AIRCRAFT WITH AT LEAST ONE HYDROGEN SUPPLY DEVICE AND AT LEAST ONE TIGHT CONTAINER IN WHICH AT LEAST ONE EQUIPMENT PART OF THE HYDROGEN SUPPLY DEVICE IS POSITIONED

Description

[0001] The present application relates to an aircraft comprising at least one hydrogen supply device as well as at least one airtight container outside said container in which at least one piece of equipment of the hydrogen supply device is positioned.

[0002] According to one embodiment, an aircraft comprises several hydrogen-powered propeller engines and at least one hydrogen supply device configured to supply the engines.

[0003] This hydrogen supply device comprises a hydrogen tank positioned in the fuselage of the aircraft, a high-pressure pump to pressurize the hydrogen, a heat exchanger configured to heat the hydrogen which passes from the liquid state to the gaseous state as well as various conduits to connect the hydrogen tank, the pump, the heat exchanger and the engine.

[0004] The conduits are double-skinned pipes to prevent any hydrogen leakage.

[0005] Designing a heat exchanger or high-pressure pump with a high level of safety against hydrogen leakage is complex or leads to high costs for this equipment.

[0006] GB899312 describes a gas turbine engine having means for storing cryogenic fuel and means for using a portion of the cryogenic fuel as an indirect coolant for the turbine. A hydrogen pipeline flows from the storage means into the engine, passing through a heat exchanger, without a sealed container to isolate said pipeline from the outside air.

[0007] Document US2015 / 344145 describes an aircraft comprising a turbine engine having a bleed air outlet duct, a cryogenic fuel system having a cryogenic fuel tank and a supply line operatively coupling said tank to the turbine engine, and an on-board inert gas generation system fluidly coupled to the bleed air outlet and having a nitrogen-rich air outlet duct and an oxygen-rich air outlet duct.

[0008] GB2587560 describes the use of hydrogen in an aircraft to reduce pollutant emissions.

[0009] Document EP4056477 describes an aircraft comprising an engine running on hydrogen and having a double-skinned pipe in which hydrogen circulates.

[0010] Document EP2644508 describes an aircraft comprising a system for cooling an electronic component, said cooling system comprising a fuel tank and a pipe for transporting the fuel contained in the tank to an engine of the aircraft, said pipe being thermally insulated over part of its length.

[0011] The present invention aims to remedy all or part of the drawbacks of the prior art.

[0012] To this end, the invention relates to an aircraft comprising at least one hydrogen engine and at least one hydrogen supply device comprising at least one hydrogen tank and at least one piece of equipment through which the hydrogen passes and positioned between the hydrogen tank and the hydrogen engine.

[0013] According to the invention, the aircraft comprises at least one airtight container outside said container, in which the equipment or at least one of the equipment of the hydrogen supply device is positioned.

[0014] Positioning the hydrogen supply device equipment(s) in at least one airtight container outside said container (and therefore containing a low oxygen content) makes it possible to obtain a safe hydrogen installation using existing equipment.

[0015] According to another characteristic, the sealed container or at least one of the sealed containers comprises at least one connector configured to connect an inert gas injection device or a vacuum extraction device.

[0016] The sealed container or at least one of the sealed containers comprises at least one oxygen sensor configured to detect a presence of oxygen or a given concentration of oxygen inside the sealed container. According to another characteristic, the sealed container or at least one of the sealed containers comprises at least one hydrogen sensor configured to detect a presence of hydrogen or a given concentration of hydrogen inside the sealed container.

[0017] The sealed container or at least one of the sealed containers comprises at least one extraction system configured to extract the oxygen present in the sealed container. According to another characteristic, the sealed container or at least one of the sealed containers comprises at least one extraction system configured to extract the hydrogen present in the sealed container.

[0018] The hydrogen supply device comprises at least one removable connection system upstream or downstream of the sealed container or at least one of the sealed containers.

