Abstract: An inlet scroll for a combustor includes an inlet, an annular outlet, a volute duct, and a transition. The volute extends from the inlet to circumscribe an axis to form a monotonically decreasing cross-sectional flow area from the inlet. The transition fluidly connects a radially inner boundary of the volute duct to the annular outlet. The transition includes a radial portion at the volute duct and an axial portion at the annular outlet.

Abstract: An exhaust assembly for a turboprop engine, the assembly having: a primary exhaust nozzle disposed at an aft end of an engine core of the turboprop engine; a secondary exhaust nozzle extending aft from the primary exhaust nozzle to an aft end of the secondary exhaust nozzle, a movable panel disposed in the aft end of the secondary exhaust nozzle and movable to decrease an area of the secondary exhaust nozzle.

Abstract: A hybrid-electric propulsion system for an aircraft is provided that includes a propulsion unit, a propulsion unit gear box, a gas turbine engine, and an electric motor drive system. The gas turbine engine has compressor, combustion, and turbine sections, and is configured to provide motive force to the propulsion unit gear box. The electric motor drive system is disposed to provide motive force to the propulsion gear box or to the gas turbine engine. The electric motor drive system (EMDS) is adapted to interchangeably use a plurality of EMDS packages, each EMDS package including an electric motor and a battery. The electric motor drive system has a set of performance parameters that vary depending upon the particular EMDS package that is used with the electric motor drive system. The electric motor drive system includes interfaces that allow each EMDS package to be interchangeably used.

Abstract: An inlet plenum for a gas turbine engine combustor includes first and second inlet ducts fluidly connected to a distribution duct. The distribution duct extends circumferentially about an axis to fluidly connect the inlet ducts to an outlet at a radially inner boundary. The first and second inlet ducts fluidly communicate with a compressor of the gas turbine engine. A radially inner boundary of the distribution duct fluidly communicates with a combustor plenum of the gas turbine engine.

Abstract: A propulsion system is provided for an aircraft. This propulsion system includes a geartrain, a propulsor rotor, a turbine engine core, an electric machine and an accessory gearbox system. The propulsor rotor is disposed to a first side of the geartrain. The turbine engine core is disposed to a second side of the geartrain. The turbine engine core is operatively coupled to the propulsor rotor through the geartrain. The electric machine is disposed to the second side of the geartrain. The electric machine is operatively coupled to the propulsor rotor and/or the turbine engine core through the geartrain. The accessory gearbox system is operatively coupled to the turbine engine core. The accessory gearbox system is circumferentially offset from the electric machine about a centerline axis of the turbine engine core. The accessory gearbox system axially overlaps the electric machine along the centerline axis of the turbine engine core.

Abstract: An aircraft powerplant includes a core of a gas turbine engine and an exhaust section. The core includes a core flowpath, a compressor section, a combustor section and a turbine section. The core flowpath extends longitudinally through the compressor section, the combustor section and the turbine section. The exhaust section includes an exhaust flowpath and a flow diverter. The flow diverter includes a diverter panel configured to pivot between a first position and a second position. The flow diverter is configured to fluidly couple the diffuser section to the first nozzle section and fluidly decouple the diffuser section from the second nozzle section when the diverter panel is in the first position. The flow diverter is configured to fluidly couple the diffuser section to the second nozzle section and fluidly decouple the diffuser section from the first nozzle section when the diverter panel is in the second position.

Abstract: An exhaust assembly for a turboprop engine, the assembly having: a primary exhaust nozzle disposed at an aft end of an engine core of the turboprop engine; a secondary exhaust nozzle extending aft from the primary exhaust nozzle to an aft end of the secondary exhaust nozzle, a movable panel disposed in the aft end of the secondary exhaust nozzle and movable to decrease an area of the secondary exhaust nozzle.

