| 摘要 |
In the case of a gas turbine plant with a combustion chamber (24) and a bypass housing (16) which connects the combustion chamber (24) to the fuel gas inlet (18) of the gas turbine, the bypass housing (16) has rows (38) of cooling air apertures (40). These rows (38) run transversely to the direction of flow (46) of the fuel gases close to the wall and are distributed one after another over the entire flow path of the fuel gases. In this way they enclose at least some areas of the internal chamber (44) of the bypass housing (16). By means of this arrangement the formation of a stable cooling air film is achieved on the inside of the bypass housing, thereby improving the cooling. <IMAGE>
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