| 摘要 |
The invention relates to a gas turbine engine comprising a first flow passage (1), and main combustion means (4) in the first flow passage (1). The engine further comprises a second flow passage (11), and first catalytic combustion means (12) in the second flow passage (11), wherein the second flow passage (11) can communicate with the first flow passage (1) at at least one upstream passage junction (13, 131) upstream of the main combustion means (4) and upstream of the first catalytic combustion means (12), and the second flow passage (11) can communicate with the first flow passage (1) at at least one downstream passage junction (151, 152) downstream of the main combustion means (4) and downstream of the first catalytic combustion means (12). |
