Abstract: The disclosure relates to thermal management of a battery cell array in a battery module for high power applications. In example embodiments, a battery module comprises: a plurality of battery cells (1011-n) arranged in an array (102); a cooling system (104) comprising a plurality of heat exchanger plates (1051-3) interleaved between rows (1031-6) of the battery cell array (102); and a plurality of thermal barrier walls (1101-3) interleaved between rows (1031-6) of the battery cell array (102).

Abstract: A powder flow monitoring system may include a computing device configured to receive image data representing illuminated powder of a powder stream between a powder delivery device and a build surface of a component, generate a representation of the powder stream based on the image data, and output the representation of the powder stream for display at a display device.

Abstract: A fan assembly for a gas turbine engine includes a fan duct, a fan, and an outlet guide vane assembly located in the fan duct axially downstream of the fan. The outlet guide vane assembly includes a first variable leading edge outlet guide vane that extends radially relative to the central axis and includes a leading edge portion and a fixed aft portion, the leading edge portion including a tip segment configured to rotate about a leading edge pitch axis and a hub segment located radially inward of and separate from the tip segment, the hub segment configured to independently rotate about the leading edge pitch axis relative to the tip segment. The assembly further includes two unique gear assemblies each configured to rotate one of the tip and hub segments.

Abstract: Methods of controlling an in-line heater for an energy storage device are provided. A determination is made that a pump is running. When running, the pump circulates a thermal management fluid through a thermal management conditioning loop, which includes the in-line heater and a heat transfer hardware configured to transfer heat between the thermal management fluid and the energy storage device, wherein the in-line heater is in thermal communication with the thermal management fluid. The in-line heater is turned on in response to the determination that the pump is running and a temperature of the thermal management fluid is below a lower control limit.

Abstract: A fuel spray nozzle includes a fuel circuit having in series a gallery, circumferentially spaced passages arranged in a row around the nozzle, and an annular spin chamber. Each passage has an inlet for receiving a respective portion of the fuel from the gallery and a metering orifice for discharging its portion of the fuel. The passages are configured such that, when the flow of liquid fuel to the inlet port is shut off, a respective differential static pressure develops across stagnant liquid fuel remaining between the inlet and the metering orifice of each passage, and the passages are further configured such that one or more selected passages develop a different differential static pressure to the remaining passages causing a flow of purging air to enter the gallery from the combustor through the selected passages and exit through the remaining passages, thereby purging the gallery and the passages of fuel.

Abstract: Embodiments described herein relate to methods and apparatuses for performing classification of a classification subject.

Abstract: An electrical power system includes: an H-bridge DC:DC power converter including first and second half-bridge circuits having low-side transistors and a high-side transistors, and an inductor connected between AC sides of the first and second half-bridge circuits; a DC power source connected to a first half-bridge circuit DC side; a DC electrical network connected to a second half-bridge circuit DC side; and a control system. The control system: controls the low-side and high-side transistors' switching state of the first and second half-bridge circuits; monitors one or more electrical power system operating parameters and determines whether there is a fault in the DC electrical network; and in response, modifies a switching operation of the low-side and high-side transistors of the first and second half-bridge circuits to supply a controlled amount of current from the DC power source to the DC electrical network.

Abstract: A battery pack module, for example, is used in an electric or hybrid aircraft. A battery pack module includes: a plurality of battery cells arranged in a battery cell array; a battery management system electrically connected to the battery cell array; an enclosure surrounding the battery cell array; a vent connected to the enclosure and arranged to provide a fluid flow path between an interior of the enclosure and an external environment; a disc arranged to provide a fluid seal between the interior of the enclosure and the vent, the disc configured to rupture upon a pressure differential between the interior of the enclosure and the external environment exceeding a predetermined threshold; and a sensing circuit connected between the disc and the battery management system and configured to provide a signal to the battery management system upon rupture of the disc.

Abstract: A turbine assembly includes a turbine case, a vane assembly, and a locating plate. The vane assembly includes a first vane and an outer platform arranged on a radially outer end of the first vane, the outer platform including a first anti-rotation protrusion extending radially outwardly away from a radially outwardly-facing surface of the outer platform. The locating plate is radially outside of the vane assembly and includes a main wall and two anti-rotation extensions extending radially inwardly. The first anti-rotation protrusion of the vane assembly is arranged to engage with one of the anti-rotation extensions so as to block circumferential movement of the vane assembly relative to the locating plate.

Abstract: A gas turbine engine includes a fan and a fan case assembly. The fan includes a fan rotor configured to rotate about an axis of the gas turbine engine and a plurality of fan blades coupled to the fan rotor for rotation therewith. The fan case assembly extends circumferentially around the plurality of fan blades radially outward of the plurality of the fan blades.

Abstract: A turbine assembly adapted for use with a gas turbine engine includes a turbine shroud assembly and a turbine vane. The turbine shroud assembly includes a carrier segment arranged circumferentially at least partway around an axis and a blade track segment supported by the carrier segment to locate the blade track segment radially outward of the axis. The turbine vane is located axially forward of the turbine shroud assembly and cooperates with the turbine shroud assembly to form a tortuous flow path therebetween.

