General Electric Company

Exxonmobil Upstream Research Company

Jonathan Kay Allen

Ilya Aleksandrovich Slobodyanskiy

Jesse Edwin Trout

Igor Petrovich Sidko

Bradford David Borchert

Almaz Kamilevich Valeev

Patrick Benedict Melton

Lucas John Stoia

Richard Martin DiCintio

Michael V Kazakis

Keith Cletus Belsom

Ronnie Ray Pentecost

Brandon Taylor Overby

Kyle Eric Benson

Matthew Eugene Roberts

Leonid Yul'evich Ginesin

Andrey Pavlovich Subbota

Richard Martin Dicintio

Jesseedwin Trout

Almaz Valeev

A system includes a turbine combustor. The turbine combustor has a combustor liner disposed about a combustion chamber, a flow sleeve, and a radial passageway. The flow sleeve disposed at an offset about the combustor liner to define a passage, wherein the passage is configured to direct an exhaust gas flow toward a head end of the turbine combustor. The radial passageway extends between the flow sleeve and the combustor liner, and the radial passageway is configured to isolate an oxidant flow through the radial passageway from the exhaust gas flow through the passage for a first operating condition and a second operating condition of the turbine combustor. The offset between the combustor liner and the flow sleeve at the first operating condition is greater than the offset between the combustor liner and the flow sleeve at the second operating condition.

System and method for an oxidant passageway in a gas turbine system with exhaust gas recirculation

A system includes a turbine combustor having a first volume configured to receive a combustion fluid and to direct the combustion fluid into a combustion chamber. The turbine combustor includes a second volume configured to receive a first flow of an exhaust gas and to direct the first flow of the exhaust gas into the combustion chamber. The turbine combustor also includes a third volume disposed axially downstream from the first volume and circumferentially about the second volume. The third volume is configured to receive a second flow of the exhaust gas and to direct the second flow of the exhaust gas out of the turbine combustor via an extraction outlet, and the third volume is isolated from the first volume and from the second volume.

Turbine system with exhaust gas recirculation, separation and extraction

A system includes a turbine combustor having a first volume configured to receive a combustion fluid and to direct the combustion fluid into a combustion chamber and a second volume configured to receive a first flow of an exhaust gas. The second volume is configured to direct a first portion of the first flow of the exhaust gas into the combustion chamber and to direct a second portion of the first flow of the exhaust gas into a third volume isolated from the first volume. The third volume is in fluid communication with an extraction conduit that is configured to direct the second portion of the first flow of the exhaust gas out of the turbine combustor.

A crossfire tube assembly between adjacent combustors includes a first sleeve adapted to provide fluid communication from a first combustor and a second sleeve adapted to connect to provide fluid communication from a second combustor. The second sleeve extends at least partially inside the first sleeve. A bias is between the first and second sleeves.

Crossfire tube assembly with tube bias between adjacent combustors

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Simpsonville, SC, United States of America

Jonathan Kay Allen