Patent ID: 8935073
Filing Date: 2015-01-13
Classification: F02K,Y02T

Abstract:
1. A turbofan engine control system comprising: a core nacelle housing a compressor and a turbine; a turbofan arranged upstream from the core nacelle and surrounded by a fan nacelle; a bypass flow path downstream from the turbofan and arranged between the core and fan nacelles, the bypass flow path including a nozzle exit area; a controller programmed to detect at least one of a take-off condition and a landing condition, the controller programmed to effectively alter the nozzle exit area to change a thrust vector in response to the at least one of the take-off and the landing conditions; and wherein the core nacelle includes a low spool supporting the compressor and turbine, the low spool for rotationally driving the turbofan through an epicyclic gear train.