FUSELAGE SECTION OF AN AIRCRAFT, AIRCRAFT FUSELAGE, AND AIRCRAFT

Abstract

In order to improve liquid hydrogen storage on aircraft, a liquid hydrogen tank is integrated into the fuselage of the aircraft. At least one portion of the tank wall is formed by specially adapted tank skin panels and/or a pressure bulkhead. The parts forming the tank wall are strengthened to contain a tank pressure of about 3 bar.

Claims

1. A fuselage section of an aircraft, the fuselage section comprising a liquid hydrogen tank for storing liquid hydrogen and a pressure bulkhead and/or at least one tank skin panel, wherein the liquid hydrogen tank has a tank wall that encloses a tank volume for storing the liquid hydrogen, wherein the tank wall comprises a tank wall portion that is formed by the pressure bulkhead and/or the at least one tank skin panel.

2. The fuselage section according to claim 1, comprising a second pressure bulkhead spaced along a forward-aft direction from the pressure bulkhead.

3. The fuselage section according to claim 1, wherein the pressure bulkhead and/or the second pressure bulkhead are or is fixed to at least one tank skin panel.

4. The fuselage section according to claim 1, wherein the tank wall is strengthened such that it can withstand a tank pressure in the tank volume above 1 bar, or up to 5 bar, or up to 3 bar.

5. The fuselage section according to claim 1, wherein the liquid hydrogen tank comprises a refilling tube that fluidly connects the tank volume to an external connector that is configured to receive a supply connector for refilling liquid hydrogen.

6. The fuselage section according to claim 1, wherein the liquid hydrogen tank comprises an evacuation tube and a pressure regulation device that is configured to, when a tank pressure exceeds a predetermined pressure threshold, discharge hydrogen gas from the tank volume via the evacuation tube to the environment.

7. The fuselage section according to claim 1, wherein the liquid hydrogen tank has a thermal insulation that is disposed on the tank wall.

8. The fuselage section according to claim 1, comprising an external protective skin disposed on the liquid hydrogen tank to protect the liquid hydrogen tank from foreign objects impacting thereon.

9. An aft fuselage section or a forward fuselage section, comprising a fuselage section according to claim 1, wherein the pressure bulkhead separates a passenger section from the tank volume.

10. The aft fuselage section or forward fuselage section according claim 9, wherein a cabin pressure in the passenger section is lower than a tank pressure in the tank volume.

11. An aircraft fuselage of an aircraft, comprising at least one fuselage section according to claim 1.

12. An aircraft comprising a fuselage section according to claim 1, and at least one engine that is configured for operating with liquid hydrogen as a fuel, wherein the tank volume is fluidly connected to the engine to enable fluid transport of hydrogen from the tank volume to the engine.

13. A method comprising using a tank section of an aircraft fuselage of an aircraft for storing liquid hydrogen as a fuel supply for the aircraft.

Description

BRIEF DESCRIPTION OF THE DRAWING

[0024] Embodiments of the disclosure herein are described in more detail with reference to the accompanying drawing.

[0025] FIG. 1 depicts a longitudinal section of an aircraft fuselage according to the disclosure herein.

DETAILED DESCRIPTION

[0026] FIG. 1 partially depicts a longitudinal section of an aircraft 10. The aircraft 10 has an aircraft fuselage 12. The aircraft fuselage 12 is divided into a passenger section 14 and a tank section 16.

[0027] The passenger section 12 comprises the usual components such as skin panels 18, stringers 20, and frame 22. The passenger section 12 may comprise in a manner known per se a passenger door 24, a galley 26, and a floor 28. The floor 28, for example, has a plurality of floor panels 30 that are supported by cross beams 32. The cross beams 32 are in turn supported by floor support beams 34, which rest on skin panels 18. The passenger section 12 has a cabin pressure P.sub.cabin. Typical cabin pressure values are around 0.6 bar when in cruise flight or higher depending on the cruising altitude of the aircraft 10.

[0028] The tank section 16 is disposed adjacent to the passenger section 12. The tank section 16 comprises a liquid hydrogen tank 36 that is configured for storage of liquid hydrogen (LH2). The liquid hydrogen tank 36 has a tank wall 38 that encloses a tank volume 40, in which the LH2 is stored.

