COMBUSTOR COOLING STRUCTURE

摘要

The invention refers to a transition piece of a combustor of a gas turbine including an impingement cooling zone, a sequential disposed liner having at least one cooling arrangement and a closing plate with respect to the sequential disposed liner. The sequential disposed liner has a cooling channel structure. The cooling channel structure forms a closed loop cooling scheme or a quasi-closed loop cooling scheme. The cooling channel structure is operatively connected to a cooling medium to cool at least one part of the sequential disposed liner.

主权项

1. A transition piece of a combustor of a gas turbine, comprising:
an impingement cooling zone, and a sequential disposed liner having at least one cooling arrangement, a closing plate with respect to the sequential disposed liner, wherein the sequential disposed liner having a cooling channel structure, wherein the cooling channel structure forms a closed loop cooling scheme or a quasi-closed loop cooling scheme, and wherein the cooling channel structure being operatively connected to a cooling medium to cool at least one part of the sequential disposed liner.