Abstract: A turbine assembly includes a bladed rotor mounted for rotation about an axis of the gas turbine engine, a case assembly, and an actively-cooled tip clearance system. The tip clearance system includes a tip clearance sensor located radially outward of an inner case of the case assembly. The actively-cooled tip clearance system includes a sensor is configured to monitor a tip clearance formed between the bladed rotor and the case assembly during operation of the gas turbine engine.

Abstract: A fan case assembly adapted for use with a gas turbine engine includes a fan casing and a bleed air flow control system. The fan casing includes an annular case and a fan track liner coupled with the annular case. The bleed air flow control system is configured to bleed selectively a portion of air flowing through a gas path of the fan case assembly for use as a cooling source in the fan case assembly.

Abstract: Disclosed is a computer-implemented method for controlling an engine system of a vehicle comprising: determining an operating condition of the vehicle; determining one or more contextual conditions relevant to the vehicle; selecting, based upon both the determined operating condition and the determined one or more contextual conditions, a control profile for the engine system from a directory comprising a plurality of control profiles having different control characteristics; applying the selected control profile to a controller of the engine system; and controlling the engine system with the controller in accordance with the selected control profile. Also disclosed are an engine control system, a gas turbine engine, and an aircraft.

Abstract: A system includes a hydrogen fuel delivery system for an engine. The hydrogen fuel delivery system includes a pump configured to pump hydrogen from a tank storing the hydrogen in a liquid state through the hydrogen fuel delivery system, and an evaporator configured to convert at least some of the hydrogen in the liquid state to a gaseous state. The system also includes a heat source thermally coupled with the hydrogen fuel delivery system and fluidly uncoupled from the hydrogen fuel delivery system. The hydrogen fuel delivery system is configured to supply the hydrogen to the engine for combustion and cool the heat source using the hydrogen.

Abstract: An engine data processor for setting a powershift reserve for an internal combustion engine includes: a control unit to adhere to a torque-limiting operating limit value and including a control target; a powershift reserve module for determining the powershift reserve for the torque-limiting operating limit value, the powershift reserve module to: receive a torque setpoint, a powershift reserve setpoint, the torque-limiting operating limit value, and an operating variable; generate an output signal from the torque setpoint, the powershift reserve setpoint, the torque-limiting operating limit value, and the operating variable which have been received; and issue the output signal to the control unit; wherein the control unit is to: adjust the control target by taking into account the output signal, so that the powershift reserve corresponds with the powershift reserve setpoint; and determine a control variable for the internal combustion engine; issue the control variable for the internal combustion engine.

Abstract: An electrically actuated propeller pitch control system includes a propeller hub assembly, a propeller assembly, and a crosshead drive system. The propeller hub assembly rotates about the central axis during operation of watercraft. The propeller assembly is configured to selectively rotate a propeller blade. The crosshead drive system includes an electric motor, a transmission, and a lead screw that rotates about the central axis.

Abstract: An aircraft propulsion system comprises a propulsor an electric motor coupled to the propulsor. The electric motor comprises a surface mounted permanent magnet electric machine comprising a rotor mounted radially inward of a stator. A Motor Diameter Ratio (MDR) is defined as an inner diameter (Dstator,in) of the motor stator in metres divided by an outer diameter (Dstator,out) of the motor stator in metres. The MDR of the electric motor stator is within 10% of the value given by the equation: MDR = 0.83 × ( Torq ? u ? e L a ? c ? t ? i ? v ? e × 1 U fan , tip ) 0 . 0 ? 8 where: T is the maximum torque rating of the electric motor in kilonewton metres; Lactive is the active length of the motor stator in metres; and Utip is the tip speed of the propulsor at the maximum rated torque of the electric motor in metres per second. In the described embodiments, the MDR is less than 1.

Abstract: A battery charging system including a battery enclosure defining an interior space containing a battery storage medium, the interior space configured to house one or more battery cells; a charging terminal electrically coupled to the one or more battery cells and configured to receive electrical power from a power source to charge one or more battery cells; wherein the interior space is configured to be coupled to a pressurising device for applying pressure to the battery storage medium in the interior space; and wherein during charging of the one or more battery cells, the battery storage medium in the interior space is pressurised to cause an isostatic pressure to be applied to the one or more battery cells. A method of charging of charging one or more battery cells provided.

Abstract: A system includes a hydrogen fuel delivery system for an engine. The hydrogen fuel delivery system includes a pump configured to pump hydrogen from a tank storing the hydrogen in a liquid state through the hydrogen fuel delivery system, and an evaporator configured to convert at least some of the hydrogen in the liquid state to a gaseous state. The system also includes a heat source thermally coupled with the hydrogen fuel delivery system and fluidly uncoupled from the hydrogen fuel delivery system. The hydrogen fuel delivery system is configured to supply the hydrogen to the engine for combustion and cool the heat source using the hydrogen.