Abstract: The present invention relates to an interactive advertising system and method of using the system. A plurality of removable RFID devices are disposed on a panel which is separate from an advertising graphic that is supported in an illuminated frame. Activation of one of the RFID devices illuminates a portion of the advertising graphic.

Abstract: The present invention relates to an advertising system and method of using the same. The advertising system includes a light source which may be activated by near field communication devices in order to extract information from the system.

Abstract: A process for the production of normal-butanol, iso-butanol and 2-alkyl alkanol is disclosed.

Abstract: A fan blade includes a lattice structure, a fill, and a structural wrap. The lattice structure defines an airfoil body that has a cavity. The lattice structure defines at least one spar that extends radially from a root of the airfoil body towards a tip of the airfoil body. The fill is disposed within the cavity. The structural wrap is disposed about the lattice structure. The structural wrap defines a plurality of plies that extend from a leading edge of the airfoil body towards a trailing edge of the airfoil body.

Abstract: A gas turbine engine comprises a fan rotor having fan blades received within an outer nacelle, and the outer nacelle having an inner surface. At least a portion of the nacelle inner surface extends radially inwardly to be radially inward of an outer diameter of the fan blades. The inner surface of the nacelle is formed with a trench, which extends into the inner surface to a radially outer extent that is spaced radially outward of the outer diameter of the fan blades.

Abstract: A blade fabrication method is provided and includes additively manufacturing a core, securing the core to a mandrel, electroforming a leading edge sheath directly onto the core and the mandrel and removing the mandrel from the core and the leading edge sheath.

Abstract: A cartridge for a fan case of a gas turbine engine includes an inlet acoustic liner section integrated with a thermally conforming liner section.

Abstract: An airfoil for a gas turbine engine according to an example of the present disclosure includes, among other things, an airfoil section that extends from a root section. The airfoil section extends between a leading edge and a trailing edge in a chordwise direction and extends between a tip portion and the root section in a radial direction. The airfoil section defines a pressure side and a suction side separated in a thickness direction, and the airfoil section includes a metallic sheath that defines an internal cavity receiving a composite core. The root section defines at least one bore dimensioned to receive a retention pin. At least one damping element is received in the internal cavity and that selectively causes the airfoil section to stiffen.

Abstract: A fan blade includes a lattice structure, a fill, and a structural wrap. The lattice structure defines an airfoil body that has a cavity. The lattice structure defines at least one spar that extends radially from a root of the airfoil body towards a tip of the airfoil body. The fill is disposed within the cavity. The structural wrap is disposed about the lattice structure. The structural wrap defines a plurality of plies that extend from a leading edge of the airfoil body towards a trailing edge of the airfoil body.

Abstract: A nacelle for a gas turbine engine, the nacelle includes an inlet axially forward of a fan section. The inlet includes an interior surface. A leading edge includes an inlet cavity. A first conduit communicates airflow to the inlet cavity for preventing accretion of ice on the leading edge. An inlet duct is open to the interior surface aft of the inlet cavity. A second conduit is in fluid communication with the first conduit and the inlet duct. The second conduit communicates airflow to the inlet duct for generating film heating airflow over the interior surface for preventing ice accretion. A gas turbine engine is also disclosed.

Abstract: A heat exchanger manifold for a gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, a manifold body extending between a first face and a second face, a first seal land defining a first fluid port extending through the manifold body between the first face and the second face, and a first seal received within the first fluid port.

Abstract: A gas turbine engine includes a fan forward of a primary flowpath inlet. The fan includes multiple fan blades distributed radially about, and connected to, a hub. A fan nacelle is positioned radially outward of the fan and includes an inner diameter. The inner diameter is sloped relative to an engine axis such that a forward portion of the fan nacelle has a smaller inner diameter than an aft portion of the fan nacelle. A fan blade spacer is disposed between a radially inward facing surface of at least one fan blade and a radially outward facing surface of the hub. The fan blade spacer has a radial thickness at least equal to a slope drop of the fan nacelle.

