| 主权项 |
1. A transition piece assembly for a gas turbine comprising:
a transition piece having one end adapted for connection to a gas combustor and an opposite end adapted for connection to a first turbine stage; said transition piece having at least one external liner and at least one internal liner, and the internal liner forms the hot gas flow channel; wherein a first section of the transition piece assembly upstream of a first turbine stage having a plurality of cooling apertures; wherein cooling medium through the cooling apertures enters the plenum, which is created between external and internal liners and a cooling medium flows along at least the first section of the transition piece assembly; wherein at least one second section upstream of the first section with respect to the hot gas flow having at least one additional air inlet system; wherein the additional air inlet system of the second section, which comprises at least one internal air plenum and at least one external air plenum, is designed in the manner that the cooling medium is discharged into the air plenum created between external and internal liners in two different directions with respect to the hot gas flow, namely one downstream direction towards the turbine and one upstream direction toward the combustor; wherein a portion of the cooling medium flows downstream in the direction of a first stage of the turbine, and the remaining portion of the cooling medium flows upstream in the direction of a combustor plenum; wherein the cooling medium portion is mixed with a cooling medium flow coming from the first section and the cooling medium mass out of that is directed via external air plenum to the combustor plenum. |
