United Technologies Corporation

Raytheon Technologies Corporation

Gary L Grogg

Eric Charles Mundell

Paul M Lutjen

Garth J Vdoviak, Jr

Thomas E Clark

Marshall Thayer

Christopher R Joe

Todd M LaPierre

Grace E Szymanski

Garth J Vdoviak

Dominic J Mongillo, Jr

Marc J Muldoon

Gregory E Reinhardt

Dmitriy A Romanov

Jeremy Drake

Blake J Luczak

James N Knapp

John D Wiedemer

Berci Cherpician

James L McClellan, Iv

Michael F Benamati

Jr Garth J Vdoviak

James L Mcclellan Iv

Garth Vdoviak

A component for a gas turbine engine includes a compartment housing that redirects oil from at least one passage in a rotational component onto a backside of a seal land.

Fluid-cooled seal arrangement for a gas turbine engine

Oil slinger systems include a seal runner comprising an annular radial member having a radius (R) and an outer axially extending member having an axial length (L) such that a ratio (L/R) is between 0.8 and 1.4, the annular radial member disposed at a first angle with respect to the outer axially extending member, a heat shield in mechanical communication with the seal runner, and a volume bounded by an outer face of the annular radial member and an inner face of the heat shield. Methods of radial convective cooling include pumping a cooling liquid through the oil slinger system and convectively cooling the oil slinger.

Oil slinger with convective cooling of radial surface

A shaft interlock system may have an a interlocking piston that translates a movable locking apparatus configured to interface with a turbine shaft having a fixed locking apparatus. The movable locking apparatus may engage and disengage the fixed locking apparatus. When the movable locking apparatus is engaged with the fixed locking apparatus, the turbine shaft is only able to turn in one direction. When the movable locking apparatus is disengaged from the fixed locking apparatus, the turbine shaft is able to turn in both directions. In this way, a turbine shaft can be prevented from reverse rotation.

Shaft interlock

An attachment interface assembly for a gas turbine engine has a component configured for attachment to an engine static structure. A fastener has a threaded body portion and an enlarged head portion. The threaded body portion is inserted through aligned holes in the component and engine static structure. A clip has a center opening that receives the threaded body portion such that the clip is positioned between the enlarged head portion and the component.

Heat shield mount configuration

A seal runner may have an inner annular member, an outer annular member, and a radial wall member joined to the inner annular member according to an angle and extending from the inner annular member to the outer annular member. The seal runner may be positioned axially along a shaft and a bearing may be positioned axially along the shaft such that it is radially between the inner annular member and the outer annular member. In this regard, the seal runner may resemble a 'C-shape.' A seal may interface with a seal land radially outboard of the outer annular member. Thus, the seal may be positioned axially near to the bearing so that the axial length of a shaft and accompanying bearing compartment hardware may be minimized.

Seal runner

A bearing housing may include a main body integrated with a bearing receiving portion. A bearing retention stop may extend from the main body and include a plurality of access cutouts for facilitating the removal of a bearing from the bearing housing without causing damage to the bearing.

Bearing race removal

An improved film damper oil delivery pathway from an oil reservoir to a thin film fluidic damper is provided. An oil supply tube may be configured to mate to a bearing outer race. The bearing outer race may comprise internal oil flow circuit(s) configured to supply oil from the oil tube to the thin film damper for improved bearing compartment designs.

Bearing outer race oil supply for thin film fluidic damping

A flange arrangement for a gas turbine engine includes a case flange between a forward flange and an aft flange.

Triple flange arrangement for a gas turbine engine

According to one embodiment of this disclosure a core includes a first end and a second end spaced generally opposite from the first end. The core further includes a stacking axis defined between the first end and second end and a first toroidal structure located between the first end and the second end. The first toroidal structure includes a first passage extending through the first toroidal structure in a first direction that is perpendicular to and passes through the stacking axis. The core also includes a second toroidal structure located between the first toroidal structure and the second end. The second toroidal structure includes a second passage extending through the second toroidal structure in a second direction. The first direction and the second direction are oriented along the stacking axis at a non-zero degree angle with respect to each other.

Core component having toroidal structures

A gas turbine engine includes a service line interface that extends from an outer surface of a bearing support such that a heat shield is spaced from the outer surface. A method of mounting a heat shield to a gas turbine engine includes trapping a heat shield within a gapped overlap spaced from an outer surface of a bearing support.

Heatshield discourager seal for a gas turbine engine

An annular spring for a bearing assembly of gas turbine engine is provided. The annular spring includes a multiple of ligaments between an inner support and an outer support.

Annular spring for a bearing assembly of a gas turbine engine

The present disclosure relates generally to a dual oil supply tube for a gas turbine engine. The dual oil supply tube locates a scheduled damper supply tube inside a compartment oil supply tube which remains full while the engine is operating.

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South Berwick, ME, United States of America

Gary L Grogg