Pole plate for use in fuel cell device

Abstract

The present invention provides a plate (12) for use in a fuel cell device (10), the plate (12) comprising a combined fiber arrangement (52) of one or more hollow fibers (54), each hollow fiber (54) configured for conducting a fluid (46) from one end portion (56) of the hollow fiber (54) to the other end portion (56), such that the fluid (46) can be pumped through the one or more hollow fibers (54).

Description

Technical Field

[0001] The invention relates to a plate for use in a fuel cell device, a method for producing the plate, an additive manufacturing device, a computer program, and a computer-readable medium or data carrier signal. Background Art

[0002] In order to achieve emission-free aircraft propulsion, fuel cells have become a promising alternative. Fuel cells, such as proton exchange membrane (PEM) fuel cells, convert the chemical energy of fuels such as hydrogen and oxidants into electrical energy that can operate electrical consumers. Other results are heat and water. Depending on the materials used, the size of the fuel cell, the stacking of the cells, etc., there is an optimal operating temperature. For a typical low-temperature PEM fuel cell, the optimal operating temperature may be in the range of 70°C to 80°C. For smaller fuel cells, it may be sufficient to control the operating temperature with the help of air cooling. Larger energy requirements will require large fuel cell sizes and stacking of several cells. This may cause the operating temperature to exceed the optimal operating temperature. In this case, it may be necessary to control the operating temperature with the help of liquid cooling. Summary of the invention

[0003] An object of the present invention is to provide a fuel cell device which is highly efficient, lightweight and small in size.

[0004] To achieve the object, the present invention provides a plate for use in a fuel cell device, a fuel cell device, a method for producing the plate, an additive manufacturing device, a computer program, and a computer-readable medium or data carrier signal.

[0005] In one aspect, the present invention provides a plate for use in a fuel cell device, the plate comprising a bonded fiber arrangement structure consisting of one or more hollow fibers, each hollow fiber being configured to conduct a fluid from one end portion of the hollow fiber to the other end portion so that the fluid can be pumped through the one or more hollow fibers.

[0006] Preferably, the hollow fibers are respectively:

[0007] - constructed of carbon fiber; and / or

[0008] - configured to provide structural reinforcement to the plate; and / or

[0009] - comprises one or more cavities extending from one of the end portions of the hollow fibers to the other of the end portions.

[0010] Preferably, the polar plate is constructed as a composite material and / or a laminate, the fiber arrangement preferably forming a carbon fiber reinforced plastic composite material.

[0011] Preferably, the hollow fibers are configured for conducting a coolant, preferably a liquid, more preferably water or a water-based coolant.

[0012] Preferably, the fiber arrangement is arranged substantially parallel to and / or in the vicinity of an active surface of the plate, which preferably comprises a plate structure.

[0013] Preferably, the fibre arrangement is integrated into the board structure.

[0014] Preferably, the one or more hollow fibers of the fiber arrangement are aligned substantially along the direction DS of the plate structure.

[0015] Preferably, one or more hollow fibers are arranged parallel to each other and / or fluidly disconnected between end portions.

[0016] Preferably, one or more hollow fibers are incorporated into the filaments, which are preferably thermoplastic filaments.

[0017] Preferably, the fiber arrangement comprises an inlet and / or an outlet, each of which is fluidically connected to a respective end portion of the hollow fibers.

[0018] In another aspect, the present invention provides a fuel cell device comprising a plate according to any of the preceding embodiments.

[0019] In another aspect, the invention provides a fuel cell arrangement comprising a fuel cell device and a fluid supply and / or exhaust device fluidly connected to the fiber arrangement to pump fluid through one or more hollow fibers.

[0020] Preferably, the fuel cell arrangement is configured as a fluid circulation system for circulating a fluid through one or more hollow fibers.

[0021] On the other hand, the present invention provides an aircraft cooling device for cooling fluid in a fluid supply and / or discharge device of an aircraft in flight, the aircraft cooling device being configured as a skin component of the aircraft, the skin component comprising a combined layer of one or more hollow fibers, each hollow fiber being configured to conduct fluid from one end portion of the hollow fiber to the other end portion, so that the fluid supply and / or discharge device is capable of pumping fluid through one or more hollow fibers when connected to the layer fluid.

[0022] Preferably, the hollow fibers are respectively:

[0023] - constructed of carbon fiber; and / or

[0024] - configured to provide structural reinforcement to the skin component; and / or

[0025] - comprises one or more cavities extending from one of the end portions of the hollow fibers to the other of the end portions.

[0026] Preferably, the skin component is constructed as a composite material and / or a laminate, the plies preferably forming a carbon fiber reinforced plastic composite material.

[0027] Preferably, the ply is incorporated in the outermost layer of the skin component.

[0028] Preferably, the hollow fibers are configured for conducting a coolant, preferably a liquid, more preferably water or a water-based coolant.

[0029] Preferably, the skin component is designed as a wing-fuselage fairing, a belly fairing and / or a part of a wing-fuselage fairing, a part of a belly fairing.

