| 摘要 |
The invention relates to a gas turbine combustion chamber having an outer combustion chamber wall (10), which is concentric with respect to a gas turbine central axis (101), and an inner combustion chamber wall (9), having a plurality of burners (1) arranged so as to be distributed over the circumference of the combustion chamber, and having air inlet recesses which are formed so as to be distributed over the circumference on an outer combustion chamber wall (10) and on an inner combustion chamber wall (9) in at least one radial plane, wherein the burner (1) is formed so as to generate a swirling flow, wherein air inlet recesses (11, 12, 12a, 13, 18, 19, 19a, 20) which are assigned to a burner (1) are dimensioned to be of different sizes in order to generate air flows of different magnitude, characterized in that at least one of the respective air inlet recesses (11, 12, 12a, 13, 18, 19, 19a, 20) is formed so as to supply air in the flow direction of the swirl of the combustion chamber flow and is provided with flow-guiding walls (31). |
