC. The metal composition is applied so as to form a metal film on the TBC surface and optionally to infiltrate porosity within the TBC beneath its surface. The metal composition is then converted to form an oxide film, with at least a portion of the oxide film forming a surface deposit on the TBC surface.

Abstract: A compositionally graded gas turbine disk is made by placing a cylindrically symmetric slip case concentrically into an interior of a cylindrically symmetric outer container. A first nickel-base superalloy powder is loaded into a radially inner first portion of the interior and a second nickel-base superalloy powder is loaded into a radially outer second portion of the interior. The slip case is removed so that the first nickel-base superalloy powder and the second nickel-base superalloy powder contact in the transition region and form a non-compacted powder mass. The non-compacted powder mass is processed into a gas turbine disk, typically by compacting the non-compacted powder mass to form a compacted powder mass, and thereafter heat treating the compacted powder mass.

Abstract: A method and system for transmitting data from a computer network security device for monitoring at least one computer network node to an operations center for monitoring at least the computer network security device and to the computer network security device from the operations center in a managed computer network security system including at least the computer network security device and operations center, including establishing security information associated with the at least one computer network security device. The established security information is used to authenticate data transmissions from the computer network security device to the operations center. The established security information is used to authenticate data transmission to the computer network security device from the operations center.

Abstract: A process for protecting a thermal barrier coating (TBC) on a component used in a high-temperature environment, such as the hot section of a gas turbine engine. The process applies a protective film on the surface of the TBC to resist infiltration of contaminants such as CMAS that can melt and infiltrate the TBC to cause spallation. The process generally entails applying to the TBC surface a metal composition containing at least one metal whose oxide resists infiltration of CMAS into the TBC. The metal composition is applied so as to form a metal film on the TBC surface and optionally to infiltrate porosity within the TBC beneath its surface. The metal composition is then converted to form an oxide film, with at least a portion of the oxide film forming a surface deposit on the TBC surface.

Abstract: A coating and coating process for incorporating surface features on an air-cooled substrate surface of a component for the purpose of promoting heat transfer from the component. The coating process generally comprises depositing a first metallic coating material on the surface of the component using a first set of coating conditions to form a first environmental coating layer, and then depositing a second metallic coating material using a second set of coating conditions that differ from the first set, such that an outer environmental coating layer is formed having raised surface features that cause the surface of the outer environmental coating layer to be rougher than the surface of the first environmental coating layer.

Abstract: A coating and coating process for incorporating surface features on an air-cooled substrate surface of a component for the purpose of promoting heat transfer from the component. The coating process generally comprises depositing a first metallic coating material on the surface of the component using a first set of coating conditions to form a first environmental coating layer, and then depositing a second metallic coating material using a second set of coating conditions that differ from the first set, such that an outer environmental coating layer is formed having raised surface features that cause the surface of the outer environmental coating layer to be rougher than the surface of the first environmental coating layer.

Abstract: A coated article having a high resistance to particle-impact damage has a substrate, and a layered coating overlying the substrate. The layered coating includes a substantially continuous quasicrystalline layer, and a substantially continuous ductile metallic layer in facing contact with the quasicrystalline layer. The coated article is preferably used in applications where it is subjected to particle-impact conditions.

Abstract: A coated article having a high resistance to particle-impact damage has a substrate, and a layered coating overlying the substrate. The layered coating includes a substantially continuous quasicrystalline layer, and a substantially continuous ductile metallic layer in facing contact with the quasicrystalline layer. The coated article is preferably used in applications where it is subjected to particle-impact conditions.

Abstract: A coating and coating process for incorporating surface features on an air-cooled substrate surface of a component for the purpose of promoting heat transfer from the component. The coating process generally comprises depositing a first metallic coating material on the surface of the component using a first set of coating conditions to form a first environmental coating layer, and then depositing a second metallic coating material using a second set of coating conditions that differ from the first set, such that an outer environmental coating layer is formed having raised surface features that cause the surface of the outer environmental coating layer to be rougher than the surface of the first environmental coating layer.

Abstract: A gas turbine engine component includes a perforate metal wall having pores extending therethrough. The wall has a first surface covered by a thermal barrier coating. The pores have first ends which are covered by the thermal barrier coating, and the pores are ventilated from an opposite second surface of the wall for cooling the thermal barrier coating.

Abstract: A coated article having a high resistance to wear damage has a substrate, and a layered coating overlying the substrate. The layered coating includes a ductile metallic layer overlying and in facing contact with the substrate, and a protective layer overlying and in facing contact with the ductile metallic layer and including a mixture of a quasicrystalline metallic phase and a non-quasicrystalline ductile phase. The coated article is preferably used in applications where it is subjected to wear conditions.

