United Technologies Corporation

Raytheon Technologies Corporation

Rtx Corporation

Joey Wong

Conway Chuong

Jose E Ruberte Sanchez

Timothy S Snyder

Jonathan Jeffery Eastwood

Ross Wilson

Kevin Joseph Low

Robert M Sonntag

Albert K Cheung

Russell B Hanson

Christopher J Peters

Tara D'Ambruoso

Dana P Stewart

Mark J Ricciardo

Michael A Mike

Peter Chen

David N Waxman

Steven Wayne Burd

Jose R Paulino

Zhijun Zheng

Randal G McKinney

George F Titterton, Iii

Constantino V Loffredo

Caroline Karanian

Chris J Niggemeier

Fernando K Grant

Christpher J Peters

Tara L D'AMBRUOSO

A retention ring for a gas turbine engine according to an example of the present disclosure includes, among other things, a main body extending in a circumferential direction about an axis to establish a continuous hoop having a first diameter and a second diameter. The main body includes first and second circumferential faces along opposite sides of the main body. The first circumferential face is dimensioned to abut a gas turbine engine component. The main body includes at least one removal feature dimensioned to sever in response to engagement with a cutting tool. A method of assembly is also disclosed.

Retention ring with removal features for gas turbine engine

A fuel nozzle for a combustor a gas turbine engine includes a flange with a first locator.

Fuel nozzle for a gas turbine engine

A seal ring for a non-contact seal may comprise an annular body comprising a first side surface, a second side surface, an outer surface, and an inner surface, and a plurality of window openings disposed in the annular body. The plurality of window openings may be configured to provide access to the seal for installation of a melting member to secure the seal shoes in an outboard direction during installation.

Halo seal access window openings

A seal assembly includes a side ring and a cartridge. The side ring comprises an annular piece of solid material. The cartridge is affixed to the side ring and comprises a shoulder, a beam connected to and extending from the shoulder, a shoe attached to an end of the beam, and a rotary seal disposed on a bottom portion of the shoe.

Hydrostatic seal pinned cartridge

A non-contact seal assembly includes a plurality of seal shoes arranged about a centerline in an annular array, the seal shoes including a first seal shoe extending axially along the centerline between a first shoe end and a second shoe end. The non-contact seal assembly may comprise a seal base circumscribing axially offset from the annular array of the seal shoes. The non-contact seal assembly may further comprise a plurality of spring elements, each of the spring elements radially distal from and connecting to a respective one of the seal shoes, and each of the plurality of spring elements is axially adjacent to the seal base.

Hydrostatic non-contact seal with offset outer ring

A gas turbine engine includes a bushing that is non-round in cross-section, the bushing receivable within an aperture. A fastener passes through the bushing to retain a second component to a third component with respect to the first component.

Alignment system and methodology to account for variation in a gas turbine engine

Aspects of the disclosure are directed to a floating, non-contact seal comprising: a shoe, and at least three beams, each beam having a first axial end and a second axial end, where the first axial ends are coupled to the shoe and the second axial ends are coupled to a ring structure. Aspects of the disclosure are directed to an engine comprising: a first structure, a second structure configured to rotate relative to the first structure, and a floating, non-contact seal that interfaces the first structure and the second structure, where the seal includes: a shoe, and at least three beams, where each beam has a first axial end and a second axial end, where the first axial ends are coupled to the shoe and the second axial ends are coupled to a ring structure.

Floating, non-contact seal with at least three beams

A gas turbine engine includes a fan, a compressor section, a combustor, a fan drive gear system, and a turbine section coupled to drive the fan through the gear system. The combustor includes an annular outer shell and an annular inner shell that define an annular combustion chamber. There is a bulkhead in the annular combustion chamber, and an annular heat shield is mounted on the bulkhead. The annular heat shield includes a segment that has a forward face and an aft face, a circumferential outer side and a circumferential inner side, a central orifice between the forward face and the aft face, a lip projecting from the forward face around the central orifice, a rail projecting from the forward face, and a plurality of through-holes between the rail and the lip. The rail contacts the bulkhead to define a cavity bounded by the rail, the lip, and the bulkhead.

Heat shield for a combustor

A seal assembly includes an annular base, a spring, a shoe, a first channel, a seal cover, and a seal. The spring includes a beam and is connected to the annular base. The shoe is disposed radially inward of the annular base and connected to the spring. The shoe includes an upstream portion, a downstream portion, and a lip connected to and extending radially outward from the upstream portion of the shoe. The spring extends from the annular base to the shoe. The first channel is positioned between the shoe and the beam of the spring. The seal is disposed between the seal cover and the shoe such that a downstream face of the seal is in contact with an upstream face of the shoe.

Floating non-contact seal vertical lip

Aspects of the disclosure are directed to a floating, non-contact seal comprising: a shoe, a first beam coupled to the shoe, and a second beam coupled to the shoe, where the first beam is oriented at a first angle with respect to the shoe, the first angle having a first value that is greater than five degrees. Aspects of the disclosure are directed to an engine comprising: a first structure, a second structure configured to rotate relative to the first structure, and a floating, non-contact seal that interfaces the first structure and the second structure, where the seal includes: a shoe, a first beam coupled to the shoe, and a second beam coupled to the shoe, where the first beam is oriented at a first angle with respect to the shoe, the first angle having a first value that is greater than five degrees.

Floating, non-contact seal with angled beams

A gas turbine engine includes a convex case section. The convex case section includes an upstream case portion having a first radius, a downstream case portion having a second radius, and an intermediate case portion between the upstream case portion and the downstream case portion. The intermediate case portion has a third radius larger than the first radius and the second radius. A tension rod extends from the upstream case portion to the downstream case portion.

Axial tension system for a gas turbine engine case

A combustor seal for use between a downstream end of a combustor and a turbine vane includes a seal body and a plurality of seal alignment features. The plurality of seal alignment features projects from the seal body. The seal alignment features are arranged such that there is only one alignment of the combustor seal with the turbine vane.

Combustor seal mistake-proofing for a gas turbine engine

Gas turbine engine systems involving I-beam struts are provided. In this regard, a representative strut assembly for a gas turbine engine includes a first I-beam strut having first and second flanges spaced from each other and interconnected by a web, the first strut exhibiting a twist along a length of the web.

Gas turbine engine systems involving I-beam struts

A system for providing a seal between a combustor and a turbine vane. The system includes a flange configured to extend radially from the combustor, and a seal. The flange includes a flange surface configured to face in an axial direction toward a surface of the vane. The seal is configured to be axially loaded between the flange surface and the surface of the vane.

Combustor seal system for a gas turbine engine

A seal sub-assembly may comprise a spacer, at least one secondary seal, and a secondary seal cover. At least a portion of the at least one secondary seal are located axially between the spacer and the secondary seal cover. The spacer is attached to the secondary seal cover. The spacer may comprise a first flange and a second flange. The at least one secondary seal may be located axially in line with and radially inward from the first flange. At least a portion of the secondary seal cover may be located axially in line with and radially inward from the second flange.

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Enfield, CT, United States of America

Joey Wong