General Electric Company

Other

Robert Paul Czachor

Michael Leon Barron

Christopher Charles Glynn

Scott Patrick Ryczek

Richard William Albrecht, Jr

George A Durgin

Tod Kenneth Bosel

George Elliott Moore

Robert J Hemmelgarn

Michael T Bonnoitt

Christopher George Housley

Harris Daniel Abramson

Andre Christopher Urso

Robert E Jones

John Alan Manteiga

Steven Alan Ross

Thomas Tracy Wallace

Steven Joseph Lohmueller

David Bruce Patterson

Robert Eugene Kraft

Norman Douglas Lathrop

Shesh Krishna Srivatsa

Daniel Edward Wines

James Anthony Groeschen

William Carl Ruehr

Donald L Bellia

Eric E Baehre

Thomas L MacLean

Joseph Charles Kulesa

Steven Andrew Strang

Brian J Humke

Claude Henry Chauvette

Gerard P Kroger

Jason Paul Hoppa

Michael Charles Eckert

Grzegorz Mlynski

Paul Michael Smith

Sugato Bhattacharjee

Laura A Iyer

Sifarat S Husain

Michael R Hesselbrock

Kelley Parker Brown

Eric Robert Oswald

Jeffrey Paul Darnell

George Albert Durgin

A tripod joint assembly for connecting first and second overlapping panel segments of a flowpath liner in a gas turbine engine includes a threaded fastener extending through an opening in the first overlapping panel segment and adjacent to an outer segment edge of the second overlapping panel segment disposed on the first overlapping segment. The assembly further includes a tripod plate having first and second plate edges and an access hole therebetween. The first plate edge contacts the first overlapping panel segment, the second plate edge contacts the outer segment edge of the second overlapping panel segment. The access hole is disposed around the threaded fastener. First and second washers are disposed around the threaded fastener, the first washer on the tripod plate opposite to the overlapping panel segments, and the second washer on the first washer opposite to the tripod plate. A threaded locknut secures the assembly.

Wear resistant frame liner joint assembly for a gas turbine engine

A method for assembling a combustor for use in a turbine engine is provided. The method includes providing at least one support leg, forming at least one opening in the support leg, wherein the at least one opening has a perimeter defined only by a plurality of non-linear segments, and coupling the support leg to the combustor.

Method and apparatus for reducing stresses induced to combustor assemblies

A method for assembling a gas turbine engine includes coupling a first structure within the gas turbine engine, wherein the first structure includes a plurality of sockets extending from a radially outer surface of the first structure, and coupling a second structure to the first structure by inserting a radial pin through the second structure and into each respective socket such that the first structure is aligned axially, circumferentially, and with respect to an engine centerline axis extending through the gas turbine engine, where the position of the pins relative to the second structure is adjustable.

Methods and apparatuses for assembling a gas turbine engine

A method for assembling a gas turbine engine includes coupling an axisymmetric structure within the gas turbine engine, wherein the axisymmetric structure includes at least one mounting bushing extending from a radially outer surface of the axisymmetric structure, and inserting a pin having a crowned surface at least partially into the mounting bushing such that the pin provides both axial and tangential support to the axisymmetric structure, and securing the pin to the gas turbine engine utilizing a retaining assembly.

A method for assembling a gas turbine engine assembly that includes mounting a gas turbine engine including an inlet and an exhaust within a module that includes an inlet area, an exhaust area, and an engine area extending therebetween, such that the gas turbine engine is housed within the module, coupling a first deflector within the module engine area such that when cooling air is channeled past the deflector, the deflector induces a substantially helically-shaped cooling air flowpath around a periphery of the gas turbine engine, and coupling an exhaust duct to an outlet of the module exhaust area.

Methods and apparatus for cooling gas turbine engines

A gas turbine engine component has an annular flange arm, a backing plate mounted to the flange arm and a bypass circuit formed between the flange arm and the backing plate. The bypass circuit includes one or more channels formed in one of the flange arm or the backing plate. When more than one channels are used, at least one connecting slot is provided between the channels. At least one inlet passage extends through the flange arm in fluid communication with the forward-most channel, and at least one outlet slot is formed between the flange arm and the backing plate in fluid communication with the aft-most channel.

