Abstract: A stator vane for a gas turbine engine section includes a stator vane having an airfoil extending between a leading edge and a trailing edge. The airfoil has a suction side and a pressure side. There is at least one piezoelectric actuator for changing a shape of at least one of the leading edge and the trailing edge. A gas turbine engine is also disclosed.

Abstract: A method for fault diagnosis of a bearing includes detecting, using an oil debris monitor (ODM) sensor, ODM data corresponding to an amount of debris flowing downstream from the bearing. The method also includes detecting, using a vibration sensor, vibration data corresponding to vibration of the bearing during use. The method also includes determining, by a controller, a vibration stage flag corresponding to a severity of damage of the bearing based on the vibration data. The method also includes determining, by the controller, a severity level of the damage of the bearing based on a combination of the vibration stage flag and the ODM data. The method also includes outputting, by an output device, the severity level.

Abstract: A system is provided for testing a component. This system includes a support structure, an excitation system and a sensor system. The support structure is configured to support the component. The excitation system includes a plurality of excitation devices arranged in an array. The plurality of excitation devices at least include a first excitation device, a second excitation device and a third excitation device. The excitation system is configured to respectively control each of the plurality of excitation devices to excite a vibratory response in the component. The sensor system is configured to output data indicative of the vibratory response.

Abstract: A gas turbine engine includes a plurality of blades circumferentially spaced from each other. A plurality of rings are spaced radially outward from the plurality of blade. At least one actuator is in mechanical communication with the plurality of rings for moving the plurality of rings in an axial direction to create an axial gap adjacent at least one of the plurality of rings.

Abstract: Provided are embodiments of a system for performing health monitoring. The system includes one or more wake-up modules configured to detect a condition, and one or more sensors operably coupled to the one or more wake-up modules, wherein the one or more sensors are configured to operate in a sleep mode and an active mode. The system also includes a spacesuit comprising one or more sensors, and a controller operably coupled to the one or more sensors, wherein the controller is configured to process measurement data from the one or more sensors. Also provided are embodiments of a method for performing health monitoring.

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: 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: A bearing assembly monitoring system includes a bearing assembly supporting rotation of a rotating member. The bearing assembly includes a fixed portion and rotatable portion. A piezoelectric element is mounted to the fixed portion and generates an electric signal in response to a vibration of the fixed portion. A first transceiver is electrically coupled to the piezoelectric element to receive the electrical signal generated by the piezoelectric element and generate a signal indicative of the vibration of the fixed portion. A gas turbine engine bearing monitoring system and a method are also disclosed.

Abstract: A morphing aerodynamic control surface geometry comprising a control surface having an articulated portion comprising a flexible skin coupled at an exterior of the articulated portion, the flexible skin comprising opposed interlocking elements sandwiched within a flexible polymer coupled to the interlocking elements; wherein the flexible skin is configured compliant responsive to an articulation of the articulated portion.

Abstract: A bearing assembly monitoring system includes a bearing assembly supporting rotation of a rotating member. The bearing assembly includes a fixed portion and rotatable portion. A piezoelectric element is mounted to the fixed portion and generates an electric signal in response to a vibration of the fixed portion. A first transceiver is electrically coupled to the piezoelectric element to receive the electrical signal generated by the piezoelectric element and generate a signal indicative of the vibration of the fixed portion. A gas turbine engine bearing monitoring system and a method are 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: 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: An optical in-situ system for a gas turbine engine blade inspection comprises a camera configured to capture images of a forward surface of at least one gas turbine engine blade; and a processor coupled to the camera, the processor configured to determine damage to the at least one gas turbine engine blade based on image analytics.

Abstract: An illustrative example elevator system includes a frame, a first elevator cab, a second elevator cab, and a plurality of sheaves associated with the first and second elevator cabs, respectively. A suspension assembly suspends the first and second elevator cabs within the frame. The suspension assembly has two ends in a fixed position relative to the frame. The suspension assembly includes a positive drive load bearing member along a first portion of a length of the suspension assembly and at least one other second load bearing member. A machine includes a drive sprocket that moves the positive drive load bearing member to cause movement of the first and second elevator cabs relative to the frame.

Abstract: A stator vane for a gas turbine engine section includes a stator vane having an airfoil extending between a leading edge and a trailing edge. The airfoil has a suction side and a pressure side. There is at least one piezoelectric actuator for changing a shape of at least one of the leading edge and the trailing edge. A gas turbine engine is also disclosed.

Abstract: A compound harmonic actuator is provided and includes a motor, a flex spline disposed about the motor and a wave generator radially interposable between the motor and the flex spline. The wave generator being rotatably drivable by the motor and shaped to form the flex spline into an elliptical shape with an axis such that wave generator rotations drive rotations of the axis of the ellipse of the flex spline.

Abstract: A method of making a carbon nanotube heater includes impregnating a dry carbon nanotube fiber matrix with a conductive resin, the conductive resin is made of an organic resin and a conductive filler material. The carbon nanotube heater is lightweight, strong, and maintains appropriate electrical conductivity and resistance for use as a heater.

Abstract: A vapor compression system (20) has: a centrifugal compressor (22) having an inlet (40) and an outlet (42); and an electric motor (28) having a stator (30) and a rotor (32). A plurality of bearings (36) support the rotor. A refrigerant charge comprises a base refrigerant and one or more oils. The one or more oils are present at a total concentration of 80-5000 parts per million (ppm) by weight.

Abstract: A gas turbine engine includes a plurality of blades circumferentially spaced from each other. A plurality of rings are spaced radially outward from the plurality of blade. At least one actuator is in mechanical communication with the plurality of rings for moving the plurality of rings in an axial direction to create an axial gap adjacent at least one of the plurality of rings.