Abstract: A method of making a metallic component includes mounting a polymeric scaffold onto a mandrel, wherein the mandrel includes one or more chucks configured to secure the polymeric scaffold onto the mandrel and wherein the mandrel is configured to rotate the polymeric scaffold; depositing, with a second additive manufacturing (AM) technique using a material applicator, a component material onto the polymeric scaffold to form the metallic component on the polymeric scaffold, wherein the component has a shape that is the same as the polymeric scaffold; removing the polymeric scaffold; and the metallic component deposited on the polymeric scaffold from the mandrel; and removing the polymeric scaffold from the metallic component.

Abstract: A component includes a component segment, a foundation built on the component segment, and a plurality of distortion mitigation structures built on the component segment. The component segment, foundation, and the plurality of distortion mitigation structures are built with a first additive manufacturing (AM) technique. The component further includes a boss built on the foundation using a second AM technique. The plurality of distortion mitigation structures are configured to radiate away from the foundation and to dissipate heat generated on the foundation when the boss is built using the second AM technique.

Abstract: A method of making a replacement part includes obtaining a physical example of a target part and imaging the physical example of the target part to produce a 3D image of the target part. The 3D image of the target part is compared to parts in a PLM database to identify a reference part to use as a basis making a replacement part for the target part. The PLM database includes a digital model for a baseline AM technique for making the reference part. The reference part is compared to the target part to identify missing and/or extraneous features on the reference part. A replacement part manufacturing method for modifying the reference part to provide missing features and/or to remove extraneous features to make a replacement part for the target part is determined. The replacement part for the target part is made using the replacement part manufacturing method.

Abstract: A structure includes a first body section that has a wall that spans in a vertical direction. The wall has a relatively thin thickness with respect to a length and a width of the wall. A second body section is arranged next to, but spaced apart from, the first body section. A gusset connects the first body section and the second body section. The gusset extends obliquely from the wall of the first body section with respect to the vertical direction such that the gusset is self-supporting. The first body section has a geometry that corresponds to an end-use component exclusive of the gusset.

Abstract: A method includes building a tubular object by a layer-by-layer additive manufacturing process. A structure integrally connected to the tubular object for supporting a portion of the tubular object is formed during building of the tubular object. The structure provides vibration dampening, heat shielding, heat transfer, stiffening, energy absorption, or mounting after the tubular object is built.

Abstract: An embodiment of an apparatus includes a centrifugal drive unit, an arm assembly, an optional dynamic balancing ring, and a workpiece fixture. The arm assembly is operatively connected to the centrifugal drive unit and configured to revolve about a primary axis perpendicular to the arm. The workpiece fixture is mounted to the arm assembly, and is configured to rotate at least one workpiece about at least one secondary axis outboard of the primary axis.

Abstract: A structure includes a first body section that has a wall that spans in a vertical direction. The wall has a relatively thin thickness with respect to a length and a width of the wall. A second body section is arranged next to, but spaced apart from, the first body section. A gusset connects the first body section and the second body section. The gusset extends obliquely from the wall of the first body section with respect to the vertical direction such that the gusset is self-supporting. The first body section has a geometry that corresponds to an end-use component exclusive of the gusset.

Abstract: An embodiment of an apparatus includes a centrifugal drive unit, an arm assembly, an optional dynamic balancing ring, and a workpiece fixture. The arm assembly is operatively connected to the centrifugal drive unit and configured to revolve about a primary axis perpendicular to the arm. The workpiece fixture is mounted to the arm assembly, and is configured to rotate at least one workpiece about at least one secondary axis outboard of the primary axis.

Abstract: A powder-derived, non-finished work piece includes a first body section that has a wall that spans in a vertical direction. The wall has a relatively thin thickness with respect to a length and a width of the wall. A second body section is arranged next to, but spaced apart from, the first body section. A gusset connects the first body section and the second body section. The gusset extends obliquely from the wall of the first body section with respect to the vertical direction such that the gusset is self-supporting. The first body section has a geometry that corresponds to an end-use component exclusive of the gusset.

Abstract: An electric taxi system (ETS) for an aircraft may include a ground speed sensor, a speed selection unit and a speed computer coupled to the ground speed sensor and to the speed selection unit. The speed computer may produce a speed error signal. A motor controller coupled to a wheel motor may control speed of the wheel motor responsively to the speed error signal.

Abstract: An assembly is provided for a turbine engine. The assembly includes a fuel injector and a fuel vaporizer. A nozzle of the fuel injector is adapted to direct fuel to impinge against the fuel vaporizer. The fuel vaporizer is adapted to substantially vaporize the impinging fuel.

Abstract: A pilot interface panel may comprise at least one input mechanism configured to receive at least one user input, generate at least one input signal corresponding to the at least one user input, and send the at least one input signal to a controller. The controller may be configured to control movement of an electric taxi system of an aircraft in a manner according to the at least one input signal, wherein the electric taxi system may be configured to rotate at least one wheel of the aircraft by force from a purely electromotive source. The pilot interface panel may further comprise at least one safety mechanism, which may be configured to prevent at least one of the at least one input mechanisms from receiving an inadvertent user input resulting from an unintended action by the user.

Abstract: An electric taxi system (ETS) for an aircraft may include a ground speed sensor, a speed selection unit and a speed computer coupled to the ground speed sensor and to the speed selection unit. The speed computer may produce a speed error signal. A motor controller coupled to a wheel motor may control speed of the wheel motor responsively to the speed error signal.

Abstract: A lever control system integrates taxi operation using an electric motor in an aircraft with speed control of a jet engine in the same aircraft. The lever control system provides a smooth transition between the electric motor system used for aircraft taxi operation, and a jet engine system used to fly the aircraft. The lever control system may include a reverse lockout mechanism to prevent unintended reverse taxi movement of the aircraft.

Abstract: A pilot interface panel may comprise at least one input mechanism configured to receive at least one user input, generate at least one input signal corresponding to the at least one user input, and send the at least one input signal to a controller. The controller may be configured to control movement of an electric taxi system of an aircraft in a manner according to the at least one input signal, wherein the electric taxi system may be configured to rotate at least one wheel of the aircraft by force from a purely electromotive source. The pilot interface panel may further comprise at least one safety mechanism, which may be configured to prevent at least one of the at least one input mechanisms from receiving an inadvertent user input resulting from an unintended action by the user.

Abstract: A powder-derived, non-finished work piece includes a first body section that has a wall that spans in a vertical direction. The wall has a relatively thin thickness with respect to a length and a width of the wall. A second body section is arranged next to, but spaced apart from, the first body section. A gusset connects the first body section and the second body section. The gusset extends obliquely from the wall of the first body section with respect to the vertical direction such that the gusset is self-supporting. The first body section has a geometry that corresponds to an end-use component exclusive of the gusset.

Abstract: A hydraulic safety stop-valve fitted with hermetic sealing means.The equalization passage between pressures above and below the stop-valve comprises two means of sealing, one provided by contact between two truncated conical bearing surfaces on the outer casing and inner tube, and the other consisting of valves, held by springs against the equalization passage inlet apertures, bored in the lower tubular element of the outer casing, and the opening of which is controlled by a truncated conical surface on the inner tube.This device ensures a high level of safety in stop-valves used in large production tubings for wells at sea.