System and method for barrier in passage of combustor of gas turbine engine with exhaust gas recirculation
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United States of America Patent
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Feb 27, 2018
Issued Date -
N/A
app pub date -
Jul 28, 2014
filing date -
Jul 30, 2013
priority date (Note) -
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Abstract
In one embodiment, a system includes a turbine combustor having a combustor liner disposed about a combustion chamber, a head end upstream of the combustion chamber relative to a downstream direction of a flow of combustion gases through the combustion chamber, a flow sleeve disposed at an offset about the combustor liner to define a passage, and a barrier within the passage. The head end is configured to direct an oxidant flow and a first fuel flow toward the combustion chamber. The passage is configured to direct a gas flow toward the head end and to direct a portion of the oxidant flow toward a turbine end of the turbine combustor. The gas flow includes a substantially inert gas. The barrier is configured to block the portion of the oxidant flow toward the turbine end and to block the gas flow toward the head end within the passage.
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