| 摘要 |
A gas turbine engine (10) includes a turbomachinery core (28) operable to generating a flow of pressurized combustion gases; a rotating fan (14) adapted to extract energy from the core (28) and generate a first flow of pressurized air; a fan stator assembly (32, 36) connected in flow communication with the fan (14) and operable to vary the first flow of pressurized air while the fan (14) operates at a substantially constant speed; a fan outer duct (48) surrounding the core (28); and a flade stage (44) comprising a supplementary fan disposed in the fan outer duct (48) and driven by the fan (14) for generating a pressurized bleed air flow. |
