Abstract: A system for detecting a fault type and faulted phase in a power grid includes a controller and a relay. The relay is configured to monitor a line of the power grid and generate a monitoring signal. The controller may be configured to determine, in response to the monitoring signal received from the relay, sequence voltages and sequence currents in the line. The controller may further determine, in response to the sequence voltages and sequence currents, an absence or a presence of a weak-infeed condition in the line. The controller may further determine, in response to the monitoring signal and the absence or the presence of the weak-infeed condition, a first plane sequence signature and a second plane sequence signature. The controller may further determine a fault type and faulted phase in the power grid in response to the first plane sequence signature and the second plane sequence signature.

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: 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.

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: 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 electric machine with a low profile retention assembly for retention of a stator core is disclosed. A first housing houses the stator core. The first housing has an axial end face with a circumferentially extending, shaped profile having recessed portions that project axially inward alternating with non-recessed portions. A portion of the stator core extends axially out from the recessed portions. A core retention spring is disposed circumferentially at the axial end face of the first housing. The core retention spring has direct contact with the portion of the stator core that extends axially out from the recessed portions of the first housing and the shaped profile of the housing. The core retention spring pushes against the portion of the stator core that extends that extends axially out from the first housing, imparting one or more of an axial load and radial load into the stator core.

Abstract: A premixer assembly for a combustor includes: at least one ring of premixers, each premixer having a central axis, an annular peripheral wall surrounding a centerbody, and at least one swirler disposed between the centerbody and the peripheral wall, wherein the peripheral wall defines an inlet area of the premixer; and a lip extending forward along the central axis from the peripheral wall, the lip extending at an oblique angle to the axis of symmetry.

Abstract: A control system and methods for controlling the position of one or more engine-mounting links of an engine-mounting linkage system are provided. In one aspect, an engine-mounting linkage system includes one or more engine-mounting links that each have an adjustable inclination angle. An inclination angle of a link may be adjusted by an actuator of the control system. One or more controllers of the control system can control the actuator and thus the inclination angle of the link by determining a control command based at least in part on an output received from one or more sensors of the control system. The controllers can then cause the actuator to change the inclination angle of the link based at least in part on the determined control command.

Abstract: A method for repairing composite components includes positioning repair material within a repair region of a composite component formed of a composite material. Furthermore, the method includes heating the repair region to a first temperature. Additionally, the method includes heating a remaining portion of the composite component to a second temperature. Moreover, the method includes melt infiltrating the repair region with an infiltrant to densify the repair material. The first temperature is at or above a melting point of the infiltrant and the second temperature is less than the melting point.

Abstract: A Brayton cycle engine and method for operation. The engine includes an inner wall assembly and an upstream wall assembly each extended from a longitudinal wall into a gas flowpath. An actuator adjusts a depth of the detonation combustion region into the gas flowpath between the inner wall assembly and the upstream wall assembly. The engine flows an oxidizer through the gas flowpath and the inner wall captures a portion of the oxidizer. The engine further adjusts the captured flow of oxidizer via the upstream wall and flows a first flow of fuel to the captured flow of oxidizer to produce rotating detonation gases. The engine flows the detonation gases downstream and to mix with the flow of oxidizer, and flows and burns a second flow of fuel to the detonation gases/oxidizer mixture to produce thrust.

Abstract: An exhaust device for a compressor bypass bleed system of a ducted fan engine includes a housing having an inlet end and an outlet end and defining a centerline axis from the inlet end to the outlet end, an inlet flow conditioner arranged at the inlet end, the inlet flow conditioner including a plurality of inlet openings for conducting a flow of compressed air therethrough into the housing, and an exit screen arranged at the outlet end of the housing. The exit screen includes a plurality of exit openings therethrough arranged at an acute angle with respect to the centerline axis so as to provide a flow of compressed air therethrough into a bypass flow passage at least partially in a same direction as a bypass airflow through the bypass flow passage.

Abstract: An acoustic core may include an array of resonant cells configured as a plurality of resonant cell groups. The resonant cell groups may include a plurality of resonant cells configured as a partitioned resonant cell that include a converging resonant cell and a diverging resonant cell. The converging resonant cell and the diverging resonant cell may be defined by a plurality of cell walls integrally formed with one another and a partition integrally formed with the plurality of cell walls. The partition may at least partially delimit the converging resonant cell from the diverging resonant cell. The converging resonant cell may define an upper resonant space delimited by the partition and a top face of the array of resonant cells. The diverging resonant cell may define a lower resonant space delimited by the partition and a bottom face of the array of resonant cells.

Abstract: A turbofan engine is provided. The turbofan engine includes a fan; a turbomachine operably coupled to the fan for driving the fan, wherein the turbomachine, the fan, or both include an engine component; a heat source; and a heat transfer system configured to reduce ice buildup or ice formation in the engine component, the heat transfer system in communication with the heat source, the heat transfer system comprising: a first heat transfer component in communication with the heat source; and a second heat transfer component that extends from the first heat transfer component to or through the engine component, wherein the first heat transfer component comprises one of a heat pipe or a graphene rod, and wherein the second heat transfer component comprises the other of the heat pipe or the graphene rod.

Abstract: A turbine engine and method of operating includes an engine core with a compressor, a combustor, and a turbine in axial flow arrangement. A flow path extends through the engine core from the compressor to the turbine to define a flow direction for a working airflow through the engine core.

Abstract: A system and method for controlling rotor dynamics at a rotor assembly. The system includes a magnetic actuator and a controller. The magnetic actuator is positioned in magnetic communication with the rotor assembly and is configured to obtain a measurement vector corresponding to the rotor assembly and a measurement vector indicative of a rotor dynamics parameter. The magnetic actuator is further configured to selectively output an electromagnetic force at the rotor assembly. The controller is configured to store and execute instructions.

Abstract: A Brayton cycle engine including a longitudinal wall extended along a lengthwise direction. The longitudinal wall defines a gas flowpath of the engine. An inner wall assembly is extended from the longitudinal wall into the gas flowpath. The inner wall assembly defines a detonation combustion region in the gas flowpath upstream of the inner wall assembly.

Abstract: A clearance control assembly for a gas turbine engine that defines an axial direction and a radial direction and includes a stage of rotor blades and a shroud hanger. The assembly includes a case configured to be positioned outward along the radial direction from the stage of rotor blades when installed in the gas turbine engine. The case is further configured to be engaged with the shroud hanger at a first location when installed in the gas turbine engine. The assembly also includes a baffle positioned outward along the radial direction from the case to define a chamber therebetween. The baffle has a forward end and an aft end. The forward end of the baffle is engaged with the case to form a first seal and the aft end of the baffle is engaged with the case to form a second seal. The baffle, the case, or both define an inlet to allow a fluid to enter the chamber and the case defines an outlet to allow the fluid to exit the chamber.