| 摘要 |
<P>PROBLEM TO BE SOLVED: To provide a method and system operating an aircraft system. <P>SOLUTION: The gas turbine engine system includes a low-pressure (LP) shaft, a high-pressure (HP) shaft, a constant speed mechanical drive assembly having an input and an output, the input mechanically coupled to the LP shaft, the output mechanically coupled to a constant frequency (CF) electrical generator, and an accessory gearbox assembly having an input and an output, the input mechanically coupled to the HP shaft, the output mechanically coupled to a variable frequency (VF) electrical generator. <P>COPYRIGHT: (C)2012,JPO&INPIT |
