A device for retaining drained fluids for a propulsive assembly includes a cavity for storing the drained fluids and two walls mounted at the opening of said cavity. The cavity has a fluid storage volume V1 when the device is in a substantially vertical position, and each wall is configured such as to define a fluid storage volume (V2 and V3 respectively) in the cavity when the device is in a substantially horizontal position, each of the volumes V2 and V3 being at least equal to the volume V1.

An aircraft nacelle may comprise an inner fixed structure and an outer sleeve. The aircraft nacelle may comprise an O-duct thrust reverser. A drain gutter may be located in the inner fixed structure. The drain gutter may comprise a labyrinth configuration. The drain gutter may drain fluids in an aft direction through the inner fixed structure. The fluids may exit through a drain fin located at a station plane aft of the outer sleeve.

A drainage system for an aircraft is taught herein. The drainage system includes a drain tube defining an orifice. The drainage system further includes a cover movable between a first cover position and a second cover position. The cover is configured to overlay the orifice when the cover is in the first cover position. The cover is configured to expose the orifice when the cover is in the second cover position. The cover is configured to move between the first cover position and the second cover position in the presence of air pressure.

Embodiments of the present invention provide a water management system for use on board a passenger transport vehicle. The water management system may be used to address and manage excess humidity, water leaks, or any other instance when water or other liquid may collect at a certain location. The disclosure provides a system for managing excess water and for optionally delivering the water to another location. The removal location may be a disposal outlet or it may be a beneficial use of the collected water on-board the vehicle.

Drainage devices intended to prevent the reentry of drained fluids, the devices including a base having a contact surface for mounting over a drainage opening in an aerodynamic surface, a mast portion connected to the base and extending away from the contact surface of the base, and a top portion connected to the end of the mast portion, the top portion having a periphery that is greater than the periphery of the mast portion and including an exit port. The top portion may include a cantilevered fence portion extending upstream relative to the aerodynamic surface, and the drainage devices may be part of a system including a first opening and a second opening in the aerodynamic surface, the second opening upstream from the first opening, where a drainage device is mounted over the first opening and the cantilevered fence portion of the drainage device extends upstream toward the second opening.

An embodiment fluid recovery structure includes a body having an interior cavity, ports integrally joined to first walls of the body and having port walls that extend away from the body, with each of the ports having a port opening that is contiguous with the interior cavity, and a drain structure integrally joined to a second wall of the body and having a drain hole that extends from the interior cavity through the drain structure.

Stub for discharging drained fluids for a propulsion unit. The stub includes a cavity for storing the drained fluids and at least one orifice for discharging the fluids contained in the storage cavity, and elements for measuring a difference in pressure outside the stub and a member for draining the storage cavity. The member is able to move between a first position of closing the discharge orifice and a second position of releasing the orifice, and is configured so as to move from the first to the second position when the difference in pressure is greater than, or equal to, a predetermined value.

A drain mast for draining liquids from an aircraft, comprising a tube that comprises an internal rim connected to the internal surface of the tube, the internal rim being located in a plane inclined with respect to the horizontal plane of the aircraft and having its lowest part located on the second end of the tube, an aperture for evacuating the liquid, the aperture being located at the lowest part of the internal rim and in the face of the tube facing the incoming airflow, the internal rim and the aperture being configured such that at the second end, the liquid is directed by gravity through the internal rim to the aperture and wherein, in use, the drained liquid flowing from the aperture is pushed by the incoming airflow to the atmosphere.

A drain mast for draining liquids from an aircraft. The drain mast comprises a tube and further comprises a pipe coupled to the inner longitudinal surface of the tube and configured such that the drained liquid flows from the tube to the pipe. The pipe has an inlet having its longitudinal axis configured to confront the coming airflow for allowing the inlet of the coming airflow into the pipe, and an outlet having its longitudinal axis inclined with respect to the longitudinal axis of the inlet and configured to discharge the airflow flowing through the pipe in a direction inclined with a component perpendicular to the fuselage of the aircraft.

Embodiments of the present invention provide a water management system for use on board a passenger transport vehicle. The water management system may be used to address and manage excess humidity, water leaks, or any other instance when water or other liquid may collect at a certain location. The disclosure provides a system for managing excess water and for optionally delivering the water to another location. The removal location may be a disposal outlet or it may be a beneficial use of the collected water on-board the vehicle.