[0030] In another aspect, the invention provides an aircraft fluid supply and / or drain arrangement comprising an aircraft cooling arrangement according to any of the preceding embodiments.

[0031] On the other hand, the present invention provides an aircraft fuel cell arrangement structure, which includes an aircraft fluid supply and / or exhaust device and a fuel cell device, wherein the fuel cell device is configured to be fluidically connected to the aircraft fluid supply and / or exhaust device, and the aircraft fluid supply and / or exhaust device is fluidly connected to the fuel cell device to cool the fuel cell device.

[0032] Preferably, the fuel cell device includes a plate including a combined fiber arrangement structure consisting of one or more hollow fibers, each hollow fiber being configured to conduct a fluid from one end portion of the hollow fiber to the other end portion so that the fluid can be pumped through the one or more hollow fibers, and the aircraft fluid supply and / or discharge device is fluidically connected to the fiber arrangement structure for pumping the fluid through the one or more hollow fibers.

[0033] In another aspect, the invention provides an aircraft comprising an aircraft fluid supply and / or exhaust device and / or an aircraft fuel cell arrangement according to any of the preceding embodiments.

[0034] In another aspect, the present invention provides a method for producing a plate for use in a fuel cell device, the method comprising:

[0035] A plate or a portion of a plate according to any of the preceding embodiments is additively manufactured by a printing device.

[0036] In another aspect, the invention provides an additive manufacturing apparatus comprising printing means adapted to print a plate or a portion of a plate according to any of the preceding embodiments, and control means adapted to perform the steps of the method.

[0037] In another aspect, the present invention provides a computer program comprising instructions for causing an additive manufacturing apparatus to perform the steps of the method.

[0038] In another aspect, the invention provides a computer readable medium having stored thereon a computer program or a data carrier signal carrying the computer program.

[0039] In one aspect, the embodiments of the present invention preferably have the following effects or advantages:

[0040] - Reduced weight compared to cast or milled cooling channels;

[0041] - Ability to reduce size compared to cast or milled cooling channels;

[0042] - Provides improved cooling due to proximity to heat sources;

[0043] - Provides improved cooling effect due to improved cooling surface / volume ratio compared to larger channels;

[0044] - Hollow carbon fibers are multifunctional because they fulfill the function of cooling channels in addition to the structural reinforcement function; and

[0045] - Functionality enhanced through the structure of hollow carbon fibers, which are an enabling factor for CFRP bipolar plates that exhibit weight reduction compared to industry existing metal bipolar plates.

[0046] On the other hand, the embodiments of the present invention preferably have the following effects or advantages:

[0047] - Application of a separate heat exchanger / radiator does not increase aerodynamic drag;

[0048] - Reduced weight compared to a separate heat exchanger;

[0049] - No additional space requirements compared to a separate heat exchanger;

[0050] - Lightens the system compared to a separate heat exchanger; and

[0051] -Compatible with the use of hollow carbon fibers as cooling elements in fuel cell stacks. BRIEF DESCRIPTION OF THE DRAWINGS

[0052] Embodiments of the present invention will now be explained in more detail with reference to the accompanying drawings, in which

[0053] Figure 1 An example of a fuel cell device having two bipolar plates is shown;

[0054] Figure 2 An example of a plate arrangement is shown;

[0055] Figure 3 Another example of a plate arrangement is shown;

[0056] Figure 4 Another example of a bipolar plate is shown;

[0057] Figure 5 An embodiment of a plate is shown;

[0058] Figure 6 and Figure 7 Shows Figure 5 Details;

[0059] Figure 8 An example of a hollow fiber is shown;

[0060] Fig. 9 and Fig.10 An electron microscope image of an example hollow carbon fiber is shown;

[0061] Fig.11 An embodiment of a fuel cell arrangement is shown;

[0062] Fig.12 and Fig.13 An example of an aircraft cooling device is shown, which is used to cool a fluid in a fluid supply and / or discharge device of an aircraft in flight;

[0063] Fig.14 An embodiment of an aircraft cooling device is shown;

[0064] Fig.15 Shows Fig.14 Details;

[0065] Fig.16 and Fig.17 An embodiment of an aircraft is shown;

[0066] Fig.18 An embodiment of an aircraft fuel cell arrangement is shown;

[0067] Fig.19 shows the use for production according to Figure 5 The steps of the method of the electrode plate;

[0068] Fig. 20 Shown according to Fig.19 another step of the method; and

[0069] Fig.21 An overview of different cooling strategies for a fuel cell device is shown. DETAILED DESCRIPTION

[0070] Figure 1 An example of a fuel cell device 10 is shown.

[0071] The fuel cell device 10 includes two polar plates or bipolar plates 12 , electrodes 14 in the form of an anode and a cathode, and a membrane 16 .

[0072] The bipolar plates 12 each include two opposing active surfaces 18 and two pairs of opposing side portions 20 that constitute a perimeter 22 of the bipolar plate 12 .

