Abstract: An aircraft brake system electromechanical actuator is provided. The actuator is configured with features that allow the electric motor to be a line replaceable unit. One such feature is a foreign-object-damage shield that inhibits dust, debris, and/or other particulate contaminants from entering the electromechanical actuator during electric motor removal and replacement.

Abstract: A linear actuator includes a thrust bearing that is integral to the actuation member. The actuator includes a translation member and an actuation member. The actuation member is responsive to a drive force to rotate. The translation member is configured to translate in response to actuation member. The thrust bearing is coupled to the actuation member and includes an inner race, an outer race, and a plurality of balls. The thrust bearing is configured as a zero lead ballscrew, with the inner race integrally formed on the actuation member, and the plurality of balls disposed between the inner and outer races.

Abstract: Electromechanical actuators (EMAs) are provided that include an output disposed at a location that is axially central between two EM devices. The EMAs include either one or two motors and an output mechanism. The motors are adapted to be energized and are operable, upon being energized, to either generate torques about a first axis or drive forces along a first axis.

Abstract: A modular electromechanical actuation system assembly is provided that includes an electronic control unit housing having a plurality of motor receptacles and a plurality of battery receptacles formed in an outer surface thereof. Each of the motor receptacles has an associated motor electrical interface, and each of the battery receptacles has an associated battery electrical interface. An electronic control unit is disposed within the electronic control unit housing and is electrically coupled to each of the motor electrical interfaces and each of the battery electrical interfaces. A plurality of motors are supported, one each, within one of the motor receptacles, and a plurality of batteries are supported, one each, within one of the battery receptacles.

Abstract: A relatively small, lightweight actuator includes a plurality of motors, an actuation element, a translation member, and a plurality of position sensors. The motors each supply a drive force to the actuation member, causing it to rotate. The translation member is configured, upon rotation of the actuator, to translate to a position. The position sensors sense the translational position of the translation member and the rotational position of each motor. The actuator is relatively small, lightweight, and can withstand the relatively severe environmental conditions and relatively significant levels of vibration and shock associated with many aerospace applications.

Abstract: A shroud is provided for separating an air turbine starter housing from a turbine wheel. The shroud comprises a ring and a bumper. The ring is configured to be disposed between the turbine wheel and the housing and has an outer peripheral surface and an inner peripheral surface that defines a flow channel. The bumper is coupled to and extends radially inwardly from the ring inner peripheral surface and defines a bumper section of the ring flow channel. At least a portion of the bumper section has a cross-sectional flow area that is less than another cross sectional flow area of the ring flow channel.

Abstract: A relatively small, lightweight valve actuator assembly that can withstand relatively high levels of vibration and shock includes a motor, a position sensor, and a drive belt mounted on an actuator housing assembly. The position sensor is preferably disposed within a sensor housing that is mounted on a side of the actuator housing assembly. As a result, the overall center-of-gravity (CG) and weight of the actuator assembly is significantly reduced, as is the overall size envelope.

Abstract: An aircraft brake actuation system includes an actuator for selectively moving to a position that corresponds to a commanded brake force. A cap assembly is coupled to the end of the actuator and is configured to engage an aircraft brake element and supply the commanded brake force to one or more aircraft wheels. The cap assembly is constructed of a low thermal conductivity material and has thermal resistance grooves formed therein. The cap assembly is also configured to compensate for certain undesired tangential movements that may occur during an aircraft brake cycle.

Abstract: A lubrication system for supplying lubricants between two environments is provided. The first environment is disposed within a first housing and the second environment is disposed within a second housing having a supply opening and an exhaust opening. The system includes a lubricant supply tube disposed within the supply opening and configured to supply lubricant from the first environment to the second environment. The system also includes a receptacle disposed within the second housing and configured to receive lubricant supplied from the supply tube and to hold a predetermined volume of the lubricant. A check valve is disposed within the second housing and is in fluid communication with the exhaust opening. The check valve is configured to receive overflow lubricant from the receptacle, if the lubricant exceeds the predetermined volume and to provide a seal between the first and second environments in response to a pressure differential therebetween.

