| 摘要 |
A gas turbine engine is disclosed having a fan system with a front stage fan rotor and an aft fan rotor coupled to a low-pressure turbine, a core having a compressor coupled to a high-pressure turbine, an annular inner bypass passage and an annular outer bypass passage. The aft fan rotor has a row of aft fan blades having an arcuate splitter that forms a portion of an inner flow passage and an outer flow passage wherein the aft fan blade pressurizes an inner flow and an outer flow and wherein the fan tip pressure ratio can be changed while the air flow into the front stage fan rotor is held substantially constant.
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