Abstract: A DC power plant generating DC power from a variety of engines including a Stirling cycle engine. The DC power plant includes a relatively small start-up power source that is discontinued after the engine is running. A method for producing DC power for a load including starting up an engine using power supplied by a relatively small power supply supplemented by a capacitor bank, providing output from the engine to a generator, producing alternating current (AC) power by the generator, converting the AC power to direct current (DC) power, disabling output of the DC power during a first set of pre-selected conditions, limiting a rate of change of current of the DC power during a second set of pre-selected conditions, reducing conducted and radiated emissions of the DC power, disconnecting the DC power from the load under a third set of pre-selected conditions, and providing the DC power to the load.

Abstract: Provided are methods, devices, and kits for the isolation and detection of one or more analytes of interest from a biological sample using microslit filter membranes. In various examples, the methods use capture particles and binding agents for specific recognition of one or more analytes of interest.

Abstract: A multi-directional fire extinguishing nozzle is disclosed. The multi-directional fire extinguishing nozzle may comprise a pylon fitting configured to receive a fire extinguishing agent. The multi-directional fire extinguishing nozzle may comprise a hose fitting coupled to the pylon fitting via a coupling nut. The multi-directional fire extinguishing nozzle may comprise a plurality of fluid distribution outlets configured to deliver the fire extinguishing agent. The fluid distribution outlets may define voids on the surface of the coupling nut, and extending through the coupling nut and the hose fitting.

Abstract: A fire suppression system for a gas turbine engine includes a fire suppressant delivery circuit, a first nozzle and a multi-directional nozzle. The fire suppressant delivery circuit includes and extends between an upstream inlet and a downstream distal end. The first nozzle is fluidly coupled with the fire suppressant delivery circuit and is disposed at the downstream distal end. The multi-directional nozzle is fluidly coupled with the fire suppressant delivery circuit and is configured serially inline between the upstream inlet and the first nozzle.

Abstract: A multi-directional fire extinguishing nozzle is disclosed. The multi-directional fire extinguishing nozzle may comprise a pylon fitting configured to receive a fire extinguishing agent. The multi-directional fire extinguishing nozzle may comprise a hose fitting coupled to the pylon fitting via a coupling nut. The multi-directional fire extinguishing nozzle may comprise a plurality of fluid distribution outlets configured to deliver the fire extinguishing agent. The fluid distribution outlets may define voids on the surface of the coupling nut, and extending through the coupling nut and the hose fitting.

Abstract: Aspects of the disclosure are directed to a shaft configured with a first hole, a bearing race coupled to the shaft and configured with a second hole and a third hole, and an oil scoop configured to receive oil and provide the oil to the shaft, where the first and second holes are oriented axially with respect to the shaft, and where the third hole is oriented radially with respect to the shaft. In some embodiments, a second oil scoop is configured to receive oil and provide the oil to the shall. The oil scoop and the second oil scoop may be concentric with respect to one another.

Abstract: A fire suppression system for a gas turbine engine includes a fire suppressant delivery circuit, a first nozzle and a multi-directional nozzle. The fire suppressant delivery circuit includes and extends between an upstream inlet and a downstream distal end. The first nozzle is fluidly coupled with the fire suppressant delivery circuit and is disposed at the downstream distal end. The multi-directional nozzle is fluidly coupled with the fire suppressant delivery circuit and is configured serially inline between the upstream inlet and the first nozzle.

Abstract: A multi-directional fire extinguishing nozzle is disclosed. The multi-directional fire extinguishing nozzle may comprise a pylon fitting configured to receive a fire extinguishing agent. The multi-directional fire extinguishing nozzle may comprise a hose fitting coupled to the pylon fitting via a coupling nut. The multi-directional fire extinguishing nozzle may comprise a plurality of fluid distribution outlets configured to deliver the fire extinguishing agent. The fluid distribution outlets may define voids on the surface of the coupling nut, and extending through the coupling nut and the hose fitting.

Abstract: Aspects of the disclosure are directed to a shaft of an engine of an aircraft, an oil scoop coupled to the shaft, a first portion of a sensor integrated with the oil scoop, and a second portion of the sensor coupled to a structure of the engine. In some embodiments, the first portion of the sensor comprises at least one tooth.

Abstract: Aspects of the disclosure are directed to a system associated with an engine of an aircraft. The system includes a shaft configured with at least one axially-oriented hole, and an oil scoop configured to receive oil and provide the oil to the shaft, wherein the oil scoop is manufactured independently from the shaft, and wherein the oil scoop includes at least one retention mechanism for coupling to the shaft after the at least one axially-oriented hole is created in the shaft.

