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

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United States of America Patent

PATENT NO 10788212
APP PUB NO 20160201916A1
SERIAL NO

14992827

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ATTORNEY / AGENT: (SPONSORED)

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Abstract

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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.

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Patent Owner(s)

  • GENERAL ELECTRIC COMPANY; EXXONMOBIL UPSTREAM RESEARCH COMPANY

International Classification(s)

Inventor(s)

Inventor Name Address # of filed Patents Total Citations
Allen, Jonathan Kay Simpsonville, US 4 16
Borchert, Bradford David Bellingham, US 5 23
Kazakis, Michael V Roebuck, US 25 393
Sidko, Igor Petrovich Moscow, RU 6 36
Slobodyanskiy, Ilya Aleksandrovich Simpsonville, US 33 583
Trout, Jesse Edwin Simpsonville, US 7 52

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