Abstract: A method for coating a component is provided. The coating method includes providing a component having at least one aperture with an aperture geometry formed in a surface thereof, positioning a filler material within the at least one aperture, the filler material extending away from the surface of the component a distance greater than a reduced coating thickness and less than an applied coating thickness, applying at least one coating over the surface of the component and the filler material to form an applied coating having the applied coating thickness, removing a portion of the applied coating to provide the reduced coating thickness and expose the filler material, and removing the filler material to extend the at least one aperture having the aperture geometry through the applied coating. Another coating method and a template for use with the coating methods are also provided.

Abstract: Beacon devices and associated components, methods, etc., are disclosed. An example beacon device includes a memory, a communication interface, and a processor to execute instructions with respect to configuration information to control the communication interface and operation of the processor based on a mode in which the beacon device is set to operate, the processor to dynamically transition among a plurality of modes based on an operating condition of the beacon device and a communication received from at least one of the receiver or the controller. In certain examples, the plurality of modes includes a configuration mode and a broadcast mode. When in the configuration mode, the operation of the processor is to process the communication received from the controller to adjust the configuration information. When in the broadcast mode, the operation of the processor is to generate a beacon signal to transmit to at least one of the receiver or the controller via the communication interface.

Abstract: A method of monitoring a patient includes recording physiological parameter data from the patient and detecting a first alarm event. A group alarm timer is activated based on an initiation time of the first alarm event, and one or more subsequent alarm events are detected while the group alarm timer is active. For each detected subsequent alarm event, a determination is made whether the respective subsequent alarm event is part of an incident group with the first alarm event. The group alarm timer is stopped at a termination time based on termination of all alarm events in the incident group. An incident group designator is generated identifying the incident group.

Abstract: A shroud segment that includes a body including a leading edge, a trailing edge, a first side edge, a second side, and a pair of opposed lateral sides. A first lateral side is configured to interface with a cavity having a cooling fluid, and a second lateral side is oriented toward a hot gas flow path. The shroud segment includes at least one channel disposed within the body, wherein the at least one channel includes a first portion extending from upstream of the trailing edge towards the trailing edge in a first direction from the leading edge to the trailing edge, a second portion extending from the trailing edge to upstream of the trailing edge in a second direction from the trailing edge to the leading edge, and a third portion extending from upstream of the trailing edge towards the trailing edge in the first direction.

Abstract: An electronics package includes an insulating substrate, a first electrical component coupled to a top surface of the insulating substrate, and a second electrical component coupled to a bottom surface of the insulating substrate. A first conductor layer is formed on the bottom surface of the insulating substrate and extends through a via formed therethrough to contact a contact pad of the first electrical component, with a portion of the first conductor layer positioned between the insulating substrate and the second electrical component. A second conductor layer is formed on the top surface of the insulating substrate and extends through another via formed therethrough to electrically couple with the first conductor layer and to contact a contact pad of the second electrical component.

Abstract: A gas turbine engine includes a compressor section and a turbine section together defining a core air flowpath. Additionally, a rotary component is rotatable with at least a portion of the compressor section and at least a portion of the turbine section. An electric machine is mounted coaxially with the rotary component and positioned at least partially inward of the core air flowpath along a radial direction of the gas turbine engine. A cavity wall defines at least in part a buffer cavity surrounding at least a portion of the electric machine to thermally insulate the electric machine, e.g., from the relatively high temperatures within the core air flowpath.

Abstract: A computer implemented method and system are provided for verifying authenticity of a medical component endpoint. The method is under control of one or more computer systems configured with specific executable instructions. The method receives, at a local medical equipment (LME) node, a cipher message combination that includes a challenge and a corresponding valid response, the LME node is unable to independently calculate the valid response. The method conveys the challenge, from the LME node, to a medical component endpoint that includes an authentication circuit, receives a candidate response from the component endpoint, where the candidate response is generated by the authentication circuit based on the challenge and determines whether the candidate response matches the valid response from the corresponding cipher message combination. The method further authenticates the component endpoint based on whether the candidate and valid responses match.

