| 摘要 |
A gas turbine engine assembly 10 including a core engine 12 has a first rotor spool 19 including a first fan assembly 50, an intermediate-pressure turbine 14, and a first shaft 26, the first fan assembly 50 including a single stage fan assembly coupled upstream from the core engine12, the intermediate-pressure turbine 14 including a single stage turbine coupled downstream from the core engine 12, the first shaft 26 extending between the first fan assembly 50 and the intermediate-pressure turbine 14. The gas turbine engine assembly 10 also has a second rotor spool 21 including a second fan assembly 52, a low-pressure turbine 15, and a second shaft 34, the second fan assembly 52 including a single stage fan assembly coupled upstream from the first fan assembly 50, the low-pressure turbine 15 including a single stage turbine coupled downstream from the intermediate-pressure turbine 14, the second shaft 34 extending between the second fan assembly 52 and the low-pressure turbine 15. |
