Raytheon Technologies Corporation

United Technologies Corporation

Rtx Corporation

Other

Sean P McGee

Joseph B Phelps

Joseph H Polly

Christopher M Valva

Adam G Smedresman

Andrew V Schwendenmann

David Barger

Aneil S Hegde

Joseph G Colucci

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.

Self-guiding carbon seal system

A seal assembly includes a rotatable shaft and a stationary housing circumscribing the shaft to form radially inner and radially outer boundaries of a seal cavity and a buffer cavity adjacent to the seal cavity. A retention member engaging the housing within the seal cavity includes an end plate extending radially at the axial boundary between the seal and buffer cavities and a protrusion extending from the end plate into the buffer cavity.

Dual windage blocker and retention feature design for seal assembly

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.

Gas turbine engine including seal plate with separable tabs

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.

Shrouded aircraft engine seal carrier

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.

Seal assembly for a gas turbine engine

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.

Bolt lubrication

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.

Bearing centering spring and damper

A machine has first and second members. A bearing has an inner race mounted to the second member and an outer race rotatable relative to the inner race about an axis. A ring holds the outer race. A radial spring extends radially between the ring and the first member. First and second damper rings extending radially between the ring and the first member at first and second axial sides of the radial spring. First and second damping chambers are radially between an outer diameter surface portion of the respective damper rings and an inner diameter surface portion of the first member.

A cutting mat includes a flat, planar sheet of rigid but flexible material with a plastic film affixed to the lower surface and extending across the length and width of the sheet. In the preferred embodiment, the mat is formed of spring steel. A holder for the mat is formed of a planar sheet of plastic material with flaps formed in the holder to removably retain the cutting mat in position on the holder.

Growing community of inventors

Andover, CT, United States of America

Sean P McGee