[0019] According to another characteristic, the hydrogen supply device comprises at least one valve upstream or downstream of the sealed container or at least one of the sealed containers.

[0020] According to another characteristic, the aircraft comprises at least one structure and the waterproof container or at least one of the waterproof containers is a waterproof housing separate from said structure of the aircraft, the aircraft comprising at least one connection system connecting the waterproof housing and said structure of the aircraft.

[0021] According to another characteristic, the aircraft comprises a wing having several boxes, the waterproof housing or at least one of the waterproof boxes being positioned in one of the boxes of the wing.

[0022] According to another characteristic, the aircraft comprises at least one structure and the sealed container or at least one of the sealed containers is at least partly delimited by said structure of the aircraft.

[0023] According to another characteristic, the aircraft comprises a wing having several boxes, the sealed container or at least one of the sealed containers being delimited by at least a part of one of the boxes of the wing and at least one sealing partition.

[0024] According to another feature, the wing comprises upper and lower walls, front and rear spars and ribs delimiting the wing boxes. In addition, at least one wall among the upper and lower walls comprises, in line with at least one piece of equipment or at least one watertight box, an opening sealed in a watertight manner by a removable hatch.

[0025] According to another characteristic, the at least one equipment of the hydrogen supply device is a pump or a heat exchanger.

[0026] According to another characteristic, the hydrogen supply device comprises a plurality of pieces of equipment through which the hydrogen passes and positioned between the hydrogen tank and the hydrogen engine, said plurality of pieces of equipment being arranged in said at least one sealed container.

[0027] According to another characteristic, the hydrogen supply device comprises a plurality of equipment items through which the hydrogen passes and positioned between the hydrogen tank and the hydrogen engine, and the aircraft comprises a plurality of airtight containers outside said container, in each airtight container being positioned at least one of the equipment items of the hydrogen supply device.

[0028] Other characteristics and advantages will emerge from the description of the invention which follows, a description given by way of example only, with reference to the appended drawings, among which: Fig. 1 is a perspective view of an aircraft, Fig. 2 is a schematic representation of a propeller engine and a hydrogen supply device illustrating one embodiment of the invention, Fig. 3 is a perspective view of a sealed container in which a heat exchanger and a pump are positioned illustrating an embodiment of the invention, Fig. 4 is a perspective view of a first sealed container in which a pump is positioned and of a second sealed container in which a heat exchanger is positioned illustrating a second embodiment of the invention, Fig. 5 is a schematic representation of a part of an aircraft wing comprising at least one watertight box, Fig. 6 is a cross-section of a sealed aircraft wing box in which a pump and a heat exchanger are positioned illustrating an embodiment of the invention, Fig. 7 is a cross-section of a sealed aircraft wing box in which a pump and a heat exchanger are positioned illustrating an embodiment of the invention, Fig. 8 is a top view of a portion of an aircraft wing illustrating a first arrangement of the invention, Fig. 9 is a top view of a portion of an aircraft wing illustrating a second arrangement of the invention, Fig. 10 is a top view of a portion of an aircraft wing illustrating a third arrangement of the invention, Fig. 11 is a cross-section of a box of an aircraft wing in which a sealed housing is positioned illustrating an embodiment of the invention, Fig. 12 is a top view of the wing visible on the figure 11 , in the absence of a trapdoor, Fig. 13 is a schematic representation of a waterproof housing attachment system visible on the figure 11 illustrating an embodiment of the invention, Fig. 14 is a cross-section of a box of an aircraft wing in which a sealed housing is positioned illustrating another embodiment of the invention, Fig. 15 is a cross-section of a box of an aircraft wing in which two sealed boxes are positioned illustrating another embodiment of the invention, Fig. 16 is a side schematic representation of a propulsion unit without a cowl and a sealed housing positioned under the wing illustrating another embodiment of the invention, Fig. 17 is a cross-section of an aircraft wing and a sealed housing positioned under the wing illustrating another embodiment of the invention, Fig. 18 is a schematic representation of a propulsion assembly illustrating another embodiment of the invention.

