Abstract: An air conditioning pack management system for controlling distribution of a predetermined amount of conditioned air from a system comprising two or more air conditioning packs, the pack management system comprising a management unit arranged to proportion the predetermined amount of conditioned air to be provided by one or more of the two or more packs based on the respective operating efficiencies of the packs or other pre-selected metrics.

Abstract: A seal assembly for a turbine engine extends along a center axis and includes a seal support and a seal carrier configured to translate relative the seal support. A seal is connected to the seal carrier and a spring is disposed between the seal support and the seal carrier. A spring carrier is disposed between the spring and the seal support. A first end of the spring is connected to the spring carrier and the spring carrier is connected to the seal support. The spring includes a second end disposed opposite the first end of the spring. The second end of the spring contacts the annular seal carrier.

Abstract: An aircraft environmental control system includes a bleed air input and a RAM air input, heat exchanger means for receiving bleed air from the bleed air input and RAM air from the RAM air input and using the RAM air to cool the bleed air, and ejector arranged to receive bleed air from the bleed air input at a nozzle shaped to reduce the pressure of the received bleed air such as to create a low pressure area in the ejector. The ejector has a port arranged such that ambient air is drawn into the ejector due to the low pressure area in the ejector. The ambient air is mixed with bleed air to provide mixed air that is further pressurised and conditioned and combined with the cooled bleed air provided to the aircraft.

Abstract: A brake cooling system of the present disclosure includes an external cooling apparatus located externally from an aircraft (e.g., available on the ground at the gate during parking of the aircraft). The external cooling apparatus is in electronic communication with the aircraft via a communication channel such that the external cooling apparatus receives live data from the aircraft for intelligent aircraft brake cooling. The live data includes measured brake temperature. The brake cooling system further includes a controller for collecting aircraft data and generating a cooling apparatus control signal.

Abstract: A combustor liner for a gas turbine engine, the combustor liner including a panel configured to at least partially define a combustion chamber. The combustor liner further includes a shell configured to mount to the panel and form a gap between the panel and the shell. The panel includes a stud and a plurality of a stand-off pins proximate to the stud defining a cavity therebetween. The shell includes a plurality of angled impingement holes located away from the cavity but extending through the shell at an orientation such that cooling air passing through the angled impingement holes is directed towards the cavity between adjacent stand-off pins and at an acute angle relative to the stud.

Abstract: An epicyclic gear system includes an input sun gear configured to receive rotational input from a turbine of a turbo charger. A first set of planet gears is distributed around and meshes with the input sun gear. A carrier holds the first set of planet gears and defines a rotational axis about which the carrier rotates. A second set of planet gears is mounted to the carrier. An output sun gear is included, wherein the second set of planet gears are distributed around and mesh with the output sun. The output sun gear is configured to deliver rotational power to an internal combustion engine. The carrier is configured to selectively be driven by a variable speed drive to regulate output to the output sun over a range of input rotational speeds of the input sun gear.

Abstract: A method of detecting passage by an individual carrying a mobile device past an impediment operably connected to an access control is provided. The method including: detecting positional data of a mobile device; transmitting an access request from the mobile device to an access control operably connected to an impediment; detecting at least one of a sound from the impediment and a motion of the impediment; and determining that an individual carrying the mobile device has moved past the impediment in response to at least one of the sound from the impediment, the motion of the impediment, and the positional data of the mobile device.

Abstract: A method of making an electrocaloric element includes forming conductive layers on opposing surfaces of a film comprising an electrocaloric material to form an electrocaloric element, wherein the forming of the conductive layers includes one or more of: vapor deposition of the conductive layers under reduced pressure for a duration of time, wherein the duration of time under reduced pressure is less than 240 minutes; vapor deposition of the conductive layers under reduced pressure for a duration of time, wherein the duration of time of exposure to conductive material deposition is less than 240 minutes; vapor deposition of the conductive layers under reduced pressure, wherein the reduced pressure is 10?8 torr to 500 torr; or maintaining the film at a temperature of less than or equal to 200° C. during forming of the conductive layers.

Abstract: An inkjet chip including a substrate, a plurality of control elements, an insulating layer, a plurality of first conductive patterns, a plurality of second conductive patterns and a plurality of heaters is provided. The insulating layer is disposed on the control element and has a plurality of openings. The openings each have a first length in a first direction. Each first conductive pattern has a first sidewall overlapping one of the openings and is electrically connected between one of the control elements and one of the heaters. Each second conductive pattern has a second sidewall overlapping the one of the openings and is electrically connected to one of the heaters. A distance in the first direction is included between the first sidewall and the second sidewall opposing to each other. The distance is less than the first length. A thermal bubble inkjet printhead adopting the inkjet chip is also provided.

Abstract: A method of applying a protective coating with improved adhesion on an aluminum alloy component includes first pretreating the surface of a component by depositing a sacrificial protective immersion layer using a zincating or similar process. Portions of the protective immersion layer as well as portions of the underlying aluminum alloy substrate are then electrolytically etched off in an ionic liquid. A protective aluminum coating is then electrodeposited on the component in an ionic liquid.

