| 摘要 |
The invention refers to an aircraft gas turbine engine including a core engine 1 comprising at least a high pressure turbine 6 and a downstream low pressure turbine 7, a bypass duct 18 surrounding the core engine 1, as well as a mixer 19 arranged in an inlet portion of the low pressure turbine 7, into which a bypass flow 20 from the bypass duct 18 and a core flow 22 from the core engine 1 are supplied. |
