| 摘要 |
<p>A draining device for draining a fluid from an aircraft engine support strut (3) comprises: a suction arrangement comprising an inlet (13) and extending along a longitudinal main axis (l-l) to form a plenum chamber (12); a drain tube (5) fluidly connected to the aircraft engine support strut (3) and extending along the longitudinal main axis (l-l), the drain tube (5) ending by an outlet (8), the outlet (8) of the drain tube (5) terminating within the plenum chamber (12) of the suction arrangement; and wherein an air flow (20) entering the inlet (13) of the suction arrangement causes a low-pressure region (19) to be created within the plenum chamber (12), substantially downstream the outlet (8) of the drain tube (5).</p> |
