Abstract: An airfoil includes a metal body that has holes, a cover panel carried on the metal body, and push fasteners that extend through the cover panel and into the holes to lock the cover panel on the metal body. Each of the push fasteners includes flexible barbs that engage sides of the holes to resist retraction of the fasteners from the holes. The heads of the push fastener are embedded in recesses in the cover panel.

Abstract: An airfoil a metal body, a cover panel carried on the metal body, and push fasteners extending through the cover panel and locking the cover panel on the metal body.

Abstract: An airfoil for a gas turbine engine according to an example of the present disclosure includes, among other things, an airfoil section extending between a leading edge and a trailing edge in a chordwise direction and extending between a tip and a root section in a spanwise direction. A composite core defines the root section and a portion of the airfoil section. First and second skins extend along opposed sides of the composite core. 12. A method of forming a composite airfoil is also disclosed.

Abstract: An airfoil a metal body, a cover panel carried on the metal body, and push fasteners extending through the cover panel and locking the cover panel on the metal body.

Abstract: A vane includes an airfoil that defines a leading edge, a trailing edge, a pressure side, and a suction side. The airfoil includes a truss structure that has ribs that define there between a plurality of through-cavities from the pressure side to the suction side. Honeycomb cells are disposed in the cavities. A face sheet defines at least one of the pressure side or the suction side. The face sheet has perforations that correspond in location to the honeycomb cells.

Abstract: A vane includes an airfoil that defines a leading edge, a trailing edge, a pressure side, and a suction side. The airfoil includes a truss structure that has ribs that define there between a plurality of through-cavities from the pressure side to the suction side. Honeycomb cells are disposed in the cavities. A face sheet defines at least one of the pressure side or the suction side. The face sheet has perforations that correspond in location to the honeycomb cells.

Abstract: An airfoil includes a body that has rib nodes that each define a node cavity therein. A cover panel is carried on the body over the rib nodes. The cover panel includes tabs that project into the node cavities. Plugs are disposed in the node cavities and pinch the tabs against the node cavities to lock the cover panel on the body.

Abstract: A gas turbine engine and a composite apparatus is disclosed. The gas turbine engine includes a composite apparatus body formed from a composite material, the composite material including a three dimensional preform, the three dimensional preform including a plurality of warp fibers disposed in a warp direction in a first plane, a plurality of fill fibers disposed in a fill direction, wherein the fill direction is perpendicular to the warp direction in the first plane, a plurality of z-yarn fibers disposed in a z-yarn direction, wherein the z-yarn direction intersects the warp direction through the first plane, and a plurality of bias fibers disposed in a bias direction, wherein the bias direction is not aligned with the warp direction and the fill direction.

Abstract: A fan blade having an opening on one side exposing one or more cavities, and a composite cover that fits over the opening, is provided. The composite cover has a variable thickness resulting from the layering of cover plies having different shapes, and is designed to achieve a lightweight fan blade having an optimal level of stiffness.

Abstract: A surgical implement training process that includes teaching an identity of a plurality of first surgical implements in a first surgical implement tray, a location of the plurality of first surgical implements in the first surgical implement tray and an actual order in which each of the first surgical implements are used when performing a surgical procedure. A surgical implement selection system includes a display portion and an input portion. The first surgical implement tray is played on a first display region of the display portion. First images of the first surgical implements in the first display region are selected which causes the first images of the selected first surgical implements to appear in a second display region of the display portion. Each of the first images includes one of the first surgical implements. The first images are organized in the second display region in a testing order based upon when the first surgical implements are used when performing the surgical procedure.

Abstract: An airfoil includes a body that has rib nodes that each define a node cavity therein. A cover panel is carried on the body over the rib nodes. The cover panel includes tabs that project into the node cavities. Plugs are disposed in the node cavities and pinch the tabs against the node cavities to lock the cover panel on the body.

