Abstract: An apparatus comprises a power electronic energy conversion system comprising a first energy storage device configured to store DC energy and a first voltage converter configured to convert a second voltage from a remote power supply into a first charging voltage configured to charge the first energy storage device. The apparatus also includes a first controller configured to control the first voltage converter to convert the second voltage into the first charging voltage and to provide the first charging voltage to the first energy storage device during a charging mode of operation and communicate with a second controller located remotely from the power electronic energy conversion system to cause a second charging voltage to be provided to the first energy storage device during the charging mode of operation to rapidly charge the first energy storage device.

Abstract: Embodiments of the present disclosure are directed to a fluid containment system, comprising a body having a set of panels and seals that define an interior cavity. One or more fluid supply sources are fluidly coupled to the interior cavity; the one or more fluid supply sources provide at least one fluid to the interior cavity. A sensor is positioned within the interior cavity, and the sensor is configured to detect a threshold lower explosive limit (LEL) of a vapor within the interior cavity. The vapor is formed from an evaporated portion of the at least one fluid within the interior cavity. A controller is communicatively coupled to the sensor, and the controller is configured to provide control signals for directing fluid movement of the at least one fluid based on one or more signals received from the sensor.

Abstract: A heat exchanger is provided that can include furcating unit cells coupled with each other. Each of the unit cells can be elongated along an axis and include a sidewall that defines annular ring openings on opposite ends of the unit cell along the axis. The sidewall also can define undulating annular rings between the annular ring openings and axially separated from each other along the axis. The sidewall can further define angled openings into the unit cell both above and below each of the undulating annular rings. At least a first opening of the annular ring openings and the angled openings can be configured to be an inlet to receive a first fluid into the unit cell and at least a second opening of the annular ring openings and the angled openings configured to be an outlet through which the first fluid exits the unit cell.

Abstract: The present disclosure is directed to additive manufacturing systems, components therein, and methods for their use. The additive manufacturing system comprises a powder material handling system comprising a virgin powder inlet. The virgin powder inlet is coupled to a virgin powder drum and configured to receive a virgin powder from the virgin powder drum. The additive manufacturing system further comprises a liquid material handling system comprising a binder inlet. The binder inlet is coupled to a binder drum and configured to receive a binder from the binder drum. The additive manufacturing system also comprises an additive manufacturing machine coupled to the powder material handling system and the liquid material handling system. The additive manufacturing machine receives the virgin powder and the binder from the powder material handling and liquid material handling systems and is configured to manufacture a work product using the virgin powder and the binder.

Abstract: A recoat assembly for an additive manufacturing system includes a base member movable in a first lateral direction and a second lateral direction opposite the first lateral direction, a powder spreading member coupled to the base member, and a containment mechanism. The base member includes a primary containment housing at least partially encapsulating the powder spreading member. The containment mechanism is positionable into a first position when the base member is moving in the first lateral direction, and positionable into a second position different from the first position when the base member is moving in the second lateral direction.

Abstract: A build material escapement assembly for an additive manufacturing system includes a retaining plate for coupling the build material escapement assembly to the additive manufacturing system. A base having a plurality of ports is disposed beneath the retaining plate, and a support frame is disposed within the base. A diaphragm is disposed around the base, and a retractable plate is disposed between the support frame and the diaphragm. A top plate is further coupled to the retractable plate through the diaphragm and a plurality of connectors are coupled to the plurality of ports of the base. The base, support frame, diaphragm, retractable plate, and top plate define a cavity, and the top plate is movable between a retracted position by applying a negative pressure and an extended position by applying positive pressure to the cavity via the plurality of connectors.

Abstract: A system for heat exchange and leak detection is generally provided, the system including a heat exchanger including a first wall defining a first passage containing a first fluid. A leak detection enclosure containing a leak detection medium is defined between the first wall and a second wall surrounding the first wall.

Abstract: A powder removal assembly includes a build module comprising module sidewalls and a moveable build plate slidably coupled to the module sidewalls, and an extraction housing removably engaged with the module sidewalls of the build module and defining a turbulence chamber between the build module and the extraction housing. The extraction housing includes one or more sidewalls comprising one or more sidewall fluid flow channels extending through the one or more sidewalls and a top wall coupled to the one or more sidewalls, wherein the one or more sidewall fluid flow channels extend from a position proximate a base of the one or more sidewalls to the top wall.

Abstract: An airfoil for a turbine engine having a spar assembly. The spar assembly including a composite spar, a metallic hub, and a composite body. The metallic hub can receive a portion of the composite spar at an interior surface to define an overlapping region. The composite body is located at the overlapping region.

Abstract: An additive manufacturing system includes a build platform and at least two laser heads. Each laser head includes at least one laser device, an optical sensor, and a computing device. The build platform includes a plurality of calibration marks. The laser device is configured to generate a laser beam. The laser beam is directed toward the plurality of calibration marks and the build platform. The optical sensor is configured to detect a scattering signal of the laser beam generated by reflecting off of the plurality of calibration marks and the build platform. The computing device is configured to receive the scattering signal from the optical sensor. The computing device is configured to align the laser heads such that the scattering signal aligns with the plurality of calibration marks and such that the laser heads align with each other.

