Nacelle fluid drain
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.
1. An aircraft engine nacelle comprising:
an outer sleeve; and
an inner fixed structure surrounding a portion of an engine and helping to define a core compartment, the outer sleeve and the inner fixed structure defining between them a bypass air duct;
the inner fixed structure comprising a gutter, the gutter configured to drain fluids in an aft direction through the inner fixed structure through a gutter outlet located aft of the bypass air duct.
2. The aircraft engine nacelle of claim 1 , wherein the gutter comprises a labyrinth structure.
3. The aircraft engine nacelle of claim 1 , wherein the gutter comprises a drain fin coupled to an outer surface of the inner fixed structure and located aft of the outer sleeve.
4. The aircraft engine nacelle of claim 1 , further comprising a drain fin located at a position of lower gravitational potential energy than the gutter.
5. The aircraft engine nacelle of claim 1 , further comprising a fire seal formed by a left half of the inner fixed structure and a right half of the inner fixed structure.
6. The aircraft engine nacelle of claim 1 , further comprising a siphon located in the inner fixed structure and comprising an orifice in an outer surface of the inner fixed structure.
7. The aircraft engine nacelle of claim 6 , wherein the siphon comprises a tube configured to transfer air from the bypass air duct to an exit of the gutter.
8. A drain gutter for an aircraft nacelle comprising:
a first semi-annular inner fixed structure (“IFS”) half; and
a second semi-annular IFS half,
wherein the first IFS half and the second IFS half form a gutter where the first IFS half and the second IFS half couple together.
9. The drain gutter of claim 8 , wherein the gutter is a labyrinth gutter comprising an upper channel and a lower channel separated by a separation platform.
10. The drain gutter of claim 9 , wherein the first IFS half and the second IFS half form a fire seal adjacent to the lower channel.
11. The drain gutter of claim 9 , wherein the labyrinth gutter is configured to prevent ignition of fluids in the lower channel.
12. The drain gutter of claim 8 , fu her comprising a vacuum tube fluidly coupled to the gutter.
13. The drain gutter of claim 8 , further comprising a drain tin coupled to the first IFS half.
14. The drain gutter of claim 8 , further comprising a compressor drain tube, a combustor drain tube, and a turbine drain tube configured to drain fluids into the gutter.
15. An aircraft nacelle comprising:
an inner fixed structure;
an outer sleeve; and
a drain gutter located within the inner fixed structure, wherein the drain gutter comprises a drain fin extending from an underside of the inner fixed structure comprising an outlet positioned aft of the outer sleeve and bypass air duct, wherein the drain gutter is configured to drain fluids in an aft direction through the inner fixed structure to the drain fin.
16. The aircraft nacelle of claim 15 , further comprising a siphon in the inner fixed structure.
17. The aircraft nacelle of claim 16 , wherein the siphon is fluidly coupled to the drain gutter.
18. The aircraft nacelle of claim 16 , wherein the siphon comprises an orifice in an outer surface of the inner fixed structure.
19. The aircraft nacelle of claim 15 , further comprising a communal collector configured to receive fluids from at least one of a compressor, a combustor, or a turbine.
20. The aircraft nacelle of claim 15 , wherein a fluid path in the drain gutter is configured to be gravitationally downhill when the aircraft nacelle is in level flight.