Abstract: A seal tube assembly of a pump system is provided. The seal tube assembly includes a single seal tube having a first axial end sealably coupled to a first vane pump and a second axial end sealably coupled to a second vane pump. The single seal tube includes transverse contact surfaces at the first axial end and transverse contact surfaces at the second axial end. The single seal tube is formed to define a first seal tube cavity at the first axial end and a second seal tube cavity at the second axial end.

Abstract: A system and method that comprises an air cycle machine, a flow of bleed air, at least one heat exchanger, and an inlet configured to supply the flow of the bleed air is provided. The bleed air flows from a source to mix with recirculated air in accordance with a high pressure mode or a recirculation chilling mode. The system and method also can also utilize the recirculated air flowing from the chamber to drive or maintain the air cycle machine in accordance with the above modes.

Abstract: An environmental control system (ECS) for an aircraft includes at least one cooling turbine, and a turbine bypass valve disposed fluidly upstream of the at least one cooling turbine. The turbine bypass valve is configured to direct a first portion of an ECS output airflow to a first air load at a first pressure via a first outlet passage, and direct a second portion of the ECS output airflow across a cooling turbine of the at least one cooling turbine and to a second air load at a second pressure lower than the first pressure for cooling thereof.

Abstract: An electrical assembly includes a first conductor, a second conductor, and a bus bar. The first conductor is disposed on a terminal block and defines a first conductor opening. The second conductor is spaced apart from the first conductor. The bus bar extends from an electrical component. The bus bar has a first bus bar surface that is arranged to engage the first conductor and a second bus bar surface that is disposed opposite the first bus bar surface. The second bus bar surface is arranged to engage the second conductor. Each of the first bus bar surface and the second bus bar surface extends between an end surface of the bus bar and the electrical component.

Abstract: An electromagnetic device is disclosed, the electromagnetic device comprising a core support having an exterior surface comprising at least one radial protrusion, a tubular magnetic core positioned around a portion of the length of the core support, the tubular magnetic core having an interior surface, at least one indent located in the interior surface of the tubular magnetic core, wherein the at least one protrusion is located within the at least one indent to prevent relative longitudinal movement between the core support and tubular magnetic core, and a primary coil and at least one secondary coil, each coil positioned around a portion of a length of the tubular magnetic core.

Abstract: An isolation valve comprising: a housing having an internal surface within the housing, the internal surface having a first outlet and second outlet; an air gate having an outward face opposite the internal surface, the air gate located within the housing and configured to move to at least one of a first position blocking flow to the first outlet, a neutral position blocking flow to neither the first outlet nor second outlet, and a second position blocking flow to the second outlet; a seal groove located on the outward face of the air gate; a seal located within seal groove, the seal configured to form a sealed connection with the internal surface around at least one of the first outlet when in the first position and the second outlet when in the second position; and a retainer configured to secure the seal within the seal groove using a fastening mechanism.

Abstract: A check valve comprises an annular housing defining a generally circular opening. A plurality of radially extending arms extend across the circular opening from the centre of the valve housing to respective nodes at the periphery of the valve housing. A plurality of cross arms extend between circumferentially adjacent nodes, thereby dividing the circular opening into a plurality of primary, generally triangular radially inner openings and a plurality of secondary, generally segment shaped radially outer openings. A plurality of primary, generally triangular flapper elements close the primary openings and a plurality of secondary, generally segment shaped flapper elements close the secondary openings. Respective mounting posts are arranged at a respective node and a respective hinge pin is mounted between respective circumferentially adjacent mounting posts.

Abstract: A cone brake no-back includes an input no-back disk, an output no-back disk; and a no-back ball ramp mechanism operably connected to the input no-back disk and the output no back disk. An input no-back cone is operably connected to and supportive of the input no-back disk. The input no-back cone is axially loaded by an input no-back spring. An output no-back cone is operably connected to and supportive of the output no-back disk. The output no-back cone is axially loaded by an output no-back spring. A no-back input shaft is operably connected to the input no-back disk and the output no back disk, and a no-back output shaft is operably connected to the output no back disk.

Abstract: A method of prognostic health monitoring is provided for use with an aircraft. The method includes performing real-time monitoring of torque generated for controlling positions of controllable surfaces at right- and left-hand-sides (RHS and LHS) of the aircraft, generating RHS and LHS torque information from results of the monitoring and comparing the RHS and LHS torque information at least with each other or with corresponding historic torque information.

Abstract: An aircraft includes a first engine that generates first bleed air flow and a second engine that generates second bleed air flow. The aircraft further includes an aircraft environmental control system (ECS) with a bleed manifold to collect the first bleed air flow and the second bleed air flow, and one or more air cycle machines to perform air conditioning consuming bleed air flow from the bleed manifold. The ECS balances the first bleed air flow and the second bleed air flow output from the first engine and second engine, respectively, based on a bleed manifold pressure of the bleed manifold.

