Abstract: The present invention includes a fastener comprising: a fastener body having a longitudinal axis and a first external male threaded portion, and two or more through-holes perpendicular to the longitudinal axis of the fastener body in the threaded portion.

Abstract: The present invention includes a bypass apparatus for lubricant in an unregulated pressurized gearbox including: a block including a lubricant inlet in fluid communication with a pressure relief valve, wherein the pressure relief valve diverts lubricant into the gearbox or into an oil filter, wherein lubricant is returned to the gearbox when the lubricant is cold and/or pressure at the pressure relief valve is high to reduce damage to the gearbox caused by high pressure during a cold start, and when the lubricant temperature increases and the pressure is reduced the pressure relief valve closes and lubricant enters the oil filter.

Abstract: A fastener includes: a shaft having longitudinal axis and a first and second threaded portions, the first and second threaded portions separated by a central portion having a reduced diameter between the first and second threaded portions, and at least one of the first or second threaded portions is chamfered to reduce friction on leading threads.

Abstract: A gearbox filler assembly includes a cylindrical insert attached to an interior of a port disposed within a housing of the gearbox. The cylindrical insert has a first end disposed within the port, a second end extending outward from the port and is configured to receive a detachable filler cap, a retaining lip around at least a portion of a first interior circumference proximate to the first end, and a retaining slot around at least a second interior circumference between the retaining lip and the second end. A retaining ring is detachably coupled within the retaining slot. A cylindrical baffle is detachably retained between the retaining ring and the retaining lip.

Abstract: A planetary gear system includes a planetary gear carrier having three or more posts extending from the planetary gear carrier, each post having a hardened exterior surface, and a planet pinion gear in contact with the hardened exterior surface of each post.

Abstract: In one embodiment, an apparatus comprises a thermal barrier configured to surround at least a portion of a driveshaft and to protect the driveshaft from heat. The thermal barrier comprises an inner wall forming a cavity in which the driveshaft lies, an outer wall enclosing the inner wall, and a space between the inner wall and the outer wall. The space is evacuated and forms a vacuum.

Abstract: The present invention includes a method for fastening a fastener body having a longitudinal axis, a first external male threaded portion, and two or more through-holes perpendicular to the longitudinal axis of the fastener body in the first external male threaded portion, wherein the through-holes are on a different plane perpendicular to the longitudinal axis of the fastener, wherein the two or more through-holes are on a different one of the planes and angle from an adjacent through-hole of the two or more through-holes; and tightening a fastening member configured to matingly engage the first external male threaded portion, wherein the two or more through-holes is capable of receiving a pin without having to rotationally adjust the fastening member such that compression is maintained between a first object and a second object.

Abstract: A ring gear includes a ring having one or more sets of inwardly facing teeth, a circumferential flange extending outward from the ring, and the flange is mounted between a first housing and a second housing. In addition, the flange protrudes into an ambient air outside the first housing and second housing.

Abstract: A cooling apparatus includes one or more fans and one or more shafts. Each of the one or more fans includes a fan blade assembly. Each of the one or more shafts is operably coupled to an engine or a gearbox that rotates the shaft. Each fan blade assembly of the one or more fans is disposed on one of the shafts.

Abstract: A method for operating a sensor system includes detecting a first wake trigger by a plurality of sensors for a component disposed in a remote location, generating, by each sensor, sensor service data that includes a battery charge level of the sensor, determining an active sensor according to the sensor service data of each sensor of the plurality of sensors, and assigning the active sensor to enter an active mode assigning each sensor of the plurality of sensors, other than the active sensor, to enter a sleep mode, generating, by the active sensor, sensor reading data for the component until an inactive trigger is detected, sending the sensor reading data using a wireless transmission to a sensor data server, and leaving the active mode by the active sensor and entering a sleep mode in response to the active sensor detecting an inactive trigger.

Abstract: An example lubrication system for a rotating component has a primary lubrication system providing continuous lubrication during normal operation of the rotating component and secondary lubrication system with a reservoir co-rotating with the component. The reservoir is continuously replenished from the primary lubrication system during normal operation of the rotating system, with the lubricant being forced through a discharge orifice by the centrifugal force generated by the rotation toward, for example, a bearing or a gear. When the primary pressurized lubrication system fails, lubrication will continue to be provided by the lubricant in the supplemental lubricant reservoir while the rotation speed or power supplied to the shaft is controllably decreased in an emergency.

Abstract: A pressure sensitive bypass valve for protecting the components of a fluid distribution system. The bypass valve includes a poppet designed to prevent fluid bypass in the event of spring failure, rather than from over-pressurization.

Abstract: The present invention includes an apparatus for preventing aircraft rollover upon a water landing comprising: a deployable first and/or second boom affixed by a first end to the aircraft and capable of deployment substantially perpendicular to a longitudinal axis of the aircraft; and a first and/or second air bladder attached to a second end of the first and/or second boom, wherein the first and/or second air bladders are configured to inflate when an aircraft lands in the water, wherein deployment of the first and second boom and air bladder prevents aircraft rollover upon water landing; or a deployable keel affixed by a first end to the aircraft and capable of deployment substantially perpendicular to a longitudinal axis and opposite a rotor of the aircraft upon a water landing, wherein the keel is sized to prevent aircraft rollover upon deployment; or both.

Abstract: The present invention includes a method of lubricating a gearbox, including moving a lubricant from the gearbox into a gear shroud via a flow-metering orifice in the gear shroud; and distributing the lubricant within the gearbox by operation of a gear turning within the gear shroud.

Abstract: The present invention includes a helicopter rotor seal assembly comprising: a rotor mast having a longitudinal axis and an outer surface; a sleeve aligned longitudinally with the axis and surrounding a portion of the rotor mast, the sleeve having an outer surface, and an inner surface; an annular horizontal seal between the inner surface of the sleeve and the outer surface of the rotor mast; and an upper annular rotor mast seal affixed to the outer surface of the rotor mast and extending outwardly sufficient to cover the annular horizontal seal.

Abstract: The present invention includes a system, method and kit for preventing or reducing water penetration of a gearbox, the system including: a fan or impeller coupled to the gearbox; and a hub coupled to the fan and shaped to provide a labyrinth seal that prevents or reduces water penetration into the gearbox.

Abstract: An apparatus for lubricating a non-pressurized gearbox includes a low-to-high lubricant level sensor configured to sense a static level of a lubricant within the gearbox and to display the static level of the lubricant.

Abstract: An engine reduction gear system includes at least two self-contained, independent engine reduction gearboxes, each capable of connecting to an aircraft engine. Each of the engine reduction gearboxes provides redundant, reduced speed to a main rotor gearbox via a shaft.

Abstract: The present invention includes a cooling system for a gearbox, the cooling system comprising: a pressurized housing in fluid communication with the gearbox configured to circulate a pressurized lubricant; and one or more cooling fins about the pressurized housing, wherein heat from the pressurized lubricant within the pressurized housing is actively convected through the one or more cooling fins.

Abstract: A cooling apparatus includes a shared cooling device for one or more systems or components, and a plurality of primary cooling pathways. Each of the primary cooling pathways includes a transition duct and a fan. The transition duct is in fluid communication with the shared cooling device. The fan is in fluid communication with the transition duct.