[0073] The plate structures 24 are respectively arranged on the active surfaces 18. The plate structures 24 include one or more gas diffusion channels 26 in the form of protrusions 28 and recesses 30, which are configured to distribute hydrogen 32 and air or oxygen 34.

[0074] In operation of the fuel cell device 10, hydrogen 32 enters through the gas diffusion channels 26 of the left bipolar plate 12 in the figure, and air or oxygen 34 enters through the gas diffusion channels 26 of the right bipolar plate 12 in the figure. The electrochemical process between hydrogen 32 and oxygen 34 results in an electron flow in an electrical circuit 36 ​​bridging the two electrodes 14, which can operate an electrical consumer 38. Other results are heat and water.

[0075] Figure 2 An example of a plate arrangement 40 is shown.

[0076] exist Figure 2 In the embodiment shown, the plate arrangement 40 comprises a first plate 12a and a second plate 12b. The first plate 12a and the second plate 12b each comprise only one active surface 18.

[0077] The plate arrangement 40 can be fluidically connected to a fluid supply and / or discharge device, which will be described later. To this end, the plate arrangement 40 further comprises a cooling section 42 for cooling the first and second plates 12a, 12b.

[0078] The cooling section 42 is arranged between the first pole plate 12a and the second pole plate 12b and includes a plurality of cooling channels 44. However, the cooling section 42 may also include a single cooling channel 44 within the scope of the present invention.

[0079] The cooling channels 44 are incorporated in the cooling section 42. Furthermore, the cooling channels 44 are arranged in parallel with each other and are fluidly disconnected between end portions 48 of the respective cooling channels 44. In addition, the plurality of cooling channels 44 extend from one end of the cooling section 42 to the other end aligned substantially along the direction DC of the cooling section 42.

[0080] The cooling channel 44 is configured for conducting a fluid 46 between end portions 48 of the cooling channel 44. The fluid 46 may be provided in the form of a gas or a liquid. The fluid 46 is preferably configured as a coolant, in particular a liquid such as water 50 or a water-based coolant.

[0081] In the present case, the cooling channels 44 are designed for conducting water 50. The active surfaces 18 of the first and second pole plates 12a, 12b are arranged on the sides of the pole plates 12a, 12b, respectively, opposite to the cooling section 42. The end portions 48 of the cooling channels 44 are arranged such that a fluid 46 can be pumped through the cooling channels 44 and / or the end portions 48 of the cooling channels 44 are accessible such that a fluid 46 can be pumped through the cooling channels 44.

[0082] Figure 3 Another example of a plate arrangement 40 is shown.

[0083] like Figure 3 The examples shown may include reference Figure 2 However, Figure 2 In contrast to the illustrated embodiment of the pole plate arrangement 40 , here the cooling section 42 comprises a single integrated cooling channel 44 extending through the cooling section 42 .

[0084] Figure 4 Another example of a bipolar plate 12 is shown.

[0085] like Figure 4 The examples shown may include reference Figure 1 , Figure 2 and Figure 3 Any of the characteristics discussed. Figure 1 The embodiment of the bipolar plate 12 shown and Figure 2 and Figure 3 In contrast to the embodiment of the illustrated plate arrangement 40 , in this case a plurality of cooling channels 42 are integrated into the bipolar plate 12 in the region between the active surfaces 18 .

[0086] Figure 5 An embodiment of a polar plate or bipolar plate 12 is shown, and Figure 6 and Figure 7 Details of the bipolar plate 12 are shown.

[0087] like Figure 5 The bipolar plate 12 shown is capable of being fluidically connected to a fluid supply and / or exhaust device, which will be described later. To this end, the bipolar plate 12 includes two fiber arrangements 52, each of which is arranged approximately parallel to and near the corresponding active surface 18. However, within the scope of the present invention, the bipolar plate 12 may also include a single fiber arrangement 52.

[0088] The fiber arrangements 52 are incorporated into the bipolar plates 12. In the present case, the fiber arrangements 52 are each incorporated into the plate structure 24 of the corresponding active surface 18. Furthermore, each fiber arrangement 52 comprises a plurality of hollow fibers 54. However, within the scope of the invention, each fiber arrangement 52 may also comprise a single hollow fiber 54.

[0089] Furthermore, the hollow fibers 54 of the respective fiber arrangements 52 are arranged parallel to each other and fluidly disconnected between end portions 56 of the respective hollow fibers 54. In addition, the plurality of hollow fibers 54 of the respective fiber arrangements 52 are aligned substantially along the direction DS of the plate structure 24.

[0090] The hollow fibers 54 are configured to conduct the fluid 46 between the end portions 56 of the hollow fibers 54. The fluid 46 may be provided in the form of a gas or a liquid. The fluid 46 is preferably configured as a coolant, in particular a liquid such as water 50 or a water-based coolant.

