Abstract: There is provided a current control circuit (20) for connection between a first electrical network (42) and a converter, the current control circuit (20) comprising: first and second input terminals (24,26) for connection to the first electrical network (42); first and second output terminals (28,30) for respective connection to converter terminals (46,48) of the converter; first and second switching limbs, the first switching limb interconnecting the first input and output terminals (24,28), the second switching limb interconnecting the second input and output terminals (26,30), each switching limb including a respective switching element (32,34,36,38); a director limb (76) extending between the first and second output terminals (28,30), the director limb (76) including at least one current director element (84) and at least one first resistive element (86), the director limb (76) including an intermediate terminal (82); a second resistive element (88), a first end of the second resistive element (88) ope

Abstract: A system and method are provided for damping power system oscillations in a power system network having one or more local inverter-based generators within a plant, the plant connected to a grid at a point of intersection (POI). The system and method include a plant-level controller or local controller that receives one or more grid signals having a characteristic indicative of a power system oscillation. The plant-level controller or local controller generates an auxiliary signal from the grid signals that is used by the local controller of the inverter-based generators. At the local controller, the auxiliary signal is used to modulate reactive power output from the inverter-based generator to change a voltage at the POI, the voltage change damping the power system oscillations.

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: A pump system for pressurizing a fluid within a closed loop thermal transport bus is disclosed herein. The example of the pump system disclosed herein includes an electric motor including a rotor shaft and a stator, wherein the rotor shaft is to generate a first torque; a pump including an impeller coupled to an impeller shaft, wherein the impeller is to increase a kinetic energy of the fluid; a driver wheel attached to the rotor shaft, wherein the driver wheel is radially connected to a follower wheel; and a co-axial magnetic coupling to connect at least one of the follower wheel to the impeller shaft or the driver wheel to the rotor shaft, wherein the co-axial magnetic coupling includes an outer hub, an inner hub, and a barrier can, the barrier can to hermetically seal a portion of the pump system from the fluid.

Abstract: A gas turbine engine includes a fan located at a forward portion of the gas turbine engine. A compressor section and a turbine section are arranged in serial flow order. The compressor section and the turbine section together define a core airflow path. A rotary member is rotatable with at least a portion of the compressor section and with at least a portion of the turbine section. An electrical machine is coupled to the rotary member and is located at least partially inward of the core airflow path in a radial direction. An enclosure at least partially encloses the electrical machine. The enclosure at least partially defines a first cooling airflow path within the enclosure that at least partially defines a first cooling airflow buffer cavity at least partially around the electrical machine.

Abstract: A turbomachine equipped with an embedded electric machine having a segmented and movable stator is provided. In one aspect, a turbomachine defines a radial direction and includes a rotating component, actuators, and an electric machine. The electric machine includes a rotor assembly rotatable with and operatively coupled with the rotating component. The electric machine also includes a stator assembly having a stator split into stator segments. Each one of the stator segments is movable by one of the actuators between a first position and a second position along the radial direction, the stator segments each being closer to the rotor assembly along the radial direction when in the first position than when in the second position.

Abstract: A dispatch advisor to assist in selecting operating conditions of a power plant that maximizes operational revenue is described. The dispatch advisor obtains a base load map for operating the power plant to meet base load power demands. The base load map includes a primary base load operating space for attaining target plant power output and efficiency, and an expanded base load portion for attaining higher plant power output and less than optimal efficiency. Both the primary base load operating space and the expanded base load portion associate power output and efficiency values of the power plant that result from a subset of operational parameter values for operating the power plant during base load. The dispatch advisor can transform the flexible base load map into one or more visualizations describing the revenue possibilities associated with operating the power plant based on operating values and attained power output and efficiency.

Abstract: Ceramic matrix composite articles include, for example a first plurality of plies of ceramic fibers in a ceramic matrix defining a first extent, and a local at least one second ply in said ceramic matrix defining a second extent on and/or in said first plurality of plies with the second extent being less than said first extent. The first plurality of plies has a first property, the at least one second ply has at least one second property, and said first property being different from said at least one second property. The different properties may include one or more different mechanical (stress/strain) properties, one or more different thermal conductivity properties, one or more different electrical conductivity properties, one or more different other properties, and combinations thereof.

Abstract: A heat shield for a fuel nozzle of a gas turbine engine combustor. The heat shield includes a radial flange extending in radial and circumferential directions and has an opening therethrough at a radially inward end of the radial flange, and an annular conical wall extending in longitudinal and circumferential directions, the annular conical wall being connected to the radial flange at the radially inward end of the radial flange. The radial flange includes a flange forward side, and a flange aft side, and has a flange outer end portion. The flange outer end portion includes a flange rounded end portion on one of the flange forward side or the flange aft side, and a flange rounded protruding lip on the other of the flange forward side or the flange aft side, the rounded protruding lip extending in the longitudinal direction.

Abstract: A bearing support assembly to support one or more bearings on a shaft. The bearing support assembly includes a bearing support frame configured to be coupled to a static frame, a plurality of ribs connected to the bearing support frame, and a bearing support connected to the plurality of ribs and configured to support a bearing of the one or more bearings. The bearing support assembly has a non-axisymmetric stiffness around a circumference of the bearing support assembly.

