| 摘要 |
<p>A secondary control for a gas turbine engine powering fighter class of aircraft serves to modify the primary control solely during transients in the combat box of the flight envelope and tends to maintain higher compressor rpm (N2), turbine inlet temperature (T4), and engine air flow (Wat2) at the idle setting by concomitantly adjusting fuel flow (Wf) and engine exhaust area (Aj).</p> |
