Energy conversion arrangement, energy system, propulsion unit and aircraft for an aircraft

Abstract

An energy conversion arrangement, an energy system, a propulsion unit and an aircraft are provided for an aircraft, the aircraft (1) comprising an energy conversion arrangement (10) and / or an energy system (2), wherein the energy conversion arrangement (10) comprises at least one exhaust outlet (13) for discharging exhaust gas (E) generated by a fuel conversion device (11), in particular a fuel cell system (70), for converting at least one fuel into electrical and / or mechanical energy in the fuel conversion device (11), and at least one exhaust assembly (400) configured to mix a flow of the exhaust gas (E) from the at least one exhaust outlet (13) with ambient air (A) from the surrounding environment (7) in at least one mixing zone (406) to facilitate the growth of water droplets by at least partially condensing water vapor contained in the exhaust gas (E) in the mixing zone (406).

Description

Technical Field

[0001] This disclosure relates to the field of anthropogenic climate change caused by cloud cover resulting from condensation generated by the energy systems of aircraft. Specifically, this disclosure relates to energy conversion arrangements for aircraft, energy systems, and in particular, energy systems and propulsion units for powering propulsion units used to propel aircraft, and to aircraft including energy conversion arrangements, energy systems, and / or propulsion units. Background Technology

[0002] Conventional aircraft engines emit water vapor and soot particles. The plume from a conventional engine mixes with ambient air and cools. This causes water vapor to become supersaturated and subsequently form droplets on the soot particles. These droplets freeze and thus form condensation trails. In ice supersaturated regions (ISSRs), these trails persist for extended periods and contribute to global warming.

[0003] For several reasons, hydrogen fuel cell aircraft are an interesting alternative to conventional aircraft propulsion and also generate electricity, as they can replace conventional auxiliary power units (APUs). In particular, hydrogen fuel cell aircraft do not emit carbon dioxide, and are therefore seen as a potential pathway to more sustainable aviation. However, hydrogen fuel cell aircraft emit significant amounts of water. If this water can form persistent condensates, it could contribute to global warming.

[0004] Fuel cells do not emit particulate matter. Due to the low concentration of ambient aerosols, only a small number of droplets can form through heterogeneous nucleation. Instead, most droplets form through homogeneous nucleation, during which molecules condense and form nuclei in the absence of foreign ions or particles. Homogeneous nucleation can occur inside the fuel cell system, such as in turbines or nozzles, or in the plume during mixing with and cooling of ambient air. The occurrence and location of homogeneous nucleation depend on system architecture, operating conditions, and environmental conditions. Homogeneous nucleation results in high concentrations of small droplets, typically less than one micrometer in radius. If these droplets freeze into persistent ice crystals, the resulting condensation trails can have a greater climate impact than those from conventional aircraft engines. Therefore, it is crucial to minimize or completely avoid condensation formation in fuel cell aircraft.

[0005] For example, EP 3 961 012 A1 relates to an apparatus for evaluating flight trails of an aircraft, the apparatus comprising: a trail sensor adapted to generate trail data representing atmospheric parameters that influence the formation of trails or observational parameters that vary according to the presence of at least one or more trails; and a processing unit adapted to calculate at least one trail value representing the amount of trail based on the trail data. The present invention provides such an apparatus and a corresponding method for evaluating the amount of trails generated by an aircraft during flight.

[0006] US 11 579 050 B2 relates to a system configured for mounting on an aircraft. The system includes a probe for collecting a condensate sample, a chamber for collecting the sample, a collection conduit for guiding the sample from the collection probe to the collection chamber, and at least one means for measuring at least one parameter characterizing the sample in the collection conduit while the sample is being guided from the collection probe to the collection chamber. With this system, it is not necessary to use a second aircraft following the aircraft to collect the condensate sample.

[0007] US 5,005,355 A describes a method for suppressing condensation formation in exhaust gas from an engine operating at low temperatures, the method comprising the steps of: providing a combination of a nucleating agent and a freezing point depressant selected from the group consisting of a water-soluble monohydric alcohol, dihydric alcohol, trihydric alcohol, or other polyhydric alcohol or mixtures thereof; forming a solution into vapor; and injecting the solution into the exhaust gas of the engine. The solution may include a non-corrosive surfactant. Another solution may include an organic nucleating agent or an inorganic nucleating agent or a mixture of organic and inorganic nucleating agents in a monohydric alcohol, dihydric alcohol, or polyhydric alcohol or mixtures thereof, and may additionally contain one or more surfactants.

[0008] EP 2 150 692 A2 describes an aircraft including a gas turbine engine, the gas turbine engine producing an exhaust gas plume during operation, and the aircraft including an ultrasonic generator having an ultrasonic actuator and a waveguide for directing ultrasonic waves to the exhaust plume to avoid the formation of condensation.

[0009] EP 2 153 043 A2 describes a method of operating an aircraft and the aircraft itself, the aircraft including a gas turbine engine for an exhaust gas plume in use, the aircraft being characterized by including an electromagnetic radiation generator and a waveguide for directing electromagnetic radiation to the exhaust gas plume to avoid the formation of condensation.

[0010] US 7,971,438 B2 relates to incorporating a condensation stage in a heat exchanger arrangement for a gas turbine engine, wherein the condensation level within the final exhaust gas stream from the engine is reduced. Furthermore, by cooling the exhaust gas stream for mixing with a bypass air stream, a moisture pressure at the exhaust gas outlet temperature can be provided below the phase transition from eutectic liquid to vapor, and thus the formation of condensation (condensation marks) is avoided.

[0011] H. Cruz Champion and S. Kabelac's "Multifunctional fuel cell system for civil aircraft: Study of the cathode exhaust gas dehumidification," International Journal of Hydrogen Energy, Vol. 42, No. 49, 2017, pp. 29518-29531, ISSN 0360-3199, (https: / / doi.org / 10.1016 / j.ijhydene.2017.09.175), describes a cathode exhaust gas dehumidification system based on an air circulation machine (compressor, heat exchanger, cyclone separator, turbine) that supplies liquid water and dry oxygen-deficient air (ODA).

[0012] Systems and methods for reducing condensation, as known from the prior art, do not meet all the requirements for condensation reduction on aircraft. Known systems require additional installation, space, weight, and power consumption. Furthermore, known systems may not be applicable to alternative fuel conversion technologies, such as fuel cells. Summary of the Invention

[0013] Therefore, the objective can be viewed as reducing the climatic impact on aviation operations due to condensation formation. In other words, the objective can be viewed as providing condensation reduction or at least reducing the negative impact of condensation, preferably also for any condensation generated by alternative fuel conversion technologies, such as fuel cells. These objectives are achieved at least in part through the main aspects of the invention.

[0014] In particular, an energy conversion arrangement structure for an aircraft is provided, comprising: at least one exhaust outlet for discharging exhaust gas generated by a fuel conversion device, particularly a fuel cell system, the fuel conversion device being used to convert at least one fuel into electrical and / or mechanical energy; and at least one exhaust assembly configured to mix the flow of exhaust gas from at least one exhaust outlet with ambient air from the surrounding environment in at least one mixing zone to promote the growth of water droplets by at least partially condensing water vapor contained in the exhaust gas in the mixing zone.

[0015] According to one aspect, an energy system is provided, specifically for providing power to a propulsion unit used in a propulsion vehicle, the energy system including a corresponding energy conversion arrangement. The energy system may include a propulsion unit. The energy system may be configured as an engine and / or power plant for the vehicle.

[0016] According to one aspect, a propulsion unit for propelling an aircraft is provided, the propulsion unit including a corresponding energy conversion arrangement structure and / or a corresponding energy system.

[0017] According to one aspect, an aircraft is provided, which includes a corresponding energy conversion arrangement structure, a corresponding energy system, and / or a corresponding propulsion unit.

[0018] At least one exhaust assembly can be arranged at at least one exhaust outlet. Exhaust gas from the exhaust outlet can be directed directly into the exhaust assembly or guided along the exhaust assembly. This helps to provide a simple, reliable, and effective way to establish a mixing zone at the exhaust outlet to reduce condensation without the need for additional major system components, which in turn would increase weight and complexity.

[0019] For example, at least one exhaust outlet can be constructed as part of at least one exhaust assembly. Alternatively or additionally, at least one exhaust assembly can be part of an exhaust outlet. Thus, the energy conversion arrangement, particularly the exhaust assembly, can be designed to provide a mixing zone in a compact and lightweight manner.

[0020] The mixing zone increases the residence time of the exhaust gas at the initial point of contact between the warm, humid exhaust flow and the cold, dry ambient air. This point of contact is highly correlated with droplet formation because the sudden drop in temperature of the flow with a high water content triggers uniform nucleation and thus generates a large number of droplets. Due to the fact that condensate is distributed on an increased number of droplets, the droplets formed in this region are numerous and do not become very large compared to droplets formed further downstream.

[0021] The advantage of this solution lies in shifting the droplet spectrum towards fewer and larger droplets by removing small droplets through their growth in the mixing zone. This is beneficial because removing small droplets is necessary to reduce the severity of the condensation trail to form. Compared to not applying this solution, fewer and larger droplets are provided downstream of the mixing zone in the atmosphere, which helps reduce the severity of the condensation trail.

[0022] The proposed solution offers a reduction in condensation formation for all types of aircraft, including but not limited to fuel cell aircraft. The solution comprises an energy system for the aircraft, including fuel cells for propulsion and / or as an APU. Compared to existing technologies, the proposed solution is lighter, cheaper, uses less space and power, and generates no new emissions. The proposed solution allows for mitigation of the potential drawbacks of fuel cell-powered aircraft by reducing their contribution to condensation formation, thus enhancing the environmental friendliness of fuel cell-powered aircraft.

[0023] Other improvements can be derived from the appended aspects of the invention and from the following description. Features described with reference to the apparatus and arrangement can be implemented as method steps, or features described with reference to the method steps can be implemented as apparatus and arrangement. Therefore, the description provided in the context of energy conversion arrangement structures, energy systems, and / or aircraft is also applicable to the corresponding methods in a similar manner. In particular, the functions of the energy conversion arrangement structure, energy system, and / or aircraft and their corresponding components can be implemented as method steps of the method, and the method steps can be implemented as the functions of the energy conversion arrangement structure, energy system, and / or aircraft.

[0024] According to one embodiment, the mixing zone is configured to gradually mix the exhaust gas into the ambient air. Gradually mixing the exhaust gas into the ambient air increases the residence time of any droplets in the mixing zone and thus promotes droplet growth. This further helps to avoid or at least limit condensation formation and undesirable condensation effects.

[0025] According to an embodiment, the mixing zone includes a premixing zone and a main mixing zone, wherein at least one exhaust branch path of the exhaust assembly guides a branch of the exhaust flow to the premixing zone, and the main passage of the exhaust arrangement guides the main stream of exhaust to the main mixing zone. In the premixing zone, a small portion of the warm, humid exhaust flow can mix with cold, dry ambient air. This results in the formation of initially relatively small droplets after the premixing zone. These droplets can then be conveyed to the main mixing zone, where the relatively larger remaining portion of the warm, humid exhaust flow mixes with the cold, dry ambient air. Here, the earlier formed, relatively small droplets can provide a phase boundary at which condensation will occur. Condensation and the associated latent heat release can reduce the supercooling of water vapor contained in the exhaust. Therefore, the nucleation rate of new droplets in the main mixing zone is much lower than in the case without a premixing zone. Overall, the resulting droplet profile consists of fewer, larger droplets. This can help to further reduce the effects of undesirable condensation trails.

[0026] According to one embodiment, the diversion path is formed as a side channel within a wall portion of the exhaust assembly that at least segmentally separates the exhaust from the ambient air, and / or between the inner wall portion of the sleeve and the main passage. Thus, a relatively small portion of the exhaust flow can be guided to the environment from the main exhaust branch and via the side channel, such as a relatively small pipe, orifice, etc. When the relatively small portion of the exhaust flow comes into contact with the ambient flow, a premixing zone is established and droplets form through nucleation. The droplets can then be transported toward the main mixing zone, where they reduce subcooling through condensation. This can again help to further reduce the effects of undesirable condensation.

[0027] According to one embodiment, the exhaust assembly is configured to promote the formation of exhaust vortices in the recirculated exhaust gas within the mixing zone. The creation of the recirculation zone allows many recently generated droplets to have increased residence time due to immersion in the recirculation zone, thus resulting in a longer time in the supersaturated flow where droplet growth occurs. Compared to the non-recirculation case, this leads to a reduction in the number of small droplets, which is beneficial in avoiding condensation formation or at least in reducing the undesirable effects of condensation.

[0028] According to one embodiment, the exhaust assembly is configured to promote the formation of air vortices in the recirculated ambient air within the mixing zone. Intentional flow stall can be promoted within the mixing zone. Ambient air can thus be drawn into the mixing zone and recirculated within the vortices. Compared to a non-recirculation configuration, this further helps to reduce the number of small droplets, which is beneficial in avoiding condensation formation or at least in reducing the effects of undesirable condensation.

[0029] According to one embodiment, the exhaust vortex and the air vortex come into contact with each other in the recirculation zone of the mixing zone. The recirculation zone can be defined by extensions of the recirculated portions of the exhaust vortex and the air vortex. The residence time of droplets in the mixing zone can be increased by this recirculation to gradually regulate temperature and relative humidity between the exhaust gas on one side and the ambient air on the other. Compared to the non-recirculation case, this further helps to reduce the number of small droplets, which is beneficial to avoiding condensation formation or at least beneficial to reducing the effects of undesirable condensation.

[0030] According to one embodiment, the exhaust assembly includes a lip edge, which provides at least one trailing edge configured to generate a mixing zone. The trailing edge may be formed at and / or provided by the lip edge. The lip edge, and therefore the at least one trailing edge, may be configured to enhance the formation of the mixing zone, particularly the recirculation zone. Thus, compared to the non-recirculation case, the lip edge helps reduce the number of small droplets, which is beneficial in avoiding condensation formation or at least beneficial in reducing the effects of undesirable condensation.

[0031] According to the embodiment, the ratio of the lip edge height to the exhaust outlet height is greater than 0.05, preferably 0.06, and most preferably 0.07. For example, the minimum lip edge height can total approximately 5 mm. The exhaust outlet height can total between 50 mm and 90 mm, preferably between 60 mm and 80 mm, and most preferably approximately 70 mm. This provides a balance between the potential resistance introduced by the lip edge and the advantage of avoiding or at least reducing undesirable condensation effects.

[0032] According to one embodiment, the exhaust assembly includes a spoiler device configured to at least partially provide a lip. The spoiler device may include a spoiler element configured to provide a lip, to promote flow stall at at least one trailing edge, and / or to promote recirculation of exhaust gas and / or ambient air in the mixing zone. The spoiler element may be configured to move between a retracted position and an extended position for modulating exhaust gas and / or airflow in the mixing zone, the retracted position providing minimized lip height and / or turbulence effect with respect to the corresponding flow, and the extended position providing maximized lip height and / or turbulence effect.

[0033] For example, the spoiler element can be at least segmented into spoiler baffles, guide surfaces, and / or guide vanes, and the spoiler element can move and / or deflect between a retracted position and an deployed position. In at least one position, preferably the deployed position, the spoiler element can be tilted at an acute angle relative to the outer wall and / or channel wall to guide ambient air and / or exhaust air toward the mixing assembly respectively. This further helps to strike a balance between the potential drag introduced by the lip on the one hand and the advantage of avoiding condensation or at least reducing the effects of undesirable condensation on the other hand; for example, the spoiler element can be deployed only if potential condensation forms.

[0034] The vertical height of the mixing zone can depend on the height of the lip and / or the spoiler device. In other words, the height of the mixing zone can be defined by the lip height and / or the spoiler height. For example, the ratio of the lip height to the mixing height can total 2 or less. The mixing height can total from 3 mm to 7 mm, preferably from 4 mm to 6 mm, and most preferably about 5 mm.

[0035] According to one embodiment, the exhaust assembly includes a concave lip segment that provides a cavity, at least partially providing a mixing zone. Due to the cavity, two relatively sharp trailing edges can be provided for the exhaust and ambient air, respectively. These relatively sharp trailing edges can contribute to the generation of corresponding flow stall. The cavity can further facilitate the formation of the mixing zone, particularly the recirculation zone. This allows for a reduction in lip height and thus a reduction in the weight and drag of the exhaust assembly.

[0036] According to one embodiment, the outlet passage leading to the exhaust outlet is configured to provide an outflow direction that extends substantially parallel to or at least at an acute angle to the flow direction of the ambient air. The outlet passage can be configured to prevent the flow of ambient air and exhaust gas from converging in the mixing zone. Therefore, the outlet passage can have a certain passage length to achieve an undisturbed attachment flow to the outlet passage.

[0037] For example, the outlet passage can have a length of at least 80 mm to 120 mm, preferably at least 90 mm to 110 mm, and most preferably about 100 mm. The outlet passage can be configured to generate substantially uniform laminar flow and can therefore extend substantially in a straight line along its passage length to promote the formation of relatively stable exhaust vortices. This further helps to establish a mixing zone, and in particular a recirculation zone.

[0038] According to alternative or additional solutions, an energy conversion arrangement structure for an aircraft is provided, comprising: a fuel conversion device, particularly a fuel cell system, for converting at least one fuel into electrical and / or mechanical energy; an exhaust outlet for discharging exhaust gas generated in the fuel conversion device; and at least one water separator arranged in the flow path of the exhaust gas generated in the fuel conversion device and configured to separate water from the products of the fuel conversion device during their journey from the fuel conversion device to the exhaust outlet; wherein the at least one water separator comprises a permeable membrane and / or an absorbent material.

[0039] This solution can be primarily considered for two components of the aircraft's fuel cell system: the fuel conversion arrangement, such as the fuel cell system itself, and the air supply system. The fuel cell system itself converts oxygen and hydrogen into water, providing electricity, water, and waste heat. The air supply provides ambient air, including oxygen, to the fuel cell and exhausts excess air, including water.

