Abstract: A propulsion system has a nacelle, and inside this nacelle, a dual flow turbojet engine includes a fan case in which are located a fan and an assembly of fixed flow-rectifying vanes. This propulsion system includes a thrust inverter located between the fan and the assembly of the fixed flow-rectifying vanes. In particular, the thrust inverter includes a plurality of windows formed in the fan case and thrust inversion flaps to send back the secondary airflow toward the outside and toward the front of the nacelle, through the windows. The thrust inversion flaps pivotally move between a normal operating position in which they allow the passage of the secondary airflow and block the windows, and a thrust inversion position in which they block the passage and clear the windows.

Abstract: The invention relates to a propulsion system including a nacelle and, inside said nacelle, a dual flow turbojet engine that itself includes a fan casing (10) in which a fan and a flow-rectifying vane assembly (15) are located. Said propulsion system includes a reverse thrust means (17) that is located between said fan and said vane assembly (15).