Abstract: A message is broadcast from an industrial device to a server. The message includes information identifying the type of the industrial device and indicates that the industrial device is to be configured. The message is received at the server, and at the server responsively determines correct configuration information associated with the type of the industrial device. The configuration information is transmitted from the server to the industrial device and a secure link is established between the server and the industrial device. The configuration information is received at the industrial device and the industrial device responsively ceases the broadcasting. Subsequently, the industrial device is configured according to the configuration information. Software from a storage unit is accessed according to the configuration information. Updated configuration information from the server to the industrial device over the secure link.

Abstract: A nozzle segment for a gas turbine engine may generally include an airfoil having an exterior surface defining a pressure side and a suction side extending between leading and trailing edges. The airfoil may define an open internal volume within its interior for receiving a cooling medium. The open internal volume may include a primary internal cavity and a plurality of internal cooling channels in flow communication with the primary internal cavity. The primary internal cavity may extend within the interior of the airfoil from a location adjacent to the leading edge to a forward end of each of the internal cooling channels. The internal cooling channels may extend within the interior of the airfoil from the primary internal cavity towards the trailing edge. In addition, the internal cooling channels may be spaced apart radially by a plurality of ribs extending within the interior of the airfoil.

Abstract: A turbofan engine is provided. The turbofan engine includes a nacelle housing including a radially outer wall and a radially inner wall that defines an interior cavity within the nacelle housing. The turbofan engine also includes a fan assembly positioned at least partially within the interior cavity. A flow passage is defined between the radially outer wall and the radially inner wall for channeling a flow of air therethrough. The flow passage is configured to couple a portion of the interior cavity upstream from the fan assembly in flow communication with an ambient environment exterior from the radially outer wall.

Abstract: A trailing edge cooling system for a turbine blade is disclosed. The system may include a cooling circuit including an outward leg, and a return leg positioned adjacent the outward leg. The outward and return leg each may extend toward and away, respectively, from a trailing edge of the turbine blade. The cooling circuit may also include a plurality of turn legs. The plurality of turn legs may include a turn leg positioned directly adjacent the trailing edge of the turbine blade, and a distinct turn leg positioned axially adjacent the turn leg, and opposite the trailing edge of the turbine blade. The distinct turn leg may be oriented non-parallel to at least one of the outward leg and the return leg.

Abstract: Various embodiments include apparatuses and systems for controlling rotational imbalance of a rotary element. In one embodiment, a rotational imbalance reduction apparatus includes at least one heating element for heating a location on a rotary element, a pulsing element configured to pulse actuate the heating element in synchronization with a multiple, fraction, or mixed fraction of the frequency of rotation of the rotary element, and a control system coupled with the pulsing element and the heating element, the control system actuating the heating element and the pulsing element to apply heat to the location of the rotary element in pulses synchronized with the multiple, fraction, or mixed fraction of the frequency of rotation of the rotary element.

Abstract: An electrical discharge machining (EDM) system, control system and related methods. Various embodiments include a control system for controlling a plurality of electrode devices in an EDM system to form holes in a workpiece. The control system can be configured to perform a process including: initiating a hole formation program for each of the plurality of electrode devices; determining whether at least one electrode has completed formation of a corresponding hole in the workpiece; and separating at least one electrode from the workpiece in response to determining that at least one electrode has completed formation of the corresponding hole.

Abstract: A patient monitoring system includes a capacitive electrode connectable to a patient to detect an output signal and a signal generator unit that transmits a carrier signal to the capacitive electrode, the carrier signal having a carrier frequency and a carrier amplitude. The patient monitoring system further includes an amplifier unit that amplifies the output signal detected by the capacitive electrode to generate an amplified output signal. A gain determination module in the patient monitoring system determines an output amplitude of a carrier frequency portion of the amplified output signal, and determines a system gain based on a comparison between the output amplitude and the carrier amplitude. A voltage determination module in the patient monitoring system filters the output signal to isolate a physiological signal detected from the patient, and determines a voltage of the physiological signal based on the system gain.

