Sean M Mcgee

US Patent:

20220298921, Sep 22, 2022

Filed:

Mar 19, 2021

Appl. No.:

17/206521

Inventors:

- Farmington CT, US
Sean P. McGee - Andover CT, US
Joseph B. Phelps - Vernon CT, US

Assignee:

Raytheon Technologies Corporation - Farmington CT

International Classification:

F01D 11/00
F02C 7/28
F16J 15/34

Abstract:

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; and a seat carried by the shaft and having a seat face in sliding sealing engagement with the seal face. The seal system is a dry face seal system. The seat further includes a section having: an outer diameter surface encircled by the seal; and a rim.

US Patent:

20220213840, Jul 7, 2022

Filed:

Jan 5, 2021

Appl. No.:

17/141432

Inventors:

- Farmington CT, US
Joseph B. Phelps - Vernon CT, US
Sean P. McGee - Andover CT, US

International Classification:

F02C 7/28
F02C 7/06

Abstract:

A gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, a compressor section, a combustor section, a turbine section, and at least one rotatable shaft. The engine further includes a seal assembly having a seal plate mounted for rotation with the rotatable shaft, a face seal in contact with the seal plate at a contact area, and a seal carrier supporting the face seal. Further, in normal operating conditions, the seal plate includes a plurality of tabs configured to separate from a remainder of the seal plate in a worn seal condition in which the seal carrier contacts the seal plate.

US Patent:

20210348563, Nov 11, 2021

Filed:

May 5, 2020

Appl. No.:

16/866633

Inventors:

- Farmington CT, US
Sean P. McGee - Andover CT, US
Joseph G. Colucci - Milford CT, US

International Classification:

F02C 7/28
F02C 7/06

Abstract:

A seal configuration for an aircraft engine includes a ring shaped sealing component defining an axis. A carrier is disposed radially outward of the ring shaped sealing component and supports the ring shaped sealing component. A housing includes a shroud portion. The shroud portion fully surrounds the carrier and is maintained in a static position relative to the carrier via a bellows spring and a plurality of rotation inhibiting features. Each rotation inhibiting feature in the plurality of rotation inhibiting features includes a tab protruding radially outward from the carrier and received in a slot intruding into the shroud portion.

US Patent:

20200300117, Sep 24, 2020

Filed:

Mar 18, 2019

Appl. No.:

16/356082

Inventors:

- Farmington CT, US
Sean P. McGee - Andover CT, US

International Classification:

F01D 25/16
F01D 11/00
F01D 25/24
F02C 7/20
F01D 25/12

Abstract:

A seal assembly for a gas turbine engine according to an example of the present disclosure includes, among other things, a rotatable shaft defining a longitudinal axis, and a bearing housing extending along the longitudinal axis to define a bearing compartment. The bearing housing has a first seal land defined along an inner diameter of the bearing housing, a seal carrier fixedly attached to an outer periphery of the shaft, and a seal member extending outwardly from the seal carrier. The seal member defines a plurality of helical grooves facing radially outward to establish a first sealing relationship with the first seal land, and each one of the helical grooves has a major component extending in an axial direction relative to the longitudinal axis. A method of sealing for a gas turbine engine is also disclosed.

US Patent:

20190323555, Oct 24, 2019

Filed:

Jul 20, 2018

Appl. No.:

16/041041

Inventors:

- Farmington CT, US
Sean P. McGee - Andover CT, US

Assignee:

United Technologies Corporation - Farmington CT

International Classification:

F16C 27/04
F16C 33/66

Abstract:

A machine has a first member, a second member, a bearing, and a spring. The bearing inner race is mounted to the second member. A spring first end portion is mounted to the first member. The bearing outer race is mounted to a spring second end portion. The spring has a flexible portion between the first end portion and the second end portion. A first annular seal is carried by an outer diameter first groove in an outer diameter surface of the second end portion and seals with an inner diameter surface of a sealing portion of the first member. A second annular seal carried by an inner diameter second groove in the first member and seals with an outer diameter surface of the second end portion. A fluid outlet in the first member opens to a chamber between the first annular seal and the second annular seal.

US Patent:

20190249605, Aug 15, 2019

Filed:

Feb 12, 2018

Appl. No.:

15/893833

Inventors:

- Farmington CT, US
David Barger - East Hartford CT, US
Sean P. McGee - Vernon CT, US

International Classification:

F02C 7/28
F02C 3/04
F16J 15/3288

Abstract:

A seal configuration for an aircraft engine includes a ring shaped sealing component defining an axis, a carrier disposed radially outward of the ring shaped sealing component and supporting the ring shaped sealing component, and a housing disposed at least partially about the carrier. The housing is maintained in a static position relative to the carrier via a bellows spring. At least one of the carrier and the housing include a plurality of rotation inhibiting features disposed in a balanced configuration about the at least one of the carrier and the housing. Each of the rotation inhibiting features including a finger extending from the housing and at least one interface feature corresponding to each finger, and being disposed on the carrier. The at least one interface feature comprises one of a notch protruding radially into the carrier and a tab protruding radially outward from the carrier.

US Patent:

20190003389, Jan 3, 2019

Filed:

Jan 13, 2017

Appl. No.:

15/405688

Inventors:

- Farmington CT, US
David Barger - East Hartford CT, US
Sean P. McGee - Vernon CT, US

International Classification:

F02C 7/06
F01D 25/18
F16N 7/28

Abstract:

Aspects of the disclosure are directed to a system comprising: a lubrication applicator device that includes: a base having a cavity that is configured to store a lubricant, and a plunger that is configured to seat a head of a bolt in a counterbore of the base, where the plunger is axially movable in the cavity and is configured to be at least partially recessed in the cavity to cause a side of the bolt to be immersed in the lubricant.