Abstract: A method and system for managing increases in electrical loads in an aircraft engine has been developed. First, demand for an increased electrical load for an electrical generator of the aircraft engine is detected. Notification of the demand for the increased electrical load is transmitted to the aircraft engine full authority digital engine control system (FADEC). The FADEC calculates the necessary power management adjustments to maintain aircraft engine turbine temperature and adjustments to the compressor variable vane and surge bleed valve schedules. The FADEC then commands the adjustment in the aircraft engine power setting parameter, compressor variable vane position, and surge bleed valve position.

Abstract: A method for controlling a motor assembly. The motor assembly includes a gas turbine engine and at least one electric machine which is mechanically coupled to a rotating shaft of the gas turbine engine so as to be rotated for generating electricity. In this control method, a mechanical power take-off setpoint by the electric machine is changed when an operating parameter of the gas turbine engine reaches a predetermined limit. A control unit adapted to perform this method, a motor assembly incorporating this control unit, the electric machine and the gas turbine engine, and a computer program for performing this method.

Abstract: A hybrid rocket engine system has: an oxidizer tank containing a liquid oxidizer; a rocket engine having a combustion chamber operatively connected to the oxidizer tank; a solid propellant fuel within the combustion chamber; a nozzle fluidly connected to the combustion chamber, the nozzle having a convergent section and a divergent section downstream of the convergent section; and a thrust vector control device operatively connected to the divergent section of the nozzle and operable to inject a fluid through at least one aperture defined through the divergent section for controlling a direction of a thrust generated by the rocket engine.

Abstract: Occlusion detection in a vacuum-based system for ophthalmic surgery includes a handpiece and aspiration and irrigation subsystems. The aspiration subsystem includes an aspiration line coupled to a handpiece, an aspiration pressure transducer, and a vacuum-based aspiration pump. The irrigation subsystem includes an irrigation line coupled to an irrigation source having an irrigation fluid, a handpiece, an irrigation pressure transducer, and a positive displacement pump. The system also includes a processor coupled to the positive displacement pump and a memory coupled to the processor. The memory includes executable instructions that cause the processor to determine a flow rate of irrigation fluid through the irrigation line, based on a rotation rate of the positive displacement pump, and provide an occlusion warning when the flow rate is below a threshold level and a vacuum is being commanded.

Abstract: A fuel system for a hydrogen fuelled gas turbine engine comprises a tank configured to store hydrogen, a pump configured to provide pressurised hydrogen at an outlet thereof, and a pre-heater configured to heat at least a portion of pressurised hydrogen fuel downstream of the pump. A preheater return offtake is configured to return at least a portion of hydrogen fuel heated by the preheater to the tank.

Abstract: A hybrid ignitor including an ignitor body with an ignitor wall defining an ignitor interior and an ignitor exterior, the ignitor body having an electrode end opposite a discharge end; a central electrode disposed within the ignitor interior, the central electrode including a spark end; a ground electrode disposed within the ignitor interior and electrically coupled with the central electrode near the spark end; an air inlet formed in the ignitor wall near the spark end; and a solid fuel disposed within the ignitor interior near the discharge end and near the spark end of the central electrode and downstream of the air inlet.

Abstract: A modulating nozzle assembly for use with an agricultural sprayer includes a nozzle base having a base edge. A spray modulating element, such as a shuttle, is movably coupled with the nozzle base. The shuttle includes a shuttle edge. A spray port is between the nozzle base and the shuttle. The spray port includes a spray port profile, and the spray port profile is formed by the base edge and the shuttle edge. A modulation actuator is coupled with the shuttle, the modulation actuator is configured to move one or more of the shuttle edge or the base edge relative to the other of the base edge or the shuttle edge to control the spray port profile.

