Abstract: A fuse-less ignition system for fireworks. An ignitor module is provided that is insertable into a firework and includes: a first end having an interface adapted to reside on an exterior surface of the firework for receiving a plug; a set of electrical contacts adapted to receive electricity from the plug; a heat element coupled to the electrical contacts and adapted to heat in response to received electricity; and a cavity adjacent to the heat element containing a pyrotechnic material, the pyrotechnic material adapted to ignite in response to a heating of the heat element.

Abstract: A method for registering one or more Greenfield devices via a virtual Internet of Things Universal Identifier (IoT UID) is provided. The method includes identifying one or more Brownfield devices, generating device property data based at least in part on the one or more Brownfield devices, and transmitting, to an IoT device registrar server, a registration request that includes the device property data. The method further includes interpreting one or more IoT UIDs generated in response to the transmitting of the registration request.

Abstract: An engine system includes an engine core assembly, a fuel system and a cooling circuit. The engine core assembly includes a core flowpath, a compressor section, a combustor section and a turbine section. The combustor section includes a combustor adjacent a plenum. The fuel system includes a fuel flowpath, a fuel reservoir, a fuel-cooling air heat exchanger and a fuel injector. The fuel flowpath is configured to direct hydrogen fuel, received from the fuel reservoir, through the fuel-cooling air heat exchanger to the fuel injector. The fuel injector is configured to introduce the hydrogen fuel into the combustor. The cooling circuit is configured to direct cooling air, bled from the plenum, through the fuel-cooling air heat exchanger to the turbine section. The fuel-cooling air heat exchanger is configured to exchange heat energy between the hydrogen fuel flowing within the fuel flowpath and the cooling air flowing within the cooling circuit.

Abstract: An aircraft propulsion system is provided that includes a turbine engine and an exhaust gas heat exchanger. The exhaust gas heat exchanger includes a central conduit, an outer radial plenum, fluid conduits, and inter-conduit passages. The fluid conduits are disposed in a nested arrangement. Each fluid conduit has inner and outer radial walls that extend axially between the forward and aft ends. The inner and outer radial walls are radially separated to form an internal fluid passage. Each fluid conduit is radially spaced apart from adjacent fluid conduits to define an axially extending exhaust gas passages. The inter-conduit passages include at least one inter-conduit passage that provides fluid communication between the central conduit and a first fluid conduit, and at least one inter-conduit passage that provides fluid communication between first and second fluid conduits. A serpentine fluid flow path extends through the fluid conduits and the inter-conduit passages.

Abstract: Optimizing copy operations in a storage array, includes combining, in dependence upon a metadata optimization policy, a plurality of copy operations into a single copy operation and splitting the single copy operation into an optimized set of executable copy operations that copy data based on memory alignment.

Abstract: In an embodiment, an apparatus where encrypted data is agnostic to encryption functionality controlled by the operating system is presented. The apparatus includes a processor and memory communicatively connected to the processor. The memory includes instructions configuring the processor to receive encrypted input data for processing by an application. The processor is configured to store the encrypted input data in a communications input buffer immediately after receipt. The OS through predetermined functionality then determines where the ultimate intended destination that data in the communications input buffer should be, moves the data to that location, referred to as the application input buffer. The processor is configured to execute the receiving application. The application is configured to run one or more programs utilizing the unencrypted input data to produce output data. The application is similarly configured to internally to optionally encrypt the output data to produce encrypted output data.

Abstract: An apparatus for an Internet of Things device registry display includes a user input processing circuit structured to interpret one or more user input command values, an Internet of Things Universal Identification (IoT UID) identification circuit structured to determine one or more IoT UIDs, based at least in part on the one or more user input command values, a device lookup circuit structured to: generate a query that includes the one or more IoT UIDs, and retrieve device property data corresponding to the one or more IoT UIDs, a query provisioning circuit structured to transmit the query to an IoT device registrar server, a device property processing circuit structured to interpret the device property data generated by the IoT device registrar server in response to the query, and a display circuit structured to display the device property data with the corresponding one or more IoT UIDs.

Abstract: An assembly includes a first die, and a second die arranged face-to-face with the first die. The first die includes a first pad, a second pad at a vertical elevation of the first pad, and mirror function circuitry configured to swap functionalities of the first pad and the second pad. The second die includes an additional first pad corresponding to the first pad of the first die, and an additional second pad at a vertical elevation of the additional first pad and corresponding to the second pad of the first die. The additional first pad is coupled to the second pad of the first die. The additional second pad is coupled to the first pad of the first die. Additional assemblies and electronic systems are also described.

Abstract: An aircraft propulsion system is provided that includes a turbine engine and an intercooler (IC). The turbine engine includes a source of non-hydrocarbon fuel, and a low pressure compressor having an LPC air inlet and outlet, and a high pressure compressor having an HPC air inlet and outlet. The intercooler has an IC air inlet, an IC air outlet, a U-shaped air passage, and crossflow tubes. The IC air inlet is in fluid communication with the LPC air outlet. The IC air outlet is in fluid communication with the HPC air inlet. The U-shaped air passage is in fluid communication with the IC air inlet and outlet. The crossflow tubes extend through the U-shaped air passage. The crossflow tubes are in fluid communication with the source of non-hydrocarbon fuel, and are configured to contain a flow of the non-hydrocarbon fuel therethrough.

Abstract: A capillary tube holder is provided for holding a capillary tube. The capillary tube holder includes a holder insert and a holder base. The holder insert includes a capillary groove configured for receiving the capillary tube. The holder base is configured for slidably receiving and retaining the holder insert therein.