[0091] In addition, the hollow fibers 54 are configured as structural reinforcements for the bipolar plate 12. Thus, the bipolar plate 12 can be configured as a composite material and / or a laminate, wherein the fiber arrangement 52 preferably constructs a carbon fiber reinforced plastic composite material. The end portions 56 of the hollow fibers 54 are arranged so that the fluid 46 can be pumped through the hollow fibers 54 and / or the end portions 56 of the hollow fibers 54 are accessible so that the fluid 46 can be pumped through the hollow fibers 54.

[0092] Figure 8 An example of a hollow fiber 54 is shown.

[0093] Figure 8The illustrated hollow fibers 54 include a single cavity 58 that extends continuously between end portions 56 of the hollow fibers 54. However, it is within the scope of the present invention that the hollow fibers 54 include more than one cavity 58. The hollow fibers 54 may be incorporated into filaments 60, which are preferably thermoplastic filaments.

[0094] In a preferred embodiment, the hollow fibers 54 are hollow carbon fibers 62. Examples of such hollow carbon fibers 62 are as follows: Fig. 9 and Fig.10 As shown, Fig. 9 and Fig.10 Electron microscope images showing hollow carbon fibers 62 of different diameters. The outer diameter DO of the hollow carbon fiber 62 having one cavity 58 may be in the range of 50 μm to 100 μm ( Fig. 9 ). This can be contrasted with solid standard carbon fibers which have diameters in the range of 7 μm to 10 μm. Alternatively, hollow carbon fibers 62 ( Fig.10 ). These hollow carbon fibers may have an outer diameter DO in the range of 10 μm to 20 μm.

[0095] Fig.11 An embodiment of a fuel cell arrangement 64 is shown.

[0096] The fuel cell arrangement 64 includes an embodiment of the fuel cell device 10 .

[0097] The fuel cell device 10 includes a Figure 5 , Figure 6 and Figure 7 The fuel cell device 10 can thus be fluidically connected to a fluid supply and / or exhaust device, which will be described later. For better representation, only the fiber arrangement 52 of the bipolar plate 12 is shown.

[0098] The fiber arrangement 52 of the bipolar plate 12 includes an inlet 66 and an outlet 68. The inlet 66 and the outlet 68 are respectively connected to the corresponding end portion 56 of the hollow fiber 54. In addition, the inlet 66 and the outlet 68 are integrated into the polar plate or bipolar plate 12. However, within the scope of the present invention, the inlet 66 and / or the outlet 68 can also be outside the polar plate or bipolar plate 12 and / or the fuel cell device 10.

[0099] The fuel cell arrangement 64 further comprises a fluid supply and / or discharge device 70 for pumping the fluid 46 through the hollow fibers 54. To this end, the fluid supply and / or discharge device 70 comprises a tank 72 filled with the fluid 46 and a pipe arrangement 74 for conducting the fluid 46 to the inlet 66. The pipe arrangement 74 comprises a pump 76 for pumping the fluid 46 to the inlet 66. In the inlet 66, the fluid 46 is distributed among the hollow fibers 54. The fluid supply and / or discharge device 70 further comprises a temperature exchange or cooling device 80 for cooling the fluid 46.

[0100] like Fig.11 The fuel cell arrangement 64 shown is configured as a fluid recirculation system 78 for circulating the fluid 46 through the hollow fibers 54. In other words, the fluid 46 from the outlet 68 is reused for cooling the fuel cell arrangement 10. To this end, the fluid 46 is conducted from the outlet 68 to a cooling device 80, where the fluid 46 can be cooled down again. From the cooling device 80, the fluid 46 returns to the tank 72 via a further pipe arrangement 82.

[0101] Within the scope of the invention, a cooling device 80 of the fluid supply and / or discharge device 70 can also be arranged upstream of the fuel cell device 10 .

[0102] The fuel cell arrangement 64 may additionally include a temperature sensor for sensing the temperature of the bipolar plate 12. Thus, the fluid supply and / or exhaust system 70 may be controlled or operated based on the measured temperature as desired.

[0103] Fig.12 and Fig.13 An example of a cooling device 80 is shown for cooling the fluid 46 in the fluid supply and / or drain 70 of an aircraft 88 in flight.

[0104] like Fig.12 As shown, cooling device 80 may be attached to engine 90 of aircraft 88. Engine 90 may include propeller 92. Cooling device 80 includes radiator or heat exchanger 96 and radiator cover 98. Fig.13 As shown, the cooling device 84 may additionally or alternatively be attached to a belly fairing 100 of an aircraft 88. In both cases, airflow 102 is directed to the cooling device 84.

[0105] Fig.14 1 shows an embodiment of an aircraft cooling device 84 for cooling a fluid 46 in a fluid supply and / or discharge device 70 of an aircraft 88 in flight. Fig.15 Shows Fig.14 details.

[0106] The aircraft cooling device 84 is designed as a skin component 104 for the aircraft 88 and / or as a skin component 104 of the aircraft 88 . The skin component 104 can be fluidically connected to the fluid supply and / or discharge device 70 .

