| 摘要 |
The invention concerns an aircraft propulsion control system for an aircraft 10 comprising a gas turbine engine 12. The gas turbine engine comprises an actuator 58 for adjusting the direction of a propulsive flow 16 produced by the engine. The control system further comprises a sensor 54 arranged to sense a condition indicative of vapour trail formation by an exhaust flow 16 from the engine. The controller is arranged to be responsive to the condition indicative of vapour trail formation and selectively control operation of the actuator so as to direct the propulsive flow relative to an airframe wake flow region caused by the aircraft in flight. The direction of the propulsive flow produced by the engine is modified by the controller according to the location of the engine relative to a portion of the airframe that induces a vortical wake flow 20. An interaction between the propulsive flow and the wake flow may reduce the optical depth of a contrail formed by propulsive flow behind the aircraft. There may be a plurality of gas turbine engines. |