Abstract: A spacecraft-borne propulsion device includes a propellant storage mechanism including a propellant storage container that stores a propellant in a vapor-liquid equilibrium state or a liquid phase, the propellant being ethanol or an aqueous ethanol solution; a propellant transport mechanism configured to supply, with an electric pump, the propellant under pressurization to a pressure exceeding 1 atm at room temperature; a gas heating mechanism including a heater including a separate heater for heating up connected via a check valve; a thruster head mechanism having a nozzle that generates a thrust with a heated gas; and a power supply mechanism including a storage battery for driving the electric pump and the heater for heating up. The propellant storage mechanism, the propellant transport mechanism, the gas heating mechanism, and the thruster head mechanism are connected in series.

Abstract: The disclosed methods, systems, and kits provide the ability to deliver entire clean sheet designs from concept to first hot fire in under six weeks with instant specific impulses above 330 seconds in some of our engines. In examples, thrusters can be delivered that are at less than half of the mass budget allowable for them and they can be delivered in weeks.

Abstract: A micropump according to the invention uses axially oriented pistons to define a pump volume. Translating the pistons axially with respect to each other within a pump housing draws a metered amount of fluid into the pump volume from a reservoir port for delivery to a cannula port when the space is collapsed. Radially situated seals on the pistons cooperate with the axial movement to close off and open the cannula port and the reservoir port respectively at different positions of the piston stroke.

Abstract: Method for starting an aeronautical free turbine and single-spool gas generator turbomachine of a twin-engine aircraft including two independent electrical networks each comprising a 28V battery selectively powering a starter-generator, in which, to ensure, under the control of a turbomachine regulation computer, the startup of the turbomachine first at a voltage of 28V by putting the two batteries in parallel and then at a voltage of 56V by putting them in series while avoiding too rapid acceleration of the gas generator, the serialization of the two batteries is ordered only once the combustion chamber of the gas generator is ignited and the speed of the gas generator is greater than a predetermined speed threshold N1 for ensuring, through this serialization, a positive acceleration margin at the point of maximum drag of the gas generator.

Abstract: An aircraft powerplant assembly includes a compressor rotor, a compressor vane structure, a diffuser structure, a combustor and an air system. The compressor rotor includes a rotor stage and a rotor hub. The rotor hub includes a hub wall connected to a rotor base. An outer surface of the hub wall forms an inner peripheral boundary of a first section of an air passage. The compressor vane structure is radially outboard of the hub wall. The diffuser structure includes a diffuser nozzle and a diffuser plenum. The combustor is disposed in the diffuser plenum. The air system includes an air circuit and a heat exchanger. The air system is configured to bleed compressed air from the diffuser plenum through a circuit inlet, cool the compressed air with the heat exchanger to provide cooled air, and direct the cooled air into the air passage through a circuit outlet.

Abstract: An injector for a liquid rocket engine includes an array of injector elements. Each injector element includes a central passage and a plurality of peripheral transverse passages. The central passages are configured to provide axial injection flow and the peripheral transverse passages are configured to provide swirl injection flow. A portion of the injector elements provide the swirl injection flow in a clockwise direction and another portion of the injector elements provide the swirl injection flow in a counter-clockwise direction. The injector elements are arranged with a single, center injector element and a plurality of circumferential rows disposed around the single, center injector element.

Abstract: Transpiration-cooled systems having permeable and non-permeable portions are provided. In one aspect, a nozzle for a rocket engine includes a non-permeable outer layer, a plurality of walls, a permeable layer, and a plurality of cooling channels. The non-permeable outer layer forms a predetermined shape of the nozzle and defines an interior space. The plurality of walls extend generally orthogonal to the non-permeable outer layer and into the interior space. The permeable layer is disposed between each set of adjacent walls of the plurality of walls. The permeable layer is spaced a distance from the non-permeable outer layer. The plurality of cooling channels are formed between the permeable layer, the non-permeable outer layer, and a set of adjacent walls of the plurality of walls. The plurality of cooling channels are configured to transport a fluid.