[0107] To this end, the skin component 104 includes a ply 106 composed of a plurality of hollow fibers 54, such that the fluid supply and / or discharge device 70, when in fluid connection with the ply 106, is capable of pumping the fluid 46 through the hollow fibers 54, the plurality of hollow fibers 54 being as described with reference to FIG. Figures 8 to 10 However, within the scope of the present invention, the ply 106 may also include a single hollow fiber 54.

[0108] The ply 106 is arranged near an outer surface 108 of the skin component 104. Furthermore, the ply 106 is incorporated into the skin component 104. Here, the ply 106 is incorporated into an outermost layer 110 of the skin component 104.

[0109] The plurality of hollow fibers 54 of the ply 106 are arranged parallel to one another and are fluidly disconnected between end portions 56 of the respective hollow fibers 54 .

[0110] The hollow fibers 54 are configured to conduct the fluid 46 between the end portions 56 of the hollow fibers 54. In addition, the hollow fibers 54 are configured as structural reinforcements for the skin component 104. Therefore, the skin component can be considered a composite material and / or a laminate, with the plies 106 preferably constituting a carbon fiber reinforced plastic composite material. The end portions 56 of the hollow fibers 54 are arranged so that the fluid 46 can be pumped through the hollow fibers 54 and / or the end portions 56 of the hollow fibers 54 are accessible so that the fluid 46 can be pumped through the hollow fibers 54.

[0111] In a preferred embodiment, the hollow fibers 54 may also be carbon fibers 62 having one or more cavities 58 .

[0112] Fig.16 and Fig.17 88. Fig.14 and Fig.15 An aircraft cooling arrangement 84 is described.

[0113] like Fig.16 As shown, the aircraft cooling device 84 may be incorporated into a wing-to-body fairing 114 between the fuselage 116 and the wings 118 of the aircraft 88. Fig.17As shown, the aircraft cooling device 84 can also be integrated into the belly fairing 100. In both cases, the airflow 102 is directed to the aircraft cooling device 84.

[0114] Fig.18 An embodiment of an aircraft fuel cell arrangement 120 for use with aircraft 88 is shown.

[0115] like Fig.16 The illustrated aircraft fuel cell arrangement 120 includes an embodiment of an aircraft fuel supply and / or exhaust assembly 122 .

[0116] The aircraft fuel supply and / or discharge device 122 includes a Fig.14 and Fig.15 An aircraft cooling device 84 is depicted, a first pipe arrangement 74a, and a second pipe arrangement 74b. Each pipe arrangement 74a, 74b has a pump 76, an inlet 66 and an outlet 68.

[0117] The aircraft fuel cell arrangement 120 also includes Fig.11 A fuel cell device 10 is described.

[0118] The skin component 104 of the aircraft cooling device 84 is fluidically connected to the inlet 66 of the first conduit arrangement 74a. Downstream thereof, the outlet 68 of the first conduit arrangement 74a is fluidically connected to the fuel cell device 10. Further downstream thereof, the fuel cell device 10 is fluidically connected to the inlet 66 of the second conduit arrangement 74b. Further downstream thereof, the outlet 68 of the second conduit arrangement 74b is fluidically connected to the skin component 104. In other words, the aircraft fuel cell arrangement 120 is also configured as a fluid circulation system 78.

[0119] In the following, reference is made to Fig.19 and Fig. 20 Describes the Figure 5 , Figure 6 and Figure 7 A method for producing a polar plate or bipolar plate 12.

[0120] Fig.19 The steps of the method are shown.

[0121] This step includes additive manufacturing of the polar plate or bipolar plate 12 . The additive manufacturing is achieved by an additive manufacturing device 124 including a printing device 126 .

[0122] In the present case, the printing device 126 comprises a coaxial printing head 128. The coaxial printing head 128 comprises a first spool 130 and a second spool 132. The hollow fiber 54 is wound around the first spool 130. The filament 60 is wound around the second spool 132.

[0123] The additive manufacturing apparatus further includes a robotic arm 134. The coaxial print head 128 is attached to the robotic arm 134.

[0124] The additive manufacturing device 124 further includes a control device (not shown) which is suitable for controlling the printing device 126 and the robot arm 134 .

[0125] A computer program (not shown) is stored in the control device. The computer program causes the additive manufacturing device 124 to perform the following steps:

[0126] The coaxial print head 128 prints the bonded filament 136. In other words, the coaxial print head 128 adds the filament 60 to the hollow fiber 54. Thus, the hollow fiber 54 is printed to be bonded in the filament 60 and / or surrounded by the filament 60.

[0127] A plurality of bonding filaments 136 can be printed parallel to each other for building the fiber arrangement 52. Thus, the bonding filaments 136 can be stacked. The bonding filaments 136 can additionally be printed equidistant from each other.

[0128] Fig. 20 A further step of the method is shown.

[0129] The bonding filament 136 is printed near the active surface 18, which is adjacent to one of the electrodes 14. Here, the bonding filament 136 is printed on the plate structure 24 and / or the bonding filament 136 is bonded to the plate structure 24. In other words, the plate structure 24 can be configured as the fiber arrangement structure 52, and the fiber arrangement structure 52 can be configured as the plate structure 24. Therefore, the fiber arrangement structure 52 is advantageously arranged close to the heat source.