Abstract: A propulsion system is provided for an aircraft. This propulsion system includes a geartrain, a propulsor rotor, a turbine engine core, an electric machine and an accessory gearbox system. The propulsor rotor is disposed to a first side of the geartrain. The turbine engine core is disposed to a second side of the geartrain. The turbine engine core is operatively coupled to the propulsor rotor through the geartrain. The electric machine is disposed to the second side of the geartrain. The electric machine is operatively coupled to the propulsor rotor and/or the turbine engine core through the geartrain. The accessory gearbox system is operatively coupled to the turbine engine core. The accessory gearbox system is circumferentially offset from the electric machine about a centerline axis of the turbine engine core. The accessory gearbox system axially overlaps the electric machine along the centerline axis of the turbine engine core.

Abstract: An aircraft propulsion system includes a propulsor, a gas turbine engine, and an electrical assembly. The gas turbine engine includes a bladed turbine rotor connected to the propulsor. The electrical assembly includes an AC electric motor, a motor control unit, and an electrical distribution system. The AC electric motor is coupled to the propulsor. The motor control unit is electrically connected to the AC electric motor and the electrical distribution system. The motor control unit is selectively operable in a normal mode and a hotel mode. The motor control unit is configured to, in the normal mode, convert electrical power from the electrical distribution system to output AC electrical power and supply the output AC electrical power to the electric motor and, in the hotel mode, apply a braking force to the rotational assembly by converting the electrical power from the electrical distribution system to output DC electrical power and supplying the output DC electrical power to the AC electric motor.

Abstract: An assembly for an aircraft propulsion system includes an engine, an aircraft aerostructure, and a heat exchanger. The engine includes a coolant system. The aircraft aerostructure forms a fuel tank for the engine. The aircraft aerostructure includes an aerostructure skin including an interior skin side and an exterior skin side. The interior skin side forms a bottom side of the fuel tank. The exterior skin side forms an aerodynamic surface of the aircraft aerostructure. The heat exchanger is disposed at the aerostructure skin. The heat exchanger includes a heat exchanger body forming a coolant passage. The coolant passage extends through the heat exchanger body between and to an inlet and an outlet. The inlet and the outlet are connected in fluid communication with the coolant system.

Abstract: An assembly is provided for an aircraft propulsion system. This assembly includes an electric machine, an exhaust duct and a mounting structure. The electric machine extends axially along an axis. The exhaust duct includes an annular first section and a non-annular second section fluidly coupled with and downstream of the annular first section. The annular first section extends circumferentially around the axis. The non-annular second section axially overlaps the electric machine and extends partially circumferentially about the electric machine. The mounting structure connects the electric machine to the exhaust duct. The mounting structure includes a duct mount, a machine mount and a framework. The duct mount is connected to the annular first section. The machine mount is connected to the electric machine. The framework extends axially between and is connected to the duct mount and the machine mount. The framework includes a plurality of struts arranged in a truss.

Abstract: A hybrid aircraft propulsion system includes a first motor operatively connected to a propulsor via a first motor driveshaft and is mounted to an engine static structure through engine mounts operable to adjust a position of the first motor and the first motor driveshaft. A second motor is an electric motor having a second motor driveshaft which is coaxial to the first motor driveshaft. The second motor is operatively connected to the propulsor via the second motor driveshaft to selectively drive the propulsor. A height compensation structure is operatively connected to the second motor and structured to adjust axial alignment of the second motor driveshaft relative to the first motor driveshaft to make the first motor driveshaft more coaxial to the second motor driveshaft.

Abstract: Systems and methods for employing virtual environmental augmentation in clinical care environments to enhance a clinician's in-the-moment knowledge, leverage past experiences of the clinician and others, and improve the quality of patient care are provided. Such virtual environmental augmentation may align with prior-established, evidence-based clinical processes and enhance the clinician's in-the-moment knowledge by extracting relevant data from one or more clinical sources and presenting a virtual representation of at least a portion of the extracted data (or a summary, exemplification, or interpretation thereof) in the clinician's field-of-view while the clinician is present in a clinical care environment and is utilizing an environmental augmentation device. Such environmental augmentation additionally may facilitate real-time documentation enabling more complete clinical records and ultimately improving the quality of patient care.

