United Technologies Corporation

Raytheon Technologies Corporation

Other

Rtx Corporation

Russell B Hanson

Paul F Croteau

Matthew Andrew Hough

John S Tu

Kevin Joseph Low

Stephen C Harmon

Joshua C Rathgeb

Michael Winter

Joey Wong

James P Bangerter

Jose E Ruberte Sanchez

Dave J Hyland

Mark J Ricciardo

Wallace A Hanson

Frank J Cunha

Zhongtao Dai

Lexia Kironn

Paul K Sanchez

Andreas Sadil

Nurhak Erbas-Sen

Gary J Dillard

Thomas R Russo

Eric D Gray

Christopher Drake

Kristin Kopp-Vaughan

Jonathan M Jause

George F Titterton, Iii

Nathan K Galle

Milton A Fong

Brian K Richardson

Jeffrey D Dickens

Raymond Lamoureux

Michael D Collier

Jose E Ruperte Sanchez

Salvatore Siciliano

Dave Hyland

George F Iii Titterton

A diffuser case support structure for a gas turbine engine includes a fairing disposed circumferentially about a longitudinal axis. The fairing defines a plurality of passages circumferentially spaced apart and forming at least a portion of a fluid path between a compressor and a combustor of the gas turbine engine. A diffuser frame includes a plurality of struts. Each of the plurality of struts is disposed between a pair of adjacent passages of the plurality of passages. The diffuser frame is configured to couple an inner diffuser case to an outer diffuser case. A sliding joint is formed between the fairing and the diffuser frame, the sliding joint comprising a fastener extending generally axially through an aperture disposed in the fairing.

Diffuser case support structure

A diffuser case assembly for a gas turbine engine includes a fairing disposed circumferentially about a longitudinal axis. The fairing defines a plurality of passages circumferentially spaced apart and forming at least a portion of a fluid path between a compressor and a combustor of the gas turbine engine. A diffuser frame includes a plurality of struts. Each of the plurality of struts is disposed between a pair of adjacent passages of the plurality of passages. The diffuser frame is configured to couple an inner diffuser case to an outer diffuser case.

Diffuser case assembly

A nut strip assembly is provided that includes a carrier and a plurality of nuts. The carrier includes a base, a plurality of first tabs and a plurality of second tabs. The base is configured with a plurality of apertures. Each of the first tabs is connected to and project out from a first side of the base. Each of the second tabs is connected to and projects out from a second side of the base. The nuts are secured to the carrier. Each of the nuts are aligned with a respective one of the apertures. Each of the nuts is captured between the base and a respective one of the first tabs. Each of the nuts captured between the base and a respective one of the second tabs.

Nut strip assembly with array of captured nuts

A diffuser case support structure for a gas turbine engine is disclosed. The diffuser case support structure includes a fairing disposed circumferentially about a longitudinal axis. The fairing forms at least a portion of a fluid path between a compressor and a combustor of the gas turbine engine. The fairing defines a plurality of apertures extending through the fairing. At least one spoke extends through at least one respective aperture of the plurality of apertures. The at least one spoke is configured to couple an inner diffuser case and an outer diffuser case of the gas turbine engine.

A system for an engine defined about an axial centerline includes an inner case that includes a bushing, a duct case radially outward of the inner case with respect to the axial centerline, and a seal located on the duct case. The system further includes a borescope plug assembly that traverses the seal and the bushing in mounting to the inner case. The borescope plug assembly includes a spring, a housing sleeve, and a washer sleeve at least partially nested within the housing sleeve. The spring is isolated from the seal by the housing sleeve and the washer sleeve such that the spring is contact-free with respect to the seal.

Borescope plug assembly

A pre-diffuser fairing for a gas turbine engine is disclosed. In various embodiments, the pre-diffuser fairing includes a first side wall, a first radially inward portion and a first radially outward portion and a second side wall, a second radially inward portion and a second radially outward portion. The first side wall and the second side wall are spaced apart to form a cavity configured to receive a strut.

