Abstract: A refrigeration system includes a compressor for compressing a refrigerant, a condenser for cooling the refrigerant, an evaporator for heating the refrigerant, and a lubrication system for providing a lubricant mist to a movable component of the compressor. The lubrication system includes an ejector arranged in fluid communication with the compressor and the evaporator, wherein the lubricant mist is carried by the refrigerant to the movable component.

Abstract: Disclosed is a direct-drive refrigerant screw compressor, having: a housing; a compression chamber in the housing; a pair of rotors, each rotor of the pair of rotors being rotationally disposed in the compression chamber and including an outer surface with a screw-geared profile; a fluid being disposed in the compression chamber, the fluid consisting of a working fluid for providing lubrication to each rotor; a first port extending through the housing and configured for directing the fluid toward the compression chamber; and when the compressor is activated, each rotor rotates and the fluid is distributed about each rotor to lubricate each rotor.

Abstract: Disclosed is a direct-drive refrigerant screw compressor, having: a housing; a compression chamber in the housing; a pair of rotors, each rotor of the pair of rotors being rotationally disposed in the compression chamber and including an outer surface with a screw-geared profile; a fluid being disposed in the compression chamber, the fluid consisting of a working fluid for providing lubrication to each rotor; a first port extending through the housing and configured for directing the fluid toward the compression chamber; and when the compressor is activated, each rotor rotates and the fluid is distributed about each rotor to lubricate each rotor.

Abstract: Aircraft electric motors are described. The aircraft electric motors include a cooling system comprising an annular heat exchanger, a motor housing arranged radially inward from the heat exchanger, the motor housing defining a rotor-stator cavity and a gear assembly cavity, a rotor sleeve arranged within the rotor-stator cavity, a gear assembly arranged within the gear assembly cavity, a first shaft operably coupled to the rotor sleeve and configured to be rotationally driven by the rotor sleeve to drive rotation of a portion of the gear assembly, and a second shaft operably coupled to the gear assembly and configured to be rotationally driven by the gear assembly.

Abstract: An airfoil for a gas turbine engine including an airfoil body extending between a leading edge and a trailing edge and between a pressure side and a suction side. The airfoil body includes a strut portion extending from the leading edge and a flap portion extending from the trailing edge. The flap portion is pivotable relative to the strut portion. A flexible skin surrounds both the strut portion and the flap portion on both the pressure side and the suction side.

Abstract: A gas turbine engine includes a fan section, a compressor section, and a turbine section. The fan section has a plurality of vane assemblies spaced circumferentially about an engine axis. The vane assemblies each include an airfoil extending between a leading edge and a trailing edge, a control rod extending through the airfoil, and a mechanism driven by the control rod to change the shape of the airfoil. A vane system for a gas turbine engine is also disclosed.

Abstract: This disclosure relates to a system and method for monitoring a sheave bearing condition, and in particular relates to passenger conveyer systems, such as elevator systems, employing the system and method. An example passenger conveyer system includes a suspension member, and a sheave configured to rotate on a bearing. The suspension member is wrapped around at least a portion of the sheave. Further, the system includes a sensor mounted adjacent an end of the suspension member, and a controller configured to determine a condition of the bearing based on an output of the sensor.

Abstract: Aircraft electric motors are described. The electric motors include a substantially annular shaped motor housing having an outer wall and an inner wall, wherein a rotor-stator cavity is defined between the outer wall and the inner wall and a gear assembly cavity is defined radially inward from the inner wall and a gear assembly arranged within the gear assembly cavity. The gear assembly includes a sun gear operably connected to a first shaft, at least one planetary gear arranged radially outward from the sun gear and rotationally engaged with the sun gear, and a ring gear arranged radially outward from the at least one planetary gear and rotationally engaged with the at least one planetary gear, wherein the ring gear is operably connected to a second shaft.

Abstract: A vibration mitigation coating for an integrally bladed rotor including a disk including an interior radius proximate an axis and an exterior radius distal from the axis, the disk including a substrate with an external surface, said external surface extends from the interior radius to the exterior radius; and a damping material disposed directly onto the external surface of the substrate.

Abstract: An illustrative example elevator assembly includes a header beam and a first elevator cab supported by the header beam. A plurality of vertically oriented rods extend beneath the first elevator cab. A horizontally oriented mid-beam is coupled to a first one of the rods near a first end of the mid-beam and coupled to a second one of the rods near a second end of the mid-beam. A second elevator cab is situated beneath the first elevator cab and beneath the mid-beam. At least one linear actuator is supported at least partially on the mid-beam. The linear actuator selectively causes vertical movement of the second elevator cab relative to the rods.

Abstract: A gas turbine engine includes a fan section, a compressor section, and a turbine section. The fan section has a plurality of vane assemblies spaced circumferentially about an engine axis. The vane assemblies each include an airfoil extending between a leading edge and a trailing edge, a control rod extending through the airfoil, and a mechanism driven by the control rod to change the shape of the airfoil. A vane system for a gas turbine engine is also disclosed.

