Patent ID: 8220246

Claim:
A crossfire tube assembly for connecting adjacent combustion cans in a gas turbine, comprising: a first tube segment having a first end and an opposite female end; a second tube segment having a first end and an opposite male end fitted concentrically within said female end with an overlap region between said female end and said male end; each of said first ends of said first and second tube segments securing to a liner of a respective combustion can; a first impingement sleeve extending from said female end to said first end of said first tube segment, and a second impingement sleeve extending from said female end in an opposite direction to said first end of said second tube segment, said impingement sleeves having a plurality of metering holes defined therein; concentric cavities defined between said first and second impingement sleeves and said first and second tube segments, respectively; and wherein combustion cooling air is directed through said impingement sleeves and flows axially along said concentric cavities, the combustion cooling air venting from said cavities into an axial combustion airflow stream between the respective combustion can liners and sleeves.