| 摘要 |
A gas turbine engine (576) having a convertible fan system is disclosed, having a fan system (501) with a front stage fan rotor (506) and an aft fan rotor (542) coupled to a low-pressure turbine (583), a core (578) having a compressor (579) coupled to a high-pressure turbine (581), an annular inner bypass passage. (571) and an annular outer bypass passage (572). The aft fan rotor (542) has a row of aft fan blades (544) having an arcuate splitter (547 that forms a portion of an inner flow passage (573) and an outer flow passage (574) wherein the aft fan blade (544) pressurizes an inner flow (563) and an outer flow (564) and wherein the fan tip pressure ratio can be changed while the air flow into the front stage fan rotor (506) is held substantially constant. A method of operating a gas turbine engine (576) having a convertible fan system is disclosed.
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