Abstract: Aircraft electric motors are described. The aircraft electric motors include a cooling system comprising an annular heat exchanger, a motor housing arranged radially inward from the heat exchanger, the motor housing defining a rotor-stator cavity and a gear assembly cavity, a rotor sleeve arranged within the rotor-stator cavity, a gear assembly arranged within the gear assembly cavity, a first shaft operably coupled to the rotor sleeve and configured to be rotationally driven by the rotor sleeve to drive rotation of a portion of the gear assembly, and a second shaft operably coupled to the gear assembly and configured to be rotationally driven by the gear assembly.

Abstract: Aircraft electric motors are described. The electric motors include a substantially annular shaped motor housing having an outer wall and an inner wall, wherein a rotor-stator cavity is defined between the outer wall and the inner wall and a gear assembly cavity is defined radially inward from the inner wall and a gear assembly arranged within the gear assembly cavity. The gear assembly includes a sun gear operably connected to a first shaft, at least one planetary gear arranged radially outward from the sun gear and rotationally engaged with the sun gear, and a ring gear arranged radially outward from the at least one planetary gear and rotationally engaged with the at least one planetary gear, wherein the ring gear is operably connected to a second shaft.

Abstract: A method for creating a carbon nanotube heater assembly includes creating a carbon nanotube heater with varying resistances and attaching the carbon nanotube heater to both carrier and encapsulating materials. Creating the carbon nanotube heater with varying resistances is accomplished by applying a carbon nanotube mixture to a substrate, adjusting the thickness or width of the carbon nanotube mixture, and drying the nanotube mixture.

Abstract: A method for creating a carbon nanotube heater assembly includes creating a carbon nanotube heater with varying resistances and attaching the carbon nanotube heater to both carrier and encapsulating materials. Creating the carbon nanotube heater with varying resistances is accomplished by applying a carbon nanotube mixture to a substrate, adjusting the thickness or width of the carbon nanotube mixture, and drying the nanotube mixture.

Abstract: A method of determining wear of a seal element includes rotating a seal plate relative to the seal element and such that the seal plate and the seal element form a rotational sealing interface. The seal element includes an insert embedded in the seal element. A portion of the seal element is worn with a sealing face of the seal plate. The insert is contacted with the sealing face of the seal plate. A portion of the insert is worn to create a wear particle of the insert. The presence of the wear particle in a lubrication oil is sensed with an oil monitoring system.

Abstract: A compressor system includes a compressor including a compressor inlet, a compressor outlet, and a bearing assembly, the compressor configured to compress a heat transfer fluid. An additive dispenser is fluidly coupled to the compressor upstream of the bearing assembly. The additive dispenser is configured to controllably release a volume of an additive material into the heat transfer fluid, the additive material configured to lubricate the bearing assembly. A method of lubricating a bearing assembly of compressor includes locating a volume of additive material at an additive dispenser fluidly coupled to a compressor, dispensing a portion of the additive material into the flow of heat transfer fluid at a selected time, flowing the heat transfer fluid containing the additive material to a bearing assembly of the compressor, and lubricating the bearing assembly of the compressor with the additive material.

Abstract: Disclosed is a direct-drive refrigerant screw compressor, having: a housing; a compression chamber in the housing; a pair of rotors, each rotor of the pair of rotors being rotationally disposed in the compression chamber and including an outer surface with a screw-geared profile; a fluid being disposed in the compression chamber, the fluid consisting of a working fluid for providing lubrication to each rotor; a first port extending through the housing and configured for directing the fluid toward the compression chamber; and when the compressor is activated, each rotor rotates and the fluid is distributed about each rotor to lubricate each rotor.

Abstract: An illustrative example elevator assembly includes a header beam and a first elevator cab supported by the header beam. A plurality of vertically oriented rods extend beneath the first elevator cab. A horizontally oriented mid-beam is coupled to a first one of the rods near a first end of the mid-beam and coupled to a second one of the rods near a second end of the mid-beam. A second elevator cab is situated beneath the first elevator cab and beneath the mid-beam. At least one linear actuator is supported at least partially on the mid-beam. The linear actuator selectively causes vertical movement of the second elevator cab relative to the rods.

Abstract: An illustrative example elevator assembly includes a header beam and a first elevator cab supported by the header beam. A plurality of vertically oriented rods extend beneath the first elevator cab. A horizontally oriented mid-beam is coupled to a first one of the rods near a first end of the mid-beam and coupled to a second one of the rods near a second end of the mid-beam. A second elevator cab is situated beneath the first elevator cab and beneath the mid-beam. At least one linear actuator is supported at least partially on the mid-beam. The linear actuator selectively causes vertical movement of the second elevator cab relative to the rods.