Sikorsky Aircraft Corporation

Lockheed Martin Corporation

United Technologies Corporation

Michael F Mullen

Clark VanTine Cooper

Adam R Glasser

Thomas L Sbabo

Stephen R Sammataro

William Wolcott

Noah McCreight

Jimmy Yeung

Ulf J Jonsson

Kenneth J Buckman

John J Baldyga

David M Lutian

Thomas L Tully

Dwaine Wint

Kyle Winters

Lindsey McKan

A gear box includes a housing, a shaft that is driven by the gear, the shaft including a recess, a bearing mounted between the shaft and the housing to support the shaft for rotation with respect to the housing about a rotation axis, and a ring assembly for axially securing the bearing to the shaft. The ring assembly surrounds the shaft and is seated in the recess. The recess has a retaining surface including a conical surface extending at an angle to the rotation axis, a curved surface, and a transition surface extending between the conical surface and the curved surface, the transition surface extending generally parallel to the rotation axis.

Bearing retention system

A lubricant system includes a first gearbox defining a first internal cavity, a second gearbox defining a second internal cavity, a first lubricant cooler positioned external the first and second internal cavities, a second lubricant cooler positioned external the first and second internal cavities, and a plurality of fluid passages fluidly connecting the first lubricant cooler and second lubricant coolers to each of the first gearbox and the second gearbox. The first lubricant cooler and the second lubricant cooler are configured to hold lubricant. The fluid passages include a first main fluid passage fluidly connecting the first lubricant cooler to the first gearbox, a second main fluid passage fluidly connecting the second lubricant cooler to the second gearbox, a first auxiliary passage fluidly connecting the first lubricant cooler to the second gearbox, and a second auxiliary passage fluidly connecting the second lubricant cooler to the first gearbox.

Gearbox lubrication system for an aircraft

A gear box includes a housing, an actuator coupled to the housing, and a bearing assembly pivotably coupled to the actuator. The bearing assembly including an outer raceway, a cylindrical housing positioned within the outer raceway, and an annular bearing positioned between the outer raceway and the housing. The cylindrical housing has a first end and a second end opposite the first end. A sensor is coupled to the first end of the cylindrical housing and configured to monitor an operating condition of the annular bearing. A linkage couples the actuator to the second end of the cylindrical housing and an output shaft is rotatably coupled to the bearing assembly.

Bearing assembly

A gearbox includes a housing including a lubricant reservoir, at least one gear system arranged in the housing, at least one lubricant delivery passage operable to direct a flow of lubricant from a lubricant reservoir onto the at least one gear system, at least one lubricant return passage operable to guide the flow of lubricant to the lubricant reservoir, and a lubricant-out sensor fluidically connected to the at least one lubricant return passage. The lubricant-out sensor is operable to detect a non-pressure based parameter of the lubricant.

System and method for detecting a lubricant-out condition in an aircraft gearbox

An aircraft tail rotor system includes a rotating pitch change shaft, a translating element, and a pitch change bearing assembly including a first bearing and a second bearing. The pitch change bearing assembly is operable to transmit movement of the translating element to the rotating pitch change shaft via the first bearing or the second bearing. A failure section is formed at an interface between the first bearing and the translating element. When the failure section decouples the first bearing from the translating element such that the first bearing does not transmit movement of the translating element to the rotating pitch change shaft, the second bearing transmits movement of the translating element to the rotating pitch change shaft.

Redundant helicopter pitch change shaft system

A locking mechanism for a driveshaft disconnect coupling includes an input jaw member defining a rotation axis, an output jaw member connectable to the input jaw member for common rotation with the input jaw member, and a cartridge assembly. The cartridge assembly is fixed to the input jaw member, includes a pin, and defines a pin movement axis. The pin is movable along the pin axis between a radially inner position and a radially outer position, the pin being disengaged from the output jaw member in the radially inner position and the pin being engaged to the output jaw member in the radially outer position.

Locking mechanisms for tail rotor drive disconnect couplings

A lubrication system includes an additive and a delivery system. During normal operational conditions, the lubricating oil circulating in the transmission system is collected and contained in a secondary oil reservoir to retain a quantity of the lubricating oil for use in an oil-out condition. When an oil-out condition is detected, the additive is injected and mixed with the collected lubricating oil in the secondary oil reservoir or dispersed directly into a power transmission gearbox housing to enhance the characteristics of the lubricating oil and increases the operational time period of the power transmission gearbox during an oil-out condition.

Secondary lubrication system with injectable additive

A method and system for magnetically detecting thermal degradation of a component. A multiple of ferrous metal segments are attached to a component not within a lubrication circuit of a lubrication system with a thermally-affected bonding agent. The thermally-affected bonding agent is operable to detach at a threshold temperature at least one of the multiple of ferrous metal segments such that the at least one of the multiple of detached ferrous metal segments enters the lubrication circuit of the lubrication system. The at least one of the multiple of ferrous metal segments which detached are then detected within the lubrication system.

Sealed bearing assembly failure detection

A mechanical system for high acceleration loading includes a mechanical element configured for rotational movement in a high acceleration environment. The mechanical element possesses a first density. A lubricant having a second density is disposed about the mechanical element. The first and second densities are substantially identical such that the mechanical element is substantially neutrally buoyant in the lubricant.

Mechanical system for high acceleration environments

There is a coated, dynamic contact surface. The contact has a substrate and a carbon-based coating on the substrate. The coating has a coefficient of friction of about 0.5 or less and an atomic hydrogen content of about 5% to about 25%. There is also a mechanical system. There is a method for increasing oil-out survivability in a mechanical system.

Process for deposition of amorphous carbon

A bearing assembly which spaces bearing elements in an unequal relationship from one bearing element pocket to the next. The spacing minimizes the likelihood that the bearing elements will rest in the exact same location on an inner and outer race to reduce the potential for false brinelling. The net result is a decreased depth of false brinelling in any one location and an increased bearing life.

A non-ferrous component comprising a thermally-affected adhesive applied to a surface of the component, and at least one ferrous metal wire attached to the surface of the component by the thermally-affected adhesive.

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Cheshire, CT, United States of America

Michael F Mullen