[0029] According to an embodiment visible on the figure 1 , an aircraft 10 comprises a fuselage 12, a wing 14 as well as propulsion units 16 positioned under the wing 14 and each connected to the latter by a mast 18.

[0030] According to an embodiment visible in particular on the figures 5 à 11 , the wing 14 extends between a leading edge 20 and a trailing edge 22, has a structure 24 which comprises an upper wall 26, a lower wall 28, a front spar 30.1, parallel to the leading edge 20, positioned near the latter and connecting the upper and lower walls 26, 28, a rear spar 30.2, parallel to the front spar 30.1, positioned near the trailing edge 22 and connecting the upper and lower walls 26, 28 as well as ribs 32 positioned in planes perpendicular to the front and rear spars 30.1, 30.2 and connecting the upper and lower walls 26, 28.

[0031] According to this configuration, the wing 14 comprises a plurality of boxes 34 delimited by the upper and lower walls 26, 28, the front and rear spars 30.1, 30.2 as well as the ribs 32.

[0032] According to one embodiment, each propulsion assembly 16 comprises a propulsion propeller 36 as well as a hydrogen engine 38 driving the propulsion propeller 36 in rotation.

[0033] According to one configuration, the mast 18 comprises a primary structure 40 connecting the propulsion assembly 16 and the wing 14 as well as a secondary structure 42 enveloping the primary structure 40 to give the mast 18 aerodynamic performance.

[0034] As illustrated on the figure 2 , the aircraft 10 comprises, for each propulsion unit 16, a hydrogen supply device 44 having at least one hydrogen tank 46 positioned in the fuselage 12, a pump 48 for pressurizing the hydrogen, a heat exchanger 50 configured to heat the hydrogen as well as hydrogen conduits connecting the hydrogen tank 46, the pump 48, the heat exchanger 50 and the hydrogen engine 38. According to one configuration, the hydrogen supply device 44 comprises a first hydrogen conduit 52 connecting the hydrogen tank 46 and the pump 48, a second hydrogen conduit 54 connecting the pump 48 and the heat exchanger 50 as well as a third hydrogen conduit 56 connecting the heat exchanger 50 and the hydrogen engine 38.

[0035] The hydrogen tank 46 may be common to several propulsion units 16. According to one configuration, the pump 48 is a high-pressure pump. The heat exchanger 50 is configured to heat the hydrogen in order to obtain a transition from the liquid state to the gaseous state for the hydrogen. The hydrogen conduits 52, 54, 56 are double-skinned pipes (or conduits).

[0036] According to one configuration, the pump 48 and the heat exchanger 50 are arranged near the hydrogen engine 38. According to this configuration, the distribution of hydrogen from the hydrogen tank 46 to the hydrogen engine 38 is carried out with the hydrogen in the liquid state. The heat exchanger 50 near the hydrogen engine 38 heats the hydrogen to change it from the liquid state to the gaseous state.

[0037] According to another configuration, the pump 48 is arranged near the hydrogen tank 46 and the heat exchanger 50 is arranged near the hydrogen engine 38. According to this configuration, the distribution of hydrogen from the hydrogen tank 46 to the hydrogen engine 38 is carried out with the hydrogen in the liquid state. The heat exchanger 50 near the hydrogen engine 38 heats the hydrogen to change it from the liquid state to the gaseous state.

[0038] According to another configuration, the pump 48 and the heat exchanger 50 are arranged near the hydrogen tank 46. According to this configuration, the distribution of hydrogen from the hydrogen tank 46 to the hydrogen engine 38 is carried out with the hydrogen in the gaseous state. An additional heat exchanger (not shown in the figures) is arranged near the hydrogen engine 38, and is configured to heat the gaseous hydrogen, before it enters the hydrogen engine 38.

[0039] The aircraft 10 comprises at least one sealed container 58 in which at least one piece of equipment is positioned among the pump 48 and the heat exchanger 50 of the hydrogen supply device 44.

