Abstract: A method for manufacturing an electrical machine includes printing a stator core; printing a first part of a stator winding; coupling the first part of the stator winding to the stator core; printing a second part of the stator winding onto the first part of the stator winding to form a stator assembly; printing a first part of a rotor shaft; printing a rotor core onto the first part of the rotor shaft; printing a second part of the rotor shaft onto the rotor core; printing a first part of a rotor winding; coupling the first part of the rotor winding to the rotor core; and printing a second part of the rotor winding onto the first part of the rotor winding to form a rotor assembly.

Abstract: A method for manufacturing a rotor assembly for an electrical machine includes printing a first part of a rotor shaft. The method also includes printing a rotor core onto the first part of the rotor shaft. In addition, the method includes printing a second part of the rotor shaft onto the rotor core; printing a first part of the rotor winding. The method also includes coupling the first part of the rotor winding to the rotor core. After coupling the first part of the rotor winding to the rotor core, the method includes printing a second part of the rotor winding onto the first part of the rotor winding to form the rotor assembly.

Abstract: A method for manufacturing a housing for an electrical machine includes printing, by a three-dimensional (3D) printing process, the housing. In addition, the method includes printing, by the 3D printing process, a cooling jacket that is integral with the housing. The method also includes printing, by the 3D printing process, at least one end cap configured to enclose a cavity defined by the housing. In addition, the method includes coupling the at least one end cap to the housing.

Abstract: The present disclosure is directed to a bearing assembly for a gas turbine engine. The bearing assembly includes a bearing housing and a bearing pad for supporting a rotary component of the gas turbine engine. The bearing pad includes at least one gas inlet and a plurality of gas outlets configured on an inner surface thereof. The gas inlet is in fluid communication with the plurality of gas outlets via a gas distribution labyrinth. Further, the gas distribution labyrinth includes a plurality of passageways configured to evenly distribute pressurized gas entering the gas inlet to an interface between the inner surface of the bearing pad and an outer diameter of the rotary component.

Abstract: The present disclosure generally relates to monolithic superstructures for supporting a rotating shaft coupled to a rotor relative to a stator. An integral superstructure supports the rotating component. The superstructure includes a bearing portion that contacts the shaft. A stator portion, is spaced a critical dimension radially outward, from the rotor. A first annular transfer portion extends axially forward from the bearing to the stator portion. A second annular transfer portion extends axially aft from the stator portion to a mounting flange. The mounting flange connects the superstructure to a frame. The superstructure maintains a critical dimension between the rotor and the stator as the temperature of the superstructure increases. The rotor may be a compressor impeller in a gas turbine engine and the stator may be an aero component that transfers air into a combustor.

Abstract: A system for strain gage calibration includes a data acquisition system operable to receive sensor inputs from a force sensor as a force input and a strain gage as a strain output. The strain gage detects a strain measurement of a structure under test in response to an excitation force applied by an excitation device, and the force sensor detects the excitation force. The system also includes a data processing system operable to perform calibration feature extraction of a plurality of calibration features from time and frequency domain responses of the force input and the strain output, and to determine a calibration factor of the strain gage based on a correlation of the calibration features to reference calibration features. The force input and the strain output are preprocessed before the calibration feature extraction to filter noise, remove outlying data, and temporally align the force input and the strain output.

Abstract: A bearing includes a bearing pad for supporting a rotary component and a housing attached to or formed integrally with the bearing pad. The housing includes a flexible column extending towards the bearing pad for providing the bearing pad with an airflow. The column supports the bearing pad from a location inward of an outer periphery of the bearing pad along an axial direction of the bearing. With such a configuration, a resistance of the bearing pad along a radial direction of the bearing is less at the outer periphery than a resistance of the bearing pad along the radial direction proximate the column.

Abstract: A coating is applied in one or more layers on a granular material, such as a granular fertilizer material or the like. The coating may include a diisocyanate in either pure form or partially polymerized form, a polyol or polyol mix, and optionally a wax. The polyol or polyol mix may be, for example, a polyester polyol, a polyether polyol, or combinations thereof. In some examples, the polyol or polyol mix may be an aliphatic glycerine initiated polyether polyol, an aliphatic amine initiated trifunctional polyol, castor oil or castor oil derivative, or ethylene diamine that has been propoxylated or ethoxylated, and combinations thereof. The coating is reacted on the granular material.

Abstract: A system, method and computer product for multiple online exchanges of multiple iterations of all or part of a wager or fantasy sports entry is disclosed. A user accesses a wager exchange website. The user creates a user account and selects a ticket for partial sale. The user indicates a percentage value of the ticket that the user wishes to sell. The ticket is split into two child tickets, a first child ticket corresponding to the percentage value the user wishes to sell and a second child ticket corresponding to a percentage value the user wishes to retain. The ticket is set as inactive, and the first child ticket is set as active. The first child ticket is offered for sale on the exchange website. A second user purchases the first child ticket, and the process repeats with the first child ticket.