Abstract: An airfoil includes a leading edge, a trailing edge, a pressure side extending between the leading and the trailing edge, and a suction side that is disposed opposite the pressure side extending between the leading edge and the trailing edge. The airfoil further includes a spar and a structural member. The spar defines the leading edge. The structural member is bonded to the spar.

Abstract: A fan blade includes a lattice structure, a fill, and a structural wrap. The lattice structure defines an airfoil body that has a cavity. The lattice structure defines at least one spar that extends radially from a root of the airfoil body towards a tip of the airfoil body. The fill is disposed within the cavity. The structural wrap is disposed about the lattice structure. The structural wrap defines a plurality of plies that extend from a leading edge of the airfoil body towards a trailing edge of the airfoil body.

Abstract: The invention relates to a process for the manufacture of polymer film graphics comprising providing a continuous substrate having a release layer thereon; applying an image layer in the shape of a graphic letter or design to the release layer; depositing an adhesive layer to the image layer and which has the same shape as the image layer graphic letter or design; curing the adhesive and image layers; and winding the polymer film graphics onto rolls. The invention further relates to a polymer film graphic comprising a substrate having an upper surface and a lower surface; a release layer overlying the upper surface of the substrate; an image layer in the shape of a graphic letter or design overlying the release layer; an adhesive layer overlying the image layer, the adhesive layer having the same shape as the image layer graphic letter or design.

Abstract: A nacelle for a gas turbine engine, the nacelle includes an inlet axially forward of a fan section. The inlet includes an interior surface. A leading edge includes an inlet cavity. A first conduit communicates airflow to the inlet cavity for preventing accretion of ice on the leading edge. An inlet duct is open to the interior surface aft of the inlet cavity. A second conduit is in fluid communication with the first conduit and the inlet duct. The second conduit communicates airflow to the inlet duct for generating film heating airflow over the interior surface for preventing ice accretion. A gas turbine engine is also disclosed.

Abstract: A gas turbine engine includes a fan forward of a primary flowpath inlet. The fan includes multiple fan blades distributed radially about, and connected to, a hub. A fan nacelle is positioned radially outward of the fan and includes an inner diameter. The inner diameter is sloped relative to an engine axis such that a forward portion of the fan nacelle has a smaller inner diameter than an aft portion of the fan nacelle. A fan blade spacer is disposed between a radially inward facing surface of at least one fan blade and a radially outward facing surface of the hub. The fan blade spacer has a radial thickness at least equal to a slope drop of the fan nacelle.

Abstract: The invention relates to a process for the manufacture of polymer film graphics comprising providing a continuous substrate having a release layer thereon; applying an image layer in the shape of a graphic letter or design to the release layer; depositing an adhesive layer to the image layer and which has the same shape as the image layer graphic letter or design; curing the adhesive and image layers; and winding the polymer film graphics onto rolls. The invention further relates to a polymer film graphic comprising a substrate having an upper surface and a lower surface; a release layer overlying the upper surface of the substrate; an image layer in the shape of a graphic letter or design overlying the release layer; an adhesive layer overlying the image layer, the adhesive layer having the same shape as the image layer graphic letter or design.

Abstract: A gas turbine engine includes a liner disposed around a flowpath. The liner has a forward end, a radially outer surface, and a radially inner surface. A hole extends axially into the forward end of the liner between the radially outer surface and the radially inner surface, and an engagement member is partially disposed in the hole and extends axially forward from the forward end of the liner.

Abstract: A gas turbine engine comprises a fan rotor having fan blades received within an outer nacelle, and the outer nacelle having an inner surface. At least a portion of the nacelle inner surface extends radially inwardly to be radially inward of an outer diameter of the fan blades. The inner surface of the nacelle is formed with a trench, which extends into the inner surface to a radially outer extent that is spaced radially outward of the outer diameter of the fan blades.