Patent ID: 8397514

Claim:
A system, comprising: a gas turbine combustor, comprising: a combustion liner disposed about a combustion region; a flow sleeve disposed about the combustion liner; an air passage extending between the combustion liner and the flow sleeve into a head end region; a fuel injector disposed along the air passage to inject fuel into the air passage; a liner mount disposed along the air passage, wherein the liner mount extends between the combustion liner and the flow sleeve; and a crossfire tube disposed along the air passage, wherein the crossfire tube extends between the combustion liner and the flow sleeve, wherein the fuel injector, the liner mount, and the crossfire tube are in line with one another in a flow enhancing arrangement along a common axis in an axial direction relative to an axis of the gas turbine combustor, wherein the flow enhancing arrangement reduces an air flow disturbance caused by the fuel injector, the liner mount, and the crossfire tube.