General Electric Company

Cummins Inc.

Cummins Engine Company, Inc.

Exxonmobil Upstream Research Company

Ge Infrastructure Technology, LLC

Scott Robert Simmons

Donald Mark Bailey

Charles Lewis Davis, Iii

Stephen Robert Thomas

Kevin Weston McMahan

Geoffrey David Myers

Wei A Chen

Ronald James Chila

Anthony A Shaull

John D Lane

Steven E Ferdon

Patrick Benedict Melton

David L Buchanan

Russell Pierson DeForest

Todd M Wieland

Bela Doszpoly

Marcus Byron Huffman

Matthew B State

James E Denton

Anthony A Cooper

Thomas Edward Johnson

Gregory Allen Boardman

Donald J Benson

David Martin Johnson

Stanley Kevin Widener

John D Crofts

Johnie Franklin McConnaughhay

Ilya Aleksandrovich Slobodyanskiy

David M Rix

Almaz Kamilevich Valeev

Jesse Edwin Trout

Mark S Cavanagh

Igor Petrovich Sidko

Joel Meador Hall

David Kenton Felling

Wesley R Thayer

Bradford David Borchert

Leonid Yul'evich Ginesin

Larry Lou Thomas

Sergey Adolfovich Oskin

Xiomara Irizarry-Rosado

Gordon K Butler

Alfred R Nerz

Frank R Hunt

Kevin Weston Mcmahan

Russell Deforest

Charles Lewis Davis Iii

Wei Chen

Charles Lewis Iii Davis

Patrick Bendict Melton

A vibration damper for a fuel conduit of a gas turbine combustor includes a mounting portion and a damping portion. The mounting portion is secured to the fuel conduit, and the damping portion includes a stack of damping washers, a bushing on top of the stack of damping washers, a spring clip secured around the stack of damping washers and the bushing, and a shoulder bolt disposed through the bushing and the stack of damping washers and engaged to the mounting portion.

Vibration damper for fluid conduit of gas turbine combustor

In accordance with an embodiment of the disclosure, a system includes a combustor liner disposed about a combustion chamber of a combustor of a gas turbine system. The combustor liner includes an inner wall portion exposed to the combustion chamber, an outer wall portion disposed about the inner wall portion, and multiple channels between the inner and outer wall portions of the combustor liner. Each channel of the multiple channels is configured to direct a coolant along the combustor liner to convectively cool the combustor liner, and each channel of the multiple channels includes a cross-sectional area that progressively changes along a length of each channel of the plurality of channels.

Systems and methods for variable microchannel combustor liner cooling

An aft frame assembly for a gas turbine transition piece includes a main body having an upstream facing surface and a downstream facing surface. A plurality of feed hole inlets are located on the upstream facing surface. The feed hole inlets are coupled to a plurality of cooling channels that pass through the main body towards the downstream facing surface. A plurality of plenums are located in or near the downstream facing surface, and each cooling channel is connected to and terminates in one of the plenums. The cooling channels are inputs to the plenums. A plurality of microchannel cooling slots are formed in or near the downstream facing surface, and each microchannel cooling slot is connected to one of the plenums. The microchannel cooling slots are outputs of the plenums. Two or more cooling channels and two or more microchannel cooling slots are connected to one of the plenums.

Aft frame assembly for gas turbine transition piece

A combustor cap assembly includes a cap plate and a cover panel. The cap plate defines an outer perimeter and fuel nozzle openings disposed through the cap plate. The cap plate has a hot side, and the cover panel has a cold side, which is attached to the hot side of the cap plate. The hot side of the cap plate and/or the cold side of the cover panel define a plurality of cooling microchannels extending in a transverse direction relative to a centerline of the combustor cap assembly. A first microchannel has a first channel outlet disposed along the outer perimeter of the cap plate, and/or a second microchannel has a second channel outlet disposed within one of the plurality of fuel nozzle openings. The cover panel may be coated with a bond coat and a thermal barrier coating.

Combustor cap assembly with cooling microchannels

An aft frame assembly has a main body with an upstream facing surface, a downstream facing surface, a radially outer facing surface and a radially inner facing surface. Feed hole inlets are located on the upstream facing surface and radially outward of the outer sleeve so that the feed hole inlets are located to receive input from a high pressure plenum. The feed hole inlets are coupled to cooling channels that pass through the main body. Microchannels are formed in or near the radially inner facing surface and the downstream facing surface. The cooling channels are connected to and terminate in the microchannels. Exit holes are connected to the plurality of microchannels, and the exit holes are located radially outward of the transition piece and radially inward of the outer sleeve. The exit holes are located to exhaust into the cooling annulus.