Abstract: An aircraft brake actuation system includes an actuator for selectively supplying a commanded brake force to one or more aircraft wheels. The actuator includes a ballscrew, a ballnut, and a plurality of balls. The ballscrew has a plurality of ball grooves formed on its inner surface, and is coupled to receive a rotational drive force. The ballnut is mounted against rotation, is disposed at least partially within the ballscrew, and includes a plurality of ball grooves formed on its outer surface. The plurality of balls are disposed within the ballnut ball grooves and at least selected ones of the ballscrew ball grooves.

Abstract: A passive ATS lubrication system is provided that includes a starter housing, a receptacle and two valves. The starter housing is adapted to couple to a gearbox assembly and includes a supply opening and an exhaust opening that are each configured to provide fluid communication between the gearbox assembly and the starter housing. The receptacle is coupled to the starter housing proximate the supply opening to thereby define a reservoir. The first valve is disposed within the reservoir and configured to open or close the supply opening in response to a pressure differential between the starter housing and the gearbox assembly. The second valve is coupled to the starter housing proximate to the exhaust opening and configured to open or close the exhaust opening in response to the pressure differential between the starter housing and the gearbox assembly.

Abstract: A fluid-cooled seal rotor is described for a seal assembly that includes a seal case, a seal stator, and wherein the rotor has a sealing face on a first side and a heat-transfer structure on a second side. The heat-transfer structure may be a roughened surface. The heat-transfer structure may have protrusions which may be fins, including fins with roughened surfaces. The heat-transfer structure may have additional heat-transfer structures thereon to create complex, including fractal, structures. The fins may be shaped as impellers to move oil over the heat-transfer structure. Channels between fins may have a width greater than twice the boundary layer thickness for the fluid engaged by the fins. The fluid-cooled rotor, the seal assembly having the fluid-cooled rotor, an air turbine starter having the seal assembly, air turbine starters and other machines with rotating shafts using the seal are within the scope of the invention.

Abstract: An improved air turbine starter that includes fluid flow control devices. The devices may be check valves, for example normally open check valves. The check valves may be located in fluid flow paths between the starter and the gearbox to which it is mounted. The starter may also include a ring seal about the output shaft to restrict fluid flow over the shaft.

Abstract: One or more stator seal assemblies are mounted in the housing of a rotating machine such as, for example, an air turbine starter for a gas turbine engine, and surround a rotating shaft. The seal assemblies each include a seal case and a seal. The seal has a face that engages an axial face of a face seal rotor to form a seal. One or more anti-rotation tabs in the seal case engage anti-rotation notches formed in the peripheral surface of the seal. The anti-rotation notches each include substantially arcuate sections formed in notch end surfaces. The arcuate sections increase the amount of wear in the notches that can be tolerated before a potential seal lock-up, thus increasing seal assembly lifetime.

Abstract: One or more stator seal assemblies are mounted in the housing of a rotating machine such as, for example, an air turbine starter for a gas turbine engine, and surround a rotating shaft. The seal assemblies each include a seal case and a seal. The seal has a face that engages an axial face of a face seal rotor to form a seal. One or more anti-rotation tabs in the seal case engage anti-rotation notches formed in the peripheral surface of the seal. The anti-rotation notches each include substantially arcuate sections formed in notch end surfaces. The arcuate sections increase the amount of wear in the notches that can be tolerated before a potential seal lock-up, thus increasing seal assembly lifetime.

Abstract: An improved air turbine starter that includes fluid flow control devices. The devices may be check valves, for example normally open check valves. The check valves may be located in fluid flow paths between the starter and the gearbox to which it is mounted. The starter may also include a ring seal about the output shaft to restrict fluid flow over the shaft.

Abstract: An air turbine starter with an improved seal assembly disposed between the turbine and the housing is provided. The seal assembly comprises a face seal, a non-contacting seal axially spaced therefrom to define an air filled annular chamber therebetween and a flow passage having an exit fluidly communicating with said chamber and an inlet fluidly communicating with a source of air.