Abstract: A fan platform for electrically grounding an airfoil of a gas turbine engine includes a flow path surface extending between a first and second side. An inner surface radially opposing the flow path surface also extends between the first and second side, and includes a body portion extending radially inwardly therefrom. At least a first conductive path for grounding travels from the first side via the body portion.

Abstract: A hybrid rotor may comprise a rotor disk having a peripheral rim, a plurality of solid rotor blades extending outwardly from the rotor disk, and a plurality of hollow rotor blades extending outwardly from the rotor disk in a blade array with the plurality of solid rotor blades. In various embodiments, the plurality of solid rotor blades may be integrally coupled to the rotor disk. In various embodiments, the plurality of hollow rotor blades may be mechanically retained in the rotor disk.

Abstract: A blade according to an exemplary aspect of the present disclosure includes, among other things, a radially inner dovetail supporting a radially outer airfoil; and the dovetail having a radial thickness which is less in a circumferentially center portion of the dovetail than circumferentially opposing outer edges.

Abstract: The present disclosure relates generally to a fan blade assembly. In an embodiment, the fan blade assembly includes an airfoil having a forward edge covered by a sheath. The airfoil and the sheath are made from dissimilar conductive materials. A nonconductive coating is applied the an airfoil contact surface of the sheath before it is bonded to the leading edge of the airfoil.

Abstract: A hybrid rotor may comprise a rotor disk having a peripheral rim, a plurality of solid rotor blades extending outwardly from the rotor disk, and a plurality of hollow rotor blades extending outwardly from the rotor disk in a blade array with the plurality of solid rotor blades. In various embodiments, the plurality of solid rotor blades may be integrally coupled to the rotor disk. In various embodiments, the plurality of hollow rotor blades may be mechanically retained in the rotor disk.

Abstract: A blade has an airfoil extending radially outwardly of a dovetail. The dovetail has edges that will be at circumferential sides of the blade when the blade is mounted within a rotor. A bottom surface of the dovetail will be radially inward when the rotor blade is mounted in a rotor, and is formed such that a circumferentially central portion of the bottom surface is radially thicker than are circumferential edges. A fan and a gas turbine engine are also described.

Abstract: A fan assembly for gas assembly engine is disclosed. The fan assembly includes a rotor that is coupled to at least one fan blade. The fan assembly also includes a spinner that extends towards the rotor and the fan blades so that an edge of the spinner engages the fan blades. The edge of the spinner thereby serves as a grounding element for the fan blade. If the spinner is fabricated from a composite or a plastic material that is not sufficiently conductive for grounding purposes, the edge may be coated with a conductive material. Alternatively, the spinner may be fabricated from a metallic material, which would eliminate the need for a conductive coating on the edge that engages the fan blades.

Abstract: The present disclosure relates generally to a fan blade spacer including a conduit disposed within a fan blade spacer composed of an elastically deformable material.

Abstract: A blade has an airfoil extending radially outwardly of a dovetail. The dovetail has edges that will be at circumferential sides of the blade when the blade is mounted within a rotor. A bottom surface of the dovetail will be radially inward when the rotor blade is mounted in a rotor, and is formed such that a circumferentially central portion of the bottom surface is radially thicker than are circumferential edges. A fan and a gas turbine engine are also described.

Abstract: Rotary machines including a hybrid rotor with an integrally bladed rotor portion are provided. The integrally bladed rotor portion for the hybrid rotor comprises a rotor disk portion and a blade portion. The rotor disk portion has a peripheral rim configured to mechanically retain an individual rotor blade. The blade portion comprises an integral rotor blade extending outwardly and integrally from the rotor disk portion. The individual rotor blade is configured to extend outwardly from the rotor disk portion in a blade array with the integral rotor blade. The hybrid rotor is also provided and comprises the integrally bladed rotor portion and a plurality of individual rotor blades extending outwardly from the rotor disk portion in a blade array with a plurality of integral rotor blades.

Abstract: A gas turbine fan fairing platform includes at least one body defining a surface and having an opening receptive to a blade, a protrusion extending outwardly from the surface in a direction that will position the protrusion along a leading edge near a root of the blade.

Abstract: Rotary machines including a hybrid rotor with an integrally bladed rotor portion are provided. The integrally bladed rotor portion for the hybrid rotor comprises a rotor disk portion and a blade portion. The rotor disk portion has a peripheral rim configured to mechanically retain an individual rotor blade. The blade portion comprises an integral rotor blade extending outwardly and integrally from the rotor disk portion. The individual rotor blade is configured to extend outwardly from the rotor disk portion in a blade array with the integral rotor blade. The hybrid rotor is also provided and comprises the integrally bladed rotor portion and a plurality of individual rotor blades extending outwardly from the rotor disk portion in a blade array with a plurality of integral rotor blades.

Abstract: The present disclosure relates generally to a fan blade assembly. In an embodiment, the fan blade assembly includes an airfoil having a forward edge covered by a sheath. The airfoil and the sheath are made from dissimilar conductive materials. A nonconductive ceramic coating is applied to a sheath receiving surface of the airfoil before it is bonded to the sheath.

Abstract: The present disclosure relates generally to a fan blade assembly. In an embodiment, the fan blade assembly includes an airfoil having a forward edge covered by a sheath. The airfoil and the sheath are made from dissimilar conductive materials. A nonconductive coating is applied the an airfoil contact surface of the sheath before it is bonded to the leading edge of the airfoil.

Abstract: A blade includes a hollow metal airfoil having an opening to an internal cavity in a first major surface. A metal cover is adhesively bonded to the airfoil around the opening. The cover encloses the cavity and provides a continuous first major surface. The cavity is divided into at least first and second subcavities. A different filler material is disposed within the first and second subcavities.

Abstract: A blade according to an exemplary aspect of the present disclosure includes, among other things, a radially inner dovetail supporting a radially outer airfoil; and the dovetail having a radial thickness which is less in a circumferentially center portion of the dovetail than circumferentially opposing outer edges.

Abstract: A fan assembly for gas assembly engine is disclosed. The fan assembly includes a rotor that is coupled to at least one fan blade. The fan assembly also includes a spinner that extends towards the rotor and the fan blades so that an edge of the spinner engages the fan blades. The edge of the spinner thereby serves as a grounding element for the fan blade. If the spinner is fabricated from a composite or a plastic material that is not sufficiently conductive for grounding purposes, the edge may be coated with a conductive material. Alternatively, the spinner may be fabricated from a metallic material, which would eliminate the need for a conductive coating on the edge that engages the fan blades.

Abstract: A fan platform for electrically grounding an airfoil of a gas turbine engine includes a flow path surface extending between a first and second side. An inner surface radially opposing the flow path surface also extends between the first and second side, and includes a body portion extending radially inwardly therefrom. At least a first conductive path for grounding travels from the first side via the body portion.

Abstract: The present disclosure relates generally to a fan blade spacer including a conduit disposed within a fan blade spacer composed of an elastically deformable material.

Abstract: A blade has an airfoil extending radially outwardly of a dovetail. The dovetail has edges that will be at circumferential sides of the blade when the blade is mounted within a rotor. A bottom surface of the dovetail will be radially inward when the rotor blade is mounted in a rotor, and is formed such that a circumferentially central portion of the bottom surface is radially thicker than are circumferential edges. A fan and a gas turbine engine are also described.