Abstract: A rotary machine includes a stator and a rotor configured to rotate with respect to the stator. The rotor is arranged with the stator at a rotor-stator interface and defines a rotor face. Further, the rotary machine includes a seal assembly at the rotor-stator interface. The seal assembly includes at least one seal and a groove formed into the rotor at the rotor-stator interface. In addition, the seal assembly includes a removable insert positioned within the groove of the seal assembly and defining at least a portion of the rotor face. As such, during operation of the rotary machine, if the rotor and the stator make undesirable contact at the rotor-stator interface, the removable insert becomes damaged to prevent damage from occurring to the rotor and the stator.

Abstract: A control system for active stability management of a compressor element of a turbine engine is provided. In one example aspect, the control system includes one or more computing devices configured to receive data indicative of an operating characteristic associated with the compressor element. For instance, the data can be received from a high frequency sensor operable to sense pressure at the compressor element. The computing devices are also configured to determine, by a machine-learned model, a stall margin remaining of the compressor element based at least in part on the received data. The machine-learned model is trained to recognize certain characteristics of the received data and associate the characteristics with a stall margin remaining of the compressor element. The computing devices are also configured to cause adjustment of one or more engine systems based at least in part on the determined stall margin remaining.

Abstract: A water-based binder solution comprises a thermoplastic binder, greater than or equal to 4 wt % to less than or equal to 20 wt % of a non-aqueous solvent having a boiling point greater than or equal to 100° C. and less than or equal to 175° C., and water. The thermoplastic binder comprises a first polymer strand having a weight average molecular weight (Mw) of from 5,000 g/mol to 15,000 g/mol; and at least one of a second polymer strand having a weight average molecular weight (Mw) of from 10,000 g/mol to 50,000 g/mol and a third polymer strand having a weight average molecular weight (Mw) of from 1,000 g/mol to 5,000 g/mol. A method of monitoring a print head of an additive manufacture process comprises depositing a water-based binder solution on the thermal paper.

Abstract: An epicyclic power gear box for a gas turbine engine delivers torque from a low speed shaft to the primary fan. The gear box includes a planet gear and a bearing pin for the planet gear, sun gear and ring gear. The planet gear and bearing pin are arranged so that a clearance between the two is maintained during a takeoff condition for the gas turbine engine.

Abstract: An airfoil for a turbine engine includes an outer wall bounding an interior and defining a pressure side and a suction side, the outer wall extending axially between a leading edge and a trailing edge to define a chord-wise direction, and also extending radially between a root and a tip to define a span-wise direction. At least one cooling conduit can be formed in the interior of the airfoil, and a tip rail can project from the tip in the span-wise direction.

Abstract: Methods for forming a unitary ceramic component are provided. The method may include: positioning a braze reactant layer in a contact area between a first densified ceramic component and a second densified ceramic component; positioning a pack material around at least a portion of the first densified ceramic component or the second densified ceramic component; positioning at least one infiltrate source in fluid communication with the braze reactant layer; and thereafter, heating the at least one infiltrate source, the pack material, the first densified ceramic component, and the second densified ceramic component to a braze temperature that is at or above a melting point of at least one phase of the infiltrate composition such that at least one phase of infiltrate composition melts and flows into the braze reactant layer and reacts with a ceramic precursor compound therein to form a ceramic material.

Abstract: A combustor for a gas turbine engine, the gas turbine engine defining a longitudinal centerline extending in a longitudinal direction, a radial direction extending orthogonally outward from the longitudinal centerline, and a circumferential direction extending concentrically around the longitudinal centerline, the combustor including: a liner at least partially defining a combustion chamber of the gas turbine engine, wherein the liner comprises a looped feature.

Abstract: An acoustic core has a plurality of cell walls formed of an additive-manufacturing material and a resonant space defined by the plurality of cell walls. At least some of the resonant cells have sound-attenuating protuberances formed of an excess amount of the additive-manufacturing material having been intentionally introduced to the cell walls and protruding into the resonant space with a semi-random orientation and/or size.

Abstract: An apparatus to refuel a vessel with cryo-compressed hydrogen is disclosed herein. The apparatus includes a refueler controller configured to defuel the vessel prior to a refuel process based on a pressure of the vessel; fill a mixing tank with at least the cryo-compressed hydrogen based on the pressure of the vessel and a pressure of the mixing tank, wherein the mixing tank is connected upstream of the vessel and is structured to include the cryo-compressed hydrogen; initiate the refuel process of the vessel; adjust a temperature of the mixing tank in response to a temperature of the vessel not satisfying a target temperature of the vessel during the refuel process, wherein the temperature of the mixing tank is to be adjusted based on an increase or a decrease of flow of supercritical hydrogen; and end the refuel process in response to the pressure of the vessel satisfying a target pressure of the vessel.

Abstract: A method of imaging a turbine engine component with a first surface and a second surface that is spaced from the first surface. The turbine engine component includes a plurality of holes with inlets formed in the second surface or interior that are fluidly coupled to outlets formed in the first surface or exterior. The method includes determining at least one fluid frequency, determining at least one sampling frequency, and pulsing fluid through at least a portion of the interior of turbine engine component while imaging the turbine engine component.