[0130] According to a preferred embodiment of the present invention, a fiber arrangement structure 52 composed of one or more hollow fibers 54 may be arranged to be incorporated in the plate 12 and close to a heat source, thereby achieving effective cooling of the plate 12 and the fuel cell device 10.

[0131] According to a preferred embodiment of the present invention, a ply 106 of one or more hollow fibers 54 may be incorporated into a skin component 104 of an aircraft 88. Thus, the airflow 102 may be used to cool down the fluid 46 in the aircraft fluid supply and / or exhaust 122.

[0132] In one aspect, the present invention provides a plate 12. The present invention also provides a fuel cell device 10, a fuel cell arrangement 64, a method for producing a plate 12, an additive manufacturing device 124, a computer program, and a computer readable medium (not shown) on which the computer program is stored.

[0133] In another aspect, the present invention provides an aircraft cooling device 84 for cooling a fluid 46 in a fluid supply and / or exhaust device 70. The present invention also provides an aircraft fluid supply and / or exhaust device 122, an aircraft fuel cell arrangement 120, and an aircraft 88.

[0134] Various aspects of the preferred embodiments of the present invention can be summarized as follows:

[0135] To achieve emission-free aircraft propulsion, fuel cells have emerged as a promising alternative to convert energy stored in liquid hydrogen tanks into electricity to power electric engines.

[0136] Figure 1 The main structure of the most commonly used proton exchange membrane (PEM) fuel cell is shown. The components from left to right are: bipolar plate, electrode, membrane, then second electrode and second bipolar plate.

[0137] Hydrogen enters through the gas diffusion channels in the left bipolar plate. Air or oxygen enters through the gas diffusion channels of the right bipolar plate. The electrochemical process between hydrogen and oxygen results in an electron flow in a circuit bridging the two electrodes (or several cells if several cells are stacked), which can operate electrical consumers. Other results are heat and water leaving the right electrode.

[0138] There is an optimum operating temperature depending on the materials used, the size of the fuel cell, the stacking of cells, etc. For a typical low temperature PEM fuel cell, the optimum operating temperature may be in the range of 70°C to 80°C. For smaller fuel cells, air cooling may be sufficient. Larger energy requirements will require a large fuel cell size and a stacking of several cells. This may cause the operating temperature to exceed the optimum operating temperature. In this case, liquid cooling may be required.

[0139] exist Figure 2 , liquid cooling of a stacked PEM fuel cell is shown with the aid of dedicated cooling channels. Here, these cooling channels are located in special cooling sections mounted between the plates (i.e., the bipolar plates are divided here into one plate each for hydrogen and oxygen). The liquid coolant is passed through the cooling channels under pressure at the rate required to maintain the optimum operating temperature. Figure 3 As shown, a single cooling channel can also be used for cooling.

[0140] exist Figure 2 The solution seen in is simple and allows to re-equip air-cooled fuel cells with liquid cooling. However, it implies an additional segment, usually made of metal. This significantly increases the weight and size of the stacked fuel cells. Therefore, this solution, while suitable for land-based applications, may not be optimal for airborne fuel cells.

[0141] Other solutions preferably include e.g. Figure 4 A bipolar plate with integrated coolant channels is shown. Figure 2 This solution, a variation of the solution in , can be constructed slightly more compact and this solution may not be so disadvantageous. However, it also applies here that the bipolar plates increase significantly in size and weight due to the additional coolant channels. Since this solution also leads to an increase in weight and volume, it may not be suitable for airborne applications.

[0142] Since the 1950s, in addition to the known solid reinforcing fibers, reinforcing fibers that exhibit one or several internal cavities have been studied. The fiber materials range from glass to carbon. There are variants with one or more cavities inside the fiber. Figure 8 shows a carbon fiber having a single continuous cavity inside, and Fig. 9 An electron microscope image thereof is shown. The outer diameter of these fibers can be in the range of 50 μm to 100 μm. This can be contrasted with solid standard carbon fibers, which have diameters in the range of 7 μm to 10 μm. Recent research has also produced new variations of hollow carbon fibers with multiple cavities, which have been shown to have outer diameters in the range of 10 μm to 20 μm (see Fig.10 These different variations of hollow carbon fibers can be used for a variety of purposes, such as transporting gases or liquids.

[0143] In addition to the well-known short-fiber and long-fiber reinforcement of additively manufactured plastic parts, recent advances also allow continuous reinforcement fibers. Fig.19 A plastic part additively manufactured by means of a print head that produces filaments with bonded continuous fibers is shown. The fibers are provided from separate spools in addition to the filament spools. The fibers can be made of standard fiber bundles ("tows" or single cables, such as copper cables). The fiber material can be glass or carbon.

