Abstract: A receiver unit of a wireless power transfer system is presented. The receiver unit includes a main receiver coil, a plurality of auxiliary receiver coils disposed about a central axis of the main receiver coil, and a receiver drive subunit. The receiver drive subunit includes a main converter operatively coupled to the main receiver coil and having a main output terminal. The receiver drive subunit may include a plurality of auxiliary converters operatively coupled to the plurality of auxiliary receiver coils. The plurality of auxiliary converters may be operatively coupled to each other to form an auxiliary output terminal coupled in series to the main output terminal to form a common output terminal. In some implementations, the receiver drive unit may be formed on a substrate of an integrated electronic component. The integrated electronic component may further include a communication subunit and a controller disposed.

Abstract: An additive manufacturing apparatus can include a stage configured to hold a component formed by one or more layers of resin. A support plate can be positioned above the stage. A radiant energy device can be positioned above the stage. The radiant energy device can be operable to generate and project energy in a predetermined pattern. A feed module can be configured to operably couple with a first end portion of a resin support and can be positioned upstream of the stage. A take-up module can be configured to operably couple with a second end portion of the resin support and can be positioned downstream of the stage.

Abstract: Certain examples disclose and describe apparatus and methods to reprogram all electronic engine control system processors through a single external network interface to an aircraft data loader. In such examples, a main processor that interfaces to an aircraft communication network is to operate as both a data loader and a loadable device. Distributed electronic engine control processors are reprogrammable from a single network interface, rather than requiring separate, direct access to each controller.

Abstract: A turbine engine includes a compressor section, a combustion section, and a turbine section, and an airfoil with an outer wall defining a pressure side and a suction side and extending between a leading edge and a trailing edge to define a mean camber line. A first thickness is defined between the pressure side and the suction side at a first location along the mean camber line.

Abstract: A system for diagnosing an additive manufacturing device is provided. The system includes one or more processors, one or more non-transitory memory modules communicatively coupled to the one or more processors and storing machine-readable instructions. The machine-readable instructions, when executed, cause the one or more processors to: determine parameters associated with at least one subsystem of the additive manufacturing device, the parameters being related to a build generated by the additive manufacturing device; compare the parameters with threshold values; and determine a failure mode, among a plurality of failure modes, associated with a subsystem of the at least one subsystem of the additive manufacturing device based on the comparison of the parameters with the threshold values.

Abstract: A circuit interruption device including first and second terminals for connection, to a respective electrical circuit or network, a current-conductive branch including first, second, and third current-conductive branch portions successively connected in series between the first and second terminals, the first current-conductive branch portion including a first switching element, the second current-conductive branch portion including a second switching element, the third current-conductive branch portion including a third switching element, each switching element configured to be switchable to selectively permit and block a flow of current in the respective current-conductive branch portion, first and second current bypass paths, the first current bypass path connected across the first and second current-conductive branch portions, the second current bypass path connected across the second and third current-conductive branch portions, and a controller configured to selectively control the switching of the swit

Abstract: A wireless power transfer system is disclosed. The wireless power transfer system includes a first converting unit configured to convert a first DC voltage of an input power to a first AC voltage. Further, the wireless power transfer system includes a contactless power transfer unit configured to receive the input power having the first AC voltage from the first converting unit and transmit the input power. Also, the wireless power transfer system includes a second converting unit configured to receive the input power from the contactless power transfer unit and convert the first AC voltage of the input power to a second DC voltage. Furthermore, the wireless power transfer system includes a switching unit configured to decouple the second converting unit from the contactless power transfer unit if the second DC voltage across the electric load is greater than a first threshold value.

Abstract: A powder dispensing assembly for an additive manufacturing machine is provided. The powder dispensing assembly includes a housing that defines a powder reservoir that receives additive powder; a first plate removably connectable to the housing, the first plate defining a first discharge orifice having a first discharge orifice geometry; and a second plate removably connectable to the housing, the second plate defining a second discharge orifice having a second discharge orifice geometry different than the first discharge orifice geometry, wherein with the first plate connected to the housing, the additive powder flows out of the first discharge orifice at a first dosing rate, and wherein with the second plate connected to the housing, the additive powder flows out of the second discharge orifice at a second dosing rate different than the first dosing rate.

Abstract: A distributed control system includes an electronic control unit to establish secure communication with a distributed control module. Upon determination that a previously negotiated session key is stored on the electronic control unit, the electronic control unit transmits encrypted communications with the distributed control module using the previously negotiated session key, negotiates a new session key with the distributed control module, and stores the new session key. Upon determination that the previously negotiated session key is not stored on the electronic control unit, the electronic control unit negotiates the new session key with the distributed control module. After negotiating the new session key with the distributed control module, the electronic control unit ceases transmission of unencrypted communications with the distributed control module, transmits encrypted communications with the distributed control module using the new session key, and stores the new session key.

Abstract: A gas turbine engine includes a fan located at a forward portion of the gas turbine engine, and a compressor section and a turbine section arranged in serial flow order. The compressor section and the turbine section together define a core airflow path. A rotary member is rotatable with the fan and with a low pressure turbine of the turbine section. The low pressure turbine includes a rotating drum to which a first airfoil structure is connected and extends radially inward toward the rotary member. A torque frame connects the rotating drum to the rotary member and transfers torque from the first airfoil structure mounted to the rotating drum to the rotary member. The torque frame includes an inner disk mounted to the rotary member, an outer ring and a second airfoil structure formed separately from the outer ring and connected thereto by a releasable connecting structure. The second airfoil structure extends radially inward from the outer ring toward the inner disk.

