| 摘要 |
The present invention relates to a gas turbine combustion chamber arrangement having an annular combustion chamber (1), having a diffuser element (2) which is arranged upstream of the annular combustion chamber (1) in the flow direction and which surrounds an annular duct, and having an axial compressor (113, 114) which is arranged upstream of the diffuser element (2), characterized in that the diffuser element (2) has an annular guide blade region (3) in which are arranged guide blades (4) which are designed to deflect an incoming flow (5) at an angle (a) in a range between 28° and 32° with respect to a central axis (6) of the gas turbine, and in that, downstream of the guide blade region (3), there is arranged a diffuser region (7) in which no flow guiding elements which have an effect on the flow are provided, wherein burners (8) arranged in the annular combustion chamber (1) are arranged with their burner axes (9) inclined with respect to the central axis (6) by an angle (ß) of between 40° and 50°. |