[0029] The tank section 16 comprises tank skin panels 42, tank stringers 44, and tank frames 46. The tank skin panels 42, the tank stringers 44, and the tank frames 46 partially form the tank wall 38 and may be strengthened compared to the corresponding parts of the passenger section 12. Preferably, the parts have a greater thickness. The tank skin panels 42, the tank stringers 44, and the tank frames 46 are strengthened such that a tank pressure P.sub.LH2 of up to 3 bar to 5 bar can be easily maintained in the tank volume 40.

[0030] The tank section 16 further comprises a pressure bulkhead 48. The pressure bulkhead 48 is welded and/or riveted to the tank skin panels 42. The pressure bulkhead 48 is arranged adjacent to the passenger section 12 and separates it from the tank section 16. In contrast to conventional pressure bulkheads, the pressure bulkhead 48 domes towards the passenger section 12 instead of away from it. The pressure bulkhead 48 also forms part of the tank wall 38.

[0031] The tank section 16 further comprises a second pressure bulkhead 50. The second pressure bulkhead 50 is arranged opposite the pressure bulkhead 48 along the forward-aft direction. The second pressure bulkhead 50 is arranged beneath the vertical tail plane 52, for example. The second pressure bulkhead 50 domes towards aft in the usual manner. The second pressure bulkhead 50 may be smaller in diameter than the pressure bulkhead 48.

[0032] The tank section 16 comprises an external connector 54 for connecting a fuel supply for refueling. The external connector 54 is disposed on one of the tank skin panels 42. The external connector 54 is fluidly connected to the tank volume 40 by a refilling tube 56.

[0033] Furthermore, the tank section 16 includes a pressure regulating device 58 that is configured to release hydrogen gas to the environment through an evacuation tube 60, when a predetermined threshold is exceeded by the tank pressure P.sub.LH2. Here, the evacuation tube 60 is running through the vertical tail plane 52.

[0034] The tank section 16 may include a thermal insulation 62. The thermal insulation 62 is arranged on the tank skin panels 42 and/or the pressure bulkhead 48 and/or the second pressure bulkhead 50.

[0035] The tank section 16 preferably has an external protective skin 64. The external protective skin 64 is arranged on the tank wall 38, preferably on the thermal insulation 62. The external protective skin 64 prevents impact of foreign objects on the tank wall 38 or the thermal insulation 62, thereby reducing the risk of leaks.

[0036] In order to improve liquid hydrogen storage on aircraft 10, the disclosure herein proposes a liquid hydrogen tank 36 that is integrated into the fuselage 12 of the aircraft 10. At least one portion of the tank wall 38 is formed by specially adapted tank skin panels 42 and/or a pressure bulkhead 48. The parts forming the tank wall 38 are strengthened so as to contain a tank pressure P.sub.LH2 of about 3 bar.

[0037] While at least one example embodiment of the present invention(s) is disclosed herein, it should be understood that modifications, substitutions and alternatives may be apparent to one of ordinary skill in the art and can be made without departing from the scope of this disclosure. This disclosure is intended to cover any adaptations or variations of the example embodiment(s). In addition, in this disclosure, the terms “comprise” or “comprising” do not exclude other elements or steps, the terms “a”, “an” or “one” do not exclude a plural number, and the term “or” means either or both. Furthermore, characteristics or steps which have been described may also be used in combination with other characteristics or steps and in any order unless the disclosure or context suggests otherwise. This disclosure hereby incorporates by reference the complete disclosure of any patent or application from which it claims benefit or priority.

LIST OF REFERENCE SIGNS

[0038] 10 aircraft [0039] 12 fuselage [0040] 14 passenger section [0041] 16 tank section [0042] 18 skin panel [0043] 20 stringers [0044] 22 frame [0045] 24 passenger door [0046] 26 galley [0047] 28 floor [0048] 30 floor panels [0049] 32 cross beams [0050] 34 floor support beams [0051] 36 liquid hydrogen tank [0052] 38 tank wall [0053] 40 tank volume [0054] 42 tank skin panel [0055] 44 tank stringer [0056] 46 tank frame [0057] 48 pressure bulkhead [0058] 50 second pressure bulkhead [0059] 52 vertical tail plane [0060] 54 external connector [0061] 56 refilling tube [0062] 58 pressure regulating device [0063] 60 evacuation tube [0064] 62 thermal insulation [0065] 64 external protective skin [0066] P.sub.cabin cabin pressure [0067] P.sub.LH2 tank pressure