[0040] According to a first embodiment visible for example on the figures 2 And 3 , the aircraft 10 comprises a sealed container 58 in which the pump 48 and the heat exchanger 50 are positioned. The sealed container 58 comprises an upstream passage orifice 60 for the first hydrogen conduit 52 and a downstream passage orifice 62 for the third hydrogen conduit 56.

[0041] According to a first configuration, the first and third hydrogen conduits 52, 56 pass through the upstream and downstream passage orifices 60, 62 and are connected in a sealed manner to the sealed container 58.

[0042] According to another configuration, at least one hydrogen conduit among the first and third hydrogen conduits 52, 56 comprises an outer section positioned outside the sealed container 58, an inner section positioned inside the sealed container 58 as well as a removable connection system connecting the outer and inner sections and positioned in line with the upstream or downstream passage orifice 60, 62 or slightly offset towards the outside of the sealed container 58. According to one arrangement, the supply device comprises two removable connection systems upstream and downstream of the sealed container 58. Thus, it is possible to separate the sealed container 58 and the elements positioned inside the rest of the hydrogen supply device 44.

[0043] According to one configuration, the hydrogen supply device 44 comprises at least one valve 64 upstream or downstream of the sealed container 58, positioned on one of the hydrogen conduits 52, 54, 56 and configured to occupy a passing state in which it allows a flow of hydrogen in the hydrogen conduit and a blocked state in which it prevents a flow of hydrogen in the hydrogen conduit. According to one arrangement, the hydrogen supply device 44 comprises two valves 64, 64' upstream and downstream of the sealed container 58. Thus, it is possible to isolate the elements positioned inside the sealed container 58 from the rest of the hydrogen supply device 44. According to one configuration, another valve 64" is positioned inside the sealed container 58 between the pump 48 and the heat exchanger 50.

[0044] According to a second embodiment visible for example on the figure 4 , the aircraft 10 comprises a first sealed container 58 in which the pump 48 is positioned as well as a second sealed container 58' in which the heat exchanger 50 is positioned. According to this embodiment, the pump 48 and the heat exchanger 50 are positioned in two separate sealed containers 58, 58'. Each sealed container 58, 58' comprises an upstream passage orifice 60 and a downstream passage orifice 62 for the hydrogen conduits 52, 54, 56.

[0045] As for the first embodiment, the hydrogen supply device 44 comprises at least one removable connection system and / or at least one valve 64 upstream and / or downstream of at least one sealed container among the first and second sealed containers 58, 58'. According to one configuration, a first valve 64 is arranged upstream of the first sealed container 58, a second valve 64' is arranged downstream of the second container 58' and a third valve 64" is arranged between the first and second sealed containers 58, 58'.

[0046] At least one of the sealed containers 58, 58' comprises at least one connector 66 configured to connect an inert gas injection apparatus or a vacuum extraction apparatus to extract the gas present in the sealed container 58, 58'. This solution makes it possible to remove the oxygen present in the sealed container 58, 58' by replacing the gas present in the sealed container 58, 58' with an inert gas or by removing it to obtain a vacuum inside the sealed container 58, 58'.

[0047] According to one embodiment, at least one of the sealed containers 58, 58' comprises at least one sensor 68 configured to detect oxygen or hydrogen present in the sealed container 58, 58'. According to one configuration, each sealed container 58, 58' comprises a first oxygen sensor 68 for detecting the presence of oxygen or a given concentration of oxygen inside the sealed container 58, 58' and a second hydrogen sensor 68' configured to detect the presence of hydrogen or a given concentration of hydrogen inside the sealed container 58, 58'.