Abstract: A composite article including a multiple of composite layers impregnated with a polymer matrix; and a nanotube material that facilitates a mechanical interlock between at least two of the multiple of composite layers. A method of manufacturing a composite article including a multiple of composite layers within a polymer matrix; and distributing a nanotube material between at least two of the multiple of composite layers to facilitate a mechanical interlock between the at least two of the multiple of composite layers adjacent an otherwise relatively low strength interlaminar interface region of the composite article.

Abstract: A gas turbine engine includes a fan mounting a first group of blades and a second group of blades. The first group of blades and the second group of blades share a profile shape. The first group of blades have a first laminate composition, and the second group of blades have a second laminate composition, distinct from the first laminate composition. A frequency of a vibratory mode of the first group of blades is offset from a frequency of a vibratory mode of the second group of blades.

Abstract: A surgical implement selection process that is used in conjunction with a first surgical implement tray having a plurality of first surgical implements therein. A surgical implement selection system is provided that includes a display portion and an input portion. An image of the first surgical implement tray is displayed in a first display region of the display portion. The first surgical implements are displayed in a second display region of the display portion in an order that corresponds to the order in which the first surgical implements are used in a surgical procedure to define a surgical implement selection template. The surgical implements are provided to a person performing the surgical procedure in the order in which the first surgical implements are displayed in the surgical implement selection template.

Abstract: An airfoil for a gas turbine engine according to an example of the present disclosure includes, among other things, an airfoil section extending between a leading edge and a trailing edge in a chordwise direction and extending between a tip and a root section in a spanwise direction. A composite core defines the root section and a portion of the airfoil section. First and second skins extend along opposed sides of the composite core. 12. A method of forming a composite airfoil is also disclosed.

Abstract: A fan containment case for a gas turbine engine includes a first inner layer and a second layer outside the first inner layer, where the second layer is made of a first material having a first fabric architecture. The fan containment case also includes a third layer outside of the second layer, where the third layer is made of a second material having a second fabric architecture, and at least one of the first material and the first fabric architecture of the second layer is different from the second material and the second architecture, respectively, of the third layer. A fourth outer layer is located outside of the third layer.

Abstract: An airfoil for a gas turbine engine includes a blade body, a leading edge sheath, and an energy absorbing insert. The blade body has a pressure side and a suction side that each between a forward portion and a trailing edge. The leading edge sheath has a leading edge portion that is spaced apart from the forward portion, a first arm that engages the pressure side, and a second arm that engages the suction side. A cavity is defined between the leading edge portion, the first arm, the second arm, and the forward portion. The energy absorbing insert is disposed within the cavity and improves the impact resistance of the airfoil.

Abstract: A preform sheet for a composite component comprises a body section and a flange section. The preform body section includes a plurality of axial tows braided with at least a plurality of first bias tows and a plurality of second bias tows. The preform flange section includes a first braided flange layer and a second braided flange layer. The first braided flange layer is defined by the first and second braided bias tows of the preform body section extending into the flange section. Neither the first nor second braided flange layers have axial tows.

Abstract: A composite article including a multiple of composite layers impregnated with a polymer matrix; and a nanotube material that facilitates a mechanical interlock between at least two of the multiple of composite layers. A method of manufacturing a composite article including a multiple of composite layers within a polymer matrix; and distributing a nanotube material between at least two of the multiple of composite layers to facilitate a mechanical interlock between the at least two of the multiple of composite layers adjacent an otherwise relatively low strength interlaminar interface region of the composite article.

Abstract: A composite article including a multiple of composite layers impregnated with a polymer matrix; and a nanotube material that facilitates a mechanical interlock between at least two of the multiple of composite layers. A method of manufacturing a composite article including a multiple of composite layers within a polymer matrix; and distributing a nanotube material between at least two of the multiple of composite layers to facilitate a mechanical interlock between the at least two of the multiple of composite layers adjacent an otherwise relatively low strength interlaminar interface region of the composite article.