| 摘要 |
A gas turbine engine comprises a fan section including a fan hub supporting a plurality of fan blades for rotation relative to a fan case, a shaft rotatable relative to the fan case about an engine center axis, and a geared architecture driven by the shaft to provide driving output to rotate the fan hub. A compressor is positioned forward of the geared architecture and radially inward of the fan blades, with the compressor being driven by the shaft. |