[0048] According to one embodiment, at least one of the sealed containers 58, 58' comprises at least one extraction system 70 configured to remove the oxygen or hydrogen present inside the sealed container 58, 58'. According to one configuration, each sealed container 58, 58' comprises a first extraction system 70 configured to extract the oxygen present in the sealed container 58, 58', for example when the first sensor 68 detects the presence of oxygen in the sealed container 58, 58'. Each sealed container 58, 58' comprises a second extraction system 70' configured to extract the hydrogen present in the sealed container 58, 58', for example when the second sensor 68' detects a hydrogen concentration in the sealed container 58, 58' greater than a given threshold.

[0049] According to a first embodiment, the sealed container 58 or at least one of the sealed containers 58, 58' is a sealed housing 72 separate from the structure of the aircraft, as illustrated in the figures 3, 4 , 11 , 13 à 18 .

[0050] For example, the waterproof case 72 is parallelepipedal.

[0051] According to one configuration, the waterproof housing 72 comprises at least two parts connected together in a sealed and removable manner to allow access to the interior of the waterproof housing 72. By way of example, the waterproof housing 72 comprises a first part having a bottom and four side walls as well as a second part in the form of a cover configured to be connected in a sealed and removable manner to the side walls of the first part. Of course, the invention is not limited to this embodiment for the waterproof housing 72.

[0052] According to a first arrangement visible on the figures 11, 13 And 14 , the pump 48 and the heat exchanger 50 are positioned in the same sealed housing 72 positioned in one of the boxes 34 of the wing 14. On the figure 11 , the waterproof housing 72 is arranged in a rear part of the wing 14 (near the rear spar 30.2, and the trailing edge 22). On the figure 14 , the waterproof housing 72 is arranged in a front part of the wing 14 (near the front spar 30.1, and the leading edge 20).

[0053] According to a second arrangement visible on the figure 15 , the pump 48 is positioned in a first sealed housing 72 positioned in a first box 34 of the wing and the heat exchanger 50 is positioned in a second sealed housing 72' positioned in the first box 34 of the wing. The first sealed housing 72 is here positioned in a rear part of the wing 14 (near the rear spar 30.2), while the second sealed housing 72' is arranged in a front part of the wing 14 (near the front spar 30.1). Of course, this configuration is not limiting. Although not shown, the heat exchanger 50 can be positioned in a second sealed housing 72' in a second box 34, separate from the first box 34. The box 34 in which at least one sealed housing 72, 72' is positioned is located as close as possible to the primary structure 40. The box 34 in which at least one sealed housing 72, 72' is positioned may or may not be sealed.

[0054] According to one configuration, at least one wall among the upper and lower walls 26, 28 comprises at least one opening 74 (visible on the figure 12 ), in line with at least one waterproof housing 72, sealed in a waterproof manner by a removable hatch 76. According to the embodiment visible on the figure 13 , the upper wall 26 comprises an opening 74 closed by a hatch 76. The hatch 76 shown in the figure 11 is arranged substantially in the middle of the upper wall 26 (between the leading edge 20 and the trailing edge 22). According to another embodiment visible on the figure 15 , the upper wall 26 comprises two openings 74, 74' closed by hatches 76, 76'. Each opening 74, 74', and therefore hatch 76, 76', is arranged above, that is to say opposite, a sealed container 58, 58', which here takes the form of a sealed box 72, 72'. These hatches 76, 76' have dimensions smaller than the dimensions of the hatch 76 of the figure 11 . According to another embodiment visible on the figure 14 , the upper wall 26 comprises a first opening 74 closed by a first hatch 76 and the lower wall 28 comprises a second opening 74' closed by a second hatch 76'. The first opening 74 and the first hatch 76 are arranged on a front portion (near the leading edge 20) of the upper wall 26, while the second opening 74' and the second hatch 76' are arranged on a central portion of the lower wall 28. The location of the openings 74, 74' and the hatches 76, 76' may vary depending on the location of the equipment 48, 50 of the hydrogen supply device 44. For example, one or more openings 74, 74' and one or more hatches 76, 76' may be present on the upper wall 26 and / or on the lower wall 28.The dimensions of the openings 74, 74' and the hatches 76, 76', as well as their number, may also vary depending on the dimensions of the watertight containers 58, 58', the watertight boxes 72, 72' and the boxes 34.

