| 摘要 |
<p>PROBLEM TO BE SOLVED: To realize a closed loop cooling scheme or a quasi-closed loop cooling scheme to cool at least one combustor of a combustion turbine interface.SOLUTION: The invention refers to a transition piece 100 of a combustor of a gas turbine including: an impingement cooling zone 200; a sequential disposed liner 300 having at least one cooling arrangement; and a closing plate 500 with respect to the sequential disposed liner. The sequential disposed liner has a cooling channel structure 400. The cooling channel structure 400 forms a closed loop cooling scheme or a quasi-closed loop cooling scheme. The cooling channel structure 400 is operatively connected to a cooling medium to cool at least one part of the sequential disposed liner.</p> |