[0040] According to this solution, a water separator can be used. The water separator may include a water separation material placed in the exhaust path of the air supply system to extract liquid and gaseous water from the exhaust stream. Water extraction results in a reduction in the humidity of the air supply exhaust stream and therefore a lower risk of condensation formation. For the dehumidification process, water can be discharged in gaseous and / or liquid form. The exhaust gas can cross-flow through the water separator relative to the separated water. The permeable membrane and / or absorbent material can be, in particular, permeable to water molecules.

[0041] The advantage of this solution is that it allows for reduced humidity output because the humidifier reduces the amount of water, such as water droplets, that can form in the exhaust gas after fuel conversion. Once such water droplets are released into a cooler environment as exhaust gas, condensation can occur. Therefore, this solution provides a simple way to reduce the effects of unwanted condensation while supporting the efficient operation of the energy conversion arrangement.

[0042] According to one embodiment, at least one water separator is configured to dehumidify the exhaust gas. Therefore, the water vapor content in the exhaust gas may decrease as it passes through the water separator. This can particularly help reduce the content of gaseous water in the exhaust gas, and thus help reduce the risk of gaseous water in the exhaust gas condensing in subsequent stages within the energy conversion arrangement and / or after the exhaust gas is released to the atmosphere, in which case the gaseous water may cause undesirable condensation.

[0043] According to embodiments, the permeable membrane and / or absorbent material each possess molecular size selectivity properties, at least segmentally. Molecular size selectivity allows for molecular diffusion of water from within the separator. This molecular diffusion can involve surface diffusion, Knudsen diffusion, and / or molecular sieve effects. For example, the permeable membrane and / or absorbent material includes Nafion®. This allows for the simple construction and efficient operation of at least one water separator.

[0044] According to one embodiment, the energy conversion arrangement further includes a heating device disposed in the flow path of the exhaust gas after at least one water separator. The heating device provides a heat source between the water separator and the aircraft's exhaust outlet. Heating reduces the saturation of the exhaust gas flow, i.e., its relative humidity. Lower saturation reduces or completely prevents droplet formation and condensation in the exhaust system. Droplet formation can still occur in the propulsion system plume. However, the likelihood of forming a large number of small droplets is reduced. This reduces the risk of condensation, especially since water may have already been drawn from the exhaust gas in the water separator before reaching the heating device.

[0045] According to an embodiment, the energy conversion arrangement further includes at least one mixing component arranged in the flow path after the water separator and configured to mix the exhaust gas with another exhaust gas from the energy conversion arrangement. Waste heat from the fuel cell aircraft system can be used in the mixing component to avoid high supersaturation in the plume of moist exhaust gas from the fuel conversion device, such as the fuel cell system. This can be achieved by mixing the moist exhaust gas from the air supply system with a warm and dry gas flow before it can be mixed with cold ambient air. As a result, the maximum supersaturation in the plume can be reduced, and therefore the number of droplets formed in the plume can be reduced. The reduction in the number of droplets reduces the amount of ice crystals that may form and thus reduces the condensation effect. In principle, the corresponding solution can utilize any heat source to provide another exhaust gas.

[0046] According to an embodiment, the energy conversion arrangement further includes an expansion device arranged in the flow path of the exhaust gas and configured to depressurize the exhaust gas; wherein at least one water separator is arranged in the flow path before the expansion device, in the flow path after the expansion device, and / or in at least one bypass pipe configured to allow the exhaust gas to bypass the expansion device on its way from the fuel conversion device to the exhaust outlet.

[0047] In a typical air supply system for a fuel conversion device, such as a fuel cell, ambient air is compressed and fed to the fuel conversion device. After the fuel conversion device, the humidified air is typically expanded in an expander, such as a turbine, and then discharged back to the environment. Bypass ducts can be connected to any duct defining the flow path and / or any kind of exhaust source upstream of the expander, thus allowing relatively humid exhaust from the fuel conversion device, such as air from the fuel cell, to partially or completely bypass the expander, such as the turbine. Therefore, no, or at least significantly less, enthalpy is extracted from the fluid exhaust compared to the case where the fluid exhaust is depressurized in the expander.

[0048] Some expansion in a bypass, such as in a valve or nozzle, may be unavoidable, potentially leading to the formation of some droplets. This is due to the high saturation caused by the low static temperature resulting from the high flow rate during expansion. Therefore, the droplets will partially or completely evaporate as the flow slows down. However, as the exhaust flow slows down, the static temperature rises again because the total temperature remains constant. This will cause the droplets formed in the bypass to partially or completely evaporate. Therefore, fewer droplets are discharged, and the condensation contribution of the energy conversion arrangement structure is reduced. Conversely, when depressurization occurs in an expansion device, such as a turbine, the droplets may not evaporate because the expansion device extracts enthalpy and thus lowers the total temperature of the flow.

[0049] This solution particularly allows bypassing the expansion device during flight through an ISSR where persistent condensation trails might form. In this way, no enthalpy is extracted from the humidified exhaust air, and the total temperature of the exhaust air remains constant. Therefore, under stagnant conditions, the saturation temperature remains constant, and thus no droplets form. Therefore, it can be seen that the main advantage of this solution lies in allowing bypassing any component of the energy conversion arrangement that contributes significantly to condensation trails under the corresponding conditions. Emitting fewer or no droplets at the exhaust outlet reduces the condensation trailing effect of the energy conversion system.

[0050] Furthermore, for example, if the expander includes a turbine, bypassing the expander can help prevent the turbine from stalling or becoming blocked under conditions of overload in the mass flow and / or volume flow of the exhaust gas entering the turbine. Therefore, bypass ducts can also be used to adjust the turbine and / or operate it within a desired operating range. Bypass ducts can also help prevent unwanted condensation of water vapor in the exhaust gas contained within the turbine. This is particularly significant if any devices located upstream of the expander, such as heating devices and / or heat exchangers, are absent, not activated, or do not provide the exhaust gas with an amount of heat sufficient to prevent condensation.

[0051] According to an embodiment of the energy conversion arrangement, a bypass pipe is connected to the flow path via a connector. A water separator can be arranged in the bypass pipe. The flow connector can divert exhaust gas to the water separator. The connector can be positioned and shaped such that it advantageously branches and / or completely guides the exhaust gas, directing it through the bypass pipe. Thus, the connector helps improve the operation and flexibility of the energy conversion arrangement.

[0052] According to embodiments of the energy conversion arrangement, the connector includes at least one switching valve for switching the flow path from the fuel conversion device to the expansion device and / or the exhaust outlet. The switching valve can be positioned, shaped, and / or operated such that it advantageously branches and / or fully directs the exhaust gas, guiding it through a bypass pipe. Therefore, the switching valve contributes to further improving the operation and flexibility of the energy conversion arrangement.

[0053] According to the implementation of the energy conversion arrangement, the switching valve allows for gradual switching of the flow path. This allows for adjustment and / or regulation of the amount of exhaust gas passing through the bypass pipe and / or expansion device as needed. This contributes to further improving the operation and flexibility of the energy conversion arrangement.

[0054] According to the implementation of the energy conversion arrangement, the switching valve allows for stepless switching of the flow path. This allows for fine-tuning and / or regulation of the amount of exhaust gas passing through the bypass pipe and / or expansion device, based on specific requirements. This contributes to further improving the controllability and flexibility of the energy conversion arrangement.

[0055] According to an embodiment, the energy conversion arrangement further includes a control unit configured to monitor at least one condensation formation parameter having a condensation formation range indicating the likelihood of condensation formation by exhaust gas from the fuel conversion device and / or by an exhaust mixture containing the exhaust gas from the fuel conversion device and another exhaust gas from the energy conversion arrangement. The control unit is configured to control the dryness ratio of the exhaust gas via at least one water separator to keep the at least one condensation formation parameter outside at least one potential influence area indicating potential condensation effects to be avoided and / or reduced, thus keeping and / or bringing it into the condensation formation range. Potential condensation effects can be avoided by avoiding or at least reducing condensation. The control unit allows the control mechanism to switch between a condensation reduction mode and a standard operating mode of the energy conversion system. Under most flight conditions, condensation reduction is not required, and water separation can be omitted or at least reduced to a minimum. For example, water separation is only performed when certain condensation formation conditions are detected.

[0056] According to one embodiment, the condensation reduction device is configured to introduce water droplets into the flow path, allowing smaller droplets in the exhaust gas to be collected through droplet condensation. The condensation reduction device may be positioned upstream of at least one water separator. The at least one water separator may have at least one exhaust gas inlet, at least one dry outlet, and at least one wet outlet. The condensation reduction device may be arranged in fluid connection with the exhaust gas flow and configured to introduce water droplets into the exhaust gas flow. Therefore, droplets injected into the flow hinder nucleation due to their own growth through condensation and the associated release of latent heat. This reduces supersaturation and thus reduces uniform nucleation. Introducing larger droplets may still be beneficial if uniform nucleation does not occur within the fuel conversion system. The droplets then provide a phase boundary for condensation in the plume. This reduces or at least suppresses uniform nucleation in the plume, thus also contributing to reduced condensation formation and enhanced natural dissipation of condensation.

[0057] According to the implementation, the water introduced by the condensation reduction device is at least partially provided by the water separation device. In other words, water extracted from the exhaust gas by means of a water separator can be reintroduced into the exhaust gas through the condensation reduction device. Therefore, the water separator or water separation device can help enhance the synergistic effect of the condensation reduction device.

[0058] According to another solution, an energy conversion arrangement structure for an aircraft is provided, comprising: a fuel conversion device, particularly a fuel cell system, for converting at least one fuel into electrical and / or mechanical energy; a supply air flow path from an air inlet for entraining air from the surrounding environment, such as the atmosphere, and / or from inside the casing, such as from the aircraft's cabin, to the fuel conversion device for fuel conversion; an exhaust flow path from the fuel conversion device to an exhaust outlet for discharging exhaust gas generated by fuel conversion in the fuel conversion device; and a humidification device arranged in the flow path and configured to humidify the supply air using water from the exhaust gas.

[0059] According to this solution, a humidifier can be used to humidify supply air, which can be supplied to the cathode side of a fuel cell system, or at least support such an air supply with humidified air. This can improve the energy conversion arrangement, particularly the efficiency and / or operation of the fuel cell system. Furthermore, for the humidification process, the discharged water can be used in gaseous and / or liquid form. The exhaust can cross-flow through the humidifier relative to the supply air.

[0060] According to the embodiment, the exhaust gas passes through the humidification device multiple times. The exhaust gas may pass through the humidifier at least twice, for example, by crossing with the supply air at least twice. Therefore, the exhaust gas can be redirected within the humidification device. This can further improve the dehumidification of the exhaust gas and / or the humidification of the supply air.

[0061] According to one embodiment, the energy conversion arrangement further includes an expansion device disposed in the exhaust flow path and configured to depressurize the exhaust; wherein a humidification device is disposed in the exhaust flow path before and / or after the expansion device. The expansion device may be configured to generate electrical and / or mechanical energy by expanding the exhaust. The expansion device may include at least one turbine. The expansion device may be part of an air supply system. Therefore, the expansion device can help improve the overall energy efficiency of the energy conversion arrangement.

[0062] Humidification devices can humidify the supply air using the relatively high humidity of the exhaust gas leaving the turbine, and thus humidify fuel conversion devices, particularly fuel cell systems. The relative humidity of the exhaust gas leaving the expander is typically higher than that of the exhaust gas entering the expander. In particular, arranging a humidification device after the expander allows for enhanced dehumidification of the exhaust gas and / or humidification of the supply air.

[0063] According to an embodiment, the humidification device includes at least two humidification stages, wherein a first humidification stage of the at least two humidification stages is configured to humidify the supply air using water from the exhaust gas from the expansion device, and wherein a second humidification stage of the at least two humidification stages is configured to humidify the supply air using water from the exhaust gas from the fuel conversion device. For example, two-stage humidification of the supply air can be performed: in the first stage, exhaust gas from the turbine can be used, and in the second stage, exhaust gas from the fuel cell device can be used. The advantage of this two-stage arrangement is that sufficient humidification can be provided even if the exhaust gas after the turbine is not sufficiently humidified. Thus, the use of two separate humidifiers can be avoided.

[0064] According to one aspect of the energy conversion arrangement, the energy conversion arrangement also includes an air supply system located upstream of the exhaust outlet for supplying supply air for fuel conversion to the fuel conversion device. Therefore, the exhaust can flow at least partially through the air supply system. Thus, the air supply system can be used to heat the exhaust. This can help reduce condensation formation because the relative humidity of the exhaust is reduced.

[0065] According to one aspect of the energy conversion arrangement, the air supply system includes: a compressor for supplying compressed inlet air to the fuel conversion unit for fuel conversion; and at least one heat exchange unit configured to extract heat from the compressor and / or the compressed air to be converted. The compressor and / or the compressed air can be cooled by means of the heat exchange unit. Therefore, heat exchange can help improve the overall energy efficiency of the energy conversion arrangement while also helping to reduce condensation.

[0066] According to one aspect of the energy conversion arrangement, at least one heat exchange unit is configured to heat the exhaust gas. Heating the exhaust gas can help reduce the relative humidity of the exhaust gas. The reduced relative humidity can reduce the amount of condensation produced and can promote the dissipation of any remaining condensation.

[0067] According to an embodiment, the energy conversion arrangement further includes at least one particulate filter element and / or at least one chemical filter element, respectively arranged in the flow path of the supply air before and / or after at least one heat exchange unit. At least one particulate filter element can help remove unwanted particles and / or contaminants from the supply air. This can contribute to further improvements in the operation of the humidification device and / or the energy conversion arrangement.

[0068] According to one embodiment, the air supply system is configured to be at least partially cooled by exhaust gas from the humidifier. Exhaust gas from the turbine (which can subsequently be cooled) can be used to cool the supply air from the compressor / filter. Therefore, the heat exchange unit can function as an air (exhaust) / air intercooler. This can contribute to further improvements in the efficient operation of the energy conversion arrangement.

[0069] According to an embodiment, the energy conversion arrangement further includes at least one water separator arranged in the flow path of the exhaust gas generated in the fuel conversion device and configured to separate water from the products of the fuel conversion device during their journey from the fuel conversion device to the exhaust gas outlet. When the exhaust gas has particularly high relative humidity, the water separator can help initially remove water from the exhaust gas. The water separated from the exhaust gas can be discharged and / or used to supply condensation reduction devices to the energy conversion arrangement. Therefore, the water separator helps avoid undesirable condensation effects.

[0070] According to one embodiment, at least one water separator is arranged between the fuel conversion unit and the humidification unit. This arrangement of the water separator can particularly help remove excess water from the exhaust gas, which may not be effectively used and / or is not necessary for the humidification process. This can contribute to further improving the efficient operation of the energy conversion arrangement.

[0071] According to an embodiment, at least one water separator includes a permeable membrane and / or an absorbent material. The permeable membrane and / or absorbent material can be, in particular, permeable to water molecules. This allows for a simple construction and efficient operation of at least one water separator.

[0072] According to one embodiment, the energy conversion arrangement also includes a control unit configured to adjust the humidity of the supply air based on at least one measurement to provide humidity control for the fuel conversion unit. This allows the control unit to switch between a condensation reduction mode and a standard operating mode of the energy conversion system and / or to adjust the humidification of the supply air according to certain operational requirements of the fuel conversion unit. This can contribute to further improvements in the operation of the humidification unit and / or the energy conversion unit, while allowing selective avoidance of undesirable condensation effects.

[0073] According to another solution, a method is provided for controlling an energy conversion arrangement structure used in an aircraft, the energy conversion arrangement structure including a fuel conversion device having a fuel cell system for converting at least one fuel into electrical energy, the method comprising the steps of: monitoring at least one condensation formation parameter having a condensation formation range indicating the likelihood of condensation formation by exhaust gas from the fuel conversion device and / or by an exhaust gas mixture containing exhaust gas from the fuel conversion device and another exhaust gas from the energy conversion arrangement structure; and controlling the mixing ratio of exhaust gas from the fuel conversion device to the other exhaust gas from the energy conversion arrangement structure to keep at least one condensation formation parameter outside and / or bring it into at least one potential influence area indicating potential condensation effects to be avoided within the condensation formation range.

[0074] According to one aspect, a control program is provided for controlling an energy conversion arrangement structure of an aircraft, the energy conversion arrangement structure including a fuel conversion device having a fuel cell system for converting at least one type of fuel into electrical energy, wherein the control program includes instructions for the control device to execute a response method when the control program is executed by the control device.

[0075] According to one aspect, a computer-readable data carrier having a corresponding control program stored thereon is provided.

[0076] According to one aspect, a control device is provided for controlling an energy conversion arrangement structure of an aircraft, the energy conversion arrangement structure including a fuel conversion device having a fuel cell system for converting at least one type of fuel into electrical energy, wherein the control device is configured to perform a corresponding method and / or includes a corresponding computer-readable data carrier.

[0077] According to one aspect, an energy conversion arrangement structure for an aircraft includes a fuel conversion device having a fuel cell system for converting at least one type of fuel into electrical energy, wherein the energy conversion arrangement structure is configured to perform a corresponding method and / or includes a corresponding control device.

[0078] According to one aspect, an aircraft including a corresponding energy conversion arrangement structure is provided.

[0079] The proposed solution allows the control mechanism to switch between a condensation reduction mode and a standard operating mode for the energy conversion system. Under most flight conditions, condensation reduction is unnecessary, and mixing can be omitted or at least reduced to a minimum. For example, mixing only occurs when certain condensation formation conditions are detected.

[0080] Depending on ice crystal density, shape, and other factors, condensation trails can have many different effects, ranging from larger to smaller climate impacts. Therefore, even if condensation trail formation cannot be completely avoided, at least some undesirable effects, such as the negative climate impacts of condensation trails, can be avoided or at least reduced. Some condensation trails have a negative radiation balance. In other words, these condensation trails contribute to climate cooling. It is recommended to distinguish between warming and cooling condensation trails.