[0055] According to a third arrangement visible on the figures 16 à 18 , the waterproof housing 72 or at least one of the waterproof housings 72, 72' is positioned outside the sail 14, in particular inside the secondary structure 42 of the mast 18. According to one configuration, the waterproof housing 72 or at least one of the waterproof housings 72, 72' is positioned under the sail 14 and connected to the latter, as illustrated in the figures 16 And 17 , or to the primary structure 40 of the mast 18 inside the secondary structure 42, as illustrated in the figure 18 . On the figure 17 , the waterproof housing 72 is positioned under the wing 14, and connected to it at the level of the lower wall 28 and the rear spar 30.2. Of course, the waterproof housing 72 could be positioned under the wing and fixed to the latter at the level of the lower wall 28, or at the level of the lower wall and the front spar 30.1.

[0056] The waterproof housing 72 or at least one of the waterproof housings 72, 72' is connected to at least one structure of the aircraft, such as the primary structure 40 of the mast 18 or the structure 24 of the wing 14 for example, by at least one connection system 78.

[0057] According to an embodiment visible on the figures 11 et 13 , the connecting system 78 comprises first and second articulations 78.1, 78.2 connecting a first lateral face of the sealed housing 72 and the rear spar 30.2 and / or the lower wall 28 of the wing 14 as well as a third articulation 78.3 connecting a second lateral face of the sealed housing 72 (opposite the first face) and the lower wall 28 of the wing 14.

[0058] According to this embodiment, each first, second or third articulation 78.1, 78.2, 78.3 comprises a yoke 80 secured to the sealed housing 72 as well as a wing 82 secured to the structure 24 of the wing 14, the yoke 80 and the wing 82 being connected by a pivot axis. According to one arrangement, the pivot axes of the first and second articulations 78.1, 78.2 are aligned and oriented in a first direction, the pivot axis of the third articulation 78.3 being oriented in a second direction approximately perpendicular to the first direction. The pivot axes are preferably removable to be able to detach the sealed housing 72 from the structure of the aircraft to which it is connected.

[0059] Of course, the invention is not limited to these attachment points for the waterproof housing 72 or to this embodiment for the connection system 78. The waterproof housing 72 could be connected to the front spar 30.1, as illustrated in the figure 14 , to the upper wall 26, as shown in the figures 14 et 15 , or only to the lower wall 28, or to one or more ribs 32. According to one configuration, the watertight housings 72, 72' can be connected to the front spar 30.1, and / or to the upper wall 26, and / or to the lower wall 28, and / or to the rear spar 30.2, to one or more ribs 32, the fixing points for the watertight housings 72, 72' being different between said housings. For example, a first watertight housing 72 may be connected to the front spar 30.1 and the top wall 26, while a second watertight housing 72' is connected to the rear spar 30.2 and the top wall 26. According to another example, a first watertight housing 72 may be connected to the front spar 30.1 and the bottom wall 28, while a second watertight housing 72' is connected to the rear spar 30.2 and the bottom wall 28.

[0060] According to a second embodiment visible on the figures 6 et 7 , the sealed container 58 or at least one of the sealed containers 58, 58' is at least partly delimited by at least one structure of the aircraft.

[0061] According to one embodiment, the sealed container 58 or at least one of the sealed containers 58, 58' is delimited by at least one part of a box 34 of the wing 14 and possibly at least one sealing partition 84, 84', 84".

[0062] According to one configuration, the sealed container 58 or at least one of the sealed containers 58, 58' is delimited by the upper and lower walls 26, 28, the front and rear spars 30.1, 30.2 and two ribs 32 of the wing 14 which are configured and connected so as to obtain a sealed box 34. According to this configuration, the box 34 may comprise a floor connecting the front and rear spars 30.1, 30.2 and two ribs 32, substantially horizontal in operation, on which is fixed at least one element among the pump 48 and the heat exchanger 50. Alternatively, the pump 48 and / or the heat exchanger 50 are fixed on the lower wall 28.