Abstract: The variable pitch propeller assembly includes a hub. The variable pitch propeller assembly also includes a plurality of propeller blade assemblies spaced circumferentially about the hub. Each of the plurality of propeller blade assemblies configured to rotate a respective propeller blade. The variable pitch propeller assembly also includes a hydraulic fluid port assembly integrally formed and including at least three hydraulic fluid ports configured to receive respective flows of hydraulic fluid from a stationary hydraulic fluid transfer sleeve. The variable pitch propeller assembly also includes a pitch actuator assembly coupled in flow communication with at least three hydraulic fluid ports through respective hydraulic fluid transfer tubes. The pitch actuator coupled to the plurality of propeller blade assemblies to selectively control a pitch of the propeller blades. The pitch actuator assembly includes a travel stop configured to limit a rotation of at least one of the pitch actuator assemblies.

Abstract: A titanium-based component having a high heat capacity surface. The high heat capacity surface prevents or inhibits titanium fires. The component is titanium-based, forming the substrate, and includes a high heat capacity surface overlying the titanium substrate. A diffusion barrier is intermediate the titanium-based substrate and the high heat capacity surface. The diffusion barrier is non-reactive with both the titanium-based substrate and the high heat capacity surface. The system eliminates the formation of detrimental phases due to diffusion between the applied high heat capacity surface and the titanium substrate. The high heat capacity material has a coefficient of thermal expansion compatible with the coefficient of thermal expansion of the titanium-based substrate.

Abstract: A system includes a sensor comprising a sensor bonding layer disposed on a surface of the sensor, wherein the sensor bonding layer is a metallic alloy. An inlay includes a planar outer surface, wherein the inlay may be disposed on a curved surface of a structure. A structure bonding layer may be disposed on the planar outer surface of the inlay, wherein the structure bonding layer is a metallic alloy. The sensor bonding layer is coupled to the structure bonding layer via a metallic joint, and the sensor is configured to sense data of the structure through the metallic joint, the structure bonding layer, and the sensor bonding layer. The inlay comprises at least one of a modulus of elasticity, a shape, a thickness, and a size configured to reduce strain transmitted to the sensor.

Abstract: A gas turbine engine comprises a fan, a core turbine engine coupled to the fan, a fan case housing the fan and the core turbine engine, a plurality of outlet guide vanes extending between the core turbine engine and the fan case, and an acoustic spacing. The fan comprises a plurality of fan blades that define a fan diameter and a BEAL. The fan case comprises an inlet and an inlet length between the inlet and the fan. The acoustic spacing comprises a distance between the fan and the plurality of outlet guide vanes, and in combination with the BEAL determines an acoustic spacing ratio of the gas turbine engine.

Abstract: A tool system for inserting into a cavity, the tool system including a first continuum having a flexible body defining a connection interface; and a second continuum having a flexible body defining a connection interface; and an engagement mechanism configured to couple the connection interfaces of the first and second continua together to form the tool.

Abstract: An ice protection system for an external surface for an aircraft. The external surface is configured to have air flow over the external surface and has a plurality of zones. At least one heat source is thermally coupled to the external surface in each zone of the plurality of zones. A controller is configured to selectively control the at least one heat source in each zone of the plurality of zones based on an operating condition related to the air flowing over the external surface.

Abstract: A dual phase magnetic component, along with methods of its formation, is provided. The dual phase magnetic component may include an intermixed first region and second region formed from a single material, with the first region having a magnetic area and a diffused metal therein, and with the second region having a non-magnetic area. The second region generally has greater than 0.1 weight % of nitrogen.

Abstract: An integrated fuel cell and combustor assembly, and a related method. The assembly includes a combustor having a combustor geometry and a combustor exit temperature. The assembly further includes multiple fuel cells fluidly coupled to the combustor, the multiple fuel cells being configured to generate a fuel cell power output using fuel and air directed into the multiple fuel cells and to direct a fuel and air exhaust from the multiple fuel cells into the combustor. The multiple fuel cells include multiple fuel cell control groups arranged in a predetermined electrical configuration about the combustor geometry. Each of the multiple fuel cell control groups has an adjustable electrical current bias.

Abstract: A system for controlling blade clearances within a gas turbine engine includes a rotor disk and a rotor blade coupled to the rotor disk. Additionally, the system includes an outer turbine component positioned outward of the rotor blade such that a clearance is defined between the rotor blade and the outer turbine component. Furthermore, the system includes a heat exchanger configured to receive a flow of cooling air bled from the gas turbine engine and transfer heat from the received flow of the cooling air to a flow of coolant to generate cooled cooling air. Moreover, the system includes a valve configured to control the flow of the coolant to the heat exchanger. In this respect, the cooled cooling air is supplied to at least one of the rotor disk or the rotor blade to adjust the clearance between the rotor blade and the outer turbine component.

Abstract: A gas turbine engine including a rotating shaft and a bearing assembly. The bearing assembly is configured to support the rotating shaft. The bearing assembly has a first bearing and a second bearing. The first bearing is configured to support an axial load of the rotating shaft when a forward thrust of the rotating shaft is greater than ten percent. The second bearing is configured to support the axial load of the rotating shaft when a thrust of the rotating shaft is between ten percent forward thrust and ten percent aft thrust, inclusive of the end points.