Gas turbine engine component having bypass circuit

A method for exchanging heat between a first fluid and a second fluid. The method includes providing a heat exchanger having a stack of at least two layers of support structures, wherein each support structure layer is formed from a lattice of support members, and substantially fluidly separating the at least two support structure layers using at least one barrier such that each layer defines a fluid passageway. The method also includes directing a flow of first fluid through a first of the fluid passageways, and directing a flow of second fluid through a second of the fluid passageways that is adjacent the first fluid passageway to facilitate exchanging heat between the first and second fluids.

Methods and apparatus for exchanging heat

A turbine assembly includes a shroud for being mounted around a last stage of the low pressure turbine rotor. The shroud includes an arcuate body having spaced-apart forward and aft ends and spaced-apart circumferential ends. Attachments are provided for securing the shroud body to the surrounding engine case. An arcuate extension member protrudes rearward from the aft end of the shroud body. The extension member has an inner surface which defines a portion of the gas flowpath through the engine. Seals may be provided to prevent leakage between adjacent shroud segments. The shroud is especially useful for protecting a downstream turbine frame from debris and thermal stress.

Turbine assembly and turbine shroud therefor

A gas turbine engine strut segment includes a strut, which may be hollow, extending radially between co-annular radially inner and outer platforms, axially spaced apart inner platform flanges extending radially inwardly from the inner platform, and axially spaced apart outer platform flanges extending radially outwardly from the inner platform. At least one inner set of coaxial tapered inner holes extend axially through the inner platform flanges and at least one outer set of coaxial tapered outer holes extend axially through the outer platform flanges. The inner set of coaxial inner holes define an inner conical surface and the outer set of coaxial outer holes define an outer conical surface. Each of the axial spaced apart platform flanges may be circumferentially continuous or scalloped having spaced circumferentially apart lugs. The strut may have two inner sets of coaxial tapered inner and outer holes extending axially through the inner and outer platform flanges, respectively.

Gas turbine engine frame having struts connected to rings with morse pins

An annular air baffle disposed in a cavity of a rotatable gas turbine engine part includes an annular split ring supporting a plurality of circumferentially spaced apart fins. The cavity is closed at a radially outer diameter and open at a radially inner diameter of the part. The ring and the fins may be integrally formed in one piece. The fins may have common surfaces with the ring and the common surfaces may be circular cross-sectional surfaces of the ring and radially outer rounded corners of the fins. The fins may have triangular cross-sectional shapes with first, second, and third sides, rounded first radially inner corners between the first and second sides, rounded second radially inner corners between the second and third sides, and the radially outer rounded corners between the first and third sides. The fins may extend radially inwardly from the annular split ring.

Gas turbine engine air baffle for a rotating cavity

A method for assembling a gas turbine engine includes coupling an outer structure within the gas turbine engine, wherein the outer structure includes a socket extending from a radially inner surface of the outer structure, and coupling an inner structure to the outer structure by inserting a radial pin through the inner structure and into the socket such that the inner structure is aligned axially, circumferentially, and with respect to an engine centerline axis extending through the gas turbine engine.

Methods and apparatus for assembling gas turbine engines

A turbomachine frame member including an annular inner hub and a concentric annular outer casing that is spaced radially outwardly from the inner hub to define an annular flow passageway. A plurality of substantially radially-extending, circumferentially-spaced struts interconnect the inner hub and outer casing. The struts are connected to the outer casing by respective pairs of connecting bolts that pass through the outer casing and into the struts to engage barrel nuts.

Turbomachine frame structure

A stiffener system includes a stiffener and a fastener means. The stiffener includes an extruded body that includes a plurality of projections. The stiffener couples to the apparatus to facilitate increasing a structural integrity of the apparatus. The fastener means secures the stiffener to the apparatus.

Method and apparatus for stiffening and apparatus

A gas turbine engine includes a non-rotatable member that includes a honeycomb seal that reduces wear to rotor seal teeth disposed within the gas turbine engine. The gas turbine engine also includes a rotatable annular member including a sealing assembly disposed between rotor and stator components. The rotatable annular member includes seal teeth that extend radially outward from the rotatable annular member. The stator components include a non-rotatable member that includes a honeycomb seal that extends radially inward. The honeycomb seal is fabricated from a material that has a melting temperature less than approximately 2000&deg; F.

Methods and apparatus for reducing seal teeth wear

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Cincinnati, OH, United States of America

Robert Paul Czachor