Abstract: A propulsion system for an aircraft includes a gas turbine engine, an electrical assembly, a powertrain, and a controller. The gas turbine engine includes a rotational structure and a second rotational structure each including a turbine rotor. The electrical assembly includes an electric machine and a control unit. The control unit is electrically connected to the electric machine. The powertrain includes a differential geartrain configured to couple the rotational structure and the second rotational structure together to the electric machine. The controller is connected in communication with the control unit. The controller is configured to maintain a predetermined power transfer ratio between a spool mechanical power transfer of the second rotational structure and an electric machine mechanical power transfer of the electric machine along a rotation speed range of the second rotational structure by controlling an electrical loading of the electric machine with the control unit.

Abstract: A water outlet device comprises a water outlet body and a cover assembly. The water outlet body comprises a plurality of water outlet ports, and the plurality of water outlet ports are configured to discharge water. The cover assembly is detachably connected to the water outlet body to cover the plurality of water outlet ports, and the cover assembly comprises a water outlet cover and a fixed cover. The water outlet cover comprises a plurality of water outlet columns that are elastically deformable, and the plurality of water outlet columns are respectively connected to and in communication with the plurality of water outlet ports. The fixed cover is detachably connected to the water outlet body, and the water outlet cover is fixedly clamped between the fixed cover and the water outlet body.

Abstract: Transpiration-cooled systems having permeable and non-permeable portions are provided. In one aspect, a nozzle for a rocket engine includes a non-permeable outer layer, a plurality of walls, a permeable layer, and a plurality of cooling channels. The non-permeable outer layer forms a predetermined shape of the nozzle and defines an interior space. The plurality of walls extend generally orthogonal to the non-permeable outer layer and into the interior space. The permeable layer is disposed between each set of adjacent walls of the plurality of walls. The permeable layer is spaced a distance from the non-permeable outer layer. The plurality of cooling channels are formed between the permeable layer, the non-permeable outer layer, and a set of adjacent walls of the plurality of walls. The plurality of cooling channels are configured to transport a fluid.

Abstract: The present disclosure is directed to an ignition device including a housing, a bulk fuel, and at least two lead wires as electrodes. The bulk fuel is made of a plastic material, such as polylactic acid (PLA) or epoxy resin. The bulk fuel contains an internally dispersed powdery conductive material, thereby obtaining a conductive solid fuel. One end of the lead wire is partially embedded in the bulk fuel. The other end of the lead wire is connected to a power source. A portion of the bulk fuel is gasified by energizing the lead wire, and the gasified fuel is combusted by reaction with an oxidant.

Abstract: A gas turbine engine includes a fan assembly, a turbomachine defining in part a working gas flowpath, the gas turbine engine defining a bypass passage over the turbomachine, a core cowl, and a heat exchanger assembly including a heat exchanger and a heat exchanger cowl defining a cooling air flowpath extending between a flowpath inlet in airflow communication with the bypass passage to receive a cooling airflow from the bypass passage and a flowpath outlet in airflow communication with the bypass passage to exhaust the cooling airflow back to the bypass passage, the heat exchanger positioned within the cooling air flowpath, the cooling air flowpath comprising a diffusion section located between the flowpath inlet and the heat exchanger.

Abstract: A burner apparatus is disclosed. The burner apparatus comprising a tube having a proximal portion, a middle portion, and a distal portion, a fuel inlet port adapted to receive fuel inside the tube. The fuel inlet port splits into a first conduit and a second conduit, an air inlet port receives air inside the tube, at least one air swirler unit positioned at the middle portion of the tube, generates a swirling air flow and an axial air flow from the air received, a block having a plurality of staged fuel tips, receives fuel from the second conduit. The block discharges a primary flame by containing the fuel received from the first conduit and the swirling air flow, and provide for a secondary flame by directing the fuel received from the plurality of staged fuel tips into the primary flame downstream of the primary flame attachment point.