Method of using a turbojet engine nacelle air inlet comprising an air inlet lip comprising a movable portion to promote a thrust reversal phase

摘要

A method of using an air inlet (2) of an aircraft turbojet nacelle (1) comprising an air inlet lip (23) comprising at least one fixed portion and at least one portion movable (3, 3 ', 4, 4', 5, 5 ', 6, 6', 7) between a first position, in which the air intake lip (23) has an aerodynamic profile so as to guide the flow of interior air on the interior wall (21) to promote a pushing phase, and a second position (B), in which the portion (3, 3 ', 4, 4', 5, 5 ', 6, 6 ', 7) is moved relative to the fixed portion so that the air inlet lip (23) has a second radial thickness (EB) in the second position (B) which is less than the first radial thickness (EA) in the first position so as to promote a reverse thrust phase. Abstract figure: Figure 4