| 摘要 |
The combustion chamber (10) of a gas turbine comprises first and second premixed fuel supply devices (11, 12) connected to a combustion device (13) having first zones (14) connected to the first premixed fuel supply devices (11) and second zones (15) connected to the second premixed fuel supply devices (12). The second fuel supply devices (12) are shifted along a combustion device longitudinal axis (16) with respect to the first fuel supply devices (11). The first zones (14) are axially upstream of the second premixed fuel supply devices (12). |
