United Technologies Corporation

Raytheon Technologies Corporation

Rtx Corporation

James B Coffin

John R Otto

Alessio Pescosolido

Todd A Davis

Michael E McCune

Jason Husband

Enzo DiBenedetto

William G Sheridan

Joseph D Walker

Tony Haugh

Marc J Muldoon

Jonathan Logan Miller

Christopher M Valva

Keven G Van Duyn

Brady Walker

David M Daley

Ernest Boratgis

Sunil Sharma

Alexander J Maret

Stephanie M Baker

Richard E Domonkos

Brad E Fiore

Kevin G VanDuyn

Eric Stehlik

A shaft bearing retainer assembly is provided that includes an axially extending shaft, a bearing, and a bearing retainer subassembly. The shaft has first and second radial surfaces, a distal end, a bearing seat, and a retainer cavity. The bearing seat is engaged with the first radial surface and extends axially inward from the distal end. The retainer cavity is disposed in the second radial surface of the shaft and extends axially inward from the distal end. The shaft includes a first threaded surface portion disposed in the retainer cavity and a second threaded surface portion in the second radial surface. The bearing has a race mounted in the bearing seat. The bearing retainer subassembly includes first and second retainer rings. The first retainer ring is in threaded engagement with the first threaded surface portion. The second retainer ring is in threaded engagement with the second threaded surface portion.

Shaft bearing retainer assembly

A system and method for preventing cracks in structural concrete associated with a building structure, the building structure having one or more wooden support columns. Each wooden support column has a base supported by a ground surface and is provided with a crack prevention member having a first, upper or top surface and a second, lower or bottom surface; an outer side wall; and an inner side wall defining a cut-out portion; the base of the wooden support beam is positioned within the cut-out portion. A concrete floor is poured on the ground surface no higher than the level of the first, upper surface of the crack prevention member, and no floor concrete or other structural concrete contacts the wooden support column. The crack prevention member may comprise various materials including rubber, plastic, resin, or other polymeric material and combinations thereof.

System and method for preventing cracks in structural concrete

A gas turbine engine includes a rotating shaft. An oil scoop rotates with the rotating shaft. The oil scoop has end walls spaced axially along an axis of rotation of the rotating shaft and an axially central recess. A duct is spaced radially outwardly of the oil scoop. The duct has an oil inlet, with an oil supply nozzle to supply oil into the oil inlet in the duct. The oil inlet is then connected to supply oil into the recess. The oil scoop has an inner hole to allow oil to flow from the recess to an outer periphery of the shaft.

Ducted oil scoop for gas turbine engine

A fan drive gear system for a turbofan engine includes a geared architecture and a gear controller supporting the geared architecture and controlling rotation of the geared architecture relative a static structure.

Fan drive gear system mechanical controller

An assembly is provided for a turbine engine. This turbine engine assembly includes a tower shaft rotatable about an axis, an engine component rotatable with the tower shaft about the axis, and a seal assembly. The engine component extends axially along the axis to an end surface. The seal assembly includes a carbon seal element, where the carbon seal element circumscribes the tower shaft and axially engages the end surface.

Shaft seal assembly for a turbine engine

A lubricant scoop is disclosed. The lubricant scoop includes an annular body configured for engagement with a shaft rotating about a central axis. The annular body includes a first annular portion and a second annular portion disposed adjacent the first annular portion. The first annular portion includes a radially oriented entrance surface and a first axially oriented transition surface. The second annular portion includes a second axially oriented transition surface, a primary redirection member spaced radially outward from the second axially oriented transition surface, a radially oriented exit surface and an exit conduit having an opening positioned on the radially oriented exit surface.

Lubricant scoop

A gas turbine engine includes a fan, an engine static structure, a geared architecture to drive the fan and supported relative to the static structure, a fan drive turbine to drive the geared architecture, a first member secured to the geared architecture, and a second member secured to the engine static structure and configured to cooperate with the first member to limit movement of the geared architecture relative to the static structure. A fan drive gear system and method are also disclosed.

Gas turbine engine geared architecture axial retention arrangement

A turbofan engine includes a fan rotatable about an axis and a compressor section including a high pressure compressor and a low pressure compressor. A turbine section includes a high pressure turbine, an intermediate turbine and a fan drive turbine. The high pressure turbine is coupled to drive the high pressure compressor. A fan drive gear system is driven by the fan drive turbine for driving the fan and a compressor drive gear system is driven by the intermediate turbine for driving the low pressure compressor.

Three spool geared turbofan with low pressure compressor drive gear system

A lubricant manifold for gear system of a turbofan engine includes a base plate defining an inlet, an outlet and a plurality of open channels. The open channels define a portion of a corresponding plurality of lubricant passages. A cover plate is attached to the base plate to complete the formation of the plurality of lubricant passages. An interlocking interface between the base plate and the cover plate secures the cover plate to the base plate.

Inseparable machined lubricant manifold

A turbofan engine is disclosed that includes a fan rotatable about an axis, a compressor section including a high pressure compressor, a medium pressure compressor and a low pressure compressor and a turbine section including a high pressure turbine, an intermediate turbine and a fan drive turbine. A fan drive gear system is driven by the fan drive turbine for driving the fan. A compressor drive gear system is driven by the intermediate turbine for driving the low pressure compressor. A gear controller controls rotation of at least one of the fan drive gear system and the compressor drive gear system relative to a static structure to vary an effective speed reduction ratio of one of the fan drive gear system and the compressor drive gear system.

Three spool geared turbofan with low pressure compressor drive gear system and mechanical controller

A method for assembling a turbofan engine () comprises coupling a bearing assembly () and a shaft () as a unit to a bearing support (). A transmission () and the fan shaft () are installed to a front frame assembly (). The bearing assembly and shaft are installed as a unit so that the shaft engages a central gear () of the transmission and the bearing support engages the front frame assembly.

Turbofan engine assembly methods

A method for distributing liquid in a gas turbine engine is disclosed. The method includes rotating a fan shaft coupled to a spool via a fan drive gear system. The spool drives rotation of the fan shaft through the fan drive gear system during operation of the gas turbine engine. A pump is driven via the fan shaft. Liquid is supplied from a sump to the pump under a first operating condition. Liquid is supplied from an auxiliary reservoir to the pump under a second operating condition. Liquid is pumped to a damper.

Apparatus and method for providing damper liquid in a gas turbine engine

A seal assembly for a gas turbine engine, may be manufactured in two pieces, the first piece is a seal plate with a cavity around its inner wall and the second piece is a sleeve that mounts in the cavity of the seal plate. The sleeve may have oil distribution channels that deliver oil to subsequent components and apertures that deliver oil to the seal plate. The volume of oil delivered to the seal plate can be set by the number of apertures and related radial holes in the sleeve. Because the sleeve delivers oil through the apertures and radial holes to an annulus in the cavity of the seal plate, cooling bores in the seal plate need only be drilled into the annulus and the number of cooling bores can be independent of the number of radial holes in the sleeve.

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Windsor, CT, United States of America

James B Coffin