Abstract: The present invention provides a composition that includes a rhenium-based alloy and a solid film lubricant. The rhenium-based alloy comprises an alloying substance including at least one constituent having a stronger affinity to oxygen than does Re when exposed to an atmosphere at a temperature of at least about 285° C.

Abstract: An aircraft engine starter assembly provides for liquid cooling of the clutch assembly and overrunning engine by integrating a pitot pump in the system. The system includes a starter motor, a torque transfer connection, a clutch assembly and the pitot pump. The torque transfer connection is adapted to be coupled to the aircraft engine. The clutch assembly is coupled to one of the starter motor or the torque transfer connection. The pitot pump is coupled to one or both of the torque transfer or the clutch assembly via a first oil line and a second oil line. The pitot pump comprises a pitot tube in fluidic communication with an oil reservoir for the delivery of oil under pressure to lubricate one or both of the torque transfer or the clutch assembly.

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 air turbine starter (ATS) configured to couple to a gearbox, the ATS including an output shaft having an outer peripheral surface, a gearbox section, and an ATS section, the gearbox section configured to be disposed within, and coupled to, the gearbox and the ATS section configured to be disposed within the ATS, and a shield plate extending radially from the outer peripheral surface and coupled to the ATS section of the output shaft.

Abstract: An aircraft engine starter assembly has a starter motor, a notch containing plate rotationally coupled to the starter motor or the aircraft engine, a strut pocket containing plate rotationally coupled to the other of the starter motor or the aircraft engine, arranged facing the notch containing plate and spaced apart therefrom by an inter-plate space, wherein the strut pocket containing plate has a spring loaded strut mounted in at least one pocket thereof, aligned to engage a notch as the two plates rotate with respect to each other about a common centerline, so that the strut engages the notch to start the engine and releases from the notch when the engine is running. A lube oil pump is provided to force oil into the inter-plate space and bearings are provided coupled to the two plates to react the expansion forces created by the pressurized lube oil.

Abstract: An improved oil seal is provided for sealing passage of a rotatable shaft through an end wall of a bearing housing in a turbomachine or the like, wherein the shaft is rotatably supported within the bearing housing by oil-lubricated bearings. The improved oil seal comprises a dynamic oil-air separator and a slinger rotor mounted on the shaft for rotation therewith, the slinger rotor having an outwardly extending slinger ring with an outboard seal face with radially oriented slots and a circumferential groove or 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: An air turbine starter for use in aircraft or other gas turbine engine applications. In a particular embodiment, the air turbine starter has a titanium unitary inlet structure. The unitary inlet structure has a housing having a longitudinal centerline. The housing defines an air inlet, a mounting surface, and a flow path therebetween. Integrally formed inside the housing and transverse to the longitudinal centerline is a stator for directing the flow of air in to the turbine blades of the turbine starter. The stator has a central circular body with a plurality of angularly spaced circumferentially mounted stator fins. An improved unitary inlet structure and method for making such a unitary inlet and stator are also provided.

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: A gearless electric thrust reverser actuator includes an electric motor that is coupled to a jack screw without any intervening gears. The actuator may additionally include all of the actuation and sensing components in a single actuation package. Thus, the actuator is relatively lightweight and compact.

Abstract: An improved oil seal is provided for sealing passage of a rotatable shaft through an end wall of a bearing housing in a turbomachine or the like, wherein the shaft is rotatably supported within the bearing housing by oil-lubricated bearings. The improved oil seal comprises a dynamic oil-air separator and a slinger rotor mounted on the shaft for rotation therewith, the slinger rotor having an outwardly extending slinger ring with an outboard seal face with radially oriented slots and a circumferential groove or grooves.

Abstract: An improved oil seal is provided for sealing passage of a rotatable shaft through an end wall of a bearing housing in a turbomachine or the like, wherein the shaft is rotatably supported within the bearing housing by oil-lubricated bearings. The improved oil seal comprises a dynamic oil-air separator and a slinger rotor mounted on the shaft for rotation therewith, the slinger rotor having an outwardly extending slinger ring with an outboard seal face with radially oriented slots and a circumferential groove or grooves.

Abstract: An air turbine starter with an improved seal assembly is provided. A fluid conduit or channel allows higher pressure fluid into one side of a bearing seal. For example, the seal assembly may include a face seal, and a second seal forming a chamber therebetween and a flow passage opens into the chamber for exposing the chamber to the higher pressure.

Abstract: A gearless electric thrust reverser actuator includes an electric motor that is coupled to a jack screw without any intervening gears. The actuator may additionally include all of the actuation and sensing components in a single actuation package. Thus, the actuator is relatively lightweight and compact.

Abstract: An improved oil seal is provided for sealing passage of a rotatable shaft through an end wall of a bearing housing in a turbomachine or the like, wherein the shaft is rotatably supported within the bearing housing by oil-lubricated bearings. The improved oil seal comprises a dynamic oil-air separator and a slinger rotor mounted on the shaft for rotation therewith, the slinger rotor having an outwardly extending slinger ring with an outboard seal face with radially oriented slots and a circumferential groove or grooves.

Abstract: An air turbine starter with an improved seal assembly is provided. A fluid conduit or channel allows higher pressure fluid into one side of a bearing seal. For example, the seal assembly may include a face seal, and a second seal forming a chamber therebetween and a flow passage opens into the chamber for exposing the chamber to the higher pressure.

Abstract: The linkage system for the variable vane stators includes a pumphandle driven by the linear actuator and a cooperating pumphandle slider bracket where the slider bracket includes a machined hard coated stop for limiting travel of the pumphandle when the vanes are at the full opened position. The pumphandle through the drive link circumferentially positions a synchronizing ring that is connected through a plurality of drive links to each of the vanes circumferentially spaced in the stator for changing the angle of each of the vanes as scheduled by a control and actuator for optimizing the performance of the compressor and gas turbine engine. The steps for assembling the linkage system and actuator for synchronizing the positions of the stops on the actuator and slider bracket relative to a given position of the stator vanes defines a method for providing a rigless variable vane system.

Abstract: Variable compressor vanes are locked into a selected position after testing. The usual sync ring and vane arms are removed. A vane lock joins adjacent vanes locking them into the selected position.