Abstract: A coaxial cable connector including a body circuit borne by a non-conducting body substrate.

Abstract: Embodiments of a method for forming an MCrAlY coating on a gas turbine engine component are provided, as are embodiments of a method for repairing a structurally-damaged region of a gas turbine engine component utilizing an MCrAlY material. In one embodiment, the method includes the step of preparing an MCrAlY slurry containing an MCrAlY powder, a low melting point powder, a binder, and a dilutant. After application over the gas turbine engine component, the MCrAlY slurry is heated to a predetermined temperature that exceeds the melting point of the low melting point powder to form an MCrAlY coating on the gas turbine engine component. The MCrAlY powder may have any one of a number of different compositions.

Abstract: A coating is disclosed that consists essentially of, by weight, about 27.5% to about 31.5% aluminum, about 0.20% to about 0.60% hafnium, about 0.08% to about 0.30% zirconium, about 0.005% to about 0.100% of two or more reactive elements selected from a group consisting of yttrium, lanthanum, and cerium, and a balance of nickel. Turbine engine components including the coating and methods of applying the coating on such components are also disclosed.

Abstract: A ground loop isolator for a coaxial cable, for example that blocks DC current but which allows a desired band of RF through the ground loop isolator, and which is small enough to fit in the areas where coupling of the desired electronic equipment is to occur. Embodiments may include an outer area allowing for easier manual coupling of the coaxial cable connector nut to electronic devices.

Abstract: A method is provided that includes depositing metal powder over a seed crystal having a predetermined primary orientation, scanning an initial pattern into the metal powder to melt or sinter the deposited metal powder, and re-scanning the initial pattern to re-melt the scanned metal powder and form an initial layer having the predetermined primary orientation. The method further includes depositing additional metal powder over the initial layer, scanning an additional pattern into the additional metal powder to melt or sinter at least a portion of the additional metal powder, re-scanning the additional pattern to re-melt a portion of the initial layer and the scanned deposited additional metal powder to form a successive layer having the predetermined primary orientation, and repeating the steps of depositing additional metal powder, scanning the additional pattern, and re-scanning the additional pattern, until a final shape of the component is achieved.

Abstract: Platinum-modified nickel-based superalloys and turbine engine components are provided. The platinum-modified nickel-based superalloy includes, by weight, aluminum, in a range of about 7.8 percent to about 8.2 percent, tantalum, in a range of about 5.0 percent to about 6.0 percent, rhenium, in a range of about 1.6 percent to about 2.0 percent, platinum, in a range of about 0.8 percent to about 1.4 percent, hafnium, in a range of about 0.20 percent to about 0.40 percent, silicon, in a range of about 0.30 percent to about 0.60 percent, about 0.02 percent carbon, about 0.01 percent boron, and a balance of nickel. The platinum-modified a nickel-based superalloy may also include, by weight, chromium in a range of about 4.0 percent to about 5.0 percent.

Abstract: A thin format crush resistant electrical cable that includes at least one bundle, having each bundle comprising a central conductor, an insulator that encapsulates the central conductor, a shielding that encapsulates the insulator, and a jacket that encapsulates the shielding wherein the jacket is crush resistant and thin format in cross section wherein a height of the jacket is smaller than a width of the jacket in cross-section and which enables a small bending radius. One or more embodiments include a small coaxial cable with width less than the jacket height in which the coaxial cable resides. Additional form fitting elements may be utilized as one or more additional bundles to provide for direction changes of the cable that may be implemented by bending the cable wherein the form fitting elements or wires maintain the form desired. The additional bundles may be conductive wire in any geometry.