[0063] According to another configuration, the sealed container 58 or at least one of the sealed containers 58, 58' is delimited by the upper or lower wall 26, 28, the front and rear longitudinal members 30.1, 30.2, two ribs 32 and a substantially horizontal sealing partition 84. The upper or lower wall 26, 28, the front and rear longitudinal members 30.1, 30.2, the two ribs 32 and the sealing partition 84 are then configured and connected so as to form a sealed container 58 in which the pump 48 and the heat exchanger 50 are positioned.

[0064] The upper or lower wall 26, 28 which delimits the sealed container 58 may comprise an opening 86 sealed by a hatch 88. The hatch 88 is fixed, in particular bolted, to the upper or lower wall 26, 28. The hatch 88 is thus structural. The hatch 88 is also removable. More precisely, the hatch 88 is articulated via ball-jointed yokes, in order to allow the opening of the hatch 88 when the fasteners (bolts) are removed. The hatch 88 comprises, for example, two yokes, between which is arranged a ball joint fixed to a front or rear side member 30.1, 30.2, or to a rib 32. The hatch 88 is articulated via the ball yokes with play, so as to allow support of the hatch 88 on each of its sides when the latter is fixed to the upper or lower wall 26, 28 (i.e. during bolting).The hatch covers 88 are put on standby, and are used only for opening the hatch 88. The hatch covers 88 are therefore not used when the hatch 88 is bolted to the upper or lower wall 26, 28.

[0065] According to another configuration visible on the figure 7 , a first sealed container 58 is delimited by the upper and lower walls 26, 28, the front spar 30.1, two ribs 32 as well as a first sealing partition 84' substantially parallel to the front spar 30.1. The upper and lower walls 26, 28, the front spar 30.1, the two ribs 32 and the first sealing bulkhead 84' are then configured and connected so as to form a first sealed container 58. A second sealed container 58' is delimited by the upper and lower walls 26, 28, the rear spar 30.2, two ribs 32 as well as a second sealing bulkhead 84" substantially parallel to the rear spar 30.2. The upper and lower walls 26, 28, the rear spar 30.2, the two ribs 32 and the second sealing bulkhead 84" are then configured and connected so as to form a second sealed container 58'.The first and second sealing partitions 84', 84" are positioned between the same pair of ribs 32. According to this configuration, the pump 48 is positioned in the first sealed container 58 and the heat exchanger 50 is positioned in the second sealed container 58'.

[0066] At least one wall among the upper and lower walls 26, 28 comprises, at least in line with the pump 48 or the heat exchanger 50, an opening 86 sealed in a sealed manner by a removable hatch 88. On the figure 7 , the upper wall 26 comprises an opening 86 closed by a structural hatch 88 in line with the pump 48, and an opening 86 closed by another structural hatch 88 in line with the heat exchanger 50.

[0067] According to one embodiment, at least one of the first and second sealed containers 58, 58' comprises a floor on which the heat exchanger 50 or the pump 48 is fixed.

[0068] Other solutions are possible for partitioning at least one box 34 of the wing 14 in order to obtain at least one watertight container 58, 58'.

[0069] Of course, the invention is not limited to the embodiments previously described for the sealed container 58, 58' or the hydrogen supply device 44. Whatever the embodiment, the aircraft 10 comprises: a. at least one hydrogen engine 38, b. at least one hydrogen supply device 44 which comprises: i. at least one hydrogen tank 46, ii. at least one piece of equipment 48, 50, such as a pump 48 or a heat exchanger 50 for example, crossed by the hydrogen and positioned between the hydrogen tank 46 and the hydrogen engine 38, c. at least one container 58 sealed against the outside air, in which the equipment of the hydrogen supply device is positioned.

