Abstract: Improved rotor/stator air gap control within the electric traction motor for an electric vehicle is provided by stator supports projecting from interior sidewalls of the motor housing and contacting portions of peripheral surfaces of the stator core. The stator supports are spaced apart from a pilot bore receiving an end of the stator. Surfaces of the pilot bore contacting the stator core and surfaces of the stator support contacting the stator core are spaced apart, with oil channels in the intervening region allow flow of combined coolant and lubricant over the stator core. The portions of the stator core contacted by the surfaces of the pilot bore are preferably located between an end of the stator core and a midpoint between the end and an opposite end.

Abstract: An apparatus includes a housing configured to receive at least a portion of an electric motor. The apparatus also includes a manifold disposed on an upper surface of the housing. The manifold includes a number of vertical jets configured to target one or more portions of the electric motor, the vertical jets includes multiple vias extending between (i) a cavity within the manifold and (ii) an interior portion of the housing. The cavity within the manifold is defined by (i) at least a portion of the upper surface of the housing, (ii) one or more side walls extending from the upper surface of the housing, and (iii) a cover lid coupled to the one or more side walls and configured to cover the cavity and the vias.

Abstract: An apparatus includes a housing configured to receive at least a portion of an electric motor. The apparatus also includes a manifold disposed on an upper surface of the housing. The manifold includes a number of vertical jets configured to target one or more portions of the electric motor, the vertical jets includes multiple vias extending between (i) a cavity within the manifold and (ii) an interior portion of the housing. The cavity within the manifold is defined by (i) at least a portion of the upper surface of the housing, (ii) one or more side walls extending from the upper surface of the housing, and (iii) a cover lid coupled to the one or more side walls and configured to cover the cavity and the vias.

Abstract: An apparatus includes a housing configured to receive at least a portion of an electric motor. The apparatus also includes a manifold disposed on an upper surface of the housing. The manifold includes a number of vertical jets configured to target one or more portions of the electric motor, the vertical jets includes multiple vias extending between (i) a cavity within the manifold and (ii) an interior portion of the housing. The cavity within the manifold is defined by (i) at least a portion of the upper surface of the housing, (ii) one or more side walls extending from the upper surface of the housing, and (iii) a cover lid coupled to the one or more side walls and configured to cover the cavity and the vias.

Abstract: In one aspect, an apparatus for storing energy comprises an enclosure including a coolant fluid inlet configured to couple to a coolant fluid system, a plurality of energy-storage cells housed in an arrangement within the enclosure, and a cell holder. The cell holder has retaining features configured to hold the plurality of cells in the arrangement, a first surface forming a cavity between the cell holder and an adjacent wall of the enclosure and a plurality of holes that pass from the cavity through the cell holder and to the region of the enclosure housing the plurality of energy-storage cells. The coolant fluid inlet is in fluid communication with the cavity. Each of the holes is positioned proximate to a cell. Coolant fluid passes through the coolant fluid inlet into the cavity and through the holes to the cells to reduce a temperature of each of the cells.

Abstract: Reversely identical transmissions for a tiltrotor aircraft include reconfigurable gearbox lubrication systems to accommodate operation in either direction of propeller rotation, using common parts. In a typical installation, at least two separate winged tiltrotor transmissions operate with opposing propeller rotations. Common parts of the two transmissions include cast housings, rotor shafts, pinion gears, lubrication sump tanks, lubrication pumps, and lubrication filter manifolds including filters having reversible orientations. Either transmission configuration can be utilized on either the left or right side of a tiltrotor aircraft by swapping the lubrication sump tank and lubrication filter manifold locations on the gearbox. In addition, a plug is used to manually reconfigure an opposite lubrication oil path to accommodate first and second rotational directions of the lubrication pump.

Abstract: In one aspect, an apparatus for storing energy comprises an enclosure including a coolant fluid inlet configured to couple to a coolant fluid system, a plurality of energy-storage cells housed in an arrangement within the enclosure, and a cell holder. The cell holder has retaining features configured to hold the plurality of cells in the arrangement, a first surface forming a cavity between the cell holder and an adjacent wall of the enclosure and a plurality of holes that pass from the cavity through the cell holder and to the region of the enclosure housing the plurality of energy-storage cells. The coolant fluid inlet is in fluid communication with the cavity. Each of the holes is positioned proximate to a cell. Coolant fluid passes through the coolant fluid inlet into the cavity and through the holes to the cells to reduce a temperature of each of the cells.

Abstract: A nozzle including a frame having a plurality of deflecting elements arranged in an array, the array extending about a longitudinal axis, and a skin positioned over the frame.

Abstract: Reversely identical transmissions for a tiltrotor aircraft may include reconfigurable gearbox lubrication systems to accommodate operation in either direction of propeller rotation, using common parts. In a typical installation, at least two separate winged tiltrotor transmissions may operate with opposing propeller rotations. Common parts of the two transmissions may include cast housings, rotor shafts, pinion gears, lubrication sump tanks, lubrication pumps, and lubrication filter manifolds including filters having reversible orientations. Either transmission configuration may be utilized on either the left or right side of a tiltrotor aircraft by swapping the lubrication sump tank and lubrication filter manifold locations on the gearbox. In addition, a plug may be used to manually reconfigure an opposite lubrication oil path to accommodate first and second rotational directions of the lubrication pump.

Abstract: A rotorcraft rotor comprises a blade having a pitch axis, a primary pitch horn for the blade, and a secondary horn opposite the primary pitch horn with respect to the pitch axis.

Abstract: A variable geometry inlet for a ducted fan is selectively transitionable between a first and second mode. The inlet includes a retractable ring that extends circumferentially about the inlet and is selectively movable between an axially extended position in the first mode and an axially retracted position in the second mode. A tube extends circumferentially proximate the retractable ring, and is pressurizable to a relatively deflated state in the first mode and to a relatively inflated state in the second mode. A stretchable skin extends circumferentially proximate the retractable ring, and is elastically deformable in at least a circumferential direction about a longitudinal axis of the fan. A leading edge of the inlet in the first mode is defined by the stretchable skin disposed against a forward edge of the retractable ring, and in the second mode by the stretchable skin disposed against at least a portion of the tube.

Abstract: A variable geometry inlet for a ducted fan is selectively transitionable between a first and second mode. The inlet includes a retractable ring that extends circumferentially about the inlet and is selectively movable between an axially extended position in the first mode and an axially retracted position in the second mode. A tube extends circumferentially proximate the retractable ring, and is pressurizable to a relatively deflated state in the first mode and to a relatively inflated state in the second mode. A stretchable skin extends circumferentially proximate the retractable ring, and is elastically deformable in at least a circumferential direction about a longitudinal axis of the fan. A leading edge of the inlet in the first mode is defined by the stretchable skin disposed against a forward edge of the retractable ring, and in the second mode by the stretchable skin disposed against at least a portion of the tube.

Abstract: A nozzle including a frame having a plurality of deflecting elements arranged in an array, the array extending about a longitudinal axis, and a skin positioned over the frame.

Abstract: A rotorcraft rotor comprises a blade having a pitch axis, a primary pitch horn for the blade, and a secondary horn opposite the primary pitch horn with respect to the pitch axis.