Abstract: A turbine engine is described that includes an intake, an inlet duct configured to receive fluid from the intake, and an outer bypass duct configured to receive fluid from the intake. The turbine engine further includes a drive shaft, a tower shaft mechanically coupled to the drive shaft, and an electric generator mechanically coupled to the tower shaft. The electric generator is located between the inlet duct and the outer bypass duct.

Abstract: A turbine engine is described that includes an intake, an inlet duct configured to receive fluid from the intake, and an outer bypass duct configured to receive fluid from the intake. The turbine engine further includes a drive shaft, a tower shaft mechanically coupled to the drive shaft, and an electric generator mechanically coupled to the tower shaft. The electric generator is located between the inlet duct and the outer bypass duct.

Abstract: A rotor assembly with a rotor hub, a plurality of permanent magnets positioned circumferentially around at least a portion of the rotor hub, and a coating on at least a portion of the plurality of permanent magnets. The coating forming a retaining band that circumferentially extends around the rotor hub and the plurality of permanent magnets. The coating includes a nano-crystalline layer including a metal or metal alloy and defines an average grain size of less than about 50 nanometers (nm).

Abstract: An article that includes a structured substrate having a macro-porous structure that defines a plurality of pores, and a metallic nano-crystalline coating on at least a portion of the structured substrate, where the metallic nano-crystalline coating defines an average grain size less than about 20 nanometers.

Abstract: A turbine engine is described that includes a drive shaft and an electric generator comprising a first rotating element comprising a magnet array, wherein the first rotating element is configured to rotate in a first direction based on a rotation of the drive shaft. The turbine engine further includes a second rotating element comprising a coil array, wherein the second rotating element is configured to rotate in a second direction based on the rotation of the drive shaft, wherein the second direction is opposite to the first direction.

Abstract: A rotor assembly with a rotor hub, a plurality of permanent magnets positioned circumferentially around at least a portion of the rotor hub, and a coating on at least a portion of the plurality of permanent magnets. The coating forming a retaining band that circumferentially extends around the rotor hub and the plurality of permanent magnets. The coating includes a nano-crystalline layer including a metal or metal alloy and defines an average grain size of less than about 50 nanometers (nm).

Abstract: A turbine engine is described that includes a drive shaft and an electric generator, wherein the electric generator includes a first rotating element comprising a first magnet array and mechanically coupled to the drive shaft. The electric generator further includes a second rotating element comprising a second magnet array and mechanically coupled to the drive shaft and an armature comprising a first coil array and a second coil array, wherein the first rotating element is configured to rotate at a particular velocity relative to the first coil array, and the second rotating element is configured to rotate at the particular velocity relative to the second coil array.

Abstract: A turbine engine is described that includes a drive shaft and an electric generator comprising a first rotating element comprising a magnet array, wherein the first rotating element is configured to rotate in a first direction based on a rotation of the drive shaft. The turbine engine further includes a second rotating element comprising a coil array, wherein the second rotating element is configured to rotate in a second direction based on the rotation of the drive shaft, wherein the second direction is opposite to the first direction.

Abstract: A turbine engine is described that includes a drive shaft and an electric generator, wherein the electric generator includes a first rotating element comprising a first magnet array and mechanically coupled to the drive shaft. The electric generator further includes a second rotating element comprising a second magnet array and mechanically coupled to the drive shaft and an armature comprising a first coil array and a second coil array, wherein the first rotating element is configured to rotate at a particular velocity relative to the first coil array, and the second rotating element is configured to rotate at the particular velocity relative to the second coil array.

Abstract: A turbine engine is described that includes an intake, an inlet duct configured to receive fluid from the intake, and an outer bypass duct configured to receive fluid from the intake. The turbine engine further includes a drive shaft, a tower shaft mechanically coupled to the drive shaft, and an electric generator mechanically coupled to the tower shaft. The electric generator is located between the inlet duct and the outer bypass duct.

Abstract: An article that includes a structured substrate having a macro-porous structure that defines a plurality of pores, and a metallic nano-crystalline coating on at least a portion of the structured substrate, where the metallic nano-crystalline coating defines an average grain size less than about 20 nanometers.

Abstract: An article that includes a polymer-based substrate; and a metallic nano-crystalline coating on at least a portion of the polymer-based substrate, where the metallic nano-crystalline coating defines an average grain size less than about 20 nanometers, where the portion of the polymer-based substrate has a first Young's modulus and the metallic nano-crystalline coating has a second Young's modulus, where the first Young's modulus is at least five times less than the second Young's modulus.

Abstract: A gas turbine engine component is disclosed having a construction that permits a working fluid to flow from one side of the component to the other. In one embodiment the construction includes multiple layers, and in one particular embodiment the construction includes three layers. One or more layers can have different properties. Additionally, one or more layers of the construction can include a cellular structure. In one embodiment the component is a gas turbine engine combustor liner.

Abstract: The present disclosure provides a multiple use threaded fastener having a plurality of redundant locking features. The fastener includes a threaded hollow lock bolt having a tapered internal wall constructed to threadingly engage a threaded aperture in a housing. A threaded lock stud having a tapered external wall is constructed to fit at least partially within the hollow lock bolt and threadingly engage the threaded aperture of the housing and engage the tapered wall of the hollow lock bolt.

Abstract: A seal system having a rotating seal section and a static seal section operable for working together to restrict fluid flow there between. An arm connected to the static seal is tuned to move the static seal asymmetrically to correspond with asymmetric movement of the rotating seal during operation to maintain a desired relative position between the static and rotating seals.

Abstract: A combustor liner assembly support is provided that is used to axially and radially position combustor liners in a gas turbine engine. The combustor liner support includes, in one embodiment, a support bracket that is coupled to a diffuser located upstream in the gas turbine engine; a support spool coupled to the support bracket; and a mount stake coupled to the support spool. The mount stake is connected to the combustor liners and maintains the spaced relation therebetween. An alignment device can be used between the support bracket and the support spool.

Abstract: One embodiment of the present invention is a unique variable geometry vane system. Another embodiment is a unique gas turbine engine. Other embodiments include apparatuses, systems, devices, hardware, methods, and combinations for gas turbine engines and turbomachinery variable geometry vane systems. Further embodiments, forms, features, aspects, benefits, and advantages of the present application will become apparent from the description and figures provided herewith.

Abstract: One embodiment of the present invention is a unique airfoil for a turbomachine. Another embodiment is a unique gas turbine engine. Yet another embodiment is a method for manufacturing an airfoil for a turbomachine. Other embodiments include apparatuses, systems, devices, hardware, methods, and combinations for airfoils and turbomachinery. Further embodiments, forms, features, aspects, benefits, and advantages of the present application will become apparent from the description and figures provided herewith.

Abstract: The disclosure is directed to a unique apparatus having a gas turbine engine flange assembly. Also disclosed is a unique system having a gas turbine engine flange assembly in which a fluid flow circuit is provided. Also disclosed are apparatuses, systems, devices, hardware, methods, and combinations for gas turbine engine flange assemblies, in which a fluid flow circuit extends between flanges or from a cavity within a turbine engine case to an interior portion of a flange assembly.

Abstract: The present invention provides an apparatus including a first metal component and a second metal component. The apparatus includes an interface between the first component and the second component, and a metal mesh interposed in the first interface. The apparatus further includes a composite component including a composite material. The composite component includes two portions, the first portion filling voids in the first interface and the second portion forming a structure that adjoins the first component and the second component. The metal mesh extends into the second portion of the composite component.