[0070] The sealed container 58 advantageously contains a low oxygen content. By low oxygen content is meant that the oxygen concentration is insufficient to cause an explosion or ignition of the hydrogen. This low oxygen content can be achieved by inerting or evacuating the interior of the sealed container 58.

[0071] Equipment means an element other than a conduit, configured to modify at least one characteristic of hydrogen, such as pressure or temperature for example.

[0072] According to one configuration, the same aircraft may comprise at least one sealed container 58 in the form of a sealed housing 72 separate from the structure of the aircraft and at least one sealed container 58 delimited at least partially by a structure of the aircraft.

[0073] The invention makes it possible to obtain a safe hydrogen installation using existing equipment.

Claims

1. Aircraft comprising at least one hydrogen engine (38) and at least one hydrogen supply device (44) comprising at least one hydrogen tank (46) and at least one item of equipment (48, 50) through which the hydrogen flows and which is positioned between the hydrogen tank (46) and the hydrogen engine (38), the aircraft comprising at least one sealed container (58, 58') sealed from the air outside said container, in which said at least one item of equipment (48, 50) of the hydrogen supply device (44) is positioned, characterized in that the hydrogen supply device (44) comprises at least one detachable connection system upstream or downstream of the sealed container (58, 58'), and in that said at least one sealed container (58, 58') comprises at least one oxygen sensor (68) configured to detect the presence of oxygen or a given concentration of oxygen inside said sealed container (58, 58') and at least one extraction system (70) configured to extract oxygen present in said sealed container (58, 58').

2. Aircraft according to the preceding claim, characterized in that said at least one sealed container (58, 58') comprises at least one connector (66) configured to connect an apparatus for injecting an inert gas.

3. Aircraft according to Claim 1, characterized in that said at least one sealed container (58, 58') comprises at least one connector (66) configured to connect an evacuation apparatus.

4. Aircraft according to one of the preceding claims, characterized in that said at least one sealed container (58, 58') comprises at least one hydrogen sensor (68') configured to detect the presence of hydrogen or a given concentration of hydrogen inside said sealed container (58, 58').

5. Aircraft according to one of the preceding claims, characterized in that said at least one sealed container (58, 58') comprises at least one extraction system (70') configured to extract hydrogen present in said sealed container (58, 58').

6. Aircraft according to one of the preceding claims, characterized in that the hydrogen supply device (44) comprises at least one valve (64, 64', 64") upstream or downstream of the sealed container (58, 58').

7. Aircraft according to one of the preceding claims, comprising at least one structure, and characterized in that said at least one sealed container (58, 58') is a sealed casing (72) separate from said structure of the aircraft, and in that the aircraft comprises at least one linkage system (78) connecting the sealed casing (72) and said structure of the aircraft.

8. Aircraft according to the preceding claim, characterized in that the aircraft comprises a wing (14) having a plurality of boxes (34), and in that said sealed casing (72, 72') is positioned in one of the boxes (34) of the wing (14).

9. Aircraft according to one of Claims 1 to 6, comprising at least one structure, and characterized in that said at least one sealed container (58, 58') is at least partly demarcated by said structure of the aircraft.

10. Aircraft according to the preceding claim, characterized in that the aircraft comprises a wing (14) having a plurality of boxes (34), and in that said at least one sealed container (58, 58') is demarcated by at least part of one of the boxes (34) of the wing (14) and at least one sealing bulkhead (84, 84', 84").

11. Aircraft according to Claim 8 or 10, characterized in that the wing (14) comprises upper and lower walls (26, 28), front and rear spars (30.1, 30.2) and ribs (32) demarcating the boxes (34) of the wing (14), and in that at least one wall from among the upper and lower walls (26, 28) comprises, in line with at least one item of equipment (48, 50) or at least one sealed casing (72, 72'), an opening (74, 74', 86) sealingly closed by a detachable hatch (76, 76', 88).

12. Aircraft according to one of the preceding claims, characterized in that the at least one item of equipment (48, 50) of the hydrogen supply device (44) is a pump (48) or a heat exchanger (50).