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US 6,910,659 B2Granted
Method and apparatus for liquid containment, such as for aircraft fuel vessels
AssigneeThe Boeing Company
InventorsStephen D. Friddell, Alan K. Prichard
Life of this patent
Estimating the term…
Abstract
A vessel, such as a wing-integrated aircraft fuel tank. The vessel can include a first surface portion, a second surface portion spaced apart from the first surface portion, and a core positioned between the first and second surface portions. The core can be sealably connected to the first and second surface portions and can be positioned to carry a load from at least one of the first and second surface portions to the other. The core can include a plurality of cells separated by cell walls, at least some of which have wall openings positioned to provide liquid communication between adjacent cells.
Claims32
An airfoil, comprising:
- a first surface portion;
- a second surface portion spaced apart from the first surface portion;
- a core positioned between the first and second surface portions, the core being sealably connected to the first and second surface portions and positioned to carry a load from at least one of the first and second surface portions to the other, the core including an aft portion, a forward portion, and a plurality of cells separated by cell walls, at least some of the cell walls having wall openings positioned to provide liquid communication between adjacent cells, the at least some of the cell walls having a first portion proximate to the first surface portion, a second portion proximate to the second surface portion, and a third portion between the first and second portions, the first, second, and third portions having at least one wall opening;
- and
- a collection chamber in the airfoil and positioned inboard the core to collect fluid flowing in a spanwise direction through the aft and forward portions of the core.
2 more elements
An airfoil, comprising:
- a first wing portion having a first external surface and a first internal surface;
- a second wing portion having a second external surface and a second internal surface, the second internal surface being spaced apart from the first internal surface;
- a core positioned between the first and second wing portions, the core being sealably connected to the first and second wing portions to form a fuel volume, the core being positioned to carry a load from at least one of the first and second wing portions to the other, the core including an outboard portion, an inboard portion, an aft portion, a forward portion, and a plurality of cells separated by cell walls, at least some of the cell walls having wall openings positioned to provide liquid communication between adjacent cells, the wall openings being sized and configured such that fuel flow through the wall openings from the outboard portion to the inboard portion provides sufficient fuel for operation of an aircraft engine, wherein at least some of the cells in the aft portion are in fluid communication with at least some of the cells in the forward portion during the course of normal engine operation;
- and
- a fuel port in liquid communication with the fuel volume, the fuel port being coupleable to the aircraft engine.
2 more elements
An airfoil, comprising:
- a first wing portion having a first external surface and a first internal surface;
- a second wing portion having a second external surface and a second internal surface, the second internal surface being spaced apart from the first internal surface;
- a core positioned between the first and second wing portions, the core being sealably connected to the first internal surface and the second internal surface to form a fuel-tight volume, the core being positioned to carry a load from at least one of the first and second wing portions to the other, the core including an outboard portion, an inboard portion, an aft portion, a forward portion, and a plurality of at least generally similarly sized and shaped cells separated by cell walls, at least some of the cell walls having wall openings positioned to provide liquid communication between adjacent cells, the wall openings being sized and configured such that fuel flow through the wall openings from the outboard portion to the inboard portion provides sufficient fuel for operation of an aircraft engine;
- a collection chamber in the airfoil and positioned inboard the core to collect fluid flowing in a spanwise direction through the aft and forward portions of the core;
- and
- a fuel port in liquid communication with the collection chamber, the fuel port being coupleable to the aircraft engine.
3 more elements
An aircraft, comprising:
- a fuselage;
- a wing coupled to the fuselage, wherein the wing includes:
- a first surface portion;
- a second surface portion spaced apart from the first surface portion;
- a core positioned between the first and second surface portions, the core being sealably connected to the first and second surface portions to form at least part of a fuel-tight volume, the core being positioned to carry a load from at least one of the first and second surface portions to the other, the core including an aft portion, a forward portion, a plurality of cells separated by cell walls, at least some of the cell walls having wall openings positioned to provide liquid communication between adjacent cells, the at least some of the cell walls having a first portion proximate to the first surface portion, a second portion proximate to the second surface portion, and a third portion between the first and second portions, the first, second, and third portions having at least one wall opening, wherein at least some of the cells in the aft portion are in fluid communication with at least some of the cells in the forward portion during the course of normal engine operation;
- and
- fuel port in liquid communication with the fuel volume;
- at least one engine coupled to at least one of the wing and the fuselage;
- and
- a fuel conduit coupled between the fuel port and the at least one engine.
7 more elements
A method for using an aircraft wing, comprising:
- disposing aircraft fuel in a fuel volume defined at least in part by an upper wing panel portion, a lower wing panel portion and a core sealably positioned between the upper and lower wing panel portions;
- applying aerodynamic loads to at least one of the upper and lower wing panel portions;
- transferring the aerodynamic loads from the at least one wing panel portion to the other through the core while the core remains at least approximately stationary relative to the upper and lower wing panel portions;
- passing the aircraft fuel from a first plurality of cells in the core to a second plurality of cells in the core through openings in walls between adjacent cells, the walls having a first portion proximate to the upper wing panel portion, a second portion proximate to the lower wing panel portion, and a third portion between the first and second portions, the first, second, and third portions having at least one opening;
- and
- collecting aircraft fuel passing in a spanwise direction through aft and forward portions of the core in a collection chamber positioned in the wing and inboard the core.
3 more elements
Dependencies are inferred from the claim text.