Abstract: A fan nacelle includes a metallic fan containment case. A nacelle inlet is secured to the metallic fan containment case by permanent fastening elements. A gas turbine engine includes a metallic fan containment case. A core engine has a static engine structure housing a compressor section, a combustor section and a turbine section. The core engine is configured to receive core airflow. A fan is arranged within the metallic fan containment case. The fan is coupled to the core engine and is arranged in a bypass flowpath provided between the core engine and the metallic fan containment case. A nacelle inlet is secured to the metallic fan containment case by permanent fastening elements.

Abstract: Aspects of the disclosure are directed to a shaft configured with a first hole, a bearing race coupled to the shaft and configured with a second hole and a third hole, and an oil scoop configured to receive oil and provide the oil to the shaft, where the first and second holes are oriented axially with respect to the shaft, and where the third hole is oriented radially with respect to the shaft. In some embodiments, a second oil scoop is configured to receive oil and provide the oil to the shall. The oil scoop and the second oil scoop may be concentric with respect to one another.

Abstract: Aspects of the disclosure are directed to a system associated with an engine of an aircraft. The system includes a shaft configured with at least one axially-oriented hole, and an oil scoop configured to receive oil and provide the oil to the shaft, wherein the oil scoop is manufactured independently from the shaft, and wherein the oil scoop includes at least one retention mechanism for coupling to the shaft after the at least one axially-oriented hole is created in the shaft.

Abstract: Aspects of the disclosure are directed to a shaft of an engine of an aircraft, an oil scoop coupled to the shaft, a first portion of a sensor integrated with the oil scoop, and a second portion of the sensor coupled to a structure of the engine. In some embodiments, the first portion of the sensor comprises at least one tooth.

Abstract: A turbomachine includes a rotor hub that has a central opening there through. A shaft extends through the central opening. A clamp is coupled with the shaft and the rotor hub such that the rotor hub is rotatable with the shaft.

Abstract: A thrust reverser system for a gas turbine engine includes a duct including a cowling movable between an open position and a closed position in a direction transverse to a centerline of the gas turbine engine. The thrust reverser is supported within the cowling and movable between an axial closed position, an axial intermediate position and an axial open position. A controller is actuateable to command movement of the thrust reverser from the axial closed position to the axial intermediate position such that the cowling is free to move to the open position.

Abstract: A gas turbine engine section comprises a rotatable shaft, first and second axially adjacent components, a nut, and a multifunction positioning lock washer. The first and second axially adjacent components are located on the rotatable shaft and are separated by an axial separation distance. The nut is configured to thread onto the rotatable shaft to hold one of the first and second axially adjacent components in compression. The multifunction positioning lock washer has antirotation geometry configured to prevent the nut from tightening or loosening. The axial length of the multifunction positioning lock washer is adjusted by removing material based on measurement of the axial separation distance to take in tolerances and reduce the axial separation distance.

Abstract: A gas turbine engine thrust reverser system includes a fan nacelle having a fixed portion and a movable portion configured to move relative to the fixed portion between opened and closed positions in response to a command to selectively provide an opening between the fixed and movable portions. A fan case is arranged within the fan nacelle. The fan case includes an integral bull nose adjacent to the opening in the open position and to the movable portion in the closed position. The bull nose has a curved wall sloping radially outward.

Abstract: A gas turbine engine section comprises a rotatable shaft, first and second axially adjacent components, a nut, and a multifunction positioning lock washer. The first and second axially adjacent components are located on the rotatable shaft and are separated by an axial separation distance. The nut is configured to thread onto the rotatable shaft to hold one of the first and second axially adjacent components in compression. The multifunction positioning lock washer has antirotation geometry configured to prevent the nut from tightening or loosening.

Abstract: A fan nacelle includes a metallic fan containment case. A nacelle inlet is secured to the metallic fan containment case by permanent fastening elements. A gas turbine engine includes a metallic fan containment case. A core engine has a static engine structure housing a compressor section, a combustor section and a turbine section. The core engine is configured to receive core airflow. A fan is arranged within the metallic fan containment case. The fan is coupled to the core engine and is arranged in a bypass flowpath provided between the core engine and the metallic fan containment case. A nacelle inlet is secured to the metallic fan containment case by permanent fastening elements.