Abstract: A fuel system for a hydrogen fueled aircraft propulsion system comprises a tank configured to store hydrogen, a first inductor provided within the tank and configured to heat hydrogen fuel within the tank, and a second inductor provided externally to the tank, and configured to induce a current in the first inductor.

Abstract: A fault detector for a control system that includes a controller, a solenoid driver, a current sensor and a solenoid. The solenoid driver provides a current to the solenoid in response to a control signal provided by the controller to the solenoid driver and the current sensor measures the current provided by the solenoid driver to the solenoid to determine a current measurement. At any moment, the control signal corresponds to one of a demanded zero current, a demanded first current magnitude or a demanded second current magnitude. The fault detector detects a fault based upon a comparison of the current measurement to an expected current range, wherein the expected current range is dependent upon which of the demanded zero current, demanded first current magnitude or the demanded second current magnitude the control system corresponds to at that moment.

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 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: There is provided a casing assembly for a gas turbine engine comprising: a casing and electrically conductive intumescent material extending around the casing. The intumescent material is being activatable in response to electrical current to expand. The casing assembly comprises an electrical activation line extending around the casing to activate the intumescent material. The activation line extends in a pattern such that an activation area which circumscribes the activation line has an axial extent of at least 50% of the casing and a circumferential extent of at least 50%, to thereby activate the intumescent material at multiple locations over a corresponding area of the casing.

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 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: A guide vane assembly includes a guide vane and a sealing assembly slidable along a span of the guide vane relative to the guide vane and extending along a chordal axis and the span of the guide vane. The sealing assembly includes a plate configured to be disposed around at least a portion of an external surface of the guide vane. The sealing assembly further includes a manifold coupled to the plate and configured to receive pressurized fluid therein. The manifold is disposed around the plate. The sealing assembly further includes a plurality of flow tubes extending between the manifold and the plate. Each of the plurality of flow tubes are configured to receive the pressurized fluid from the manifold.

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 method of operating a laser additive manufacturing machine includes manufacturing at least one first fluid-flow coupon, that includes a plate defining a plurality of holes, at a corresponding beam offset value of the laser additive manufacturing machine. The method further includes disposing the at least one first fluid-flow coupon in a testing rig, directing a fluid flow towards the at least one first fluid-flow coupon, measuring a fluid flow rate through the at least one first fluid-flow coupon, determining a calibration curve by correlating a beam offset of the laser additive manufacturing machine with a flow parameter based on the fluid flow rate through the at least one first fluid-flow coupon and the corresponding beam offset value, determining a target beam offset value corresponding to a target flow value of the flow parameter, and calibrating and operating the laser additive manufacturing machine using the target beam offset value.

Abstract: The disclosure relates to a battery pack module, for example for use in an electric or hybrid aircraft. Example embodiments include a battery pack module (600) comprising: a plurality of battery cells (6011-n) arranged in a battery cell array (602); an enclosure (604) comprising a plurality of walls surrounding the battery cell array (602); and a vent (605) connected to the enclosure (604) and arranged to provide a fluid flow path between an interior (607) of the enclosure (604) and an external environment (610) upon a pressure differential between the interior (607) of the enclosure (604) and the external environment (610) exceeding a predetermined threshold, wherein the walls of the enclosure (604) are composed of a fire-resistant laminated material comprising a plurality of fabric layers.

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

Abstract: A rotary assembly of a pressurized air system for an aircraft with a rotor configured to be mechanically coupled to a spool of a gas turbine engine and a flow modifier with a first section and a second section. The first section defining a plurality of first flow channels configured to receive flow from the rotor. The second section defining a plurality of second flow channels configured to direct flow towards the rotor. The rotary assembly is configured to permit relative movement between the rotor and the flow modifier to move between a turbine configuration in which the rotor is configured to receive air from an external air source to drive the spool to rotate and a compressor configuration in which the rotor is configured to be driven to rotate by the spool and to receive and compress air from the gas turbine engine.

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: The disclosure relates to electrical machine condition monitoring by placement of a Fibre Bragg Grating (FBG) in the stator of an electrical machine. Example embodiments include an electrical machine comprising: a stator having a plurality of stator teeth having windings around each tooth; a rotor rotatably mounted within the stator; and an optical fibre mounted to the stator, wherein the optical fibre comprises a Fibre Bragg Grating, FBG, positioned between an adjacent pair of stator teeth and oriented to measure a tangential strain between the pair of stator teeth.

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 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 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.