United Technologies Corporation

Raytheon Technologies Corporation

Rtx Corporation

Christopher T Anglin

Yuk-Kwan Brian Yuen

Russell B Witlicki

Christopher M Valva

Brian P Cigal

Dwayne E Messerschmidt

Kaleb Von Berg

Heriberto Rodriguez

Todd M Gaulin

Daniel S Rogers

Adam G Smedresman

Marios C Soteriou

Leslie Charles Kurz

Matthew Nickerson

Kiomarys Mariel Toro

Graham B Fulton, Iii

Camron Najafi

Shiling Zhang

Lawrence A McLean

Graham B Fulton Iii

Russel B Witlicki

A turbine engine assembly includes a shaft rotatable about an engine axis, the shaft includes slots that are formed on an outer surface and passages between an inner cavity to the outer surface, and a bearing assembly that is configured to support rotation of the shaft. The bearing assembly includes an inner race that is supported on the outer surface of the shaft over the slots. At least one bearing member is supported in the inner race, an outer race, a first cover that is disposed on a forward side of the inner race and a second cover that is disposed on an aft side of the inner race. Each of the first cover and the second cover include radially extending grooves for communicating lubricant from the slots to the bearing member.

Bearing oil distribution scheme

An apparatus has: a first member; a shaft rotatable relative to the first member about an axis; and a seal system. The seal system has: a seal carried by the first member and having a seal face; a seal carrier; a seat carried by the shaft and having a seat face in sliding sealing engagement with the seal face; and one or more springs biasing the seal carrier relative to the first member so as to bias the seal face against the seat face. The seal carrier has: an axially-extending wall having an inner diameter (ID) surface; and a radially-extending wall having a first surface. The seal carrier axially-extending wall ID surface has a radially inwardly open groove having a first sidewall and a second sidewall and a base. A wave-form split ring contacts the first sidewall and biases the seal into engagement with the radial wall first surface.

Carbon face seal

An assembly for a compartment of a gas turbine engine that includes a housing, a gear, and a baffle disposed about the gear. The baffle includes an upstream portion and a downstream portion. The upstream portion includes an upstream inner wall and an upstream outer wall separated from the gear. The upstream inner wall is positioned between the upstream outer wall and the gear. An upstream flow channel is formed between the upstream inner wall and the upstream outer wall. The downstream portion of the baffle includes a downstream inner wall and a downstream outer wall separated from the gear. The downstream inner wall is positioned between the downstream outer wall and the gear. A downstream flow channel is formed between the downstream outer wall and the downstream inner wall.

Secondary flow oil separator

A fan assembly of a gas turbine engine includes a fan rotor including a fan rotor hub, and a plurality of fan blades extending radially outwardly from the fan rotor hub, and a fan case including an inner case portion and an outer case portion surrounding the plurality of fan blades. A plurality of struts extend between the inner case portion and the outer case portion. A bearing assembly is configured to support the fan rotor at the inner case portion. The bearing assembly includes a bearing inner race secured to the fan rotor, a bearing outer race secured to the inner case portion, and a plurality of bearing elements located radially between the bearing inner race and the bearing outer race.

Housing less front bearing compartment for gas turbine engine

A gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, a bearing compartment, a seal assembly configured to establish a seal of the bearing compartment. The seal assembly includes a seal plate. The gas turbine engine further includes a gutter configured to collect oil slung from the seal plate. The gutter extends only partially around the seal plate. A method is also disclosed.

Partial arc gutter for gas turbine engine

A seal assembly for a bearing compartment of a gas turbine engine includes a seal carrier, a seal element, a seal plate, and a trough. At least a portion of the seal element is within the seal carrier. The seal plate is in contact with the seal element and is configured to rotate relative to the seal element. The trough extends around the seal plate and comprises an annular channel positioned to capture oil slung from the seal plate.

Oil control for seal plates

A thrust-sensing assembly for a bearing compartment of a gas turbine engine includes a spacer and a retaining ring. The spacer includes an outer frusto-conical portion and an inner ring. The outer frusto-conical portion includes an axial row of a plurality of slots. Each slot of the plurality of slots includes a first rounded end, a second rounded end, a first side-face, and a second side face that faces the first side-face. The retaining ring includes a plurality of axial extensions with distal ends that are in contact with the outer frusto-conical portion of the spacer.

Strain measuring device for bearing compartment

A lubricating fluid damped anti-rotational system is provided comprising a pawl carrier having an axis of rotation and a radial aperture, a pawl pivotably mounted to the pawl carrier on a pivot joint, the pawl having a contact portion and a counterweight portion, a lubricating fluid jet configured to propel a lubricating fluid through the radial aperture toward the contact portion.

Lubricating fluid damped anti-rotational systems

A seal plate is disclosed herein that is annular in shape and configured to rotate about a centerline. The seal plate includes a seal body having a first axial end forming a sealing surface and a second axial end opposite the first axial end, a slinger ring axially rearward of the seal body and having a plurality of radially extending tabs separated by a plurality of slots, and a groove between the seal body and the slinger ring. The tabs on the slinger ring are configured to direct lubricant at least partially radially inward into the groove and at least partially in a direction of rotation of the seal plate to cool the seal body.

Seal plate lubricant slinger

An assembly is provided for a gas turbine engine. This assemble includes a stationary structure configured with a first side, a second side and a bore that extends through the stationary structure between the first side and the second side. The assembly also includes a fluid transfer tube extending within the bore and forming a plenum between a sidewall of the fluid transfer tube and the stationary structure. The fluid transfer tube is configured with a first end at the first side, a second end at the second side, a flowpath and an aperture. The flowpath is at least partially formed by the sidewall and extends through the fluid transfer tube between the first end and the second end. The aperture fluidly couples the flowpath with the plenum.

Damped fluid transfer tube for a gas turbine engine

An insulated seal seat assembly comprises a shaft configured and arranged to rotate about an axial axis, a seal seat that is secured to the shaft, and a thermal insulator configured and arranged radially between the shaft and the seal seat.

Insulated seal seat

A gear assembly is provided. The gear assembly includes a first gear that rotates about a first axis and includes a first gear face with a plurality of first gear teeth; a second gear that rotates about a second axis and includes a second gear face with a plurality of second gear teeth, where the first axis is not parallel with the second axis and the first and second teeth rotatably engage as the first gear rotates about the first axis and the second gear rotates about the second axis; a scraper that includes a distal interference surface in face-to-face proximity with at least one of the first plurality of teeth as the first gear rotates about the first axis, where the interference surface removes oil entrained adjacent to the plurality of first or second gear teeth as the first or second gears rotate.

Oil scraper

A tower shaft support for a gearbox of a gas turbine engine includes a mounting ring, first and second gussets, and first and second tower shaft bearing mounts. Each gusset extends outward from and substantially normal to an outer circumference of the mounting ring. The first and second tower shaft bearing mounts are positioned between the first and second gussets.

Two-shaft tower shaft support

A damped anti-rotational system is provided comprising a pawl carrier having an axis of rotation, a pawl pivotably mounted to the pawl carrier on a pivot joint, the pawl having a contact portion and a counterweight portion, a stop pin axially disposed in the pawl carrier and configured to contact the contact portion of the pawl in response to radially inward movement of the pawl, wherein the stop pin is mounted to the pawl carrier at a forward portion of the stop pin and an aft portion of the stop pin, wherein a forward O ring is disposed on the forward portion of the stop pin and an aft O ring is disposed on the aft portion of the stop pin.

Growing community of inventors

Manchester, CT, United States of America

Christopher T Anglin