Abstract: The present disclosure generally relates to separating entrained solid particles from an input airflow in a gas turbine engine. A cyclonic separator receives the input airflow from a compressor and separates a first portion of the input airflow. The cyclonic separator remove solid particles from the first portion of the input airflow to provide a first cleaned airflow to a first cooling system. A clean air offtake downstream from the cyclonic separator separates a second cleaned airflow from a remaining portion of the input air stream and provides the second cleaned airflow to a second cooling system. The remaining portion of the input airflow is provided to a combustor.

Abstract: The present disclosure generally relates to separating solid particles from an airflow in a gas turbine engine. A separator includes a plurality of vortex chambers arranged about a longitudinal axis of the gas turbine engine, each vortex chamber having a clean air outlet at a first end, a dirty outlet at a second end, and an air inlet transverse to the vortex chamber located at the first end. The separator also includes a sealable collection chamber in fluid communication with the dirty outlet of the each of the plurality of vortex chambers.

Abstract: The present disclosure generally relates to separating solid particles from an airflow in a gas turbine engine. A system for separating debris includes a first separation device in fluid communication with an inlet flow path of a compressor and a second separation device in fluid communication with an outlet flow path of the compressor and an inlet flow path of a combustor. The first separation device is adapted to remove coarse particles from the airflow. The second separation device is adapted to remove fine particles from the airflow. The course particles have a larger mean particle diameter than the fine particles.

Abstract: A connector brick for a cable communication system includes a header frame including end spacers and side spacers defining a header opening. The header frame is configured for mating with a circuit card. A plurality of cable connectors are received in the header opening and connected to the header frame. Each cable connector has cables extending therefrom. Each cable connector has a header holding signal contacts at a mating end of the header and configured for mating with a corresponding card connector of the circuit card. Float mechanisms extend from the header frame. The float mechanisms allow limited movement in at least two directions of the header frame. The float mechanisms allow alignment of the header frame with the circuit card. The cable connectors float with the header frame as a unit for mating with the corresponding card connectors.

Abstract: Embodiments of a stage for a turbomachine have been provided herein. In some embodiments, a stage for a turbomachine may include a bearing having a housing, the bearing defining an interior cavity; an outer ring disposed radially outward from the housing; and a plurality of airfoils disposed between the housing of the bearing and the outer ring.

Abstract: A turbomachine includes a compressor section, a turbine section, and a rotary component. The rotary component is attached to and rotatable with a portion of at least one of the compressor section and the turbine section. The turbomachine additionally includes a seal having a gas bearing. The gas bearing defines an inner surface along a radial direction of the turbomachine, a high pressure end, and a low pressure end. The gas bearing supports the rotary component and also prevents an airflow from the high pressure end to the low pressure end between the rotary component and the inner surface of the gas bearing.

Abstract: The present disclosure is directed to an oil-free gas turbine engine. The gas turbine engine includes a compressor section, a combustion section, a turbine section, and an exhaust nozzle section. Further, the gas turbine engine includes at least one rotary component configured to drivingly connect at least a portion of the turbine section to at least a portion of the compressor section. Moreover, the gas turbine engine includes one or more gas-lubricated bearings configured to support the rotary component. In addition, the gas turbine engine includes a direct-drive starter-generator configured to start the gas turbine engine. Thus, the gas turbine engine of the present disclosure provides an engine that is at least partially oil free.

Abstract: A rotary machine for an aeronautical device includes a thrust generator. The rotary machine additionally includes a rotary component rotatable with the thrust generator. Moreover, the rotary machine of the present disclosure includes a plurality of gas bearings, with the plurality of gas bearings substantially completely supporting the rotary component of the rotary machine.

Abstract: The present disclosure is directed to a gas-lubricated bearing assembly for a gas turbine engine and method of damping same. The bearing assembly includes a bearing pad for supporting a rotary component and a bearing housing attached to or formed integrally with the bearing pad. The bearing housing includes a first fluid damper cavity, a second fluid damper cavity in restrictive flow communication with the first fluid damper cavity via a restrictive channel configured as a clearance gap, and a damper fluid configured within the first and second fluid damper cavities. More specifically, the damper fluid of the present disclosure is configured to withstand the high temperature environment of the engine. Thus, the bearing housing is configured to transfer the damper fluid from the first fluid damper cavity to the second fluid damper cavity via the restrictive channel in response to a force acting on the bearing pad.

Abstract: The present disclosure is directed to a bearing assembly for a gas turbine engine. The bearing assembly includes a bearing housing and a bearing pad for supporting a rotary component of the gas turbine engine. The bearing pad includes at least one gas inlet and a plurality of gas outlets configured on an inner surface thereof. The gas inlet is in fluid communication with the plurality of gas outlets via a gas distribution labyrinth. Further, the gas distribution labyrinth includes a plurality of passageways configured to evenly distribute pressurized gas entering the gas inlet to an interface between the inner surface of the bearing pad and an outer diameter of the rotary component.