Abstract: A cooling system for a grate bar of an incinerator of solid materials is provided includes a feed grate having a plurality of grate bars, at least one of the grate bars including a body having a top surface, a bottom surface, a first end and a second end, a first aperture in the body and a second aperture in the body, and an internal passageway defined within the body and fluidly connecting the first aperture to the second aperture, the first aperture arranged to receive a gas therethrough into the body, and the second aperture arranged to provide an egress for the gas out of the body. The cooling system further includes a manifold duct fluidly coupled to the second aperture for receiving the gas from the second aperture. The gas is independent of the primary combustion air of the incinerator.

Abstract: A turbomachine includes a compressor portion, and a turbine portion operatively connected to the compressor portion. The turbine portion includes a turbine casing. A combustor assembly, including at least one combustor, fluidically connects the compressor portion and the turbine portion. At least one of the compressor portion, turbine portion and combustor assembly includes a sensing cavity. A passive clearance control system is operatively arranged in the turbomachine. The passive clearance control system includes at least one passive flow modulating device mounted in the sensing cavity, and at least one cooling channel extending from the sensing cavity through the casing. The at least one passive flow modulating device selectively passes the fluid from the sensing cavity through the at least one cooling channel to adjust a clearance between stators and rotating airfoils in the turbine portion.

Abstract: A method of determining salinity of multi-phase fluids in a conduit includes exciting a sensing device to cause emission of electromagnetic waves of one or more frequencies into the multi-phase fluid. The method includes receiving transmitted or reflected electromagnetic waves from the multi-phase fluid. Furthermore, the method includes determining an intermediate parameter from the received electromagnetic waves. The method also includes obtaining estimated values of a plurality of parameters from the intermediate parameter. The estimated values comprise at least one of an estimated value of conductance, an estimated value of susceptance, an estimated value of differential conductance, an estimated value of differential susceptance, an estimated value of a real part of complex permittivity, and an estimated value of an imaginary part of complex permittivity. Salinity of the fluid is determined based, at least in part, on the estimated values of the plurality of parameters.

Abstract: An airfoil assembly for a gas turbine engine and a method of transferring load from the ceramic matrix composite (CMC) airfoil assembly to a metallic vane assembly support member are provided. The airfoil assembly includes a forward end and an aft end with respect to an axial direction of the gas turbine engine. The airfoil assembly includes a radially outer end component, a radially inner end component, and a hollow airfoil body extending therebetween. The radially outer end component including a radially outwardly-facing end surface having a non-compression load-bearing feature extending radially outwardly and formed integrally with the outer end component, the load-bearing feature configured to mate with a complementary feature formed in a radially inner surface of a first airfoil assembly support structure and selectively positioned orthogonally to a force imparted into the airfoil assembly.

Abstract: A method for supplying electrical power to a gradient amplifier that drives a gradient coil for a magnetic resonance imaging system is provided. The method includes predicting a gradient voltage required to drive the gradient coil for a scan based at least in part on a gradient coil model. The method further includes calculating a voltage set point for a power supply based at least in part on the predicted gradient voltage. The method further includes providing electrical power to the gradient amplifier via the power supply based at least in part on the calculated voltage set point. The gradient coil model is based at least in part on historical data acquired prior to the scan.

Abstract: Ceramic matrix composite (CMC) airfoils and methods for forming CMC airfoils are provided. In one embodiment, an airfoil is provided that includes opposite pressure and suction sides extending radially along a span and opposite leading and trailing edges extending radially along the span. The leading edge defines a forward end of the airfoil, and the trailing edge defines an aft end of the airfoil. A trailing edge portion is defined adjacent the trailing edge at the aft end, and a pocket is defined in and extends within the trailing edge portion. A heat pipe is received in the pocket. A method for forming an airfoil is provided that includes laying up a CMC material to form an airfoil preform assembly; processing the airfoil preform assembly; defining a pocket in a trailing edge portion of the airfoil; and inserting a heat pipe into the pocket.