[0144] The idea of ​​the preferred embodiment of the present invention is to achieve effective liquid cooling of stacked fuel cells by using multifunctional hollow carbon fibers directly as gas diffusion channels in the bipolar plates. This arrangement will save weight because no space needs to be added for large cooling channels, and the coolant acts closer to the heat source, which is the electrode / membrane with the electrochemical reaction. The fibers are multifunctional in that they function structurally and transport liquid coolant.

[0145] Figure 5 , Figure 6 and Figure 7An additively manufactured thermoplastic bipolar plate with bonded continuous hollow carbon fibers used as structural reinforcement as well as cooling channels is shown. The thermoplastic material can be provided with, for example, graphene at the faces for better electrical connections and with, for example, carbon nanotubes (CNTs) to improve internal conductivity.

[0146] Using multiple coolant channels is more efficient than using one or a few large channels. The reason is that for a given volume of liquid coolant, using smaller channels increases the total surface area.

[0147] As can be seen from the figure, the hollow carbon fibers are arranged in the wall region between the gas diffusion channels on both sides of the bipolar plate, ie for both hydrogen and air / oxygen.

[0148] exist Fig.11 In Figure 1, a schematic diagram of the cooling function of the hollow carbon fiber is shown, including a coolant tank, a pump, the hollow carbon fiber, and a possible recirculation system. Therefore, the hollow carbon fiber helps to cool the bipolar plate because the cooling liquid passes through the hollow carbon fiber. This effect is promoted by the proximity to the heat source, which is the electrode membrane section of the fuel cell.

[0149] Fig. 20 An example of how hollow carbon fibers can be incorporated into a bipolar plate is shown. Fig.19 The additive manufacturing print head discussed incorporates cables or fiber bundles into the thermoplastic filaments. Figure 8 , Fig. 9 and Fig.10 The hollow carbon fibers in question are used here as binding fibers in the filaments. As can be seen in the figure, the hollow fibers are arranged to function as cooling channels and are positioned close to the edge and adjacent to the electrodes of the fuel cell, ie close to the source of heat generation.

[0150] There are different cooling strategies for fuel cells. The simplest is to let the air embedded in the cathode also act as an air coolant, see Fig.21 The leftmost strategy in the figure. The next strategy is to use a separate cooling section with air channels, see the second strategy from the left in the figure. The next strategy is a separate liquid cooling section, see the third strategy from the left in the figure. Evaporative cooling (fourth strategy from the left) and cooling with a heat spreader 138 (rightmost strategy) are also shown.

[0151] In order to cool the coolant in land and air vehicles, headwind cooling is often used. Especially in aircraft, where the outside temperature is approximately −60° C., there is a cooling potential that should be utilized.

[0152] Depending on the size and location of the fuel cell, this offers the possibility of: a heat exchanger / radiator at the engine, such as is suitable for piston engines, see Fig.12 ; or heat exchangers / radiators in other upwind locations, such as radiators in belly fairings, see Fig.13 What these solutions all have in common is that they generate considerable aerodynamic drag, which increases energy consumption.

[0153] The idea of ​​a preferred embodiment of the invention is to have a large effective cooling surface for the fuel cell liquid coolant without affecting the aerodynamics.

[0154] The preferred embodiment of the invention proposes to use hollow carbon fibers to cool the cooling liquid of the fuel cells in the aircraft and to have them act as reinforcements in one of the outermost layers of the composite laminate as the outer skin facing the cold outside air (-60°C). In this way, the surface will remain aerodynamic and will not create additional drag. At the same time, if ducts are used, little weight will be required compared to a "radiator" type heat exchanger. In this way, a relatively large cooling surface can be used compared to the limited radiator area.

[0155] Fig.14 A composite laminate having hollow carbon fibers in the outermost layer is shown, with details such as Fig.15 shown.

[0156] Fig.18 The overall system for cooling a fuel cell stack in an aircraft by means of a liquid coolant cooled by air flow over an aerodynamic composite laminate is shown.

[0157] Fig.16 and Fig.17 An example of practical application of an aerodynamic heat exchanger with hollow carbon fibers in the outermost layer as a wing-fuselage fairing ( Fig.16 ) and belly fairing ( Fig.17 ). In this way, no additional aerodynamic drag will occur and weight is reduced compared to a separate heat exchanger in the form of a radiator.

[0158] Reference numerals:

[0159] 10 Fuel cell device

[0160] 12-pole plate or bipolar plate

[0161] 12a First plate

[0162] 12b Second plate

[0163] 14 electrodes

[0164] 16 Film

[0165] 18 Active Surface

[0166] 20 Side

[0167] 22 circumference

[0168] 24-board structure

[0169] 26 Gas Diffusion Channel

[0170] 28 protrusion

[0171] 30 recesses

[0172] 32 Hydrogen

[0173] 34 Air / Oxygen

[0174] 36 Circuits

[0175] 38 Power Consumables

[0176] 40 plate arrangement structure

[0177] 42 Cooling section

[0178] 44 cooling channels

[0179] 46 Fluid (gas or liquid)