AFT frame assembly for gas turbine transition piece

An aft frame assembly for a gas turbine transition piece has a main body with an upstream facing surface, a downstream facing surface, a radially outer facing surface and a radially inner facing surface. A plurality of feed hole inlets are located on the upstream facing surface. Each of the feed hole inlets are coupled to one of a plurality of cooling channels passing through the main body towards the radially inner facing surface. A plurality of microchannels are formed near the radially inner facing surface and extend at least partially along the downstream facing surface. The cooling channels are connected to and terminate in the microchannels. A pre-sintered preform is located on the radially inner facing surface of the main body.

A combustor cap module is provided with a retention system to facilitate assembly and disassembly. The combustor cap module further includes a cap face assembly having a cooling plate; a cylindrical sleeve including a connecting surface for attaching the cap face assembly to the retention assembly; and a coupling member mounted in a downstream fuel nozzle opening in the cooling plate. The retention system includes a support plate having an inner panel that defines an upstream fuel nozzle opening. The coupling member extends through the upstream fuel nozzle opening, such that its upstream end extends upstream of the support plate. A retaining ring at least partially encircles the upstream end of the coupling member and is engaged by a spring plate that is removably secured to the support plate at multiple locations. A method for assembling a combustor cap module is also provided.

Combustor cap module and retention system therefor

A system having a gas turbine engine is provided. The gas turbine engine includes a turbine and a combustor coupled to the turbine. The combustor includes a combustion chamber, one or more fuel nozzles upstream from the combustion chamber, and a head end having an end cover assembly. The end cover assembly includes an oxidant inlet configured to receive an oxidant flow, a central oxidant passage, and at least one fuel supply passage. The central oxidant passage is in fluid communication with the oxidant inlet, and the central oxidant passage is configured to route the oxidant flow to the one or more fuel nozzles. The at least one fuel supply passage is configured to receive a fuel flow and route the fuel flow into the one or more fuel nozzles.

Systems and methods for high volumetric oxidant flow in gas turbine engine with exhaust gas recirculation

A method of providing fuel to a combustion chamber of a combustion can in a radial direction of the combustion can, and a micromixer cap having axially arranged fuel stages that receive fuel from a radial direction, the fuel stages supplies fuel to different radial zones of micromixer tubes arranged in a concentric configuration to provide a mixture of fuel and air for combustion.

Axially staged micromixer cap

A fuel nozzle assembly for a gas turbine engine includes a flange and a pre-mix tube. The flange includes a first end that is configured to couple to an end cover of the combustor, and a second end that is opposite said first end. The pre-mix tube is coupled at a first end to the flange second end. The flange and the pre-mix tube are fabricated to operate at a natural frequency that is different from an operating frequency of the gas turbine engine.

Fuel nozzle assembly for a gas turbine engine

A fuel pump is disclosed wherein a substantially cylindrical plunger bore is provided with an annular drain groove fluidically coupled to a drain duct. A pump plunger is driven by a drive system located in a separate mechanical compartment that holds a reservoir of lubricating oil. An annular seal is provided adjacent the drain groove substantially at the end of the bore and retained in position by a seal support. Exemplary embodiments provide the drain groove and seal as being positioned immediately adjacent one another so that the seal forms a lower wall of the drain groove.

Fuel pump

A transition piece seal assembly includes a first seal, and a second seal joined to the first seal. The second seal being spaced from the first seal to define a coolant passage.

Transition piece seal assembly for a turbomachine

A combustor nozzle includes a downstream surface having an axial centerline. A plurality of passages through the downstream surface provide fluid communication through the downstream surface, and a downstream section of each passage has at least one of a frusto-conical or frusto-spherical shape. A method for modifying a combustor nozzle includes machining a downstream side of a body to remove a recast surface in a plurality of passages that provide fluid communication through the body. The method may further include machining a downstream section in each passage to form at least one of a frusto-conical or frusto-spherical surface in each passage proximate to the downstream side of the body.

Combustor nozzle and method for modifying the combustor nozzle

A combustor nozzle includes a downstream surface having an axial centerline. A plurality of passages extend through the downstream surface and provide fluid communication through the downstream surface. A plurality of slits are included in the downstream surface, and each slit connects to at least two passages. A method for modifying a combustor nozzle includes machining a plurality of slits in a downstream side of a body. The method further includes connecting each slit to at least two passages that pass through the body.

A fluid control device for use in a high pressure fluid system, the device including a device body with a cavity and a high pressure circuit, a plunger positioned for reciprocal movement in the cavity, and a leakage reduction cap mounted to the plunger for reducing fluid leakage flow. In one implementation, the leakage reduction cap includes a flexible portion positioned between the device body and the plunger, and defining an annular clearance gap between the leakage reduction cap and the device body. The flexible portion of the leakage reduction cap resiliently flexes radially outwardly in response to fluid pressure forces to reduce the annular clearance gap so as to minimize fluid leakage flow through the annular clearance gap.

Low leakage plunger assembly for a high pressure fluid system

Growing community of inventors

Simpsonville, SC, United States of America

Scott Robert Simmons