[0081] To avoid heating condensation, the mixing ratio can be increased. In the case of cooling condensation, mixing can be omitted or at least reduced, as the mixing process may result in energy and / or pressure losses and may also introduce undesirable upstream effects in the energy conversion arrangement. This distinction increases the likelihood of cooling condensation formation. Therefore, this solution has the advantage over existing technologies in that it achieves a selective and efficient way to reduce the effects of undesirable condensation. Consequently, fuel cell aircraft can operate efficiently without causing negative climate effects due to condensation formation, or at least minimize such negative climate effects.

[0082] According to the implementation of the method, in order to control the mixing ratio, the amount of exhaust gas mixed with another exhaust gas and / or the amount of another exhaust gas mixed with the exhaust gas are controlled. Considering the current potential area of ​​impact, the corresponding mixing amount can be specifically tailored to adjust at least one condensation formation parameter. For example, the properties of the cooling condensation (droplet size, number, etc.) can be adjusted by adding a defined amount of TMS effluent to the ASP effluent and thus adding heat to the ASP effluent. This adds another degree of freedom to the proposed condensation avoidance possibilities. In particular, ice crystal aging and the resulting ice crystal shape may be affected. Therefore, condensation can be generated in a manner with minimal or even positive climate impacts, even when condensation may be undesirable or acceptable.

[0083] According to the implementation of the method, the mixture ratio, the amount of exhaust gas mixed with another exhaust gas, and / or the amount of another exhaust gas mixed with the exhaust gas are each kept below a mixing threshold. The mixing threshold can be predefined. For example, the mixing threshold can be predefined for the corresponding state of the energy conversion arrangement and / or the atmosphere surrounding the aircraft. Therefore, the mixture ratio can be limited so as not to negatively impact the efficiency and / or operability of the fuel conversion arrangement.

[0084] According to the implementation of the method, the mixing ratio is defined as the ratio of the amount of the other exhaust gas as the numerator and the amount of exhaust gas as the denominator, and if the exhaust gas of the fuel cell system is outside at least one potential area of ​​influence of the condensation formation range, the mixing ratio remains zero or at least substantially close to zero. Outside of condensation formation conditions, the effluents of the TMS and ASP are separate, with no cross-flow. This helps to avoid energy losses due to the mixing process.

[0085] According to an implementation of the method, in a first influence region indicating the first potential condensation effect within the condensation formation range, exhaust gas from the fuel conversion device is mixed with another exhaust gas from the energy conversion arrangement structure, and / or in a second influence region indicating the second potential condensation effect within the condensation formation range, another exhaust gas from the energy conversion arrangement structure is mixed with the exhaust gas from the fuel conversion device. For example, under flight conditions that form a warming condensation trail, ASP effluent can be completely mixed with TMS effluent, while under flight conditions that form a cooling condensation trail, a controlled amount of TMS effluent can be added to the ASP effluent to optimize the properties of the cooling condensation trail. The remaining TMS effluent can be discharged separately. This further helps to avoid energy losses due to the mixing process, as the mixing process is specifically adapted to the corresponding flight conditions.

[0086] According to the implementation of the method, the relative humidity of the exhaust gas is reduced at least temporarily. For example, the relative humidity of the exhaust gas from an energy conversion arrangement structure can be reduced by heating the exhaust gas. Furthermore, the relative humidity can be temporarily reduced through a mixing process, particularly since TMS effluent may be relatively drier than ASP effluent. This temporary reduction in the relative humidity of the exhaust gas facilitates the specific and / or selective application of condensation countermeasures as desired or required under appropriate flight conditions and / or on the ground.

[0087] According to the implementation of the method, condensation formation parameters include exhaust temperature, exhaust pressure, and / or exhaust humidity values ​​of the exhaust gas, another exhaust gas, and / or exhaust gas mixture, and / or atmospheric temperature, atmospheric pressure, atmospheric humidity, and / or atmospheric aerosol values ​​of the atmosphere surrounding the aircraft. For example, any extrinsic and / or intrinsic physical and / or chemical properties of the exhaust gas, another exhaust gas, and exhaust gas mixture can be obtained before, during, and / or after mixing the exhaust gas. Atmospheric aerosol concentration can indicate the corresponding particles and / or droplets contained in the atmosphere, which can serve as nuclei for droplet and / or ice crystal formation. This further enhances the possibility of controlled application of the solution, which further facilitates the application of condensation reduction methods in a flexible and adaptive manner.

[0088] According to an embodiment of the method, the condensation formation parameters include a plume state value, which indicates at least one aspect of the physical and / or chemical state of the plume of exhaust gas and / or exhaust gas mixture behind the aircraft. The plume state value can be detected by visual inspection devices and / or radar inspection devices, and can be detected from the aircraft, satellite, ground station, and / or from another aircraft. The plume state value may include at least one parameter value indicating the temperature, pressure, humidity, and / or composition of the plume, including potential ice crystals contained therein. This further enhances the possibility of controlled application of the solution, which further facilitates the application of condensation reduction methods in a flexible and adaptive manner.

[0089] According to an embodiment, the energy conversion arrangement further includes a mixing component having at least one first control valve and / or at least one second control valve. The at least one first control valve is configured to mix the exhaust gas from the fuel conversion device with another exhaust gas from the energy conversion arrangement, and the at least one second control valve is configured to mix the other exhaust gas from the energy conversion arrangement with the exhaust gas from the fuel conversion device. The control valves may be configured as throttling devices to throttle the flow of exhaust gas and / or the other exhaust gas entering the mixing component, respectively. This provides a flexible and adaptive method for adjusting the mixing ratio in the exhaust gas mixture.

[0090] According to an embodiment of the energy conversion arrangement, at least one first control valve is arranged in the exhaust flow path of the fuel conversion device downstream of the air supply system of the energy conversion arrangement, and / or at least one second control valve is arranged in another exhaust flow path downstream of the thermal management system of the energy conversion arrangement. The air supply system (ASP) can supply air to the fuel conversion arrangement. The thermal management system (TMS) can help regulate the temperature of the fuel conversion arrangement. By arranging the corresponding control valves downstream of the AFP and / or TMS, the control valves can still fully perform their respective functions, and the impact of the mixing process on the operation of the fuel conversion arrangement can be minimized.

[0091] According to another solution, a method is provided for controlling an energy conversion arrangement structure used in an aircraft, the energy conversion arrangement structure including a fuel conversion device having a fuel cell system having at least two fuel cell elements for converting at least one fuel into electrical energy, the method comprising the steps of: monitoring at least one condensation formation parameter having a condensation formation range indicating the likelihood of condensation formation by exhaust gas from the fuel conversion device and / or by an exhaust gas mixture containing exhaust gas from the fuel conversion device and another exhaust gas from the energy conversion arrangement structure; and controlling the fuel cell system such that the at least two fuel cell elements each operate at different current densities to keep at least one condensation formation parameter outside and / or bring it into at least one potential influence area indicating potential condensation effects to be avoided within the condensation formation range.

[0092] Typically, the voltage provided by a fuel cell decreases as current density increases, while the power density increases with increasing current density. In other words, fuel cells are generally highly efficient at low power levels but inefficient at high power levels. The lower the efficiency, the more waste heat is generated. However, the amount of water produced per unit amount of hydrogen in a fuel cell should remain constant.

[0093] A fuel cell system may include at least one fuel cell unit comprising multiple fuel cell elements and / or may consist of at least one fuel cell unit comprising multiple fuel cell elements, wherein a fuel cell element may be a single fuel cell that constitutes the corresponding smallest controllable element of the fuel cell unit. An aircraft may include multiple fuel cell units that can be used to generate electrical energy for the propulsion of the aircraft and / or to power auxiliary systems of the aircraft, such as an auxiliary power unit (APU).

[0094] Intentional efficiency reduction can be achieved by operating fuel cell elements at different power densities. This can be done by operating some fuel cell-driven propulsion units and / or engines at higher power levels and thus operating other fuel cell-driven propulsion units and / or engines at relatively lower power levels. Another option is to operate one or more fuel cell elements, such as fuel cell stacks, within a fuel cell engine at a higher power density than other fuel cell elements. Therefore, some stacks will provide little power with high efficiency, while others will provide a large amount of power with lower efficiency. In general, hydrogen consumption is higher when efficiency is lower than at equivalent power densities, but the total power supplied to the aircraft can remain constant.

[0095] Therefore, considering that fuel cells typically have lower efficiency at higher power densities, the proposed solution allows for an intentional reduction in the efficiency of the fuel cell reaction and can be applied to generate more heat so that the exhaust stream has a lower relative humidity. Thus, the combined exhaust stream and / or exhaust mixture can be warmer and drier than the exhaust stream from the air supply system itself. This significantly reduces the risk of droplet condensation in the engine plume and therefore reduces the risk of unwanted condensation formation.

[0096] Depending on ice crystal density, shape, and other factors, condensation trails can have a variety of effects, ranging from larger to smaller climate impacts. Therefore, while condensation trail formation cannot be completely avoided, some undesirable effects, such as the negative climate impacts of condensation trails, can be avoided or at least reduced. Consequently, appropriate controlled condensation trail reduction measures should only be applied during flights passing through areas at risk of condensation trail formation.

[0097] According to an implementation of the method, at least two fuel cell elements are associated with corresponding different fuel cell stacks of a fuel cell system. In other words, stack imbalance can be used to operate at least two fuel cell elements at different current densities. This imbalance can be a simple way to provide increased heat output to keep at least one condensation formation parameter outside at least one potential influence area indicating a potential condensation region to be avoided within the condensation formation range.

[0098] According to an embodiment of the method, at least one of the at least two fuel cell elements operates at a different fuel conversion rate than at least another of the at least two fuel cell elements. Different current densities in the at least two fuel cell elements can be achieved through different fuel conversion rates. The resulting imbalance in the fuel conversion rates of the at least two fuel cell elements can again be a simple way to provide increased heat output for keeping at least one condensation formation parameter outside at least one potential influence area indicating a potential condensation region to be avoided within the condensation formation range.

[0099] According to an embodiment of the method, at least one of the at least two fuel cell elements operates at a different power density than at least another of the at least two fuel cell elements. For example, two fuel cell elements of the same fuel cell unit can operate at different power densities. This provides a highly flexible way to adjust the power output of the fuel cell system and thus the waste heat ratio of the fuel cell system.

[0100] According to an embodiment of the method, the waste heat ratio of the fuel cell system is increased at least temporarily to bring at least one condensation formation parameter outside the condensation formation range. For example, the waste heat ratio can be increased by operating at least two fuel cell elements at different current densities. Alternatively or additionally, the thermal management system can be controlled in a manner that at least temporarily increases the waste heat ratio. This can further help reduce the relative humidity of the exhaust gas and thus reduce the risk of condensation formation.

[0101] According to an embodiment of the method, the temperature of the exhaust gas generated by fuel conversion in the fuel conversion device is increased at least temporarily to bring at least one condensation formation parameter outside the condensation formation range. For example, the temperature can be increased by operating at least two fuel cell elements at different current densities. Alternatively or additionally, the thermal management system can be controlled in a manner that at least temporarily increases the temperature. This can further help reduce the relative humidity of the exhaust gas and thus reduce the risk of condensation formation.

[0102] According to an embodiment of the method, the relative humidity of the exhaust gas is reduced at least temporarily to bring at least one condensation formation parameter outside the condensation formation range. This temporary reduction in relative humidity over a selected flight area can be achieved by selectively applying the proposed solution, adjusting the internal balance of the fuel cell elements and / or the energy output of the fuel cell system, such that thermal energy output can be increased for at least a portion of the selected flight path to keep at least one condensation formation parameter outside at least one potential influence area indicating a potential condensation effect to be avoided, and / or bring it into the condensation formation range.

[0103] According to the implementation of the method, the aircraft speed and / or aircraft altitude remain substantially constant within predefined speed and / or altitude ranges, respectively. In other words, the aircraft can increase the fuel consumption and / or power output of the energy conversion arrangement by adjusting the internal balance of the fuel cell elements and / or the energy output of the fuel cell system without changing the speed and / or altitude, thereby bringing at least one condensation formation parameter outside the condensation formation range. At lower efficiency, the fuel cell generates more waste heat relative to the water produced. This reduces the relative humidity at the combined exhaust and thus reduces the risk of droplet formation, condensation, and condensation formation.

[0104] According to the implementation of the method, condensation formation parameters include exhaust temperature, exhaust pressure, and / or exhaust humidity values ​​of the exhaust gas, another exhaust gas, and / or exhaust gas mixture, and / or atmospheric temperature, atmospheric pressure, atmospheric humidity, and / or atmospheric aerosol values ​​of the atmosphere surrounding the aircraft. For example, any extrinsic and / or intrinsic physical and / or chemical properties of the exhaust gas, another exhaust gas, and exhaust gas mixture can be obtained before, during, and / or after mixing the exhaust gas. Atmospheric aerosol concentration can indicate the corresponding particles and / or droplets contained in the atmosphere, which can serve as nuclei for droplet and / or ice crystal formation. This further enhances the possibility of controlled application of the solution, which further facilitates the application of condensation reduction methods in a flexible and adaptive manner.

[0105] According to an embodiment of the method, the condensation formation parameters include a plume state value, which indicates at least one aspect of the physical and / or chemical state of the plume of exhaust gas and / or exhaust gas mixture behind the aircraft. The plume state value can be detected by visual inspection devices and / or radar inspection devices, and can be detected from the aircraft, satellite, ground station, and / or from another aircraft. The plume state value may include at least one parameter value indicating the temperature, pressure, humidity, and / or composition of the plume, including potential ice crystals contained therein. This further enhances the possibility of controlled application of the solution, which further facilitates the application of condensation reduction methods in a flexible and adaptive manner.

[0106] According to another possible solution, a method is provided for controlling an energy conversion arrangement structure used in an aircraft, the energy conversion arrangement structure including a fuel conversion device having a fuel cell system for converting at least one fuel into electrical energy, the method comprising the steps of: monitoring at least one condensation formation parameter having a condensation formation range indicating the likelihood of condensation formation by exhaust gas from the fuel conversion device and / or by an exhaust gas mixture containing exhaust gas from the fuel conversion device and another exhaust gas from the energy conversion arrangement structure; and controlling the fuel cell system such that the energy output of the fuel cell system is increased to keep at least one condensation formation parameter outside and / or bring it into at least one potential influence area indicating potential condensation effects to be avoided within the condensation formation range.

[0107] According to an embodiment of the method, the fuel cell system has at least two fuel cell elements, and the current density of at least one of the at least two fuel cell elements is increased. The fuel cell elements may be associated with corresponding different fuel cell stacks of the fuel cell system. The fuel cell system may include fuel cell units comprising multiple fuel cell elements and / or may consist of fuel cell units comprising multiple fuel cell elements, where a fuel cell element may be a single fuel cell that constitutes the corresponding smallest controllable element of the fuel cell unit. An aircraft may include multiple fuel cell units that can be used to generate electrical energy for the aircraft's propulsion and / or to power the aircraft's auxiliary systems, such as the auxiliary power unit (APU). This allows for the controlled application of solutions to selected fuel cell elements, which further facilitates the flexible and adaptive application of condensation reduction methods.

[0108] According to the implementation of the method, the fuel conversion rate of the fuel cell system is increased. At least one of the at least two fuel cell elements or units can operate at a different fuel conversion rate than at least another of the at least two fuel cell elements or units. At least one of the at least two fuel cell elements or units can operate at a different power density than at least another of the at least two fuel cell elements or units. This further allows for the controlled application of the solution to selected fuel cell elements, which further facilitates the flexible and adaptive application of condensation reduction methods.

[0109] According to the implementation of the method, the electrical and / or thermal output of the energy conversion arrangement structure is increased. The increased electrical output can be provided to the aircraft's propulsion system and / or energy storage system. The waste heat ratio of the fuel cell system can be increased, at least temporarily. The additional waste heat can be used to reduce the relative humidity of the exhaust gas and thus reduce the risk of condensation formation.

[0110] According to an embodiment of the method, the energy supply to at least one propulsion unit of the aircraft is increased. The propulsion system may include multiple propulsion units. The corresponding at least one propulsion unit thus delivers higher thrust than the other propulsion units of the aircraft. This can further help reduce the waste heat of at least one propulsion unit relative to the relative humidity of the exhaust gas, and therefore the risk of condensation formation can be reduced to a desired level.

[0111] According to an embodiment of the method, the temperature of the exhaust gas generated by fuel conversion in the fuel conversion device is increased at least temporarily. For example, the thermal management system can be controlled such that the temperature of the exhaust gas and the fuel conversion device is increased at least temporarily, thereby increasing the heat flux of the exhaust gas. This can further help reduce the relative humidity of the exhaust gas and thus reduce the risk of condensation formation.

[0112] According to the implementation of the method, the relative humidity of the exhaust gas is at least temporarily reduced. This temporary reduction in relative humidity in the selected flight area can be achieved by selectively applying the proposed solution, adjusting the energy output of the fuel cell system such that the energy output of the fuel cell system can be increased for at least a portion of the selected flight path to keep at least one condensation formation parameter outside and / or bring it into at least one potential influence area indicating a potential condensation effect to be avoided within the condensation formation range.

[0113] According to the implementation of the method, the aircraft speed and / or aircraft altitude are increased, respectively. In other words, the aircraft can accelerate and / or climb to keep at least one condensation formation parameter outside the condensation formation range. Due to the acceleration and / or climb, the energy output of the fuel cell system can increase at least temporarily. The aircraft speed and / or aircraft altitude can remain substantially constant before and / or after the increase to remain within a predetermined speed range and / or altitude range, respectively. The increase in the speed of the fuel cell aircraft during flight can be particularly applied to areas with a certain risk of condensation formation. The increased flight speed requires more power, which means that the fuel cell operates at a lower efficiency. At lower efficiency, the fuel cell generates more waste heat relative to the water produced. This reduces the relative humidity at the combined exhaust and thus reduces the risk of droplet formation, condensation, and condensation formation.

