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: 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: 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 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.

Abstract: A reusable upper stage rocket or other atmospheric re-entry vehicle includes a nose, a base opposite the nose, and a propulsion engine toward the base. The propulsion engine includes a high pressure chamber and a nozzle configured to exhaust gas generated by the high pressure chamber. The nozzle includes an initial nozzle portion, a secondary nozzle portion downstream of the initial nozzle portion, and a nozzle exit at a downstream end of the secondary nozzle portion. The secondary nozzle portion includes an inner expansion surface, an outer expansion surface outboard of the inner expansion surface, and an expansion cavity defined between the inner expansion surface and the outer expansion surface.

Abstract: A gas turbine engine includes a compressor section having a first compressor and a second compressor, the second compressor having a higher pressure than the first compressor, and a turbine section having a first turbine and a second turbine, the second turbine having a higher pressure than the first turbine. The first compressor is connected to the first turbine via a first shaft. The second compressor is connected to the second turbine via a second shaft. An electric motor is connected to the first shaft such that rotational energy generated by the electric motor is translated to the first shaft. A fan is connected to the first shaft via a gear system. The gas turbine engine includes at least a takeoff mode of operations, a top of climb mode of operations and a maximum cruise mode of operations. The gas turbine engine is sized to operate at peak efficiency in the maximum cruise mode of operations.

Abstract: A thruster system includes a tank for holding liquid propellant, a catalyst bed connected with the tank and operable to decompose the liquid propellant and generate a gas, a plenum connected with the catalyst bed for receiving the gas, a heat exchanger connected with the plenum to cool the gas to a temperature below a threshold temperature and thereby generate a cooled gas, at least one thruster connected with the heat exchanger to receive the cooled gas, and at least one control valve between the heat exchanger and the at least one thruster controlling flow of the cooled gas to the thruster. At least one control valve includes a soft material valve seal.

Abstract: An upright sprinkler is disclosed. The sprinkler comprises a housing having a conduit extending therethrough, a heat-sensitive valve assembly configured above the conduit, and a nozzle arrangement configured below the conduit. The nozzle arrangement is fluidically connected to the conduit via the valve assembly, such that actuation of the valve assembly enables the flow of a fluid from the conduit to the nozzle arrangement via the valve assembly and further sprays the fluid at different downward-facing angles through the nozzle arrangement.

Abstract: The invention relates to a hydrogen storage power plant (1) comprising: in order to produce hydrogen (H2) from methane or natural gas, a pyrolysis device for methane pyrolysis and/or natural gas pyrolysis and/or a plasmalysis device (6) for methane plasmalysis and/or natural gas plasmalysis; -a storage device (11), which is coupled on the output side to the pyrolysis device, for storing the hydrogen (H2) or a storage device (11), which is coupled on the output side to the plasmalysis device (6), for storing the hydrogen (H2); and a hydrogen combustion engine (12) which is coupled on the outlet side to the storage device (11) and has a closed noble gas circuit (12.1) for circulating noble gas, which noble gas circuit leads from an outlet channel (12.2) of the hydrogen combustion engine (12) via a circulation path to an inlet channel (12.3) of the hydrogen combustion engine (12) and guides a noble gas (EG) from the outlet channel (12.2) via the inlet channel (12.

Abstract: A quick-fill lavage system that is used in a medical environment to prevent the contamination of wounds. The quick-fill lavage system comprises of a gun shaped body that houses a refillable reservoir. A suction ball that is used to refill the reservoir. A one-way valve is used to dispense a liquid from the refillable reservoir. The one-way valve uses a suction tube system to connect the refillable reservoir to pull the liquid from the refillable reservoir. A dispensing tube system attaches to an outlet section of the one-way valve. The dispensing tube removes the liquid from the quick-fill lavage system. A trigger system is used to open the one-way valve to dispense the liquid in a control and manual manner.