Abstract: An emblem integrated trunk switch module, wherein a trunk lock and a trunk switch are integrated with an emblem by mounting a push type push button for switching on and off a tact switch of a trunk switch for opening a trunk on an upper end of the emblem, and a push and rotation type push cover for finishing a front surface of the trunk lock on a lower end of the emblem.

Abstract: A hollow article includes a metallic hollow article formed from a having a first major surface, an internal cavity with an opening in the first major surface, and a socket around the opening; a cover of composite material received in the socket and covering the opening; and a filler material of foam in the internal cavity.

Abstract: A fan blade has a blade body, a composite rib and a cover. The blade body extends from a blade root to an opposed blade tip along a longitudinal axis. The blade body defines a leading edge and a trailing edge. A first airfoil surface extends from the leading edge to the trailing edge A pocket is defined between the leading edge, the trailing edge, the blade root, and the blade tip. The pocket has a bottom surface that opposes the first air-foil surface across the blade body. The composite rib is disposed in the pocket. The cover is mounted to the composite rib and the blade body to form a second airfoil surface opposed to the first airfoil surface.

Abstract: A fan blade includes a blade body, a composite segment and a cover. The blade body extends from a blade root to an opposed blade tip along a longitudinal axis. The blade body defines a leading edge and a trailing edge. A first airfoil surface extends from the leading edge to the trailing edge. A pocket is defined between the leading edge, the trailing edge, the blade root and the blade tip. The pocket has a bottom surface that opposes the first airfoil surface across the blade body. The composite segment is disposed in the pocket. The cover is mounted to the composite segment and to the blade body to form a second airfoil surface opposed to the first airfoil surface.

Abstract: The present disclosure relates generally to a cover for a fan blade. The cover encloses a hollowed portion formed in the fan blade and includes at least one extending portion that wraps around at least one of a trailing edge, a leading edge, and a root of the fan blade.

Abstract: A fan rotor includes a fan blade for use in a gas turbine engine includes a sheath formed of a material that is more conductive than a main fan blade body. A grounding element provides a grounding path from the sheath into a rotor receiving the fan blade. A gas turbine engine incorporating the fan blade is also disclosed.

Abstract: A blade for use in a gas turbine engine has an airfoil and a dovetail. The airfoil extends radially outwardly of the dovetail. An inner surface of the dovetail includes a slot extending along a length of the dovetail between a leading edge and a trailing edge.

Abstract: A blade assembly comprises a blade (120) and one or more wear pads (170, 172). The blade has an airfoil (122) having a leading edge (126), a trailing edge (128), a pressure side (130), a suction side (132), and extending from an inboard end to a tip (125). The blade further includes an attachment root (124). The one or more wear pads are along the attachment root. The one or more wear pads have a plurality of slits (228, 230 242).

Abstract: Hollow fan blades for gas turbine engines are disclosed. The hollow fan blades include a body having a convex side and a concave side wherein the convex side has a cavity formed therein. The cavity is covered by two covers including an inner cover that may be adhered to the body of the fan blade assembly and an outer cover that may be adhered to the inner cover and/or the body of the fan blade assembly. The covers may be made of titanium, more than two covers may be employed and more than one cavity may be employed.

Abstract: A blade of a gas turbine engine includes a blade portion. The blade portion includes a first portion located radially outwardly that is located in a flow path and a second portion located radially inwardly of the first portion that is not located in the flow path. A plurality of external cavities is in the second portion of the blade portion.

Abstract: An example airfoil for a gas turbine engine includes a body having a first surface extending from a first edge to a second edge and a cavity disposed in the body. A first cover is at least partially disposed within the cavity. The first cover includes a first portion cooperates with a corresponding second portion. A second cover covers the first cover and forms at least a portion of the first surface with the body. The first cover is disposed between the body and the second cover. The first cover and the second cover have a different coefficient of thermal expansion than the body.

Abstract: An airfoil includes a dovetail root having a base. A grooved slot is disposed in the base and a plurality of root lightening cavities is disposed in the grooved slot.

Abstract: A fan blade for a turbofan gas turbine engine is disclosed. The fan blade includes a body having a pressure side and a suction side and a cover. The suction side of the body includes an opening exposing at least one cavity to reduce the weight of the fan blade. The cover overlays the opening and includes a leading portion and a trailing portion that are tapered in the direction of the cover leading edge and cover trailing edge.

Abstract: A fan blade has an airfoil main body extending between a leading edge and a trailing edge. The airfoil also has suction and pressure sides. A cavity is formed into said main body, and receives a filler material. A cover closes off the cavity, and is attached to the main body, with the cover having a thickness defined in a direction perpendicular to the suction side. The main body has a spar which extends along the cavity, with a thickness of the spar at a central location between ends of the cavity which has a second thickness. A ratio of the first thickness to the second thickness is between 0.5 and 2. A fan rotor and a gas turbine engine are also disclosed.

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 door holding device for a vehicle, may include a door handle having a first side disposed on a door base turnably and a second side in which a holder extending inwardly of the door base may be formed, a door lever hinged to the door base and having a guide that may be locked to the holder of the door handle so as to turn with the door handle, and a blocking lever disposed on the door base turnably by a hinge shaft and having a stopper formed to correspond to turning tracks of the holder of the door handle and the guide of the door lever.

Abstract: A hollow article includes a metallic hollow article formed from a having a first major surface, an internal cavity with an opening in the first major surface, and a socket around the opening; a cover of composite material received in the socket and covering the opening; and a filler material of foam in the internal cavity.

Abstract: A fan blade has an airfoil main body extending between a leading edge and a trailing edge. The airfoil also has suction and pressure sides. A cavity is formed into said main body, and receives a filler material. A cover closes off the cavity, and is attached to the main body, with the cover having a thickness defined in a direction perpendicular to the suction side. The main body has a spar which extends along the cavity, with a thickness of the spar at a central location between ends of the cavity which has a second thickness. A ratio of the first thickness to the second thickness is between 0.5 and 2. A fan rotor and a gas turbine engine are also disclosed.

Abstract: An example airfoil for a gas turbine engine includes a body having a first surface extending from a first edge to a second edge and a cavity disposed in the body. A first cover is at least partially disposed within the cavity. The first cover includes a first portion cooperates with a corresponding second portion. A second cover covers the first cover and forms at least a portion of the first surface with the body. The first cover is disposed between the body and the second cover. The first cover and the second cover have a different coefficient of thermal expansion than the body.

Abstract: A fan rotor includes a fan blade for use in a gas turbine engine includes a sheath formed of a material that is more conductive than a main fan blade body. A grounding element provides a grounding path from the sheath into a rotor receiving the fan blade. A gas turbine engine incorporating the fan blade is also disclosed.