[0114] According to the implementation of the method, condensation formation parameters include exhaust temperature, exhaust pressure, and / or exhaust humidity values ​​of the exhaust gas, another exhaust gas, and / or exhaust gas mixture, and / or atmospheric temperature, atmospheric pressure, atmospheric humidity, and / or atmospheric aerosol values ​​of the atmosphere surrounding the aircraft. For example, any extrinsic and / or intrinsic physical and / or chemical properties of the exhaust gas, another exhaust gas, and exhaust gas mixture can be obtained before, during, and / or after mixing the exhaust gas. Atmospheric aerosol concentration can indicate the corresponding particles and / or droplets contained in the atmosphere, which can serve as nuclei for droplet and / or ice crystal formation. This further enhances the possibility of controlled application of the solution, which further facilitates the application of condensation reduction methods in a flexible and adaptive manner.

[0115] According to an embodiment of the method, the condensation formation parameters include a plume state value, which indicates at least one aspect of the physical and / or chemical state of the plume of exhaust gas and / or exhaust gas mixture behind the aircraft. The plume state value can be detected by visual inspection devices and / or radar inspection devices, and can be detected from the aircraft, satellite, ground station, and / or from another aircraft. The plume state value may include at least one parameter value indicating the temperature, pressure, humidity, and / or composition of the plume, including potential ice crystals contained therein. This further enhances the possibility of controlled application of the solution, which further facilitates the application of condensation reduction methods in a flexible and adaptive manner.

[0116] According to alternative or additional solutions, an energy conversion arrangement structure for an aircraft is provided, comprising: a fuel conversion device, particularly a fuel cell system, for converting at least one fuel into electrical and / or mechanical energy; and an exhaust outlet for discharging exhaust gas generated by fuel conversion in the fuel conversion device; wherein at least one mixing component is arranged in the exhaust gas flow path before and / or after the exhaust outlet and configured to mix the exhaust gas with another exhaust gas from the energy conversion arrangement structure.

[0117] Waste heat from fuel cell aircraft systems can be used in mixing components to avoid high supersaturation in the plume of moist exhaust streams emitted by fuel conversion devices, such as fuel cell systems. This can be achieved by mixing the moist exhaust stream from the air supply system with a warm and dry gas stream before it can be mixed with cold ambient air. This reduces the maximum supersaturation in the plume and therefore the number of droplets formed in the plume. The reduction in the number of droplets decreases the amount of ice crystals that may form and thus reduces the effects of condensation. In principle, the corresponding solution can utilize any heat source to provide another exhaust stream.

[0118] According to one aspect of the energy conversion arrangement, the energy conversion arrangement also includes a thermal management system configured to generate an additional exhaust stream. This additional exhaust stream provided by the thermal management system can be advantageous because it provides a significant amount of waste heat and is typically located near the wet exhaust stream from the fuel conversion unit. Therefore, the thermal management system can help enhance the overall energy efficiency of the energy conversion arrangement while reducing condensation.

[0119] According to one aspect of the energy conversion arrangement, the thermal management system is constructed as a heat exchanger. Thus, the thermal management system can extract waste heat and / or residual heat from any component of the aircraft to provide additional exhaust. This helps to further improve the overall energy efficiency of the aircraft, while also contributing to condensation reduction.

[0120] According to one aspect of the energy conversion arrangement, the thermal management system includes at least one heat exchanger element configured to extract heat from the fuel conversion unit and / or any auxiliary energy conversion unit. The heat exchanger element can help cool the fuel conversion unit and / or any auxiliary energy conversion unit to a desired operating temperature. This further contributes to improving the overall energy efficiency of the aircraft while also contributing to condensation reduction.

[0121] According to one aspect of the energy conversion arrangement, the thermal management system is configured to draw in cooling air, heat the cooling air, and discharge the heated cooling air as another exhaust. Otherwise, cooling air might have to be injected from the aircraft anyway. Therefore, using cooling air to at least partially provide another exhaust provides a synergistic effect when the other exhaust is applied for condensation reduction.

[0122] According to one aspect of the energy conversion arrangement, the thermal management system is configured to draw in cooling air from the surrounding environment. If cooling air is drawn from the environment, particularly at the aircraft's cruising altitude, the air may be exceptionally cold and dry. Therefore, heating the cooling air by the thermal management system further increases its relative dryness. Thus, mixing the relatively dry cooling air with the exhaust can help reduce the overall humidity of the aircraft's exhaust, which can be beneficial in reducing condensation.

[0123] According to one aspect of the energy conversion arrangement, the thermal management system is configured to supply coolant at the coolant inlet temperature to the fuel conversion unit and recover coolant at the coolant outlet temperature from the fuel conversion unit, wherein, at least when the fuel conversion unit operates at its operating temperature, the coolant inlet temperature is lower than the coolant outlet temperature. Therefore, the coolant helps regulate the temperature of the fuel conversion unit. Consequently, the coolant can help enhance the overall energy efficiency of the energy conversion arrangement while reducing condensation.

[0124] According to one aspect of the energy conversion arrangement, the energy conversion arrangement also includes an air supply system located upstream of the exhaust outlet for supplying supply air for fuel conversion to the fuel conversion device. Therefore, the exhaust can flow at least partially through the air supply system. Thus, the air supply system can be used to heat the exhaust. This can help reduce condensation formation because the relative humidity of the exhaust is reduced.

[0125] According to one aspect of the energy conversion arrangement, the air supply system includes: a compression device for supplying compressed inlet air to the fuel conversion device for fuel conversion; and at least one heat exchange unit configured to extract heat from the compression device and / or the compressed air to be converted. The compression device and / or the compressed air can be cooled by means of the heat exchange unit. Therefore, heat exchange can help improve the overall energy efficiency of the energy conversion arrangement while also helping to reduce condensation.

[0126] According to one aspect of the energy conversion arrangement, at least one heat exchange unit is configured to heat the exhaust gas. Heating the exhaust gas can help reduce the relative humidity of the exhaust gas. The reduced relative humidity can reduce the amount of condensation produced and can promote the dissipation of any remaining condensation.

[0127] According to one aspect of the energy conversion arrangement, the energy conversion arrangement also includes an expansion device for depressurizing the exhaust gas, disposed in the flow path of the exhaust gas upstream of the mixing component. The expansion device can be configured to generate electrical and / or mechanical energy by expanding the exhaust gas. The expansion device may include at least one turbine. The expansion device may be part of an air supply system. Therefore, the expansion device can help improve the overall energy efficiency of the energy conversion arrangement.

[0128] According to one aspect of the energy conversion arrangement, another exhaust provides a relatively drier gas flow compared to the first exhaust. Therefore, mixing this second exhaust with the first can help reduce the overall humidity of the aircraft's exhaust, which can be beneficial in reducing condensation. Mixing operations can be applied whenever needed to achieve the desired amount of condensation reduction. Therefore, mixing operations help provide a flexible and diverse reserve of measures for condensation reduction.

[0129] According to one aspect of the energy conversion arrangement, the mixing component includes another exhaust outlet opening configured to discharge another exhaust gas to the surrounding environment; wherein the exhaust outlet has an exhaust outlet opening configured to discharge exhaust gas to the surrounding environment; and wherein the other exhaust outlet is arranged ahead of the exhaust outlet along an exhaust line extending substantially parallel to the direction of motion of the aircraft during standard operation of the aircraft. The other exhaust outlet opening can be arranged ahead of the exhaust outlet opening such that, during aircraft operation, the warm and dry exhaust air is mixed with the humid air exhaust gas from the fuel conversion unit. Mixing the other exhaust gas with the exhaust gas in this manner can help to further reduce the relative humidity of the overall exhaust gas of the aircraft. Reduced relative humidity can reduce the amount of condensation produced and can promote the dissipation of any remaining condensation.

[0130] According to another solution, an energy conversion arrangement structure for an aircraft can be provided, comprising: a fuel conversion device, particularly a fuel cell system, for converting at least one fuel into electrical and / or mechanical energy; and an exhaust outlet for discharging exhaust gas generated by fuel conversion in the fuel conversion device; wherein at least one heating device is arranged in the flow path of the exhaust gas prior to the exhaust outlet and configured to heat the exhaust gas.

[0131] A heating element provides a heat source between the fuel conversion unit and the aircraft's exhaust outlet. Heating reduces the saturation of the exhaust gas stream, i.e., its relative humidity. Lower saturation reduces or completely prevents droplet formation and condensation in the exhaust system. Droplet formation can still occur in the propulsion system plume. However, the likelihood of forming a large number of small droplets is reduced. This lowers the risk of condensation. Compared to existing technologies, this solution is lighter, has lower cost, and uses less space and power.

[0132] According to one aspect of the energy conversion arrangement, the energy conversion arrangement may also include an expansion device arranged in the flow path of the exhaust gas and configured to generate electrical and / or mechanical energy by expanding the exhaust gas. The electrical and / or mechanical energy generated by the expansion device can be used to operate the energy conversion arrangement, particularly the fuel conversion device. Therefore, the overall energy efficiency of the energy conversion arrangement can be improved.

[0133] According to one aspect of the energy conversion arrangement, the expansion device includes at least one turbine. Electrical and / or mechanical energy can be generated by depressurizing the exhaust gas using at least one turbine. Therefore, at least one turbine contributes to improving the overall energy efficiency of the energy conversion arrangement.

[0134] According to one aspect of the energy conversion arrangement, the expansion device is positioned in the exhaust flow path after the heating device. The expansion device can be positioned between the heating device and the air outlet, i.e., before the air outlet. The heating device can thereby increase the exhaust temperature and thus increase the power output of the expansion device used to generate electrical and / or mechanical energy. Therefore, the heating device helps improve the overall energy efficiency of the energy conversion arrangement.

[0135] According to one aspect of the energy conversion arrangement, the heating device includes a catalytic converter for converting fuel residues not converted by the fuel conversion device into heat. The catalytic converter can be configured to convert at least one type of fuel into heat. For example, a catalytic converter configured as a catalytic combustor can process residual hydrogen from a fuel cell reaction. Hydrogen reacts with oxygen to produce water, releasing heat in the process. Thus, the catalytic combustor can help enhance condensation reduction by means of the heating device. Furthermore, the catalyst can prevent fuel emissions from the energy conversion arrangement.

[0136] According to one aspect of the energy conversion arrangement, the catalytic converter is configured to convert additional fuel into heat. Furthermore, additional hydrogen can be added to the stream upstream of the catalytic converter. Thus, the effectiveness of the catalytic converter in providing heat to be added to the exhaust gas via a heating device can be optimized to further enhance condensation reduction.

[0137] According to one aspect of the energy conversion arrangement, the energy conversion arrangement also includes a residue sensor element configured to measure at least one residue parameter value corresponding to the amount of fuel residue. In other words, the residue sensor element can measure the amount of fuel residue, such as hydrogen residue, in the exhaust gas. The amount of fuel residue can be represented by the residue parameter value. The residue parameter value can be used to optimize the operation of the energy conversion arrangement to further reduce condensation.

[0138] According to one aspect of the energy conversion arrangement, the energy conversion arrangement also includes an auxiliary fuel inlet, which is arranged in the exhaust flow path before the catalytic converter for adding at least one type of fuel to the exhaust. By adding at least one type of fuel and / or an auxiliary fuel, the thermal output of the catalytic converter can be adapted to corresponding requirements. Therefore, the effectiveness of the catalytic converter in providing heat to be added to the exhaust through a heating device can be optimized to further enhance condensation reduction.

[0139] According to one aspect of the energy conversion arrangement, the heating device includes at least one combustion unit configured to burn at least one fuel to heat exhaust gas. The combustion unit may be supplied with hydrogen from the same source as the fuel cell. The combustion unit can provide additional heat introduced by the heating device. Therefore, the combustion unit can help ensure a desired level of condensation reduction.

[0140] According to one aspect of the energy conversion arrangement, the heating device includes at least one heat exchange unit configured to heat exhaust gas. The heat exchanger can transfer heat from the hotter flow in the fuel cell system. The heat exchange unit can provide any type of waste heat and / or residual heat for use by the heating device. Therefore, the heat exchange unit can provide an effective means for reducing condensation.

[0141] According to one aspect of the energy conversion arrangement, the energy conversion arrangement also includes a compression device for supplying compressed supply air to the fuel conversion device for fuel conversion; wherein at least one heat exchange unit is configured to extract heat from the compression device and / or the compressed supply air to be converted. The compressed supply air can be cooled by means of the heat exchange unit. Therefore, the heating device can help further improve the overall energy efficiency of the energy conversion arrangement while also helping to reduce condensation.

[0142] According to one aspect of the energy conversion arrangement, at least one heat exchange unit is configured to extract heat from the fuel conversion device and / or any auxiliary energy conversion unit. The heat exchange unit may be configured to cool at least a portion of the heat exchange unit and / or any auxiliary energy conversion unit. For example, the auxiliary energy conversion unit may be an electrical energy converter and / or a mechanical energy converter. Thus, the heating device can help further improve the overall energy efficiency of the energy conversion arrangement while also contributing to condensation reduction.

[0143] According to one aspect of the energy conversion arrangement, at least one heating device includes an electrically heated element. Electricity for electric heating can be supplied from the energy conversion arrangement. For example, electricity can be provided through any energy recovery device. Heating the exhaust gas with electricity can help ensure a desired level of condensation reduction.

[0144] According to another solution, an energy conversion arrangement structure for an aircraft can be provided, comprising: a fuel conversion device, particularly a fuel cell system, for converting at least one fuel into electrical and / or mechanical energy; and a condensation reduction device arranged in the flow path of exhaust gas generated in the fuel conversion device and configured to introduce water droplets into the flow path, such that smaller droplets in the exhaust gas are collected by droplet condensation.

[0145] A condensation reduction device can be arranged in fluid connection with the exhaust flow and configured to introduce water droplets into the exhaust flow. The droplets injected into the flow thus hinder nucleation due to their own growth through condensation and the associated release of latent heat. This reduces supersaturation and therefore reduces homogeneous nucleation. Introducing large droplets may still be beneficial if homogeneous nucleation does not occur within the fuel conversion system. The droplets then provide a phase boundary for condensation in the plume. This reduces or at least suppresses homogeneous nucleation in the plume, thus also contributing to reduced condensation formation and enhanced natural dissipation of condensation.

[0146] According to one aspect of the energy conversion arrangement, the condensation reduction device also includes jet nozzles, a pump, and piping, wherein the piping is fluidly connected to the pump and adapted to guide water to the jet nozzles. Droplets, preferably large droplets, can be introduced by one or more jet nozzles, which are then pumped. Therefore, only a few lightweight and low-cost additional components are required to implement the condensation reduction device. The power consumption of these components is relatively low. This allows for effective condensation reduction.

[0147] According to one aspect of the energy conversion arrangement, the injection nozzle is configured to introduce water droplets with a diameter of at least approximately 20 micrometers. In contrast, droplets already present in the exhaust gas before it reaches the condensation reduction device, when the exhaust gas leaves the fuel conversion device, particularly the fuel cell, and / or any other device after the fuel conversion device, can be expected to be relatively small, with most droplets having a diameter well below 1 µm (micrometer). Introducing large droplets with a diameter of at least 20 µm can help promote droplet condensation and thus promote condensation reduction.

[0148] According to one aspect of the energy conversion arrangement, the water introduced by the jet nozzles is at least partially a reaction product from the fuel conversion unit. Liquid water can be supplied from the fuel cell system. The water from the fuel cell system is a byproduct of fuel conversion, which must be discharged from the aircraft anyway. Therefore, using wastewater from the fuel conversion unit to reduce condensation has a synergistic effect, as the wastewater can be used in a beneficial manner.

[0149] According to one aspect of the energy conversion arrangement, the water introduced by the injection nozzles originates at least partially from an external storage tank. This external storage tank can provide water for condensate reduction during the load phase of the fuel conversion unit when the unit itself does not generate sufficient wastewater. Therefore, providing an external storage tank helps enhance the readiness of the condensate reduction unit.

[0150] According to one aspect of the energy conversion arrangement, the water introduced by the jet nozzles originates at least partially from a water separation device, preferably a water separation device downstream of the condensation reduction device. Particularly downstream of the fuel cell stack, the water separator can provide liquid water that must be discharged from the aircraft anyway. Therefore, the water separation device helps enhance the synergistic effect of the condensation reduction device.

[0151] According to one aspect of the energy conversion arrangement structure, the energy conversion arrangement structure also includes a compression device and an expansion device, wherein the compression device and / or expansion device are configured to increase the power output of the energy conversion arrangement structure. The expansion device may include a turbine. Thus, the energy efficiency of the energy conversion arrangement structure can be further improved.

[0152] According to one aspect of the energy conversion arrangement, the injection nozzle is positioned in the air outlet downstream of the expander, preferably in the air outlet inside the expander. Within the expander, the water vapor saturation line can be crossed, and with sufficiently high supersaturation, uniform nucleation of water droplets can occur. This can result in a relatively large number of tiny droplets growing through condensation. The corresponding phase change and associated latent heat release can lead to a return to thermodynamic equilibrium. Therefore, introducing droplets downstream of the expander and / or even inside the expander can help promote the formation of larger droplets after the expander, which then helps reduce condensation formation or at least promotes the dissipation of any condensation.

[0153] According to one aspect of the energy conversion arrangement, the injection nozzle includes multiple nozzle elements. These multiple nozzle elements can be arranged in parallel and / or in series along the exhaust flow path to optimize droplet introduction. This enhances the collection of smaller droplets in the exhaust through droplet condensation.

[0154] According to one aspect of the energy conversion arrangement, the energy conversion arrangement also includes an air inlet, wherein the air inlet is fluidly connected to ambient air and / or cabin air of the aircraft. Ambient air and / or cabin air can be supplied to the energy conversion arrangement, particularly the fuel conversion device. Since ambient air can be quite dry and cold, while cabin air can be quite warm and dry compared to ambient air, utilizing fuel conversion can help optimize the conversion temperature in the fuel conversion device and thereby help reduce condensation.

