| 摘要 |
Disclosed is a gas turbine (10) in which a first plurality of burners (22a, b, c) that are regularly and concentrically arranged relative to the axis of rotation conducts hot gas (12) into a turbine through an associated combustion chamber outlet (11). A second plurality of guide vanes (15; 15a, b, c, d) is arranged in a ring at the inlet of the turbine, at a regular distance around the axis of rotation. Cooling ports through which cooling air is injected into the hot gas flow at the combustion chamber outlet (11) are distributed around the circumference. In order to improve the flow conditions in the hot gas in such a gas turbine, the cooling ports are subdivided into first groups of cooling ports (20a, b, c, d) and second groups of cooling ports (21'), the arrangement of the first groups of cooling ports (20a, b, c, d) corresponds to the arrangement of the guide vanes (15; 15a, b, c, d), and the arrangement of the second groups of cooling ports (21') corresponds to the regular arrangement of the burners (22a, b, c). |