Abstract: Nickel-based alloys and turbine components are provided. In an embodiment, by way of example only, a nickel-based alloy includes, by weight, about 29.5 percent to about 31.5 percent aluminum, about 0.20 percent to about 0.60 percent hafnium, about 0.08 percent to about 0.015 percent yttrium, and a balance of nickel. In another embodiment, by way of example only, a nickel-based alloy includes, by weight, about 9.7 percent to about 10.3 percent of cobalt, about 15.5 percent to about 16.5 percent of chromium, about 6.6 percent to about 7.2 percent of aluminum, about 5.7 percent to about 6.3 percent of tantalum, about 2.7 percent to about 3.3 percent of tungsten, about 1.8 percent to about 2.3 percent of rhenium, about 0.20 percent to about 1.2 percent of hafnium, about 0.20 percent to about 0.60 percent of silicon, and a balance of nickel.

Abstract: Methods are provided for repairing an engine component. In an embodiment, a method includes forming at least one layer of a first braze alloy mixture including about 40% by weight of a first base alloy material and about 60% by weight of a first braze alloy material, over a structural feature of the component. The first braze alloy material includes chromium, cobalt, tungsten, tantalum, aluminum, hafnium, carbon, boron, and a balance of nickel. A second braze alloy mixture is disposed over the at least one layer of the first braze alloy mixture, the second braze alloy mixture including between about 50% and about 60% by weight of a second base alloy material, and between about 40% and about 50% by weight of a second braze alloy material. The component is then subjected to heat treatment, and may be further subjected to machining, coating and final inspection.

Abstract: Methods are provided for forming coating systems on advanced single crystal superalloy turbine airfoils. A method includes applying a layer of an additive material onto a substrate, the additive material comprising a precious metal and the substrate comprising a nickel-based superalloy, diffusion heat treating the substrate to form an intermetallic coating which comprises ?-Ni and ??-Ni3Al phases alloyed with the additive material and one or more reactive elements from the substrate including hafnium, yttrium, chromium, and silicon, and finally depositing a thermal barrier coating over the intermetallic coating to form the coating system.

Abstract: Methods are provided for repairing a degraded section of a turbine blade, the turbine blade comprising a base material. In one embodiment, and by way of example only, the method includes the step of electro-spark depositing a first material on the turbine blade degraded section to form an intermediate layer thereon, the first material comprising a material that is substantially similar to the base material. Next, a second material is laser welded onto the intermediate layer to form a repaired section. This invention combines the low-heat input of electro-spark deposition with the high welding quality and high deposition rate of laser powder fusion welding.

Abstract: The present invention provides a low-melt nickel-based alloy powder applied in an activated diffusion brazing repair on gas turbine components. In one embodiment, and by way of example only, the low-melt alloy powder comprises between about 6.7% and about 9.2% by weight Cr, between about 9.7% and about 10.3% by weight Co, between about 3.7% and about 4.7% by weight W, between about 3.3% and about 6.3% by weight Ta, between about 3.6% and about 5.2% by weight Al, between about 1.3% and about 4.0% by weight Hf, between about 0.02% and about 0.06% by weight C, between about 1.0% and about 3.2% by weight B, and Ni. Optionally, the low-melt alloy powder may include between about 1.4% and about 3.2% by weight Re.

Abstract: Intermetallic braze alloys and methods of repairing an engine component are provided. In an embodiment, by way of example only, an intermetallic braze material includes between about 10% to about 15% chromium, by weight, between about 1% to about 3% aluminum, by weight, between about 0.1% to about 0.5% zirconium, by weight, between about 18% to about 25% hafnium, by weight, and a balance of nickel. In another embodiment, by way of example only, an intermetallic braze material includes between about 10% to about 15% chromium, by weight, between about 1% to about 3% aluminum, by weight, between about 10% to about 13% zirconium, by weight, between about 0.3% to about 0.7% hafnium, by weight, and a balance of nickel.

