Abstract: An aircraft includes an aircraft heat source; a propulsion system including an electric propulsion engine, the electric propulsion engine including an electric motor and a fan rotatable by the electric motor, the electric propulsion engine further defining a fan air flowpath; a thermal management system including a heat source exchanger in thermal communication with the aircraft heat source, a heat sink exchanger in thermal communication with the fan air flowpath of the electric propulsion engine, and a thermal distribution bus extending from the heat source exchanger to the heat sink exchanger; and a control system operably connected to the thermal management system for selectively thermally coupling the heat sink exchanger with the heat source exchanger.

Abstract: A system for heat exchange and leak detection is generally provided, the system including a heat exchanger including a first wall defining a first passage containing a first fluid. A leak detection enclosure containing a leak detection medium is defined between the first wall and a second wall surrounding the first wall.

Abstract: A system for heat exchange and leak detection is generally provided, the system including a heat exchanger including a first wall defining a first passage containing a first fluid. A leak detection enclosure containing a leak detection medium is defined between the first wall and a second wall surrounding the first wall.

Abstract: A scheme to initiate fast charging of a battery based on inference, situation, and/or need. The scheme uses a situational fast charging algorithm that detects user's situation and judges if fast battery charging is needed and enables fast charging. Once the need for fast charging need is detected, there are at least two options to follow. In the first option, when a charger cannot provide enough power to support both system and battery fast charging, the system turns down system power (e.g., reduces display brightness) and starts fast charging with available charger power to a sufficient charge level. In the second option, when a charger can provide enough power to support both system and battery fast charging, the system starts fast charging to a sufficient charge level.

Abstract: An electric machine includes a stator assembly including a first stator segment and a second stator segment, the first and second stator segments each including a plurality of laminations extending generally along a circumferential direction, each pair of adjacent laminations of the first and second stator segments defining a gap therebetween. The first and second stator segments are assembled together such that the laminations of the first stator segment are arranged at least partially in the gaps between the laminations of the second stator segment.

Abstract: In one aspect, a wheel hub apparatus including a wheel hub that is rotatable about a central axis and has a unitary, one-piece construction. The wheel hub apparatus further includes a circular brake element having a unitary, one-piece construction and extending about the wheel hub. The wheel hub and the circular brake element include engaged portions securing the wheel hub and the circular brake element together. The engaged portions of the wheel hub and the circular brake element fix the circular brake element against axial movement along the wheel hub. In this manner, the engaged portions of the wheel hub and the circular brake element provide a mechanical joint that connects the wheel hub and the circular brake element using the material of the wheel hub and the circular brake element.

Abstract: An electric machine is provided which includes a rotor disk extending along a radial direction and a having a rotor magnet embedded within the rotor disk. The electric machine further includes a stator assembly in axial or radial magnetic flux communication with the rotor magnets to generate a torque.

Abstract: An electric machine is provided which includes a rotor disk extending along a radial direction and having a rotor flange attached to or formed integrally with the rotor disk and extending substantially along the axial direction. A plurality of rotor magnets are mounted on the rotor disk and supported by the rotor flange such that the rotor flange absorbs centrifugal loads exerted on the magnets and enables high speeds of operation.

Abstract: An axial flux electric machine includes a rotor assembly rotatable about an axis, and a stator assembly. The stator assembly includes a stator face defining an air gap along an axial direction with the rotor assembly, the stator assembly further including a yoke, the yoke including a back surface, the back surface defining an inwardly sloped angle with the radial direction greater than two degrees.

Abstract: A tubular array heat exchanger and a method of manufacturing the same are provided. The heat exchanger includes a plurality of tubes extending between a tube inlet and a tube outlet. An inlet manifold includes an inner wall and an outer wall defining an inlet plenum and one or more baffles extending between the inner wall and the outer wall to divide the inlet plenum into a plurality of fluid passageways, each of the plurality of fluid passageways extending between the inlet plenum and a respective one of the tube inlets. The tubes, the inlet manifold, and an outlet manifold identical to the inlet manifold are manufactured as a single monolithic component.

Abstract: A heat exchanger and a method for additively manufacturing the heat exchanger are provided. The heat exchanger includes a housing defining a flow passageway having a plurality of heat exchange banks stacked therein. Each heat exchange bank includes a plurality of heat exchange tubes that form a lattice structure that extends from a first end proximate a central manifold outward along the radial direction toward a second end proximate an annular outer manifold. The central manifolds and the annular outer manifolds fluidly couple the heat exchange tubes of adjacent heat exchange banks in an alternating manner to form a serpentine flow path for a flow of heat exchange fluid.