[0155] According to one aspect of the energy conversion arrangement, the energy conversion arrangement also includes a device for increasing droplet condensation, which is preferably a vortex generator. Within the vortex of exhaust gas generated by the vortex generator, the local pressure changes and / or alternations of the laminar and / or turbulent flow of the exhaust gas can help promote droplet condensation. Therefore, the vortex generator can further reduce condensation trails.

[0156] According to one aspect of the energy conversion arrangement structure, the energy conversion arrangement structure also includes sensors for measuring environmental conditions and / or sensors for measuring condensation and droplet size. Environmental conditions, condensation, and / or droplet size can significantly affect condensation formation. Therefore, measuring environmental conditions, condensation, and / or droplet size using appropriate sensors can help optimize the operation of the energy conversion arrangement structure, particularly the condensation reduction device, and thus contribute to effectively reducing condensation.

[0157] According to one aspect of the energy conversion arrangement, the energy conversion arrangement also includes heating and / or cooling devices for adjusting the water temperature to increase droplet size. Increasing droplet size can help promote condensation. Therefore, the operation of the energy conversion arrangement, particularly the condensation reduction device, can be further optimized to effectively reduce condensation.

[0158] According to one aspect of the energy conversion arrangement, the energy conversion arrangement also includes at least one of a humidifier, a dehumidifier, and a heat exchanger. The humidifier, dehumidifier, and / or heat exchanger can further influence droplet condensation. Therefore, the humidifier, dehumidifier, and / or heat exchanger can help optimize the operation of the energy conversion arrangement, particularly the condensation reduction device, and thus contribute to effectively reducing condensation.

[0159] According to an additional solution, an energy conversion arrangement structure for an aircraft can be provided, comprising: a fuel conversion device, particularly a fuel cell system, for converting at least one fuel into electrical and / or mechanical energy; an expansion device arranged in the flow path of exhaust gas generated in the fuel conversion device and configured to depressurize the exhaust gas; and a condensation reduction device configured to introduce water droplets into the flow path of the exhaust gas before and / or within the expansion device.

[0160] Water droplets can be added before the air supply expander (turbine or nozzle) of a fuel conversion system, such as a fuel cell system. These droplets can shift the condensation initiation point upstream of the exhaust flow path within the expander. In other words, adding droplets before the expander can lead to earlier condensation. Earlier condensation reduces the maximum supersaturation of the flow. This is due to the phase change and associated latent heat release during the condensation of the injected droplets. Overall, the droplet spectrum leaving the expander can shift to a smaller number and a larger radius, which reduces the climatic impact of subsequent condensation trails.

[0161] According to one aspect of the energy conversion arrangement, the condensation reduction device includes a jet nozzle for injecting water into the exhaust gas. The jet nozzle can be optimized to produce droplets of a desired size. This enhances condensation reduction.

[0162] According to one aspect of the energy conversion arrangement, the energy conversion arrangement also includes a pump for pressurizing the water before introducing water droplets into the exhaust gas. The water pressure can be optimized for injecting water into the flow path of the exhaust gas. This helps to further enhance condensation reduction.

[0163] According to one aspect of the energy conversion arrangement, water is at least partially a reaction product from the fuel conversion unit. The water from the fuel conversion unit must be discharged from the aircraft anyway. Liquid water can be supplied from the fuel cell system. Therefore, using water from the fuel conversion unit helps to provide a synergistic effect in achieving condensation reduction devices.

[0164] According to one aspect of the energy conversion arrangement structure, the energy conversion arrangement structure also includes a water separator for separating water from the products of the fuel conversion device. Particularly after the fuel cell stack, the water separator can provide liquid water that must be discharged from the aircraft anyway. Therefore, for example, the byproduct (liquid water) of the fuel cell system can be used for condensation reduction. Thus, only a few additional components for water injection are needed, without the need for an additional main system to reduce condensation.

[0165] According to one aspect of the energy conversion arrangement, the expander is configured to generate electrical and / or mechanical energy by depressurizing the exhaust gas. The electrical and / or mechanical energy generated by the expander can be used to operate the energy conversion arrangement, particularly the fuel conversion device. Therefore, the overall energy efficiency of the energy conversion arrangement can be improved.

[0166] According to one aspect of the energy conversion arrangement, the expansion device includes a turbine. With the aid of the turbine, electrical and / or mechanical energy can be generated by depressurization of the exhaust gas. Therefore, the turbine helps improve the overall energy efficiency of the energy conversion arrangement.

[0167] According to one aspect of the energy conversion arrangement, the expansion device includes at least one throttling section. The expansion device may include a throttling valve. Through the throttling section and / or the throttling valve, a desired exhaust pressure reduction rate can be achieved, a rate that may not cause any turbulence in the exhaust flow, or the turbulence caused is at least less than that that might be generated by the turbine. Therefore, the throttling section and / or the throttling valve can help provide pressure reduction while maintaining a substantially laminar fluid flow. Furthermore, the throttling section and / or the throttling valve can be located in a bypass duct, which can be arranged such that at least a portion of the exhaust bypasses the turbine section. Therefore, the throttling section and / or the throttling valve can help optimize conditions for condensation reduction.

[0168] According to one aspect of the energy conversion arrangement, the expansion device includes at least one turbine section. The expansion device may include multiple turbine sections. At least one turbine section may be arranged such that condensation in the exhaust flow path can be reduced.

[0169] According to one aspect of the energy conversion arrangement, the condensation reduction device is configured to introduce droplets between at least one throttling section and at least one turbine section. For example, at least one injection point may be located after the throttling section and before the turbine section, or at least one injection point may be located after the turbine section and before the throttling section. Other injection points along the flow path are possible, including injection points directly at the aircraft's exhaust. The energy conversion arrangement may also include an exhaust outlet for discharging exhaust gases generated by the conversion in the fuel conversion system. Introducing droplets between at least one throttling section and at least one turbine section can help optimize condensation reduction.

[0170] According to one aspect of the energy conversion arrangement, the condensation reduction device is configured to introduce droplets into the exhaust flow path at at least two different inlet points. These at least two different inlet points can be used independently of each other to introduce droplets. Therefore, at least two inlet points allow for optimized water introduction and thus optimized condensation reduction.

[0171] According to one aspect of the energy conversion arrangement, at least two distinct inlet points are radially and / or axially spaced apart from each other along the flow path. Any radial and / or axial distribution of the inlet points along the flow path can be optimized. This can further improve condensation reduction.

[0172] According to one aspect of the energy conversion arrangement, the condensation reduction device is configured to introduce droplets into the intermediate turbine section, thereby entering the exhaust flow path. For example, the intermediate turbine section can be arranged between two turbine sections or within a turbine section. Introducing droplets into the intermediate turbine section can facilitate the use of thermodynamically optimized conditions for water introduction, thereby further enhancing condensation reduction.

[0173] According to another additional solution, an energy conversion arrangement structure for an aircraft can be provided, comprising: a fuel conversion device, particularly a fuel cell system, for converting at least one fuel into electrical and / or mechanical energy; an expansion device arranged in the flow path of exhaust gas generated in the fuel conversion device and configured to depressurize the exhaust gas; an exhaust outlet for discharging the exhaust gas generated by fuel conversion in the fuel conversion device; and at least one bypass duct configured to allow the exhaust gas to bypass the expansion device on its journey from the fuel conversion device to the exhaust outlet.

[0174] In a typical air supply system for a fuel conversion device, such as a fuel cell, ambient air is compressed and fed to the fuel conversion device. After the fuel conversion device, the humidified air is typically expanded in an expander, such as a turbine, and then discharged back to the environment. Bypass ducts can be connected to any duct defining the flow path and / or any kind of exhaust source upstream of the expander, thus allowing relatively humid exhaust from the fuel conversion device, such as air from the fuel cell, to partially or completely bypass the expander, such as the turbine. Therefore, no, or at least significantly less, enthalpy is extracted from the fluid exhaust compared to the case where the fluid exhaust is depressurized in the expander.

[0175] Some expansion in a bypass, such as in a valve or nozzle, may be unavoidable, potentially leading to the formation of some droplets. This is due to the high saturation caused by the low static temperature resulting from the high flow rate during expansion. Therefore, the droplets will partially or completely evaporate as the flow slows down. However, as the exhaust flow slows down, the static temperature rises again because the total temperature remains constant. This will cause the droplets formed in the bypass to partially or completely evaporate. Therefore, fewer droplets are discharged, and the condensation contribution of the energy conversion arrangement structure is reduced. Conversely, when depressurization occurs in an expansion device, such as a turbine, the droplets may not evaporate because the expansion device extracts enthalpy and thus lowers the total temperature of the flow.

[0176] This solution particularly allows bypassing the expansion device during flight through an ISSR where persistent condensation trails might form. In this way, no enthalpy is extracted from the humidified exhaust air, and the total temperature of the exhaust air remains constant. Therefore, under stagnant conditions, the saturation temperature remains constant, and thus no droplets form. Therefore, it can be seen that the main advantage of this solution lies in allowing bypassing any component of the energy conversion arrangement that contributes significantly to condensation trails under the corresponding conditions. Emitting fewer or no droplets at the exhaust outlet reduces the condensation trailing effect of the energy conversion system.

[0177] Furthermore, for example, if the expander includes a turbine, bypassing the expander can help prevent the turbine from stalling or becoming blocked under conditions of overload in the mass flow and / or volume flow of the exhaust gas entering the turbine. Therefore, bypass ducts can also be used to adjust the turbine and / or operate it within a desired operating range. Bypass ducts can also help prevent unwanted condensation of water vapor in the exhaust gas contained within the turbine. This is particularly significant if any devices located upstream of the expander, such as heating devices and / or heat exchangers, are absent, not activated, or do not provide the exhaust gas with an amount of heat sufficient to prevent condensation.

[0178] According to one aspect of the energy conversion arrangement, the bypass pipe is connected to the flow path via a connector. The connector can be positioned and shaped such that it advantageously branches and / or completely guides the exhaust gas, directing it through the bypass pipe. Therefore, the connector helps improve the operation and flexibility of the energy conversion arrangement.

[0179] According to one aspect of the energy conversion arrangement, the connector includes at least one switching valve for switching the flow path from the fuel conversion device to the expansion device and / or the exhaust outlet. The switching valve can be positioned, shaped, and / or operated such that it advantageously branches and / or fully directs the exhaust gas, guiding it through a bypass pipe. Therefore, the switching valve contributes to further improving the operation and flexibility of the energy conversion arrangement.

[0180] According to one aspect of the energy conversion arrangement, the switching valve allows for gradual switching of the flow path. This allows for adjustment and / or regulation of the amount of exhaust gas passing through the bypass pipe and / or expansion device as needed. This contributes to further improving the operation and flexibility of the energy conversion arrangement.

[0181] According to one aspect of the energy conversion arrangement, the switching valve allows for stepless switching of the flow path. This allows for fine-tuning and / or regulation of the amount of exhaust gas passing through the bypass pipe and / or expansion device, depending on specific requirements. This contributes to further improving the controllability and flexibility of the energy conversion arrangement.

[0182] According to one aspect of the energy conversion arrangement, the bypass duct terminates near the exhaust outlet. Thus, the flow path guiding the exhaust through the expansion device and the flow path guiding the exhaust through the bypass duct can be connected near the exhaust outlet. This can facilitate mixing the exhaust from the expansion device and the bypass duct in an advantageous manner, for example by means of a corresponding mixing assembly, which may include the flow path of the exhaust leaving the expansion device and / or the flow path of the exhaust defined by the bypass duct and / or its corresponding outlet, thereby reducing condensation.

[0183] According to one aspect of the energy conversion arrangement, the bypass duct terminates within the exhaust outlet. Thus, the bypass duct, or its end or outlet opening, can form part of the exhaust outlet and / or be integrated into it. This can further facilitate mixing the exhaust from the expansion device and the bypass duct in a way that reduces condensation, for example, by means of a corresponding mixing assembly.

[0184] According to one aspect of the energy conversion arrangement, at the exhaust outlet, the flow path guiding through the expansion device and the flow path guiding through the bypass pipe are connected. The exhaust outlet may include both an outlet guiding the flow path through the expansion device and an outlet guiding the flow path through the bypass pipe. This can further facilitate mixing the exhaust from the expansion device and the bypass pipe in an advantageous manner, for example by means of a corresponding mixing component, to reduce condensation.

[0185] According to one aspect of the energy conversion arrangement, the flow path leading through the expansion device and the flow path leading through the bypass pipe extend and / or terminate at least partially parallel and / or coaxial with respect to each other. On the one hand, this can help arrange the flow paths such that heat exchange is allowed between the exhaust gas led through the expansion device and the exhaust gas led through the bypass pipe. On the other hand, the mixing of the exhaust gas from the expansion device and the bypass pipe can be enhanced in an advantageous manner, for example by means of a corresponding mixing component, to reduce condensation.

[0186] According to one aspect of the energy conversion arrangement, the energy conversion arrangement also includes at least one sensor for providing at least one measurement value representing the temperature, pressure, and / or humidity of the exhaust gas and / or the energy conversion arrangement. The measurement value can be obtained in or at the flow path of the exhaust gas before, after, and / or within the expansion device. Furthermore, measurements representing the environment around the energy system and / or the aircraft including the energy system can be obtained, such that the measurement value represents any state of the atmosphere surrounding the aircraft. Thus, at least one measurement value can help operate the energy conversion arrangement in a manner that avoids or at least reduces condensation.

[0187] According to one aspect of the energy conversion arrangement, the energy conversion arrangement also includes a control unit configured to adjust the flow path through the bypass duct based on at least one measurement. Specifically, bypassing the turbine may reduce the energy efficiency of the energy system because no or at least very little enthalpy can be regained from the exhaust stream. Therefore, it may be advantageous to activate the bypass only when persistent condensation is likely to occur, such as during flight through the ISSR. Furthermore, the control unit can help operate the expander in a desired and / or required manner. Thus, the control unit contributes to improving the operation and flexibility of the energy conversion arrangement.

[0188] According to one aspect of the energy conversion arrangement, the control unit is configured to maintain at least one measured value within a predefined range and / or above or below a predefined limit. The switching valve can be used as a two-way or three-way vent valve. Preferably, the bypass duct can be activated only when there is a risk of persistent condensation formation. This activation mode of the bypass duct can help reduce the overall impact of bypassing the expansion device on the energy system efficiency. When activated, system efficiency may decrease because enthalpy cannot be regained from the turbine. Therefore, the control unit contributes to further improving the operation and flexibility of the energy conversion arrangement.

[0189] According to one aspect of the energy conversion arrangement, a bypass duct is connected to at least one mixing assembly, which is arranged in the exhaust flow path before and / or after the exhaust outlet and configured to mix the exhaust with another exhaust from the energy conversion arrangement. The bypass duct may be configured to bypass at least one condensation reduction device, heating device, and / or heat exchange device, respectively, arranged in the flow path of the air supplied to the fuel conversion unit and / or in the exhaust flow path. This can contribute to further improvements in the operation, flexibility, and efficiency of the energy conversion arrangement. Attached Figure Description

[0190] The subject matter will be described below in conjunction with the following figures, wherein the same reference numerals denote the same elements, and in the figures:

[0191] Figure 1 It is a schematic side view of an aircraft including an energy system with an energy conversion arrangement that generates exhaust plumes during flight.

[0192] Figure 2 It is a schematic diagram of the energy conversion arrangement structure including the condensation reduction device.

[0193] Figure 3 yes Figure 2 The diagram shows a condensation reduction device in operation, representing the energy conversion arrangement structure shown.

[0194] Figure 4 yes Figure 2 Another schematic diagram of the energy conversion arrangement structure shown in the diagram during operation of the condensation reduction device.

[0195] Figure 5 This is a schematic diagram of another embodiment of the energy conversion arrangement structure including the condensation reduction device.

[0196] Figure 6 yes Figures 1 to 5 A schematic diagram of the expansion device of the energy conversion arrangement structure shown.

[0197] Figure 7yes Figures 1 to 6 The diagram shows an expansion device for an energy conversion arrangement, in which the condensation reduction device is in operation.

[0198] Figure 8 This is a schematic diagram illustrating the effect of water droplet injection on the maximum nucleation rate of water droplets within the exhaust gas of the energy conversion arrangement structure.

[0199] Figure 9 This is a schematic diagram of another embodiment of the energy conversion arrangement structure equipped with a heating device.

[0200] Figure 10 yes Figure 9 The diagram shows a schematic of an energy conversion arrangement, in which the heating device includes a catalytic converter.

[0201] Figure 11 yes Figure 9 and Figure 10 The diagram shows an energy conversion arrangement, in which the heating device includes a combustion chamber.

[0202] Figure 12 yes Figures 9 to 11 The diagram shows an energy conversion arrangement, in which the heating device includes a heat exchange device.

[0203] Figure 13 yes Figures 9 to 12 The diagram shows an energy conversion arrangement, in which the heating device includes an electric heating element and is provided with a bypass pipe.

[0204] Figure 14 This is a schematic diagram of a thermal management system for any embodiment of the energy conversion arrangement structure shown in this document.

[0205] Figure 15 This is a schematic diagram showing the mixing lines of plumes in the atmosphere.

[0206] Figure 16 This is a schematic diagram of the relative humidity within a plume when it mixes in the atmosphere.

[0207] Figure 17 It is a schematic side view of the aircraft, satellite, and control station, which is configured to monitor and / or control the exhaust plume during the flight of the aircraft.

[0208] Figure 18 This is a schematic top view of an aircraft, which includes control devices for monitoring and controlling the properties of exhaust components.

[0209] Figure 19This is a schematic diagram of another embodiment of the energy conversion arrangement structure, which is provided with at least one control valve for mixing exhaust gas into another exhaust gas and / or for mixing another exhaust gas into exhaust gas.

