| 摘要 |
<p>The invention relates to the jet propulsion unit of an aircraft, which comprises a turbofan engine (3), faired by a nacelle, comprising a thrust reverser device in two parts: one part including a means for feeding back air (15) towards the outside of the propulsive unit, on a first angular sector of the nacelle; one part including internal deflectors which can be removed and controlled, suitable for channelling the secondary air flow, circulating in a secondary jet between the propulsive unit and the fairing in a second angular sector of the nacelle, such as to offset the latter angularly in the secondary jet towards a certain external thrust reversal means. The internal deflectors consist of at least two mobile surfaces (22, 23), each rotatably hinged between an inoperative position, in which the mobile surface is continuous with the inner surface of the fairing of the nacelle, and a thrust reversal position, in which said mobile surfaces (22, 23) locally interrupt the longitudinal secondary air flow, and channel the latter gradually towards some of the air feedback means.</p> |