Abstract: Nickel-based superalloys, repaired turbine components, and methods repairing turbine components are provided. In an embodiment, by way of example only, a nickel-based superalloy consists essentially of, by weight percent, chromium in a range of from about 7.0 percent to about 8.0 percent, cobalt in a range of from about 5.5 percent to about 6.5 percent, tungsten in a range of from about 3.0 percent to about 4.0 percent, rhenium in a range of from about 2.2 percent to about 2.8 percent, aluminum in a range of from about 7.5 percent to about 8.5 percent, tantalum in a range of from about 5.5 percent to about 6.5 percent, silicon in a range of from about 0.2 percent to about 0.5 percent, hafnium in a range of from about 0.15 percent to about 0.25 percent, and a balance of nickel.

Abstract: Single crystal nickel-based superalloy compositions, single crystal nickel-based superalloy components, and methods of fabricating such components are provided. In an embodiment, by way of example only, a single crystal nickel-based superalloy composition consists essentially of, in weight percent from about 3.8 to about 4.2 percent chromium, from about 10.0 to about 10.5 percent cobalt, from about 1.8 to about 2.2 percent molybdenum, from about 4.8 to about 5.2 percent tungsten, from about 5.8 to about 6.2 percent rhenium, from about 5.5 to about 5.8 percent aluminum, from about 5.8 to about 6.2 percent tantalum, from about 3.8 to about 4.2 percent ruthenium, from about 0.13 to about 0.17 percent hafnium, and a balance of nickel.

Abstract: Intermetallic braze alloys and methods of repairing an engine component are provided. In an embodiment, by way of example only, an intermetallic braze material includes between about 10% to about 15% chromium, by weight, between about 1% to about 3% aluminum, by weight, between about 0.1% to about 0.5% zirconium, by weight, between about 18% to about 25% hafnium, by weight, and a balance of nickel. In another embodiment, by way of example only, an intermetallic braze material includes between about 10% to about 15% chromium, by weight, between about 1% to about 3% aluminum, by weight, between about 10% to about 13% zirconium, by weight, between about 0.3% to about 0.7% hafnium, by weight, and a balance of nickel.

Abstract: Methods are provided for repairing an engine component. In an embodiment, a method includes forming at least one layer of a first braze alloy mixture including about 40% by weight of a first base alloy material and about 60% by weight of a first braze alloy material, over a structural feature of the component. The first braze alloy material includes chromium, cobalt, tungsten, tantalum, aluminum, hafnium, carbon, boron, and a balance of nickel. A second braze alloy mixture is disposed over the at least one layer of the first braze alloy mixture, the second braze alloy mixture including between about 50% and about 60% by weight of a second base alloy material, and between about 40% and about 50% by weight of a second braze alloy material. The component is then subjected to heat treatment, and may be further subjected to machining, coating and final inspection.

Abstract: Single crystal superalloy compositions and components made from such compositions are provided. One composition consists essentially of, in weight percent, from about 4 to about 7 percent chromium; from about 8 to about 12 percent cobalt; from about 1 to about 2.5 percent molybdenum; from about 3 to about 6 percent tungsten; from about 2 to about 4 percent rhenium; from about 5 to about 7 percent aluminum; from about 0 to about 1.5 percent titanium; from about 6 to about 10 percent tantalum; from about 0.08 to about 1.2 percent hafnium; no more than about 0.0002 percent sulfur; no more than about 0.007 percent zirconium; and the balance nickel.

Abstract: Methods are provided for repairing cracks in a damaged section of a gas turbine engine component with an in-situ brazing process. In an embodiment, by way of example only, the method includes applying a braze paste to the damaged section of the component, the braze paste comprising a braze material and an organic binder. The method also includes subjecting the damaged section of the component to a first temperature that is below a brazing temperature of the braze material to thereby substantially decompose and evaporate the organic binder, and heating the braze material using laser energy to a second temperature that is substantially equal to or above the brazing temperature to form the brazed joint on the component.

Abstract: A method for producing environment-protective coatings on a gas turbine engine component includes forming a substrate having an outer surface. The substrate includes a nickel-based superalloy that contains at least one reactive element. A first coating comprising aluminum is then formed on the substrate outer surface. The at least one reactive element is then diffused into the first coating to produce a reactive element-modified aluminide coating.