[0210] Figure 20 This is a schematic diagram of possible steps in a method for operating an energy conversion arrangement structure.

[0211] Figure 21 This is a schematic diagram of an exemplary embodiment of an energy conversion arrangement structure including a humidification device.

[0212] Figure 22 This is a schematic diagram of another exemplary embodiment of an energy conversion arrangement structure including a humidification device.

[0213] Figure 23 This is a schematic diagram of another exemplary embodiment of an energy conversion arrangement structure including a humidification device.

[0214] Figure 24 This is a schematic diagram of yet another exemplary embodiment of an energy conversion arrangement structure including a humidification device.

[0215] Figure 25 This is a schematic diagram of an exemplary embodiment of an energy conversion arrangement structure including a water separator.

[0216] Figure 26 This is a schematic diagram of another exemplary embodiment of an energy conversion arrangement structure including a water separator.

[0217] Figure 27 This is a schematic diagram of another exemplary embodiment of an energy conversion arrangement structure including a water separator.

[0218] Figure 28 This is a schematic diagram of yet another exemplary embodiment of an energy conversion arrangement structure including a water separator.

[0219] Figure 29 This is a schematic semi-transparent 3D diagram of a water separator.

[0220] Figure 30 This is a schematic diagram of a model used in an implementation of an exhaust assembly for generating a mixing zone, which is an energy conversion arrangement structure.

[0221] Figure 31 It is as follows Figure 30 The diagram shows a schematic representation of the mixing zone generated by the implementation of the exhaust assembly.

[0222] Figure 32 This is a schematic diagram of an embodiment of an exhaust assembly including a spoiler device.

[0223] Figure 33 This is a schematic diagram of another embodiment of the exhaust assembly including the cavity.

[0224] Figure 34 This is a schematic diagram of droplet formation parameters provided according to an embodiment of the exhaust assembly that generates the mixing zone.

[0225] Figure 35 This is a schematic diagram of an embodiment of an exhaust assembly configured to generate a mixing zone including a premixing zone and a main mixing zone.

[0226] Figure 36 This is a schematic diagram of another embodiment of an exhaust assembly configured to generate a mixing zone including a premixing zone and a main mixing zone.

[0227] Figure 37 This is a schematic diagram of droplet formation parameters provided according to an embodiment of the exhaust assembly, which is configured to generate a mixing zone including a premixing zone and a main mixing zone. Detailed Implementation

[0228] The following detailed description is exemplary in nature only and is not intended to limit the invention or its uses. Furthermore, one should not be bound by any theories set forth in the foregoing background or the following detailed description. The representations and illustrations in the accompanying drawings are schematic and not drawn to scale. The same numerals denote the same elements. A deeper understanding of the subject matter can be obtained by reviewing the illustrations and the subsequent detailed description.

[0229] Figure 1 A schematic side view of an aircraft 1 is shown, which includes an energy system 2 and a fuselage 3, the fuselage 3 having an outer shell 4 and being surrounded by the outer shell 4. For example, the energy system 2 includes a propulsion unit 5 that discharges a plume 6 of humidified exhaust air into the atmosphere 7 behind the aircraft 1 as the aircraft 1 travels along the direction of travel F through the atmosphere 7. The humidified exhaust air from the air supply system is discharged from the aircraft and mixes with the ambient cool air. The humidified exhaust air itself can be unsaturated, supersaturated, or saturated in the presence of droplets. Typical values ​​for the temperature and relative humidity of the discharged humidified air are 30°C to 80°C and 60% to 300%, respectively. Furthermore, the outer shell 4 can surround any internal space of the aircraft, including a cabin for transporting passengers and cargo and any components including the energy system 2.

[0230] Figure 2A schematic diagram of the energy conversion arrangement structure 10 of the energy system 2 of the aircraft 1 is shown. The energy conversion arrangement structure 10 includes a fuel conversion device 11, which is configured, for example, as a fuel cell system, for converting hydrogen into electricity and for converting exhaust gas E, primarily water vapor, into fuel. Air A, for example, obtained from the surrounding environment, such as the atmosphere 7 and / or the interior of the outer shell 4, such as the cabin of the aircraft 1, is supplied to the fuel conversion arrangement structure 11 through the air inlet 12 of the energy conversion arrangement structure 10. Exhaust gas E is released to the atmosphere 7 through the exhaust outlet 13 of the energy conversion arrangement structure 10.

[0231] Air A is guided from air inlet 12 to fuel conversion device 11 along a corresponding flow path 14. Exhaust gas E is guided from fuel conversion device 11 to exhaust outlet 13 along a corresponding flow path 15. A compression device 16 of the energy conversion arrangement 10 is disposed in the flow path 14 between air inlet 12 and fuel conversion device 11 for compressing the inlet air A. An expansion device 17 is disposed in the flow path 15 between fuel conversion device 11 and exhaust outlet 13 for depressurizing exhaust gas E. The compression device 16 is connected to the expansion device 17 via a transmission line 18, which may include any kind of mechanical and / or electrical energy transmission device and may be implemented, for example, as a shaft. The compression device 16 may include a turbine 19 (see...). Figure 6 ).

[0232] Furthermore, the energy conversion arrangement includes a condensation reduction device 20. A water supply line 21 is configured to connect the condensation reduction device 20 to the fuel conversion device 11. Thus, the condensation reduction device 20 can be supplied with water W generated in the fuel conversion device 11 through fuel conversion.

[0233] Air inlet 12 supplies ambient air A to compressor 16, which in turn supplies air A at elevated pressure to fuel conversion unit 11. Moistened exhaust gas E, such as the exhaust air from a fuel cell system in fuel conversion unit 11, expands in a turbine to power the compressor. During expansion in expander 17, the water vapor saturation line may be crossed, and homogeneous nucleation may occur at sufficiently high supersaturation. This results in the growth of numerous tiny exhaust gas droplets D via condensation. E (See) Figure 3 ).

[0234] This phase transition and the associated release of latent heat lead to a return to thermodynamic equilibrium. The resulting exhaust droplet D E diameter d E They are expected to be small, with most being well below 1 micrometer. If a large number of small exhaust droplets D are being emitted from spacecraft 1... EThere is a high risk of dense condensation forming from plume 6, which could have strong negative climate impacts. To mitigate this risk, the condensation reduction device 20 is supplied with liquid water W, which may be a byproduct of fuel conversion.

[0235] Figure 3 It shows Figure 2 The diagram shows a schematic of the condensation reduction device 20 of the energy conversion arrangement 10 in operation. The condensation reduction device 20 includes a pump 22 disposed in a water supply line 21 to pressurize water W and a spray nozzle 23 disposed in an air duct 25 to spray water W into an exhaust gas E. The exhaust gas E may contain droplets d having an average droplet diameter of approximately less than 1 µm before reaching the condensation reduction device 20. DE droplet D E Liquid water W is supplied to the injection nozzle 23, which produces an average diameter d. DW Water droplets larger than 20 micrometers D W .

[0236] Smaller exhaust droplets D E Condensation in larger water droplets D W This leads to the formation of condensed droplets C. Effectively, the number of droplets decreases and the average diameter d... AVG Increased. Condensed droplet C results in less harmful condensation because the combined surface area of ​​condensed droplet C is smaller than that of exhaust droplet D. E and water droplet D W The surface and. Water droplets D ejected from nozzle 23 W The size and velocity of the droplet must be chosen such that the critical Weber number does not exceed approximately 12. Otherwise, the water droplet D... W It will split into much smaller droplets, thus negating the desired effect.

[0237] Figure 4 It shows Figure 2 The energy conversion arrangement shown illustrates another illustrative phase of the condensation reduction device 20 during operation. Here, exhaust droplets D do not appear due to the lack of supersaturation of water vapor in the exhaust gas E. E If the supersaturation before the condensation reduction device 20 is insufficient to form droplets, the condensation reduction device 20 can still reduce the risk of condensation formation. Without venting droplets D E In this case, the water vapor in plume 6 becomes supersaturated during plume mixing outside the aircraft 1. Similarly, a large number of small-diameter droplets will form through uniform nucleation. In this case, the water vapor generated in the condensation reduction device 20 grows through condensation in the slightly supersaturated flow to form larger water droplets D'. WThe droplets, or droplets grown in an unsaturated flow, remain large enough to persist upon launch from spacecraft 1. During plume mixing, these pre-existing droplets D W D' W A phase boundary can be provided for condensation, which prevents high supersaturation and homogeneous nucleation. This results in a small number of large droplets D'. W Instead of a large number of small droplets D W .

[0238] Figure 5 A schematic diagram of another embodiment of the energy conversion arrangement structure 10, including the condensation reduction device 20, is shown. Here, the condensation reduction device 20 is arranged in the flow path 15 between the fuel conversion device 11 and the expansion device 17, which includes a turbine 19 (see...). Figure 6 Liquid water W supplied by the fuel conversion device 11 is injected into the flow path 15 of the exhaust gas W upstream of the expansion device 17 using the injection nozzle 23, as shown. Figure 3 and Figure 4 As illustrated in the diagram. Once supersaturation is reached during expansion in expansion device 17, water droplet D... W Growth begins through condensation. This is limited by the phase change and the release of latent heat, which restricts the maximum supersaturation that can be achieved.

[0239] A lower maximum supersaturation corresponds to water droplet D W The nucleation rate is relatively small. This reduction is greater than the number of droplets introduced by the jet nozzle 23. Overall, the droplet spectrum shifts again towards fewer, larger droplets C, D' W Offset. Fewer droplets freezing result in optically “thinner” condensation trails, thus reducing their climate impact because the combined droplet surface is smaller.

[0240] Figure 6 It shows Figures 1 to 5 The diagram shows an expansion device 17 including a turbine 19 in the energy conversion arrangement 11. Without any condensation reduction measures, water vapor in the plume 6 may become supersaturated during plume mixing outside the aircraft 1. Similarly, a large number of droplets with small diameters will form through uniform nucleation.

[0241] Figure 7 It shows Figures 1 to 6 The diagram shows an expansion device 20 of an energy conversion arrangement, in which the turbine 19 and the condensation reduction device 20 in the flow path 15 of the exhaust gas E located upstream of the turbine 19 are in operation. (Water droplet D) W The injection of the gas during the expansion of the exhaust gas E within the turbine 19 provides a phase boundary for condensation, which prevents high supersaturation and reduces or avoids uniform nucleation. This results in a small number of large droplets C, D'W Instead of a large number of small droplets D E The injected water droplet D W It should be as small as possible. The larger the surface area of ​​the injected combined droplets, the stronger the reduction in maximum supersaturation and nucleation rate.

[0242] Water droplets D are injected in front of turbine 19. W There is a risk of droplet erosion, corrosion, and other damage due to liquid water W. However, corresponding mitigation measures are known from steam turbine research.

[0243] Another option is to operate the condensation reduction device 20 in any of the embodiments described herein only if there is a risk of condensation formation. However, the efficiency of the turbine 19 may also be improved due to the reduced phase change losses when operating the condensation reduction device 20. W The fact that injection reduces the maximum nucleation rate is well-known in the scientific community (see [link]). Figure 8 ).

[0244] Figure 8 The image shows water droplets D. W Water droplets D injected into the exhaust gas E of the energy conversion arrangement structure 10 W A schematic diagram illustrating the effect of the maximum nucleation rate (see Teymourtash et al., “The effects of rate of expansion and injection of water droplets on the entropy generation of nucleating steamflow in a Laval nozzle,” Heat Mass Transfer (2009) 45: 1185-1198, p. 1196). Figure 20 The effect of injected droplets on the nucleation rate (α=6°). It will become apparent here that the nucleation rate is influenced by the droplet D... W The latent heat released into the exhaust gas E is reduced. This can be interpreted as the latent heat released to the steam being reduced through a finite phase change from vaporized water to liquid water. However, this is dominated by the subsequent condensation of the water. If the final pressure is the same, the amount of liquid water formed should also be the same. However, this amount should be distributed in a reduced number of droplets, which can help reduce condensation. In this example, it is assumed that the divergence angle α of the Laval nozzle is 6°.

[0245] Figure 9A schematic diagram of another embodiment of the energy conversion arrangement 10 is shown, which includes a heating device 30. The heating device 30 is located in the flow path 15 between the fuel conversion device 11 and the exhaust outlet 13. Specifically, the heating device 30 is located in the flow path 15 of the exhaust gas E upstream of the expansion device 17. The exhaust gas E, for example, the humidified exhaust air from the fuel cell system of the fuel conversion device 11, is heated in the heating device 30. The heated exhaust gas E expands in the expansion device 17, for example, its turbine 19, to power the compression device 16 via the transmission line 18.

[0246] During expansion in the expansion device 17, saturation increases. However, due to heating provided by the heating device 30, the overall saturation level is relatively low. Alternatively or additionally, the heating device 30 may be placed in the flow path 15 downstream of the expansion device 17. This completely prevents droplet formation or at least significantly reduces it. The fewer droplets, the lower the risk of forming dense condensation trails. Even without droplets or with very few droplets, the flow of exhaust gas E released into the atmosphere 7 may still lead to droplet formation in the plume 6 outside the aircraft 1. However, this is still considered beneficial because the maximum saturation level reached in this process is assumed to be lower than the saturation level without heating. A smaller maximum saturation level corresponds to fewer, larger droplets C, D' W .

[0247] Figure 10 It shows Figure 9 The schematic diagram of the energy conversion arrangement 10 shown includes a heating device 30 comprising a catalytic converter 31. The catalytic converter 31, for example configured as a catalytic burner, can process residual fuel, such as hydrogen from the fuel cell reaction performed in the fuel conversion unit 11. The fuel reacts with oxygen to produce water, releasing heat in the process. Increased heat overcompensation is due to the increased saturation caused by the increased water W. The catalytic burner also prevents fuel emissions from the energy conversion arrangement 10. A sensor 32 may be provided to measure the fuel concentration in the flow path 15 of exhaust gas E before and / or after the catalytic burner 31. Additional fuel B may be added to the flow path 15 of exhaust gas E upstream of the catalytic burner 31 (see [reference]). Figure 11 ).

[0248] Figure 11 It shows Figure 9 and Figure 10The schematic diagram of the energy conversion arrangement shown includes a heating device 30 comprising a combustion chamber 33. A fuel cell system with a combustion chamber for burning hydrogen is depicted. In the combustion chamber 33, supplementary fuel B reacts with oxygen; for example, hydrogen added as supplementary fuel B reacts with oxygen to produce water W, releasing heat in the process. The increased heat overcompensates for the increased saturation caused by the added water W. Combustion also prevents fuel emissions from the energy conversion arrangement 10.

[0249] Figure 12 It shows Figures 9 to 11 The schematic diagram of the energy conversion arrangement 10 shown indicates that the heating device 30 includes a heat exchange device 34. The heat exchange device 30 adds heat to the exhaust gas E of the fuel conversion device 11 and thereby reduces the saturation before the expansion device 17. Alternatively or additionally, the condensation reduction device 20, the heating device 30, the catalytic converter 31, the sensor 32 and / or the combustion chamber 33 may be arranged before, within and / or after the expansion device 17 in the flow path 15 of the exhaust gas E. Heat not transferred from the exit of the compressor in the flow path 14 of the air A can be obtained from other heat sources of the fuel conversion system 10, particularly from the thermal management system 40, which may include multiple heat exchange devices 30 and / or heat exchange elements (see [link to relevant documentation]). Figure 14 ).

[0250] Figure 13 It shows Figures 9 to 12 The diagram shows a schematic of the energy conversion arrangement 10, in which the heating device 30 includes an electric heating element 35. The heating element 35 can provide electric heating to reduce condensation formation. The increased heat reduces the saturation level prior to the expansion device 17. Electricity can be supplied to the heating element 35 from the fuel conversion device 11 and / or from other sources (not shown) via transmission line 18.

[0251] Furthermore, the energy conversion arrangement 10 may include a bypass conduit 36 ​​connected to the flow path 15 of the exhaust gas E via a flow connector 37. The flow connector 37 may include a switching valve 38, which may be steplessly operated, for example, to allow the exhaust gas E to pass through the expansion device 17 and / or to guide the exhaust gas E to the exhaust outlet 13 via the bypass conduit 36. The switching valve 38 may be operated with the assistance of a control unit 39, which may be connected to at least one of the sensors 32 via a corresponding transmission line 18 for transmitting energy and / or information.

[0252] In operation of the energy conversion arrangement 10, exhaust gas E can branch off from the flow path 15 at the flow connector 37 to bypass the expansion device 17 via the bypass pipe 36, thereby forming an alternative or auxiliary flow path 15 for exhaust gas E in addition to the main flow path 15 that guides exhaust gas E through the expansion device 17. The amount of exhaust gas E bypassing the expansion device 17 can be controlled by means of the control unit 39 so that any measured values, such as temperature, pressure and / or humidity values, measured by means of at least one of the sensors 32 before, within and / or after the expansion device 17 are kept within, above and / or below the corresponding desired or required value range and / or limits.

[0253] Alternatively or additionally, flow joint 37 may be arranged within the expansion device 17, for example, between certain sections of the expansion device 17. Flow paths 15 guiding through the expansion device 17 and flow paths 15 guiding through the bypass conduit 36 ​​may be connected within and / or after the expansion device 17 and / or exhaust outlet 13. The bypass conduit 36 ​​may be used to bypass any section or component of the energy conversion arrangement structure 10 as described herein. Therefore, at least one flow joint 38 may be arranged as desired or required to bypass the expansion device 17, condensation reduction device 20, heating device 30, and / or heat exchange device 34.

[0254] Figure 14 A schematic diagram of a thermal management system 40 is shown in any embodiment of the energy conversion arrangement 10 illustrated herein. The thermal management system 40 can discharge another exhaust gas G, such as air and / or gas, which preferably has a higher temperature and / or lower relative humidity than exhaust gas E. The other exhaust gas G can be released from the aircraft 1 by being discharged outside the outer casing 4 in the direction of travel F before exhaust gas E. Exhaust gas E may have already passed through an air supply system 41 including a compression device 16, an expansion device 17, a heating device 30, and / or a heat exchange device 34. The corresponding exhaust outlets 13 for exhaust gas E and the other exhaust gas G can be provided with a mixing assembly 42.

