Abstract: A splitter is disclosed that can be coupled with a splitter support and used within a diffuser of a gas turbine engine. The splitter includes apertures for receiving a portion of the splitter support. The splitter support includes support arms that are adapted to be slidingly received within the apertures of the splitter.

Abstract: A tape that can be used to detect cracks in a structure to which it is attached is disclosed herein. The tape includes a plurality of structural fibers. The tape also includes an electrically-insulating binder at least partially encapsulating the plurality of structural fibers. The tape also includes quantities of electrically conductive particles, each quantity of electrically conductive particles connected with one of the plurality of structural fibers.

Abstract: A method for suspending a fan case and a fan case assembly in which a fan case is suspended are disclosed herein. The fan case assembly includes an inner ring encircling an axis. The fan case assembly also includes a first outer ring encircling the axis and having an annular flange. The fan case assembly also includes a plurality of struts each extending radially outward from an inner end engaged with the inner ring to an outer end engaged with the first outer ring. The fan case assembly also includes a second outer ring abutting the first outer ring along the axis. The fan case assembly also includes a plurality of leaves each fixed to the second outer ring and extending along the axis. The leaves are slid over an outer surface of the first outer ring to engage the first and second outer rings together.

Abstract: A system includes a nut plate and a polymer sleeve passing through the nut plate. The polymer sleeve contains adhesive for attachment of the nut plate to a substrate. The interior of the sleeve includes an epoxy and a catalyzing agent initially separated from one another, but mixed by kneading the sleeve. A portion of the sleeve can be used to apply the adhesive to a bottom surface of the nut plate.

Abstract: A system includes a nut plate and a polymer sleeve passing through the nut plate. The polymer sleeve contains adhesive for attachment of the nut plate to a substrate. The interior of the sleeve includes an epoxy and a catalyzing agent initially separated from one another, but mixed by kneading the sleeve. A portion of the sleeve can be used to apply the adhesive to a bottom surface of the nut plate.

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.

Abstract: One embodiment is a gas turbine engine component including a metal foam nanofiber composite. Another embodiment is a gas turbine engine component including a ceramic foam nanofiber composite. Other embodiments include unique gas turbine engine components including foam nanofiber composites.

Abstract: One embodiment is a unique apparatus having a gas turbine engine flange assembly. Another embodiment is a unique system having a gas turbine engine flange assembly. Still other embodiments include apparatuses, systems, devices, hardware, methods, and combinations for gas turbine engine flange assemblies. Further embodiments, forms, objects, features, advantages, aspects, embodiments and benefits shall become apparent from the following descriptions, drawings, and claims.

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 gas turbine engine. Other embodiments include apparatuses, systems, devices, hardware, methods, and combinations for gas turbine engines and components thereof. 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 method for producing a turbomachine airfoil. Other embodiments include unique methods for manufacturing an airfoil for a gas turbine engine. Still other embodiments include apparatuses, systems, devices, hardware, methods, and combinations for airfoils for gas turbine engines and other turbomachinery. 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: A morphable composite structure includes at least first and second layers fixed relative to one another. Each of the first and second layers includes structural fibers oriented substantially parallel to one another and a quantity of binder substantially fixing the structural fibers together. The fibers of the first layer are oriented asymmetrically to the fibers of the second layer. The morphable composite structure also includes at least one pattern of electrically-conductive particles connected with the first layer and spaced from the second layer. A current can be directed through the pattern to heat the fibers of the first layer and change the shape of the morphable composite structure.

Abstract: A method for suspending a fan case and a fan case assembly in which a fan case is suspended are disclosed herein. The fan case assembly includes an inner ring encircling an axis. The fan case assembly also includes a first outer ring encircling the axis and having an annular flange. The fan case assembly also includes a plurality of struts each extending radially outward from an inner end engaged with the inner ring to an outer end engaged with the first outer ring. The fan case assembly also includes a second outer ring abutting the first outer ring along the axis. The fan case assembly also includes a plurality of leaves each fixed to the second outer ring and extending along the axis. The leaves are slid over an outer surface of the first outer ring to engage the first and second outer rings together.

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: A fan is disclosed herein. The fan includes a shaft rotatable about an axis. The fan also includes a blade engaged with the shaft for rotation about the axis. The fan also includes a case encircling the axis. The case is positioned radially outward of the blade and the shaft. The fan also includes a blanket mounted to the case. The case and the blanket are operable to cooperate with one another to prevent the blade from escaping the case upon the blade separating from the shaft. The blanket is at least partially impregnated with shear thickening fluid.

Abstract: A gas turbine engine and method of fabrication includes a gas turbine engine with a structure having movable portions and static portions. At least a portion of the structure includes a composite material having an electrically conductive path formed from carbon nanotubes configured for conducting electrical signals therealong.

Abstract: A composite spacer operable to be mounted on a first component is disclosed herein, wherein compression loads associated with attaching the first component to some other structure are born by the composite spacer to limit compressive deformation of the first component. The composite spacer includes a first body formed of resin and defining an aperture extending along an axis. The composite spacer also includes a plurality of first fibers positioned in the first body about the aperture. Each of the first fibers extends substantially parallel to the axis and increases a compressive strength of the first body relative to the axial direction.

Abstract: One embodiment is an apparatus comprising an aircraft airflow duct, and a rotatable member disposed within the duct. The rotatable member is rotatable to vector airflow and is capable of being spun in different directions at a variety of rotational rates. Some embodiments include stationary rotatable members.

Abstract: A composite spacer operable to be mounted on a first component is disclosed herein, wherein compression loads associated with attaching the first component to some other structure are born by the composite spacer to limit compressive deformation of the first component. The composite spacer includes a first body formed of resin and defining an aperture extending along an axis. The composite spacer also includes a plurality of first fibers positioned in the first body about the aperture. Each of the first fibers extends substantially parallel to the axis and increases a compressive strength of the first body relative to the axial direction.