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.

Abstract: A thruster includes a current loop, a magnetic circuit within the current loop, a channel, a propellant reservoir and an ejection outlet. The channel forms an ejection path from an output of the propellant reservoir to the ejection outlet. The current loop is driven by a tuned current density based on at least a selected propellant. The selected propellant is ejected down the channel due to an applied electric field.

Abstract: A vehicle fire-extinguishing and passenger-cooling device includes a fire-extinguishing fluid spray device and a cooling gas discharge device. In the event of a vehicle fire occurring in a seat on which a passenger is seated, the fire-extinguishing fluid spray device sprays fire-extinguishing fluid around the passenger, and the cooling gas discharge device discharges, to the passenger, cooling gas to minimize burns caused by flames. As a result, the vehicle fire-extinguishing and passenger-cooling device protects the passenger from the vehicle fire and encourages the passenger to rapidly escape from a vehicle.

Abstract: The invention relates to a nozzle assembly for a combustor of an engine, including at least one nozzle for injecting fuel into a combustion chamber of the combustor, wherein the nozzle has a nozzle main body which extends along a nozzle longitudinal axis and a nozzle holder connected to the nozzle main body and having at least one fuel supply line. The nozzle main body comprises a central fuel pipe extending along the nozzle longitudinal axis and sealed against an in-flow of air, in which fuel supplied via the at least one fuel supply line can be guided within the nozzle main body up to a fuel outlet opening of the fuel pipe provided at a nozzle end of the nozzle, via which the fuel can be introduced into the combustion chamber.

Abstract: An assembly is provided for an engine. This engine assembly includes an engine structure and a fuel injector. The engine structure includes an injector receptacle and a fuel supply passage. The injector receptacle extends longitudinally through the engine structure along a centerline. The fuel supply passage extends laterally within the engine structure to the injector receptacle. The fuel injector is mated with the injector receptacle. The fuel injector includes a nozzle passage and a nozzle outlet. The nozzle passage spirals about the centerline within the fuel injector towards the nozzle outlet. The nozzle passage fluidly couples the nozzle outlet to the fuel supply passage.

Abstract: A bearing chamber is provided. The bearing chamber includes an interior surface comprising a terminal block defining a keyway and a conduit terminating at the keyway and an oil nozzle defining an internal channel. The oil nozzle includes a base tightly fittable in the keyway. When the base is tightly fit in the keyway, the internal channel is communicative with the conduit and an orientation of the keyway and a configuration of the oil nozzle are cooperatively established to aim the oil nozzle at a predefined target within the bearing chamber.

Abstract: A vehicle is disclosed. The vehicle includes a battery device, a fire extinguishing agent tank accommodating a fire extinguishing agent, a first flow path connected to the battery device and the fire extinguishing agent tank, a valve configured to regulate opening of the first flow path, a second flow path connected to the fire extinguishing agent tank, and an external inlet connected to the second flow path and configured to receive the fire extinguishing agent from an external device.

Abstract: A method of operating a turbomachine includes producing an estimate of a power gain resulting from operation of one or more power augmentation features of the turbomachine using a statistical model and producing an estimate of an economic benefit resulting from operation of the one or more power augmentation features of the turbomachine using an economic model. The method further includes activating the one or more power augmentation features of the turbomachine based on the estimate of the economic benefit.