Abstract: In accordance with at least one aspect of this disclosure, there is provided a system for an aircraft engine. In embodiments, the system includes an accessory box and a fuel accessory located in an interior space within the accessory box, where a vent is defined through a wall of the accessory box. In embodiments, the vent includes a plurality of holes or slots in an outer wall of the accessory box for passage of gaseous fuel from the interior space. In embodiments, the vent is configured for passive ventilation of the interior space.

Abstract: An electronic indicator on a see-through optical scope indicates whether an optical system is canted. The visual indicator may include one or more LEDs coupled to a microprocessor that is also coupled to a solid-state electronic inclinometer incorporated into the internal structure of the optical system. The microprocessor is configured to selectively illuminate the visual indicator based on the output of the inclinometer, thereby indicating how the reticle is canted, if at all.

Abstract: A method for determining a trust indicator is provided. The method may include interpreting, via an Internet of Things Universal Identifier (IoT UID) processing circuit, an IoT UID corresponding to a device and identifying, via a record management circuit and based at least in part on the IoT UID, a record in a database corresponding to the device. The method may further include determining, via a trust analysis circuit and based at least in part on the record, a risk indicator of the device and transmitting, via an indicator provisioning circuit, the risk indicator.

Abstract: An aircraft propulsion system is provided that includes a turbine engine and an exhaust gas heat exchanger. The exhaust gas heat exchanger includes a central conduit, an outer radial plenum, fluid conduits, and inter-conduit passages. The fluid conduits are disposed in a nested arrangement. Each fluid conduit has inner and outer radial walls that extend axially between the forward and aft ends. The inner and outer radial walls are radially separated to form an internal fluid passage. Each fluid conduit is radially spaced apart from adjacent fluid conduits to define an axially extending exhaust gas passages. The inter-conduit passages include at least one inter-conduit passage that provides fluid communication between the central conduit and a first fluid conduit, and at least one inter-conduit passage that provides fluid communication between first and second fluid conduits. A serpentine fluid flow path extends through the fluid conduits and the inter-conduit passages.

Abstract: An aircraft propulsion system is provided that includes a turbine engine and an intercooler (IC). The turbine engine includes a source of non-hydrocarbon fuel, and a low pressure compressor having an LPC air inlet and outlet, and a high pressure compressor having an HPC air inlet and outlet. The intercooler has an IC air inlet, an IC air outlet, a U-shaped air passage, and crossflow tubes. The IC air inlet is in fluid communication with the LPC air outlet. The IC air outlet is in fluid communication with the HPC air inlet. The U-shaped air passage is in fluid communication with the IC air inlet and outlet. The crossflow tubes extend through the U-shaped air passage. The crossflow tubes are in fluid communication with the source of non-hydrocarbon fuel, and are configured to contain a flow of the non-hydrocarbon fuel therethrough.

Abstract: An engine system includes an engine core assembly, a fuel system and a cooling circuit. The engine core assembly includes a core flowpath, a compressor section, a combustor section and a turbine section. The combustor section includes a combustor adjacent a plenum. The fuel system includes a fuel flowpath, a fuel reservoir, a fuel-cooling air heat exchanger and a fuel injector. The fuel flowpath is configured to direct hydrogen fuel, received from the fuel reservoir, through the fuel-cooling air heat exchanger to the fuel injector. The fuel injector is configured to introduce the hydrogen fuel into the combustor. The cooling circuit is configured to direct cooling air, bled from the plenum, through the fuel-cooling air heat exchanger to the turbine section. The fuel-cooling air heat exchanger is configured to exchange heat energy between the hydrogen fuel flowing within the fuel flowpath and the cooling air flowing within the cooling circuit.

Abstract: An engine system is provided that includes an open propulsor rotor, an engine core assembly, a bypass flowpath and a condenser. The engine core assembly is configured to drive rotation of the open propulsor rotor. The engine core assembly includes a core flowpath, a compressor section, a combustor section and a turbine section. The core flowpath extends through the compressor section, the combustor section and the turbine section from an inlet into the core flowpath to an exhaust from the core flowpath. The bypass flowpath bypasses the engine core assembly. The condenser is configured to exchange heat energy between combustion products flowing within the core flowpath downstream of the combustor section and bypass air flowing within the bypass flowpath.

Abstract: An aircraft propulsion system and method is provided. The system includes compressor, combustor, and turbine sections, a fuel source, a heat exchanger, a compressor bleed air passage, and a cooling air passage. The fuel source is configured to contain a non-hydrocarbon fuel. The heat exchanger has separate air and fuel passages. The air passage permits passage of the compressed air therethrough. The fuel passage is configured to permit a passage of the non-hydrocarbon fuel therethrough. The compressor bleed air passage is configured to receive compressed air bleed off a core flow path upstream of the combustor section. The compressor bleed air passage is in fluid communication with the air passage air inlet. The cooling air passage is configured to receive compressed air exiting the air passage air outlet and configured to direct the compressed bleed air to the vane stage or rotor stage of the turbine section, or both.

Abstract: An oven vent heat diverter device is disclosed which is a heat diversion barrier placed under the control panel of an oven or other appliance and redirects the heat to the exhaust fan. The oven vent heat diverter device comprises a body component consisting of several hinged panels attached to one another. In use, the hinged panels are secured together in a square configuration and positioned over the cooking surface of the free-standing range vent area, and under a control panel of an over-the-range (OTR) microwave or other suitable oven appliance. Further, the device can be folded up substantially flat for easy and convenient storage.

Abstract: Provided are a computer product, system, and method for dynamic assignment of device queues to virtual functions to provide to virtual machines. Queues are assigned to a virtual function to access the physical functions of the device. The virtual function is provided to a virtual machine to use to access the physical functions of the device. A determination is made of a utilization of the queues assigned to the virtual function accessed by the virtual machine. A number of the queues assigned to the virtual functions for requests submitted by the virtual machine is changed in response to the determined utilization.