Abstract: An aircraft includes an aircraft heat source; a propulsion system including an electric propulsion engine, the electric propulsion engine including an electric motor and a fan rotatable by the electric motor, the electric propulsion engine further defining a fan air flowpath; a thermal management system including a heat source exchanger in thermal communication with the aircraft heat source, a heat sink exchanger in thermal communication with the fan air flowpath of the electric propulsion engine, and a thermal distribution bus extending from the heat source exchanger to the heat sink exchanger; and a control system operably connected to the thermal management system for selectively thermally coupling the heat sink exchanger with the heat source exchanger.

Abstract: A system for heat exchange and leak detection is generally provided, the system including a heat exchanger including a first wall defining a first passage containing a first fluid. A leak detection enclosure containing a leak detection medium is defined between the first wall and a second wall surrounding the first wall.

Abstract: An annular duct including a modular annular heat exchanger for a gas turbine engine is provided, where the modular annular heat exchanger includes a plurality of radial modules in circumferentially adjacent arrangement. Each radial module includes a cooled fluid inlet plenum segment, a plurality of blades, and a cooled fluid outlet plenum segment. The plurality of blades is configured in circumferentially adjacent arrangement and defines an angular space that is conformal between each circumferentially adjacent blade. The cooled fluid inlet plenum segment, the plurality of blades, and the cooled fluid outlet plenum segment are in serial axial flow arrangement and define an internal cooled fluid flowpath and an external cooling fluid flowpath parallel to the internal cooled fluid flowpath. Each radial module further includes an inner annular ring segment and an outer annular ring segment. The inner annular ring segment and the outer annular ring segment define a plurality of blade retainers.

Abstract: An electric machine includes a stator assembly including a first stator segment and a second stator segment, the first and second stator segments each including a plurality of laminations extending generally along a circumferential direction, each pair of adjacent laminations of the first and second stator segments defining a gap therebetween. The first and second stator segments are assembled together such that the laminations of the first stator segment are arranged at least partially in the gaps between the laminations of the second stator segment.

Abstract: An axial flux electric machine includes a rotor assembly rotatable about an axis, and a stator assembly. The stator assembly includes a stator face defining an air gap along an axial direction with the rotor assembly, the stator assembly further including a yoke, the yoke including a back surface, the back surface defining an inwardly sloped angle with the radial direction greater than two degrees.

Abstract: A heat exchanger and a method for additively manufacturing the heat exchanger are provided. The heat exchanger includes a housing defining a flow passageway having a plurality of heat exchange banks stacked therein. Each heat exchange bank includes a plurality of heat exchange tubes that form a lattice structure that extends from a first end proximate a central manifold outward along the radial direction toward a second end proximate an annular outer manifold. The central manifolds and the annular outer manifolds fluidly couple the heat exchange tubes of adjacent heat exchange banks in an alternating manner to form a serpentine flow path for a flow of heat exchange fluid.

Abstract: An aeronautical propulsion system includes a fan having a plurality of fan blades rotatable about a central axis and defining a fan pressure ratio, FPR. The propulsion system also includes an electric motor mechanically coupled to the fan for driving the fan, the electric motor including a number of poles, npoles, and defining a maximum power, P. The relationship between the fan pressure ratio, FPR, of the fan, the number of poles, npoles, of the electric motor, and the maximum power, P, of the electric motor is defined by an equation: n pole p = C 1 · e - 9.062 · FPR + C 2 · e - 1.2604 · FPR ; wherein C1 is a constant having a value between 22,000 and 52,000, wherein C2 is a constant having a value between 4.0 and 9.8, and wherein e is Euler's number.

Abstract: An aeronautical propulsion system includes a fan having a plurality of fan blades rotatable about a central axis and defining a fan pressure ratio, FPR. The propulsion system also includes an electric motor mechanically coupled to the fan for driving the fan, the electric motor including a number of poles, npoles, and defining a maximum power, P. The relationship between the fan pressure ratio, FPR, of the fan, the number of poles, npoles, of the electric motor, and the maximum power, P, of the electric motor is defined by an equation: n pole P = C 1 · e - 9.062 · FPR + C 2 · e - 1.2604 · FPR ; wherein C1 is a constant having a value between 22,000 and 52,000, wherein C2 is a constant having a value between 4.0 and 9.8, and wherein e is Euler's number.

Abstract: A tubular array heat exchanger and a method of manufacturing the same are provided. The heat exchanger includes a plurality of helical tubes defining a primary diameter around the centerline to define interstitial voids between the plurality of tubes. The plurality of tubes defines an increased surface area compared to a single heat transfer tube having the same primary diameter, thereby resulting in improved heat transfer efficiency or a smaller footprint. In addition, the helically formed tubes and optional stiffening structures improve the structural resiliency of the heat exchanger to better absorb thermal expansion and contraction with improved modal response.