[0180] 48 End portion of cooling channel

[0181] 50 water

[0182] 52 fiber layout structure

[0183] 54 Hollow Fiber

[0184] 56 End portion of hollow fiber

[0185] 58 Cavity

[0186] 60 filaments

[0187] 62 Carbon Fiber

[0188] 64 Fuel cell layout

[0189] 66 Entrance

[0190] Exit 68

[0191] 70 Fluid supply and / or discharge device

[0192] 72 cans

[0193] 74 Pipeline layout structure

[0194] 74a First pipeline arrangement structure

[0195] 74b Second pipeline arrangement structure

[0196] 76 Pumps

[0197] 78 Fluid Recirculation System

[0198] 80 Temperature exchange / cooling device

[0199] 82 Another pipeline layout structure

[0200] 84 Aircraft cooling device

[0201] 88 aircraft

[0202] 90 Engine

[0203] 92 propeller

[0204] 96 Radiator / Heat Exchanger

[0205] 98 Radiator Cover

[0206] 100 Belly Fairing

[0207] 102 Airflow

[0208] 104 Skin parts

[0209] 106 layers

[0210] 108 outer surface

[0211] 110 Outermost layer

[0212] 114 Wing-to-Fuse Fairing

[0213] 116 body

[0214] 118 Wing

[0215] 120 Aircraft fuel cell layout structure

[0216] 122 Aircraft fluid supply and / or discharge device

[0217] 124 Additive Manufacturing Device

[0218] 126 Printing device

[0219] 128 coaxial print head

[0220] 130 First Spool

[0221] 132 Second Spool

[0222] 134 Robotic Arm

[0223] 136 combined filament

[0224] 138 heat diffuser

[0225] Direction of DS board structure

[0226] DO outer diameter

[0227] Direction of DC cooling section.

Claims

1. A plate (12) for use in a fuel cell device (10), the plate (12) comprising a bonded fiber arrangement (52) consisting of one or more hollow fibers (54), each hollow fiber (54) being configured to conduct a fluid (46) from one end portion (56) of the hollow fiber (54) to another end portion (56), so that the fluid (46) can be pumped through one or more of the hollow fibers (54).

2. The electrode plate (12) according to claim 1, wherein: The hollow fibers (54) are respectively: constructed of carbon fiber (62); and / or configured to provide structural reinforcement to the plate (12); and / or One or more cavities (58) are included, the cavities (58) extending from one of the end portions (56) of the hollow fibers (54) to the other of the end portions (56).

3. A polar plate (12) according to any one of the preceding claims, wherein: The hollow fibers (54) are configured to conduct a coolant, preferably a liquid, more preferably water (50) or a water-based coolant.

4. A polar plate (12) according to any one of the preceding claims, wherein: The fiber arrangement (52) is arranged substantially parallel to and / or in the vicinity of an active surface (18) of the plate (12), the active surface (18) preferably comprising a plate structure (24).

5. The electrode plate (12) according to claim 4, wherein: The fiber arrangement (52) is integrated into the plate structure (24).

6. The electrode plate (12) according to claim 4 or 5, wherein: One or more of the hollow fibers (54) of the fiber arrangement structure (52) are aligned substantially along the direction (DS) of the plate structure (24), and / or wherein one or more of the hollow fibers (54) are arranged parallel to each other and / or are fluidically disconnected between the end portions (56) of the hollow fibers (54).

7. A polar plate (12) according to any one of the preceding claims, wherein: One or more of the hollow fibers (54) are incorporated into a filament (60), which is preferably a thermoplastic filament.

8. A polar plate (12) according to any one of the preceding claims, wherein: The fiber arrangement (52) comprises an inlet (66) and / or an outlet (68), each of which is fluidically connected to the corresponding end portion (56) of the hollow fiber (54).

9. A fuel cell device (10) comprising a plate (12) according to any one of the preceding claims.

10. A fuel cell arrangement (64), comprising a fuel cell device (10) according to claim 9 and a fluid supply and / or discharge device (70), wherein the fluid supply and / or discharge device (70) is fluidically connected to the fiber arrangement (52) for pumping a fluid (46) through one or more of the hollow fibers (54).

11. The fuel cell arrangement (64) according to claim 10, wherein: The fuel cell arrangement (64) is configured as a fluid circulation system (78) for circulating the fluid (46) through one or more of the hollow fibers (54).

12. A method for producing a plate (12) for use in a fuel cell device (10), the method comprising: A polar plate (12) or a portion of the polar plate (12) according to any one of claims 1 to 8 is additively manufactured by a printing device (126).

13. An additive manufacturing device (124), comprising a printing device (126) suitable for printing a plate (12) or a part of the plate (12) according to any one of claims 1 to 8, and a control device suitable for executing the steps of the method according to claim 12.

14. A computer program comprising instructions for causing an additive manufacturing device (124) according to claim 13 to execute the steps of the method according to claim 12.

15. A computer-readable medium on which is stored a computer program according to claim 14 or a data carrier signal carrying a computer program according to claim 14.

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