[0255] The thermal management system 40 can receive additional air H from the atmosphere 7 and / or from inside the housing 4. This additional air H can be used in the thermal management system 40 to cool the coolant K, which is then supplied to the fuel conversion unit 11 to maintain the desired temperature level for effective fuel conversion within the fuel conversion unit 11. The coolant K can then be returned to the thermal management system 40. The additional air H can be heated by means of the coolant K from the fuel conversion unit 11.

[0256] Figure 15 A schematic diagram showing the mixing line of plume 6 in atmosphere 7 is shown, represented by the corresponding partial pressure of water vapor as a function of temperature. The narrow solid line (line V) is with respect to the saturation pressure of liquid water. The dashed line X represents the mixing of moistened exhaust air E at point III with atmospheric air at point IV.

[0257] The mixing line X intersects the saturation line V. This means that all points on line X to the right of line V are supersaturated. The mixing line represents the ideal path that plume temperature and water vapor partial pressure would follow when mixing in atmosphere 7 if condensation does not occur.

[0258] exist Figure 15 In the diagram, an exemplary condition for this flow is represented by point III.

[0259] Point II represents the result of the mixing of humid exhaust air (point III) and warm, dry air (point I). The mixing process between these two streams is represented by the dashed line Y. The thick solid line Z represents the mixing line between the mixed exhaust state (point II) and ambient air (point IV).

[0260] Figure 16 A schematic diagram of the relative humidity within the plume 6 when mixed in the atmosphere 7 is shown. Figure 2 The solid line R above represents the evolution of the relative humidity R of plume 6 as exhaust gas E and another exhaust gas G (points III and I, respectively) mix with air under ambient atmospheric conditions (point IV). Clearly, in Figure 2 In the diagram, the mixing line R (solid line) does not extend as far into the supersaturated region as the mixing line S (dashed line), and the mixing line S is not characterized by any trace reduction solution. The maximum supersaturation is much smaller compared to the case without a trace reduction solution. This means fewer droplets are formed and less condensation occurs, thus reducing trace formation and climate risk. In short, the goal is to reduce the gradient of the mixing line S. The warmer and drier the exhaust gas G is, and the greater the mass flow, the stronger the effect.

[0261] This principle also applies to both undersaturated and supersaturated humidified exhaust streams. If a humidified exhaust stream becomes saturated in the presence of droplets, its state lies precisely on the saturation line. In this case, mixing with a warmer, drier stream results in (partial) evaporation of the droplets. However, the gradient of the mixing line S associated with ambient air decreases. In a preferred embodiment, the stream of another exhaust G from the thermal management system 40 is mixed with the humidified stream of exhaust E from the air supply system 41. In principle, other waste heat streams also play a role, but the thermal management system 40 provides a large mass stream of dry, warm air near the air supply system 41. It is preferable to still perform the mixing operation within the aircraft 1, or at least only at the respective exhaust outlets 13 and / or combined exhaust outlets 13 for exhaust E and the other exhaust G, as this provides optimal control over the mixing process.

[0262] Other alternative and / or additional implementations of the proposed solution may involve different air supply architectures, such as blowers replacing compressors, air from the nacelle replacing ambient air, nozzles replacing turbine 19 and / or supplementing turbine 19, electric motors on the shaft between compressor 16 and turbine 19, humidifiers, dehumidifiers, heat exchangers, etc. Different sources of liquid water W can be used, i.e., water separation devices downstream of tanks, nacelle systems, thermal management system 40, and / or air supply system 41. Multiple injection nozzles 23 or other devices for generating dispersed liquid water W may be located inside turbine 19 and / or fuel conversion unit 11.

[0263] Sensor 32 can be used to measure environmental conditions and / or to measure condensation and droplet size in the energy conversion arrangement structure 10. Furthermore, sensor 32 can be used to measure the effectiveness of condensation generation and condensation reduction devices 20. The controller can be used to adapt the jet flow to different droplet sizes, constant mode, active mode, etc. Heating and / or cooling devices 30 can be used to adapt the liquid water temperature to achieve smaller droplet sizes.

[0264] Figure 17A schematic side view of spacecraft 1, satellite 8, and control station 9 is shown. Control station 9 is configured to monitor and / or control the properties of exhaust plume 6 during flight of at least one of the spacecraft in spacecraft 1, particularly regarding at least one condensation formation parameter P of the exhaust, plume 6, and / or atmosphere 7. Satellite 8 may orbit in space and monitor spacecraft 1 and its plume 6. Ground station 9 may be located on the ground g. Spacecraft 1, satellite 8, and / or ground station 9 may be connected to, and / or each include a control system 50 and / or a computer system 51, configured to perform monitoring and control functions for and / or related to the operation of energy system 2 of spacecraft 1.

[0265] As part of the control system 50, the aircraft 1, satellite 8, and / or ground station 9 may include and / or be connected to at least one computing device 51, at least one control device 54, and / or at least one control element 59 (see [link]). Figure 18 Thus, the spacecraft 1, satellite 8, and / or ground station 9 can individually and / or in combination with each other keep at least one trajectory formation parameter P outside and / or bring it into the trajectory formation range outside at least one potential influence area indicating potential trajectory effects to be avoided. The spacecraft 1, satellite 8, and / or ground station 9 can communicate with each other via corresponding communication channels c, which are configured, for example, for digitally exchanging data used by the operation control system 50.

[0266] Figure 18 A schematic top view of an aircraft 1 is shown, which includes a control device 54 for monitoring and controlling the composition and properties of exhaust gas E, another exhaust gas G, and / or exhaust gas mixture M. The aircraft 1 also includes a fuel storage system 52 for supplying fuel B to at least one energy conversion arrangement 10 of the aircraft 1, configured to supply electricity e to the aircraft 1, for example, to the propulsion unit 5 and / or energy storage system 53, such as a battery. The control device 54 for controlling the operation of the carrier 1, energy system 2, propulsion unit 5, fuel conversion arrangement 10, and / or fuel conversion device 11 may be incorporated into the carrier 1 and / or at least partially integrated into the fuel conversion arrangement 10 itself. The control device 54 can be connected to the carrier 1, energy system 2, propulsion unit 5, fuel conversion arrangement structure 10 and / or fuel conversion device 11 via a corresponding communication line 55. The communication line 55 can be configured as a transmission line 18 and / or a data connector, which is configured to transmit data, for example, through a communication channel c and / or transmit power e in any kind of wired and / or wireless manner.

[0267] The control device 54 may include a processing unit 56, an interface module 57, a storage module 58, and / or a control element 59 that can be interconnected via corresponding communication lines 55. The communication lines 55 may be configured to transmit any kind of information, data, power, and / or energy. The carrier 1 and / or the energy conversion arrangement 2 may be equipped with a computing device 60, which may include the control device 54 or vice versa. For example, a control program 61 in the form of a computer program may be stored on a computer-readable data carrier 62, which may take the form of a computer-readable medium 63 and / or a data carrier signal 64. The control device 54 may include the computing device 60, the computer program 61, the computer-readable data carrier 62, and / or any kind of control element, as well as communication lines 55 for exchanging data between the corresponding components. The control element 59 can be any kind of data source and / or data sink, such as the measuring elements, sensors 32, control units 39, output devices and / or actuators of the vehicle 1, energy conversion arrangement structure 2 and / or propulsion unit 5. These components can form part of the control system 50 for controlling a function of the control system 50, for example by means of an interface module 54 connected to the control element 59.

[0268] In this example, the energy conversion arrangement 2 includes a fuel conversion device 11, which may include or take the form of a fuel cell system 70, as in any other embodiment of the energy system 2 described herein. The fuel conversion device 11 and the corresponding fuel cell system 70 may be combined to form an energy conversion arrangement 10 including a thermal management system 40, an air supply system 41, and / or a mixing assembly 42. The energy conversion arrangement 10 may be located within the outer shell 4 of the aircraft 1, for example, inside the fuselage 3 and / or within the nacelles of each propulsion unit in the propulsion unit 5.

[0269] The aircraft 1 and / or energy system 2 may include multiple fuel cell systems 70, each of which may include multiple fuel cell units 71. The fuel cell units 71 can generate electrical energy e to propel the aircraft 1 and / or to power auxiliary systems of the aircraft, such as the auxiliary power unit (APU), and the fuel cell units 71 may be stored in an energy storage system 53. The fuel cell system 70 may include at least one fuel cell unit 71 comprising multiple fuel cell elements 72 and / or may consist of at least one fuel cell unit 71 comprising multiple fuel cell elements 72, where each fuel cell element 72 may be a single fuel cell capable of constituting a corresponding minimum controllable element of the fuel cell unit 71. The fuel cell units 71 may be arranged, for example, in the form of a fuel cell stack. Each fuel cell unit 71 may include multiple fuel cell elements 72.

[0270] The fuel conversion device 11 can draw in air A from the air supply system 41 and fuel B from the fuel storage system 52, and generate exhaust E, such as relatively humid air, when converting fuel B into electrical energy e in the form of heat energy while generating exhaust E. The exhaust E from the fuel conversion device 11 and / or the fuel cell system 70 can pass through the air supply system 41, which may include a compressor 16, an expander 17, a heater 30, and / or a heat exchanger 34. A corresponding exhaust outlet 13 for exhaust E can direct exhaust E to the air supply system 41, the mixing assembly 42, and / or outside the housing 4.

[0271] In the mixing assembly 42, exhaust gas E can be mixed in a controlled manner with another exhaust gas G from the thermal management system 40 to obtain an exhaust mixture M of exhaust gas E and another exhaust gas G. The exhaust mixture M can be discharged outside the aircraft shell 4 through the corresponding exhaust outlet 13 of the mixing assembly 42. The thermal management system 40 can receive another air H from the atmosphere 7 and / or from inside the shell 4.

[0272] Another air H can be used in the thermal management system 40 to cool the coolant K, which is then supplied to the fuel conversion unit 11 and / or the fuel cell system 70 to maintain the desired temperature level for efficient fuel conversion in the fuel conversion unit 11 and / or the fuel cell system 70. The coolant K can then be returned to the thermal management system 40. The other air H can be heated by means of the coolant K from the fuel conversion unit 11 to provide another exhaust gas G.

[0273] Figure 19 A schematic diagram of another embodiment of the energy conversion arrangement 10 is shown, which is provided with at least one control valve 43 for mixing exhaust gas E with another exhaust gas G and / or for mixing another exhaust gas G with exhaust gas E. For example, the mixing assembly 42 may include at least one first control valve 43a and / or at least one second control valve 43b, the first control valve 43a being configured to mix exhaust gas E from the fuel conversion device 11 with another exhaust gas G from the energy conversion arrangement 10, and the second control valve 43b being configured to mix another exhaust gas G from the energy conversion arrangement 10 with exhaust gas E from the fuel conversion device 11. At least one first control valve 43a may be arranged in the flow path 15 of exhaust gas E from the fuel conversion device 11 downstream of the air supply system 41 of the energy conversion arrangement 10 and / or at least one second control valve 43b may be arranged in the flow path 15 of another exhaust gas G downstream of the thermal management system 40 of the energy conversion arrangement 10.

[0274] Control valve 43 may be configured as switching valve 38 and may be operated with the assistance of a corresponding control unit 39, which may be connected to at least one of the sensors 32 via a corresponding transmission line 18 for transmitting energy and / or information, and may be further connected to a control device 54. Control valves 43 may each be located and / or arranged at a flow joint 37, configured to branch and / or redirect exhaust gas E and / or another exhaust gas G from their flow path 15 to an alternative auxiliary flow path 15, bypass pipe, etc. The amount of branching and / or redirection of exhaust gas E and / or another exhaust gas G may be controlled by means of control unit 39 and / or control device 54 so that any measured values, such as temperature, pressure, and / or humidity values, measured by means of at least one of the sensors 32 before, within, and / or after the expansion device 17 are maintained within, above, and / or below the corresponding desired or required value range and / or limits.

[0275] In this example, the mixing assembly 42 includes a mixing device 44 that can be arranged within the housing 4. A first control valve 43a can be arranged in the flow path 15 of exhaust gas E after the air supply system 41 to enable exhaust gas E to branch and / or turn to the mixing device 44 before and / or upon reaching exhaust outlet 13. Alternatively or additionally, a second control valve 43b can be provided in the flow path 15 of another exhaust gas G after the thermal management system 40 to enable exhaust gas E to branch and / or turn before and / or upon reaching the mixing device 44 and / or exhaust outlet 13 to mix with exhaust gas E at a corresponding flow joint 37. In each case, a corresponding sensor 32 can be provided in the flow path 15 of exhaust gas E before and / or after the corresponding flow joint 37 and / or control valve 43 and after and / or at any exhaust outlet 13.

[0276] Figure 20 A schematic diagram of possible steps of a method for an energy conversion arrangement structure 10 is shown. For example, in a first step, at least one condensation formation parameter P may be monitored. If, in a second step S2, it is deemed desirable and / or necessary to keep at least one condensation formation parameter P outside and / or bring it into at least one potential influence area indicating a potential condensation effect to be avoided within the condensation formation range, then in a third step S3, exhaust gas E may be mixed with another exhaust gas G and / or in a fourth step S4, another exhaust gas G may be mixed with exhaust gas E. Mixing can be achieved by operating a first control valve 43a and / or a second control valve 43b to provide a corresponding mixing ratio Q, such as a first mixing ratio Q.a and / or the second mixing ratio Q b To achieve the first mixing ratio Q a Second mixing ratio Q b These represent the amount of exhaust gas E mixed into another exhaust gas G and / or the amount of another exhaust gas G mixed into exhaust gas E, respectively.

[0277] The mixing ratio Q can be defined as the ratio of the amount of another exhaust gas G as the numerator and the amount of exhaust gas E as the denominator, and if the exhaust gas E of the fuel cell system 70 is outside at least one potential influence region of the condensation formation range, the mixing ratio Q can be kept zero or at least substantially close to zero. The amount of corresponding exhaust gas E mixed to the other exhaust gas G and / or the amount of another exhaust gas G mixed to exhaust gas E can be kept below a mixing threshold I, which can indicate a limit on the corresponding mixing ratio Q. In and / or after steps S2, S3 and / or S4, and / or after steps S2, S3 and / or S4, a return to step S1 can be made to create a control loop for continuously monitoring the condensation formation parameter P, thereby assessing whether any mixing process is needed to keep at least one condensation formation parameter P outside and / or bring it into at least one potential influence region of the condensation formation range that indicates potential condensation effects to be avoided.

[0278] Alternatively and / or additionally, in step S5, an assessment is made as to whether the energy output e of the fuel cell system 70 should be increased, for example, to raise the temperature value T of exhaust gas E and / or another exhaust gas G. In step S6, the fuel cell system 70 may be controlled such that the energy output e of the fuel cell system 70 should be increased to keep at least one condensation formation parameter P outside and / or bring it into the condensation formation range outside at least one potential influence region indicating a potential condensation effect to be avoided. Alternatively and / or additionally, in step S7, the fuel cell system 70 may be controlled such that at least two fuel cell elements 72 each operate at different current densities to keep at least one condensation formation parameter P outside and / or bring it into the condensation formation range outside at least one potential influence region indicating a potential condensation effect to be avoided.

[0279] Any of the steps S3, S4, S6, and S7 used to mix exhaust gases E and G and / or increase the energy output of the fuel cell system 70 may be combined with each other as desired or required to keep at least one condensation formation parameter P outside at least one potential influence area indicating potential condensation effects to be avoided within the condensation formation range. For example, it may be determined in step S5 that if a certain mixing threshold I is reached in steps S3 and / or S4 without achieving the desired effect on at least one condensation formation parameter P, then alternatively and / or additionally, steps S6 and / or S7 may be applied to provide a corresponding additional energy output e and / or an increase in temperature value T and thus provide an increased heat flux and / or output to enhance the outcome of any process in the corresponding mixing process, for example, to reduce the relative humidity of exhaust gas E, another exhaust gas G, and / or exhaust mixture M.

[0280] The described method enables the control mechanism to allow mixing of the TMS (another exhaust gas G leaving the TMS) effluent and the ASP (exhaust gas E leaving the ASP) effluent, i.e., and / or allow two separate effluents. Thus, mixing can be selectively performed under condensation formation conditions. Therefore, any thermodynamic losses caused by the mixing process occur only when necessary. Accurate prediction of condensation formation conditions can be performed in each step of the method, particularly in step S1, while monitoring at least one condensation formation parameter P. This can be achieved via sensor 32 and / or control element 59 on aircraft 1 and / or via information provided from external sources such as other aircraft 1, satellite 8, and / or ground station 9.

[0281] Alternatively or additionally, steps S5, S6, and / or S7 allow a controlled amount of heat, for example, in the form of TMS effluent to ASP effluent, to be added to the exhaust gas. This allows control over droplet formation in the ASP effluent. Adding heat reduces relative humidity and thus delays droplet formation. Not adding heat promotes droplet formation. Depending on the aerodynamics of the effluent, enhancing or delaying droplet formation reduces or increases the final number and size of droplets. This adds another degree of freedom and provides control over the properties of the condensation trail.

[0282] Figure 21 A schematic diagram of an exemplary embodiment of an energy conversion arrangement structure 10 including a humidifier 130 is shown, the humidifier 130 having at least one humidification stage 131, 132 (see also...) Figure 16 The energy conversion arrangement 10 may also include an intercooler assembly 140 and / or at least one filter device 150, which may have at least one particulate filter element 151 and / or a chemical filter element 152. Furthermore, the energy conversion arrangement 10 may include at least one water separator 210.

