United Technologies Corporation

Raytheon Technologies Corporation

Rtx Corporation

Todd A Davis

Brian P Cigal

Christopher M Valva

Enzo DiBenedetto

Armando Amador

David Allen Stachowiak

James B Coffin

Russell B Witlicki

Mark Ronski

Joseph D Walker

Gregory E Reinhardt

David C Kiely

Andrew Newton

Gabriel L Suciu

William G Sheridan

Brian D Merry

Paul R Hanrahan

Francis Parnin

Nigel David Sawyers-Abbott

Reade W James

Aneil S Hegde

Daniel Rosen

Timothy Webb

Ramin M Rafatpanah

Dale C Humphries

Ryan William Lureau

Daniel L Gysling

Jorn Axel Glahn

Michael D Greenberg

Denman H James

John R Otto

Chintan Jain

Adam G Smedresman

Andrew V Schwendenmann

Dawnray Young

Kaleb Von Berg

Peter T Schutte

Ernest Boratgis

Sunil Sharma

Greg Alan Cox

Viswa Vaddi

Andrew Shea

Enzo Dibenedetto

Brad E Fiore

Raj Chinnakonda

David Joseph Hierl

Joanna Mamrowicz

Jennifer Reid

Gianna E Sabino

Shadd Andrew Bradshaw

Eric Stehlik

Juan Jimenez

Dennis Cheung

Zhenyin Yang

Ryan Lureau

Russel B Witlicki

A seal assembly for a gas turbine engine may include an annular seal carrier extending about an assembly axis. An annular contacting-type seal member may be secured along a shelf of the seal carrier. At least one spring carrier may extend from the seal carrier. At least one spring member may be received in a spring pocket of the respective at least one spring carrier. The at least one spring member may be arranged to bias an annular seal face of the seal member against a seal land at an interface. The at least one spring carrier may extend past the seal face relative to the assembly axis. A method of sealing for a gas turbine engine is also disclosed.

Seal assembly for gas turbine engines

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 gas turbine engine includes a fan that has fan blades wherein the fan delivers airflow to a bypass duct. A gearbox is defined along an engine axis. A low spool is arranged aft of the gearbox and coupled to drive the gearbox. A front center body assembly is defined around the engine axis. A flexible support supports the gearbox relative to the front center body assembly. A bearing package is mounted to the front center body assembly and the low spool. A front wall is mounted to the front center body assembly. The front wall is removable from the front center body assembly to access at least one of the gearbox or the bearing package. The low spool includes a low pressure compressor hub that provides an engagement feature for engaging the bearing package.

Gas turbine engine front center body architecture

A seal system has: a first member; a seal carried by the first member and having a seal face; and a second member rotatable relative to the first member about an axis. The second member has: a seat on a first piece of the second member, the seat having a seat face in sliding sealing engagement with the seal face; and a radially outwardly closed collection channel for collecting centrifuged oil; a second piece encircling and attached to the first piece and having a circumferential array of apertures; and cooperating with the first piece to define a plenum; and a flowpath from the collection channel passing radially outward axially spaced from the seat face to cool the seat face and passing axially away from the seat face in the plenum.

Oil-cooled carbon seal

A fan drive gear system for a turbine engine includes a carrier that supports rotation of a plurality of planet gears and is rotatable about an engine longitudinal axis. The carrier includes an axially facing seal plate that defines a lubricant passage to the carrier. A transfer bearing assembly has a seal member that defines a lubricant supply path to the seal plate and at least one biasing member that biases the seal member against the seal plate.

Axial transfer bearing

A fan drive gear system for a turbine engine includes a sun gear that is configured to be driven by an engine shaft that is rotatable about an axis. The sun gear includes a first gear portion and a second gear portion. A plurality of intermediate gears are coupled to the first gear portion of the sun gear, a ring gear is coupled to the plurality of intermediate gears, a carrier supports rotation of the plurality of intermediate gears, and an accessory component is coupled to the second gear portion of the sun gear.

Component mounting and drive in a geared turbofan architecture

A fan drive gear system for a turbine engine includes a sun gear that is configured to be driven by an engine shaft rotatable about an axis. A plurality of intermediate gears are coupled to the sun gear, a ring gear is coupled to the plurality of intermediate gears, and a carrier supports rotation of the plurality of intermediate gears. The carrier includes a gear portion and an accessory component that is coupled to and driven by the gear portion of the carrier.

A gas turbine engine has a shaft having an inner diameter surface. A plug is mounted in the shaft. An oil nozzle is positioned to direct a flow of oil to an interior of the shaft. The plug has: a first section; a second section having an outer diameter periphery; and an axial gap between the first section and the second section.

Turbine engine shaft plug

A scupper suitable for a bearing compartment of a gas turbine engine includes a windage blocker in a gutter section upstream of a drain hole, the windage blocker extends from a wall of the gutter section. A method for capturing wept oil in a bearing compartment of a gas turbine engine includes positioning a windage blocker adjacent to a drain hole forming a passage space and increasing a pressure upstream of the windage blocker to generate a vortex downstream of the windage blocker creating an oil re-circulation zone promoting oil drainage into the drain hole.

Windage blocker for oil routing

A gas turbine engine includes a first bearing compartment and a seal assembly within the first bearing compartment that includes a rotatable seal seat, a gutter radially outward of the seal seat and fixed against rotation. The gutter includes a channel on its radially inner face. A second bearing compartment is also included. A scavenge pump is in communication with a first supply line configured to supply the first bearing compartment and a second supply line configured to supply the second bearing compartment. The gutter is in communication with the scavenge pump through a gutter scavenge line.

Seal oil systems

A gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, a bearing compartment, a seal runner, a seal configured to cooperate with the seal runner to seal the bearing compartment, and a catcher in contact with the seal runner to minimize deflection of the seal runner. A method is also disclosed.

Seal runner with deflector and catcher for gas turbine engine

A bearing compartment of a gas turbine engine includes a rotationally fixed structure defined about an engine longitudinal axis; a gutter section formed in the front support; an oil drainback assembly mountable to the gutter section to direct oil into a drain passage to communicate oil from the gutter.

Oil drainback assembly for a bearing compartment of a gas turbine engine

A gas turbine engine includes a fan that has fan blades wherein the fan delivers airflow to a bypass duct. A gearbox is defined along an engine axis. A low spool is arranged aft of the gearbox and coupled to drive the gearbox. A front center body assembly is defined around the engine axis. A flexible support supports the gearbox relative to the front center body assembly. A bearing package is mounted to the front center body assembly and the low spool. A front wall is mounted to the front center body assembly. The front wall is removable from the front center body assembly to access at least one of the gearbox or the bearing package. The low spool includes a low pressure compressor hub that provides a spline for engaging the bearing package.

A bearing assembly of a gas turbine engine includes a bearing inner race, a bearing outer race located radially outboard of the bearing inner race and a plurality of bearing elements located between the bearing inner race and the bearing outer race. A centering spring is operably connected to and supports the bearing outer race. The centering spring is an annular structure including a base portion, a tip portion, and a plurality of beams extending axially between the base portion and the tip portion.

Low profile rotating bearing centering spring

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Tolland, CT, United States of America

Todd A Davis