Abstract: An article for use in a hot gas path of a gas turbine assembly, a metallic skin for such an article, and a method for making such an article are presented with, for example, the article comprising a spar, the spar providing mechanical support for the article and comprising a cooling fluid delivery system, a top end, and a bottom end; a standoff structure attached to the spar, the standoff structure comprising a plurality of spacing elements in a spaced-apart relation to each other, the spacing elements having first ends adjacent to the spar and second ends opposite to the first ends; a skin conformally surrounding the spar and the standoff structure, the skin comprising a top end and a bottom end, wherein the standoff structure separates the spar and the skin, wherein the plurality of spacing elements is disposed with an inner surface of the skin adjacent to the second ends of the spacing elements to form a plurality of plena between the spar and the skin, the plena in fluid communication with the cooling flu

Abstract: A method and system for transmitting data from a computer network security device for monitoring at least one computer network node to an operations center for monitoring at least the computer network security device and to the computer network security device from the operations center in a managed computer network security system including at least the computer network security device and operations center, including establishing security information associated with the at least one computer network security device. The established security information is used to authenticate data transmissions from the computer network security device to the operations center. The established security information is used to authenticate data transmission to the computer network security device from the operations center.

Abstract: An article for use in a hot gas path of a gas turbine assembly, a metallic skin for such an article, and a method for making such an article are presented with, for example, the article comprising a spar, the spar providing mechanical support for the article and comprising a cooling fluid delivery system, a top end, and a bottom end; a standoff structure attached to the spar, the standoff structure comprising a plurality of spacing elements in a spaced-apart relation to each other, the spacing elements having first ends adjacent to the spar and second ends opposite to the first ends; a skin conformally surrounding the spar and the standoff structure, the skin comprising a top end and a bottom end, wherein the standoff structure separates the spar and the skin, wherein the plurality of spacing elements is disposed with an inner surface of the skin adjacent to the second ends of the spacing elements to form a plurality of plena between the spar and the skin, the plena in fluid communication with the cooling flu

Abstract: An actively cooled TBC bond coat wherein active convection cooling is provided through micro channels inside or adjacent to a bond coat layer applied to a substrate. The micro channels communicate directly with at least one cooling fluid supply contained within a turbine engine component, thereby providing direct and efficient cooling for the bond coat layer. Because the substrate is covered with an actively cooled bond coat layer, it will reduce the cooling requirement for the substrate, thus allowing the engine to run at higher operating temperature without the need for additional cooling air, achieving a better engine performance. In one form, the component includes a substrate having at least one substrate channel with a first and second end. At least one micro channel is in fluid communication with a plenum which in turn is in fluid communication with at least one substrate channel through an exit orifice in the substrate channel which is at a first end of the substrate channel.

Abstract: A cooling system for cooling of the flow path surface region of an engine component used in a gas turbine engine and a method for making a system for cooling of the flow path surface region of an engine component used in a gas turbine engine. The method comprises the steps of channeling apertures in a substrate to a diameter of about 0.0005″ to about 0.02″ to allow passage of cooling fluid from a cooling fluid source; applying a bond coat of about 0.0005″ to about 0.005″ in thickness to the substrate such that the bond coat partially fills the channels; applying a porous inner TBC layer of at least about 0.01″ in thickness to the bond coat, such that the TBC fills the channels; applying an intermediate ceramic layer that is more dense than the inner TBC layer on top of the porous TBC; applying an outer TBC layer over the intermediate layer; and, passing cooling fluid from a cooling fluid source through the channel into the porous TBC.

Abstract: A gas turbine engine component includes a perforate metal wall having pores extending therethrough. The wall has a first surface covered by a thermal barrier coating. The pores have first ends which are covered by the thermal barrier coating, and the pores are ventilated from an opposite second surface of the wall for cooling the thermal barrier coating.

Abstract: The present invention provides a process for forming active convection cooling micro channels within or adjacent to a bond coat layer applied to a turbine high pressure turbine airfoil. When placed adjacent or within a porous TBC, the micro channels additionally provide transpiration cooling through the porous TBC. The micro channels communicate directly with at least one cooling circuit contained within the airfoil from which they receive cooling air, thereby providing direct and efficient cooling for the bond coat layer. Because the substrate includes an actively cooled flow path surface region that can reduce the cooling requirement for the substrate, the engine can run at a higher firing temperature without the need for additional cooling air, achieving a better, more efficient engine performance. In one embodiment, a metallic bond coat is applied to an airfoil.