Abstract: A method for initializing an engine control system of an aircraft may include authenticating a boot loader, authenticating a manifest in response to authentication of the boot loader wherein the manifest contains hashes of one or more software components, and in response to authentication of the manifest, loading a first set of software components from among the one or more software components onto a non-transitory computer-readable medium, calculating a hash of each software component of the first set of software components, authenticating the first set of software components by comparing the calculated hash of each software component of the first set of software components to the hash of a corresponding software component in the manifest, and executing the first set of software components in response to authentication of the one or more software components. Devices and systems are also provided for initializing an engine control system of an aircraft.

Abstract: The present invention relates to an additive manufacturing system and its methods. The system includes a material conveyor, an energy source, and a micro-forging device. The material conveyor is configured to convey material. The energy source is configured to direct an energy beam toward the material, the energy beam fuses at least a portion of the material to form a solidified portion. The micro-forging device is movable along with the material conveyor for forging the solidified portion, wherein the micro-forging device comprises a first forging hammer and a second forging hammer, the first forging hammer is configured to impact the solidified portion to generate a first deformation, and the second forging hammer is configured to impact the solidified portion to generate a second deformation greater than the first deformation.

Abstract: A method of transient control of a thermal transport bus of a turbomachine includes measuring a measured temperature and a measured pressure of a working fluid; determining a selected run state of a turbomachine, wherein the selected run state is one of a plurality of run states; selecting a desired operating condition comprising a desired temperature range and a desired pressure range as a function of a desired state of the working fluid; comparing the measured temperature with the desired temperature range, and comparing the measured pressure with the desired pressure range; and modulating control of the thermal transport bus as a function of the comparing of the measured temperature with the desired temperature range and the comparing of the measured pressure with the desired pressure range.

Abstract: A method, apparatus, and program for additive manufacturing. In one aspect, the method comprises: forming an at least partially solidified portion within a first scan region (801), wherein the solidified portion within the first scan region (801) is formed by irradiating a build material along a first irradiation path (811). A second portion of a build material may be irradiated along a second irradiation path (813), wherein the second scan region (803) is offset with respect to the first scan region (801) thereby defining an offset region (802). The offset region (802) is at least partially solidified by the first irradiation path (811) and the second irradiation path (813) and a reference line (819) intersects the first irradiation path (811) and the second irradiation path (813) within the offset region (802), wherein the reference line (819) is substantially parallel to a side (810) of the first scan region (801).

Abstract: A system includes one or more debris sensors or particulate sensors are used to sense engine inlet debris or particulate matter which are drawn into the engine during flight, in real-time. The system employs that information, in conjunction with other engine health and module health techniques, to identify which gas-path modules of the aircraft engine may require maintenance or repair. In one embodiment, existing engine health technique may be based on various engine operational parameters for a new engine or an average engine.

Abstract: Methods and apparatus to produce hydrogen gas turbine propulsion are disclosed. An example apparatus to produce propulsion in a gas turbine engine includes a fluid line to transport hydrogen from a hydrogen supply and an inert gas from an inert gas supply to a gas turbine combustor. The apparatus also includes at least one heat exchanger coupled to the fluid line to heat the inert gas and the hydrogen in the fluid line.

Abstract: A composite airfoil having a non-metallic leading edge protective wrap is provided. In one aspect, the airfoil has a composite core having a pressure sidewall and a suction sidewall each extending between a core leading edge and a core trailing edge. A leading edge protective wrap protects the core leading edge and includes a trailing wrap and a leading wrap. The trailing wrap wraps around the core leading edge and is connected to the composite core. The leading wrap wraps around the core leading edge and is connected to the trailing wrap. The trailing and leading wraps both have leading edges that are spaced from one another. A filler is positioned between the leading edges of the trailing and leading wraps. A protective nose is connected to the leading edge of the leading wrap. The components of the leading edge protective wrap are formed of non-metallic materials.

Abstract: The present disclosure relates to wind turbine blades (22) configured to receive a peripheral device (250a, 250b, 250c) at a portion of the outer surface (211) of the blade (22), and wherein the wind turbine blade (22) is configured to magnetically couple to the peripheral device (250a, 250b, 250c). The present disclosure also relates to wind turbine blade assemblies (200) and methods (700) to provide the same.

Abstract: A coating system configured to be applied to a thermal barrier coating of an article includes an infiltration coating configured to be applied to the thermal barrier coating. The infiltration coating infiltrates at least some pores of the thermal barrier coating. The infiltration coating decomposes within the at least some pores of the thermal barrier coating to coat a portion of the at least some pores of the thermal barrier coating. The infiltration coating reduces a porosity of the thermal barrier coating. The coating system also includes a reactive phase spray formulation coat configured to be applied to the thermal barrier coating. The reactive phase spray formulation coating reacts with dust deposits on the thermal barrier coating.

Abstract: A turbomachinery engine can include a fan assembly with a plurality of variable pitch fan blades. The fan blades are configured such that they define a first VPF parameter and a second VPF parameter. The first VPF parameter is within a range of 0.10 to 0.40 and is defined as the hub-to-tip radius ratio divided by the fan pressure ratio. The second VPF parameter is within a range of 1-30 lbf/in2 and is defined as the bearing spanwise force divided by the fan area. In certain examples, the turbomachinery engine further includes a pitch change mechanism, a vane assembly, a core engine, and a gearbox.