Aircraft wing comprising a storage tank for gaseous hydrogen

Patent metadata

Field	Value
Publication number	US-2025115347-A1
Application number	US-202318729431-A
Country	US
Kind code	A1
Filing date	Jan 4, 2023
Priority date	Feb 4, 2022
Publication date	Apr 10, 2025
Grant date	—

Abstract

A storage tank for gaseous hydrogen includes a continuous tank wall defining a serial array of hollow elongate tank portions of substantially constant cross-section and hollow connecting portions defining an internal storage volume, wherein adjacent ends of any pair of adjacent hollow elongate tank portions are connected by a hollow connecting portion having a cross-sectional dimension smaller than those of the adjacent hollow elongate tanks portions. The tank may be included in an aircraft wing such that it extends spanwise through one or more internal spars of the wing, thus providing a continuous gas storage volume at a given chordwise position notwithstanding the spars, and providing for storage of gaseous hydrogen at higher gravimetric efficiency than is achievable by a plurality of coupled discrete tanks disposed between the spars.

First claim

What is claimed is:

1 - 9 . (canceled)

10 . An aircraft wing comprising a plurality of spars each being located at a respective spanwise position and extending substantially chordwise and having a respective aperture therein, wherein the aircraft wing further comprises a first storage tank for gaseous hydrogen, the first storage tank comprising a continuous tank wall defining a serial array of hollow elongate tank portions of substantially constant cross section and hollow connecting portions defining a storage volume, adjacent ends of any pair of adjacent hollow elongate tank portions being connected by a hollow connecting portion having a cross-sectional dimension smaller than those of the adjacent hollow elongate tank portions, the storage tank passing through the aperture of each spar such that each hollow connecting portion of the storage tank coincides with an aperture in a respective spar.

11 . An aircraft wing according to claim 10 wherein the apertures are each located at a first chordwise position and form a first set of apertures, and wherein the storage tank is linear and extends spanwise.

12 . An aircraft wing according to claim 11 wherein each spar has a respective second aperture located at a second chordwise position, and wherein the wing comprises a second storage tank like to the first, the second storage tank being linear and extending spanwise substantially parallel to the first storage tank and passing through each second aperture such that each hollow connecting portion of the second storage tank coincides with a second aperture of a respective spar.

13 . An aircraft wing according to claim 12 wherein each spar is divided in a plane substantially parallel to the plane of the wing, the plane bisecting the apertures of a corresponding spar.

14 . An aircraft wing according to claim 11 and further comprising a plurality of storage tanks each like to the first tank, each tank of the plurality of tanks being linear, extending spanwise within the wing and being distributed in a direction normal to the plane of the wing.

15 . An aircraft wing according to claim 14 wherein the storage volumes of the tanks are connected in series.

16 . An aircraft wing according to claim 14 wherein the storage volume of the tanks are connected such that at least one tank is connected two or more serial arrays of tanks.

17 . An aircraft wing according to claim 11 wherein the hollow elongate tank portions of the first tank are substantially cylindrical.

18 . An aircraft wing according to claim 17 wherein any given hollow connecting portion of the first tank has a diameter which varies with axial position such that its diameter equals those of the hollow elongate tank portions it connects at the axial positions of the adjacent end thereof and passes through a minimum value between said positions.

19 . An aircraft wing according to claim 17 wherein a terminal hollow elongate tank portion of the serial array of hollow elongate tank portions of the first tank has a domed or hemispherical end.

20 . An aircraft wing according to claim 17 wherein the wall thickness of the first tank at a given axial position is a decreasing function of the cross-sectional dimension or diameter of the tank at that axial position.

21 . An aircraft wing according to claim 17 wherein the first tank is fabricated from one of an organic composite material, an organic composite laminate material, a metal and a metal alloy.

Assignees

• Rolls Royce Plc

Inventors

• Palmer Chloe J
• Hillel Malcolm L
• Clark Daniel

Classifications

• F17C2270/0189

  Planes · CPC title

• F17C2223/036

  Very high pressure (>80 bar) · CPC title

• F17C2221/012

  Hydrogen · CPC title

• F17C2205/013

  Two or more vessels · CPC title

• F17C2201/0152

  Lobes · CPC title