Abstract: A rotor blade system. The rotor blade system includes a rotor and a plurality of blades coupled to the rotor. The plurality of blades are arranged in an airfoil distribution pattern. The airfoil distribution pattern includes one or more baseline blades and one or more intentionally mistuned blades including an intentional mistuning feature.

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 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 variable guide vane assembly is provided for a turbine defining a core air flowpath. The variable guide vane assembly includes an airfoil band defining a flowpath surface and a cavity. The variable guide vane assembly further includes an airfoil including a first end extending at least partially into the cavity of the airfoil band and an opposite second end, the airfoil extending generally along an axis between the first end and the second end and being moveable generally about the axis relative to the airfoil band. The variable guide vane assembly further includes a sealing element operable to form a seal between the first end of the airfoil and the airfoil band.

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: A method, medium, and system to obtain an assignment of one of a plurality of different additive manufacturing (AM) print parameter sets to each of a plurality of 3D volume elements forming a representation of the model of the part; define a plurality of groupings based on margin parameter values associated with the model of the part; assign a print parameter set to each grouping; automatically assign each of the plurality of print parameter sets to a laser of a multi-laser AM device; save a record of the determined print parameter sets to laser assignments; and transmit the record of the determined print parameter sets to laser assignments to an AM controller to control the multi-laser AM device to generate the part based on the model of the part and the determined print parameter sets to laser assignments, the generated part to be built in a single build.

Abstract: Systems and methods for forecasting aircraft engine operational data are provided. The forecasted data can be used for use with predictive analytics, for example. In one aspect, a method is provided. The method includes receiving engine data associated with an engine. The engine data includes data points for various operational parameters. The method further includes determining forecasted data points for the operational parameters. The forecasted data points for a given one of the operational parameters are determined by applying one or more regression techniques to the data points associated with the given one of the operational parameters. The forecasted data points can be input into various types of models, such as a cumulative damage model. For instance, using the forecasted data points, a cumulative damage model can generate a plurality of forecasts and can output a cumulative probability distribution.

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 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 process of repairing a component includes identifying a void in a component; determining at least one approximate physical configuration of the void; inserting borescope into the component in order to view the void; providing a repair rod approximately equivalent to at least one of the least one approximate physical configuration of the void; inserting the repair rod into component; confirming insertion of the repair rod in the void; separating the repair rod to leave a repair plug in the void; and depositing braze paste over the repair plug in the void.

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 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: A machine is cleaned by directing a foam detergent into the machine to remove contaminants from inside the machine. An effluent portion of the foam detergent exits from the machine with some of the contaminants. One or more of a turbidity, a salinity, an amount of total dissolved solids, or a concentration the contaminants in the effluent is measured. A cleaning time period during which the foam detergent is to be directed into the machine is determined based on the turbidity, the salinity, the amount of total dissolved solids, and/or the contaminant concentration that is measured from the effluent. The foam detergent continues to be directed into the machine during the cleaning time period, and the flow of the foam detergent into the machine is terminated on expiration of the time period.

Abstract: Jet engine thermal transport bus pumps are disclosed. Disclosed herein is an aircraft comprising a gas turbine engine configured to burn fuel at a fuel flow rate to generate an engine power (Pengine), the fuel characterized by a first specific heat capacity (cp_fuel) and a net heat of combustion (NHCfuel); and a thermal management system configured to transfer heat from a working fluid to the fuel, the working fluid characterized by a second specific heat capacity (cp_pump) and a first density (?pump), the thermal management system including a pump configured to generate a pump power (Ppump) to pressurize the working fluid, and wherein P ? O ? W = P p ? u ? m ? p ( c p_pump c p_water ) ? ( ? w ? a ? t ? e ? r ? p ? u ? m ? p ) 2 , F ? F ? R = ( P e ? n ? g ? i ? n ? e N ? H ? C f ? u ? e ? l ) ? ( c p_fuel c p_pump ) 0.008?POW/FFR5/3?12, FFR is between 0.

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: 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, 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 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.

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.