Abstract: A hybrid propulsion system includes a heat engine configured to drive a heat engine shaft. An electric motor configured to drive a motor shaft. A transmission system is connected to receive rotational input power from each of the heat engine shaft and the motor shaft and to convert the rotation input power to output power. A first lubrication/coolant system is connected for circulating a first lubricant/coolant fluid through the heat engine. A second lubricant/coolant system in fluid isolation from the first lubrication/coolant system is connected for circulating a second lubricant/coolant fluid through the electric motor.

Abstract: A sensor array having a lattice topology includes interconnects having an electrically-conductive layer sandwiched between two dielectric layers, the interconnects defining first-axis interconnects, second-axis interconnects, and interconnect junctions, sensor nodes located on associated interconnect junctions thereby defining an associated first-axis line and second-axis line, a sensor on an associated sensor node, a primary first-axis interconnect interface that is electrically connected to the first-axis interconnects, and a primary second-axis interconnect interface that is electrically connected to the second-axis interconnects. Each sensor node includes a first electrode that is electrically connected to an associated first-axis line, a second electrode that is electrically connected to an associated second-axis line, and a bypass bridge that electrically isolates the associated second-axis line from the associated first-axis line.

Abstract: An attachment assembly includes a first component, a second component, and a locking device assembly. The locking device assembly is structured to move between an unlocked position corresponding to the second component being attachable to, and removable from, the first component and a locked position corresponding to the second component being securely coupled to the first component.

Abstract: A compressor case for a gas turbine engine includes an annular body that extends circumferentially around a center axis and extends axially along the center axis. A first bleed manifold is formed on an outer surface of the annular body and encloses a first plenum. A second bleed manifold is formed on the outer surface of the annular body and is axially aft of the first bleed manifold. The second bleed manifold encloses a second plenum. A bleed inlet extends through the annular body and into the first bleed manifold. Cooling passages are formed in the annular body, and each of the cooling passages extends from the first plenum to the second plenum and fluidically connects the first plenum to the second plenum.

Abstract: An epicyclic gear system includes an input sun gear configured to receive rotational input from a turbine of a turbo charger. A first set of planet gears is distributed around and meshes with the input sun gear. A carrier holds the first set of planet gears and defines a rotational axis about which the carrier rotates. A second set of planet gears is mounted to the carrier. An output sun gear is included, wherein the second set of planet gears are distributed around and mesh with the output sun. The output sun gear is configured to deliver rotational power to an internal combustion engine. The carrier is configured to selectively be driven by a variable speed drive to regulate output to the output sun over a range of input rotational speeds of the input sun gear.

Abstract: A rotor assembly of a gas-turbine engine may comprise a first rotor blade, a second rotor blade, a third rotor blade, a first platform sealing assembly and a second platform sealing assembly. The first platform sealing assembly may be disposed between a first platform of the first rotor blade and a second platform of the second rotor blade. The second platform sealing assembly may be disposed between the second platform and a third platform of the third rotor blade.

Abstract: A gas turbine engine includes a first spool, a second spool, a primary combustor, and a diffuser. The first spool includes a first compressor rotationally driven by a first turbine via a first shaft. The second spool includes a second compressor driven by a second turbine via a second shaft. The first compressor, the diffuser, and the primary combustor are arranged in series to provide a compressed airflow discharged from the first compressor to the primary combustor via the diffuser, which includes walls that diverge towards the primary combustor. The second compressor is fluidly coupled to the diffuser to receive at least a portion of the compressed airflow from the diffuser. The second turbine is fluidly coupled to the diffuser to discharge an expanded airflow to the diffuser.

Abstract: A rotor blade for a gas turbine engine including an inner ply layer group includes a flared region and an airfoil region, a neck region between the flared region and the airfoil region; and a platform shell that comprises a platform shell root region, a platform shell platform region, and a platform shell neck region between the platform shell root region and the platform shell platform region, the platform shell root region sheathes the flared region, and the platform shell neck region flares outwardly away from the neck region to intersect the platform shell platform region at a platform shell neck region perimeter around an airfoil opening perimeter.

Abstract: A furnace for removing a molybdenum-alloy refractory metal core through sublimation comprising a retort furnace having an interior; a sublimation fixture insertable within the interior of the retort furnace, the sublimation fixture configured to receive at least one turbine blade having the molybdenum-alloy refractory metal core; a flow passage thermally coupled to the retort furnace configured to heat a fluid flowing through the flow passage and deliver the fluid to the molybdenum-alloy refractory metal core causing sublimation of the molybdenum-alloy refractory metal core.

Abstract: A seal assembly includes a first feather seal with a first cooling hole extending through the first feather seal. The seal assembly also includes a second feather seal adjacent to the first feather seal. The second feather seal includes a second cooling hole extending through the second feather seal. The first cooling hole is positioned over at least a portion of the second cooling hole.