Abstract: A hybrid aircraft power plant includes an air mover for propelling an aircraft, a gas turbine engine operable to drive the air mover, a bifurcated exhaust duct conveying combustion gas from the gas turbine engine, and an electric motor mounted to the exhaust duct and operable to drive the air mover. The turbine engine includes a turbine extracting energy from an annular stream of the combustion gas and being rotatable about a rotation axis. The exhaust duct includes a first branch conveying a first portion of the combustion gas toward a first direction away from a rotation axis of the turbine, and a second branch conveying a second portion of the combustion gas toward a second direction away from the rotation axis.

Abstract: Deployable structures, methods and apparatus for deployment of deployable structures, and associated manufacturing methods. Such deployable structures suitably comprise components for space structures, such supports for solar arrays, antennas or other similar systems. The deployable structure comprises a lattice element arrangeable in a stowed configuration and a deployed configuration. The lattice element comprises a pre-stressed strip arranged in a clockwise helix, a pre-stressed strip arranged in an anticlockwise helix, and a plurality of fasteners for rotatably coupling the strips to one another at a plurality of positions distributed along the length of the strips. The fasteners are provided at unequal spacings along the length of the strips such that on deployment the lattice element bends to a curved deployed configuration.

Abstract: A spreading apparatus for use with fibre-reinforced composite tapes, and related methods are disclosed. The spreading apparatus comprises an input side to receive an incoming tape to be spread, and an output side from which tape is delivered after spreading. The apparatus further comprises a tape heater (150, 250, 650) to in use apply heat to a tape; and a tape spreader (100, 1, 200, 600) to in use to apply contact pressure to the heated tape to thereby spread the tape.

Abstract: An aircraft system is provided that includes an open propulsor rotor, a gas turbine engine, an electric machine and a drivetrain. The gas turbine engine includes a first rotating assembly, a compressor section, a combustor section, a turbine section and a flowpath extending through the compressor section, the combustor section and the turbine section. The first rotating assembly is coupled to and is configured to drive rotation of the open propulsor rotor. The first rotating assembly includes a first turbine rotor in the turbine section. The electric machine is outside of the gas turbine engine. The electric machine includes an electric machine rotor. The drivetrain couples the electric machine rotor to the first rotating assembly.

Abstract: An assembly is provided for an aircraft propulsion system. This assembly includes a housing, a rotor and a system. The rotor is next to the housing. The system includes a mechanical load, a belt drive, a cradle, a slide and an adjustment link. The mechanical load is operatively coupled to the rotor through the belt drive. The mechanical load is fixed to the cradle. The cradle includes a track and extends laterally between a first side and a second side. The cradle is coupled to the housing through the adjustment link at the first side. The cradle is pivotally coupled to the housing at the second side. The slide is connected to the housing. The slide is mated with and configured to move along the track. The adjustment link is configured to change a distance between the housing and the cradle to adjust a tension of the belt drive.

Abstract: An aircraft system is provided that includes a propulsor rotor, a geartrain, a thermal engine, a drivetrain and an electric machine. The geartrain includes a power output, a first power input and a second power input. The power output is coupled to the propulsor rotor. The thermal engine is configured to drive rotation of the propulsor rotor through the geartrain. The thermal engine is coupled to the first power input. The drivetrain includes a first driveshaft and a second driveshaft. The first driveshaft is coupled to and between the second power input and the second driveshaft. The second driveshaft is angularly offset from the first driveshaft. The electric machine is configured to drive rotation of the propulsor rotor through the drivetrain and the geartrain. The second driveshaft is coupled to and between the first driveshaft and the electric machine.

Abstract: The present disclosure relates to deployable structures, to methods and apparatus for deployment of deployable structures, and to associated manufacturing methods. Such deployable structures suitably comprise components for space structures, such supports for solar arrays, antennas or other similar systems. The deployable structure (500) comprises a first lattice (514) arrangeable in a stowed configuration and a deployed configuration. The deployable structure also comprises a second lattice (516) arrangeable in a stowed configuration and a deployed configuration, wherein with the lattices arranged in the stowed configuration the second lattice (516) nests in the first lattice (514).