Thermally isolated combustor pre-diffuser

A wall assembly for a combustor of a gas turbine engine is provided. The wall assembly includes a support shell with a contoured region to define at least one convergent passage between the support shell and a multiple of liner panels. A method of cooling a wall assembly for a combustor of a gas turbine engine is also provided. This method includes a step of directing cooling air into at least one convergent passage between the support shell and a multiple of liner panels.

Gas turbine engine wall assembly with support shell contour regions

An assembly for a turbine engine includes a combustor bulkhead, a swirler and a mounting strap. The swirler includes a mounting lug and a tubular swirler body that extends along an axis. The mounting lug projects radially out from the swirler body. The mounting strap is attached to the combustor bulkhead. The mounting lug is axially restrained between the combustor bulkhead and the mounting strap.

Swirler assembly for a turbine engine

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

An iso-grid composite component according to an exemplary aspect of the present disclosure includes a spacer transverse to a uni-tape ply bundle, the spacer interrupted by the uni-tape ply bundle.

Iso-grid composite component

A wall assembly is provided for a gas turbine engine. This wall assembly includes a support shell with a contoured region; and a multiple of liner panels mounted to the support shell. At least one of the multiple of liner panels includes an end rail. The contoured region is deformable to selectively contact at least a portion of the end rail. A method of assembling a wall assembly within a gas turbine engine is also provided. This method includes locating a stud that extends from a cold side of a liner panel through a support shell; and attaching a fastener onto the stud to at least partially close a gap defined between the panel and shell.

Gas turbine engine wall assembly interface

A combustor floatwall panel includes a stack of layers of a sintered material forming in the aggregate a panel, an attachment stud, and a cooling flow passageway. The panel has a first surface and a second surface parallel to the first surface. The attachment stud projects from the second surface. The cooling flow passageway includes a feeder hole extending through the attachment stud, and at least one effusion cooling hole extending to the first surface. The effusion cooling hole is fluidly connected to the feeder hole. The effusion cooling hole extends along a first axis where the effusion cooling hole meets the first surface. The feeder hole extends along a second axis. The first axis is at a first angle relative to the first surface. The second axis is at a second angle relative to the first surface. The second angle is greater than the first angle.

Attachment stud on a combustor floatwall panel with internal cooling holes

An annular seal includes an annular outer casing, a plurality of seal segments, and a plurality of spring components. The plurality of seal segments is coupled to the annular outer casing to cumulatively form an annular sealing surface, the annular sealing surface is configured to face a rotating structure to inhibit fluid leakage between the rotating structure and the annular sealing surface, and each seal segment of the plurality of seal segments is configured for independent radial movement relative to other seal segments of the plurality of seal segments. In various embodiments, the plurality of spring components are configured to bias the plurality of seal segments relative to the radial movement.

Segmented annular seal

A fuel injector component includes a body, an elongate void and a plurality of bores. The body has a first surface and a second surface. The elongate void is enclosed by the body and is integrally formed between portions of the body defining the first surface and the second surface. The plurality of bores extends into the second surface to intersect the elongate void. A process for making a fuel injector component includes building an injector component body having a void and a plurality of ports connected to the void using an additive manufacturing process that utilizes a powdered building material, and removing residual powdered building material from void through the plurality of ports.

Hollow-wall heat shield for fuel injector component

A method of defining a rib structure within an iso-grid composite component according to an exemplary aspect of the present disclosure includes, among other things, defining a first rib at least partially with a uni-tape ply bundle at a first level, the uni-tape ply bundle including uni-tape plies and a first spacer ply, and defining a second rib transverse to the first rib at least partially with a spacer at the first level, the spacer including a second, different spacer ply, the spacer transverse to the uni-tape ply bundle such that the spacer is interrupted by the uni-tape ply bundle.

Growing community of inventors

Jupiter, FL, United States of America

Russell B Hanson