| 摘要 |
<p>A fuel control system for a gas turbine engine of the kind having at least one compressor (12, 14) and turbine spool (20, 22) and a free turbine (24), comprising a pneumatic fuel metering device (34) whose metering valve is controlled by a pneumatic mechanism as a function of the difference between a reference pressure (Px) and a modulated control pressure (Py) which can be varied either by a first governor (50) responsive to turbine speed (Ng) or by a second governor (48) responsive to free turbine speed (Nf), said governors thus providing a parallel governing mode. According to this invention, at least one of said governors (48, 50) is an electronic control unit generating an electrical signal indicative of a desired engine output power, and there is provided an interface means (44, 46) converting said signal into a corresponding variation of the control pressure (Py). For use particularly in control systems for helicopters and the like.</p> |