Abstract: An aircraft is provided. The aircraft includes a pressurized volume and an air conditioning system. The air conditioning system operates in a first mode or a second mode. The first mode includes when a first medium and a second medium and are mixed and provided to the pressurized volume. The second mode includes when only the first medium is provided to the pressurized volume.

Abstract: A multifunctional phase separation apparatus is provided herein. The multifunctional phase separation apparatus includes a porous tube, a phase separator, and liquid collecting modules. The porous tube includes a first entry port and an exit port. The phase separator includes a second entry port. The multifunctional phase separation apparatus also includes a reservoir. The reservoir is on a first end of the liquid collecting modules.

Abstract: A method of performing a built in test on a watchdog circuit including a watchdog timer includes: initiating the built in test with a processor being monitored by the watchdog circuit, wherein initiating includes enabling a watchdog circuit built in test reset inhibit circuit (WD BIT reset inhibit circuit) connected between an output of an active watchdog integrated reset circuit connected to the processor and a reset input of the processor; and ceasing to provide a strobe signal to the active watchdog integrated reset circuit that resets a watchdog counter in the active watchdog integrated reset circuit, the active watchdog integrated reset circuit causing a reset of the processor via its output when the watchdog counter expires by providing a signal to a reset input of the processor.

Abstract: An apparatus includes a process scanner and a processor connected with the process scanner. The processor is configured to retrieve, via the processing scanner, operation information indicative of a serial number of an operation, an operation number, an order number of an order associated with the operation, a work time spent on the operation, and a material number of a material associated with the operation. The processor associates the operation information with a first user assigned to the operation, and saves, to a history database, a process record. The record includes the first user, a time element, a location of the operation, a completion status of the operation, a current status of the operation, and one or more turnbacks of the operation. The processor outputs to a display a graphic of the operation information and a balance of user time associated with the operation information.

Abstract: A thrust bearing arrangement includes a top plate extending about a rotation axis, a thrust plate extending about the rotation axis and axially offset from the top foil plate, and a bump plate. The thrust plate is orthogonal relative to the rotation axis. The bump foil plate extends about the rotation axis, is axially offset from the thrust plate, and has an annular portion and two or more bump plate foil portions. The annular portion of the bump plate is circumferentially interrupted by the bump plate foil portions of the bump plate. Rotating machines and methods of making thrust bearing arrangements for rotating machines are also described.

Abstract: A system is described for positioning and locking in place a nozzle within a cylindrical bore of a body, and a method for positioning and locking in place a nozzle within a cylindrical bore of a body is also described. The system has a nozzle having a tubular shape extending between a first end and a second end with an outer cylindrical surface and an inner surface, said inner surface comprising a thread. The system also has a locking member provided within said nozzle and comprising an outer circumferential surface having a thread that corresponds to the thread of the inner surface of the nozzle. The system also has means for providing torque to said locking member to screw said locking member into and within said nozzle via said threaded surfaces to thereby create a press-fit between said outer cylindrical surface and an inner surface of said cylindrical bore.

Abstract: Embodiments include systems, methods, and devices for voltage regulation of a hybrid energy storage module (HESM). The embodiments include a system controller including a first voltage regulator and a second voltage regulator, a first HESM coupled to the system controller, where the first HESM is coupled to a first bus, and a second HESM coupled to the system controller, where the second HESM is coupled to a second bus, and the first bus and the second bus are different.

Abstract: A fuel tank inerting system is provided including an air flow comprising air from a first source having a first temperature and air from a second source having a second temperature. The second temperature is cooler than the first temperature. At least one separating module is configured to separate an inert gas from the air flow.

Abstract: Disclosed is a multiple start torpedo including an aft body having an exhaust conduit defining a turbine end and a seawater end having an orifice. The multiple start torpedo includes an exhaust valve associated with the exhaust conduit including. The exhaust valve includes a fore section having a head and a valve stem. The exhaust valve includes an aft section tapered from the turbine end to the seawater end and defining a receptacle sized to receive the valve stem. The exhaust valve includes a biasing member disposed to bias the head in an extended position spaced apart from the aft section and abut the orifice in the extended position.

Abstract: Disclosed is a transmission having: an input shaft configured to rotationally communicate with a gas turbine engine; an output shaft configured to rotationally communicate with an aircraft accessory; and a gear system connected between the input shaft and the output shaft, the gear system including: a plurality of clutches that are axially aligned and radially offset, the plurality of clutches configured to engage in parallel the output shaft and shift the transmission to generate a plurality gear speeds; and a plurality of pistons that are configured to engage the respective plurality of clutches, the plurality of pistons being hydraulically controlled and adapted to receive fluid from a respective plurality of ports in the output shaft.