[0283] A humidifier 130 is arranged in the flow path 14 of the supply air A and the flow path 15 of the exhaust air E. The humidifier 130 is configured to humidify the supply air A using water W from the exhaust air E. In this example, the humidifier 130 is arranged in the flow path 14 of the supply air A between the intercooler assembly 140 and the fuel conversion device 11, particularly the fuel cell system 70; and / or in the flow path 15 of the exhaust air E between the intercooler assembly 140 and the water separator 210.

[0284] The intercooler assembly 140 may include at least one heat exchange unit 34. In this example, the intercooler assembly 140 may be arranged in the flow path 14 of the supply air A between the humidifier 130 and the filter device 150, and / or in the flow path 15 of the exhaust air E between the humidifier 130 and the air supply system 41, particularly the turbine 19 of the air supply system 41. At least one filter device 150 may be arranged in the flow path 14 of the supply air between the air inlet 12 and the air supply system 41, particularly the compressor 16 of the air supply system 41, and / or in the flow path 14 of the supply air between the air supply system 41, particularly the compressor 16 of the air supply system 41, and the intercooler assembly 140.

[0285] Alternatively or additionally, the humidifier 130 can be used as a water separator. For example, the humidifier 130 can have a separation structure including a permeable membrane and / or absorbent material. The permeable membrane can be provided in the form of a capillary assembly or pore arrangement and / or include a capillary assembly or pore arrangement that can be configured to maximize the separation surface provided by the permeable membrane. Thus, the capillary assembly can include a plurality of capillary elements and / or pores that form guide channels for separating water W from exhaust gas E. Due to the corresponding small flow channels, the humidifier 130 can filter out tiny droplets from the flow, especially if the humidifier 130 is placed downstream of the turbine 19. Tiny droplets may condense in the turbine 19 and might otherwise be difficult to separate from the exhaust gas E.

[0286] In operation, exhaust gas E can enter the humidifier 130 through the exhaust inlet and travel along the separation structure, for example, through the capillary element of the separation structure, so that the water W contained in the exhaust gas E can be fused through the permeable membrane, while the remaining relatively dry exhaust gas E travels to the dry outlet of the humidifier, where it can be discharged from the humidifier 130. The collected water W can be discharged through the wet outlet of the humidifier 130, which can be connected to the water supply line 21 or pipeline (see...). Figures 22 to 24 ).

[0287] In the operation of the energy conversion arrangement structure 10, supply air A can be drawn in from the atmosphere 7 and / or from inside the outer shell 4, for example from the cabin of the aircraft 1, through air inlet 12. Supply air A can then pass through at least one filter device 150 to filter out any unwanted particles and / or chemical components. Afterward, supply air A can pass through air supply system 41, particularly compressor 16, to be pressurized to a desired level. The pressurized supply air A can then (again) pass through at least one filter device 150 to filter out any unwanted particles and / or chemical components.

[0288] In the intercooler assembly 140, the supply air A can be cooled by corresponding heat exchange with the exhaust gas E. The relatively dry supply air A can then pass through a humidification device 130 to be humidified using water W (liquid water and / or water vapor) from the exhaust gas E. For example, the supply air A and the exhaust gas E can be guided in a counter-current arrangement in the humidification device 130, at least in sections. After the humidification device 130, the supply air A can be supplied to the fuel conversion unit 11, particularly the fuel cell system 70.

[0289] Exhaust gas E from fuel conversion unit 11, particularly fuel system 70, can be directed through water separator 210, where water W can be separated from exhaust gas E and directed away through corresponding water supply lines 21 and / or pipes. Exhaust gas E can then pass through humidification unit 130. Afterward, exhaust gas E can be directed through intercooler assembly 140 and then through air supply system 41, particularly the turbine 19 of air supply system 41. For example, exhaust gas E can then be directed to exhaust outlet 13 and / or mixing assembly 42, etc.

[0290] In this example, sensor 32 can be positioned at the air inlet 12, the exhaust outlet 13, the flow path 14 of the supply air A into the fuel conversion device 11, particularly the fuel cell system 70, and / or any of the aforementioned locations, to enable the adjustment of the humidity of the supply air A and / or exhaust air E based on at least one measurement, thereby providing humidity control for the fuel conversion device 11 by means of the control device 54 of the control system 50. The humidification device 130, the intercooler assembly 140, and / or at least one filter device 150 can be substantially considered as part of the thermal management system 40 and / or the air supply system 41. Therefore, any component of the humidification device 130, the intercooler assembly 140, and / or at least one filter device 150 can be used individually and / or in combination with any other configuration and / or exemplary embodiment of the energy conversion arrangement structure 10 described herein.

[0291] Figure 22 A schematic diagram of another exemplary embodiment of the energy conversion arrangement structure 10, including the humidification device 130, is shown. For the sake of simplicity and efficiency, only this exemplary embodiment of the energy conversion arrangement structure 10 will be discussed in the following text. Figure 21 The differences between the embodiments shown are explained below. For example, the humidifier 130 can be operated such that the supply air A and the exhaust air E are guided at least in a cross-flow arrangement. The intercooler device 140 can be cooled by another air H and / or exhaust air E leaving the humidifier 130 as desired or required and / or can be incorporated into the filter device 150, or the filter device 150 can be incorporated into the intercooler device 140.

[0292] For example, a particulate filter element 151 may be arranged in the flow path 14 of the supply air A between the air supply system 41, particularly the compressor 16 of the air supply system 41, and the intercooler assembly 140, specifically to remove unwanted particles from the supply air A. A chemical filter element 152 may be arranged in the flow path 14 of the supply air A between the intercooler assembly 140 and the humidifier 130, specifically to remove unwanted components from the supply air A. The intercooler assembly 140, the particulate filter element 151, and / or the chemical filter element 152 may be arranged back-to-back with each other.

[0293] Figure 23 A schematic diagram of another exemplary embodiment of the energy conversion arrangement structure 10 including a humidification device is shown. For the sake of simplicity and efficiency, only this exemplary embodiment of the energy conversion arrangement structure 10 will be discussed in the following text. Figure 21 and Figure 22 The differences between the embodiments shown are explained below. For example, the humidifier 130 can be operated such that the supply air A and the exhaust air E are guided at least in sections in a counter-current and / or cross-current arrangement. For such an arrangement, two humidification stages 131, 132 can be provided in the humidifier 130.

[0294] For example, a first humidification stage 131 and a second humidification stage 132 may be provided. In the first humidification stage 131, the supply air A from the intercooler assembly 140 and / or filter device 150 can be humidified by means of the exhaust gas from the air supply system 41, particularly the turbine 19 of the air supply system 41. In the second humidification stage 132, the supply air from the first humidification stage 131 can be humidified, for example, after leaving the water separator 210, by means of the exhaust gas E from the fuel conversion device 11, particularly the fuel cell system 70.

[0295] Figure 24A schematic diagram of yet another exemplary embodiment of an energy conversion arrangement structure including a humidification device is shown. For the sake of simplicity and efficiency, only this exemplary embodiment of the energy conversion arrangement structure 10 will be discussed in the following text. Figures 21 to 23 The differences between the embodiments shown are explained below. For example, the first humidification stage 131 and the second humidification stage 132 can be separated from each other because exhaust gas E leaves the humidification device 130 after the first humidification stage 131 and is then supplied to the air supply system 41, particularly the turbine 19 of the air supply system 41. After leaving the turbine 19, exhaust gas E can be directed to the second humidification stage 132. After the second humidification stage 132, exhaust gas E can be directed through the intercooler assembly 140 and then towards the exhaust outlet 13.

[0296] Figure 25 A schematic diagram of an exemplary embodiment of an energy conversion arrangement 10 including a water separator 210 or a water separation device is shown. For the sake of brevity and efficiency, only the differences between this exemplary embodiment of the energy conversion arrangement 10 and other embodiments of the energy conversion arrangement 10 disclosed herein will be explained below. The arrangement 10 includes at least one water separator 210, which is arranged in the flow path 15 of the exhaust gas E generated in the fuel conversion device 11 and configured to separate water W from the products of the fuel conversion device 11 during the journey from the fuel conversion device 11 to the exhaust outlet 13.

[0297] Water W drawn from exhaust E can be directed through a corresponding water supply line 21 and / or conduit. For example, water W drawn from exhaust E can be discharged from aircraft 1 through water supply line 21 and / or directed to condensation reduction device 20. Material separator 210 can partially or completely separate gaseous or liquid water W, which can then be discharged. For example, discharged water W in the form of large droplets is unlikely to contribute to condensation formation.

[0298] The water separation material in water separator 210 may cause pressure loss, which reduces the potential power of the turbine 19, which is part of or part of the expansion device 17. Therefore, the energy conversion arrangement 10 described herein, and any energy conversion arrangement, may include a motor 300, such as an electric motor, which may be configured to compensate for any energy loss caused by water separation upstream of water separator 210. In particular, the motor 300 may drive a compression device 16 other than the expansion device 17, such as the turbine 19. The motor 300 may be arranged and / or adapted to transmit power to a transmission line 18, which may be at least partially configured as a drive shaft driven by the motor 300.

[0299] Figure 26 A schematic diagram of another exemplary embodiment of an energy conversion arrangement structure including a water separator 210 is shown. For the sake of brevity and efficiency, only the differences between this exemplary embodiment of the energy conversion arrangement structure 10 and other embodiments of the energy conversion arrangement structure 10 disclosed herein will be explained below. In this example, the energy conversion arrangement structure 10 may include a bypass conduit 36 ​​connected to a flow path 15 of the exhaust gas E via a flow connector 37, wherein at least one water separator 210 is arranged in the bypass conduit 36.

[0300] The flow connector 37 may include a switching valve 38, which may be steplessly operated, for example, to allow exhaust gas E to pass through the expansion device 17 and / or to guide exhaust gas E to the exhaust outlet 13 via the bypass pipe 36. The switching valve 38 may be operated with the assistance of a control unit 39, which may be connected to at least one of the sensors 32 via corresponding transmission lines 18 and / or communication lines 55 for transmitting energy and / or information. Therefore, the operation of the switching valve 38 may be controlled by means of a control system 50, particularly a control device 54, to provide a control valve 43 for controlling the amount of exhaust gas E guided to the water separator 210 via the bypass pipe 36.

[0301] In operation of the energy conversion arrangement 10, the exhaust gas E can branch off from the flow path 15 at the flow joint 37 to bypass the expansion device 17 via the bypass pipe 36 leading to the water separator 210, thereby forming an alternative or auxiliary flow path 15 for the exhaust gas E in addition to the main flow path 15 that guides the exhaust gas E through the expansion device 17. The amount of exhaust gas E that bypasses the expansion device 17 and is guided through the water separator can be controlled by means of the control unit 39 and / or the control system 50, particularly the control device 54, so that any measured values, such as temperature, pressure and / or humidity values, measured by means of at least one of the sensors 32 before, within and / or after the expansion device 17 are kept within, above and / or below the corresponding desired or required value range and / or limits.

[0302] Alternatively or additionally, flow joint 37 may be arranged within the expansion device 17, for example, between certain sections of the expansion device 17. Flow paths 15 guiding through the expansion device 17 and flow paths 15 guiding through the bypass conduit 36 ​​may be connected within and / or after the expansion device 17 and / or exhaust outlet 13. The bypass conduit 36 ​​may be used to bypass any section or component of the energy conversion arrangement structure 10 as described herein. Therefore, at least one flow joint 38 may be arranged as desired or required to bypass the expansion device 17, condensation reduction device 20, heating device 30, and / or heat exchange device 34.

[0303] Figure 27 A schematic diagram of another exemplary embodiment of the energy conversion arrangement structure 10, including a water separator 210, is shown. For the sake of simplicity and efficiency, the differences between this exemplary embodiment of the energy conversion arrangement structure 10 and other embodiments of the energy conversion arrangement structure 10 disclosed herein will only be explained below. In this example, the water separator 210 is arranged upstream of the expansion device 17, particularly the turbine 19. Therefore, the relative humidity of the exhaust gas E entering the expansion device 17, particularly the turbine 19, can be reduced to a level that prevents water W from condensing in the expansion device, particularly the turbine 19.

[0304] Figure 28 A schematic diagram of yet another exemplary embodiment of the energy conversion arrangement structure 10, including a water separator 210, is shown. For the sake of brevity and efficiency, only the differences between this exemplary embodiment of the energy conversion arrangement structure 10 and other embodiments of the energy conversion arrangement structure 10 disclosed herein will be explained. In this example, the water separator 210 replaces and / or is arranged as the expansion device 17 in the flow path 15 of the exhaust gas E. For example, the pressure drop in the exhaust gas E within the water separator 210 can be used to facilitate the separation process.

[0305] Figure 29A schematic semi-transparent perspective view of the water separator 210 is shown (see Bocciardo and Davide, “Optimisation and integration of membrane processes in coal-fired powerplants with carbon capture and storage,” 2015, https: / / www.researchgate.net / publication / 292788149_Optimisation_and_integration_of_membrane_processes_in_coalfired_power_plants_with_carbon_capture_and_storage). At least one water separator 210 may have at least one exhaust inlet 211, at least one wet outlet 212, and / or at least one dry outlet 213, the dry outlet 213 being provided, for example, at an enclosure 214, such as the housing or piping of the water separator 210.

[0306] The enclosure 214 may at least partially provide a flow path 15 for the exhaust gas E and includes a separation structure 215 extending along the flow path 15 for the exhaust gas E provided by the water separator 210. For example, the separation structure 215 includes a permeable membrane 216 and / or absorbent material. The permeable membrane 216 may be provided in the form of a capillary assembly 217 or a pore arrangement and / or includes a capillary assembly 217 or a pore arrangement configured to maximize the separation surface provided by the permeable membrane 216. Therefore, the capillary assembly 217 may include a plurality of capillary elements 218 and / or pores, which form guiding channels for separating water W from the exhaust gas E.

[0307] In operation, exhaust gas E can enter water separator 210 through exhaust inlet 211 and travel along separation structure 217, for example through capillary element 218 of the separation structure, such that water W contained in exhaust gas E can be absorbed through permeable membrane 216, while the remaining relatively dry exhaust gas E travels to dry outlet 213, where it can be discharged from water separator 210. The collected water W can be discharged through wet outlet 212, which can be connected to water supply line 21 or pipeline.

[0308] For example, a water separator 210 containing water separation material can be placed anywhere in the energy conversion arrangement 10 where the flow of exhaust gas E has the highest or at least a relatively high content of liquid water and / or water vapor. This supports the separation process. Furthermore, the separation material constituting the separation structure 215 does not necessarily need to be concentrated in a single water separation component, such as the water separator 210. The separation material can also be incorporated into the pipe walls and all other component surfaces of the energy conversion arrangement 10 that are in contact with the relatively wetted flow of exhaust gas E. For the effectiveness of the materials used, important, if not paramount, factors can be seen in the corresponding water flux per unit surface area of ​​the permeable membrane 216. The available surface area should be maximized, for example, by filling the flow path with the volume of hollow fibers, capillaries, narrow tubes, etc., which can be arranged as corresponding capillary components 217.

[0309] Figure 30 A schematic diagram of a model used in an embodiment of the exhaust assembly 400 of the energy conversion arrangement structure 10 is shown. The exhaust assembly 400 may include a wall portion 401, which may provide an outer wall segment 402 and an inner wall segment 403. A lip 404 may be disposed between the outer wall segment 402 and the inner wall segment 403.

[0310] The inner wall section 403 may at least partially define the flow path 15 for exhaust gas E, particularly its outlet passage 405, which leads to an exhaust outlet 13 for discharging exhaust gas E into the atmosphere 7, which can be considered adjacent to the mixing assembly 400. The mixing assembly 400, particularly the outlet passage 405, is illustrated as having an optional plane of symmetry s. An asymmetrical configuration of the mixing assembly 400 may be achieved as desired or required. A mixing zone 406 is formed near and / or around the lip 404 at the exhaust outlet 13.

[0311] Figure 31 It shows the result of, as Figure 30 The diagram illustrates a model of a mixing zone 406 formed by an embodiment of the exhaust assembly 400. During the operation of the aircraft 1, under certain operating and / or atmospheric conditions, a droplet source 407 of relatively large droplets C formed from water vapor contained in the exhaust E can be established in the mixing zone 406. The formation of droplets C can be facilitated by providing an outer trailing edge 408, for example, between the outer wall section 402 and the lip 404, for the flow of ambient air A generated by a specific flight speed in the direction of travel F, and / or an inner trailing edge 409 between the inner wall section 403 and the lip 404, for the flow of exhaust E. This can contribute to the formation of a recirculation zone 410 in the mixing zone 406.

[0312] The recirculation region 410 may include an air vortex 411 driven at least partially by ambient air A and / or an exhaust vortex 412 driven at least partially by exhaust gas E. An outer trailing edge 408 and / or an inner trailing edge 409 respectively promote the formation of the air vortex 411 and / or the exhaust vortex 412. The recirculation region 410 may be established between the air vortex 411 and the exhaust vortex 412, wherein the corresponding flows of ambient air A, exhaust gas E, and / or the mixture of ambient air A and exhaust gas E are at least partially opposite and therefore can flow substantially parallel to the direction of travel F. In other words, the recirculation region 410 may include and / or consist of the air vortex 411 and / or the exhaust vortex 412 and / or may be composed of the air vortex 411 and / or the exhaust vortex 412. Therefore, in the recirculation region 410, ambient air A may gradually mix with exhaust gas E to promote the formation of relatively large droplets C, which may generate a plume 6.

[0313] The mixing height h of mixing zone 406 M It can depend on the lip margin height h of 404. L The exit height h of exit 13 13 and / or the outlet length l of the outlet passage 405 13 For example, the height of the lip edge h L With exit height h 13 The ratio can exceed 0.05, preferably 0.06, and most preferably 0.07. It can be determined by the minimum mixing height h of the mixing zone 406 at the lip edge 404. M The effective mixing height can be a total of 3 mm to 7 mm, preferably 4 mm to 6 mm, and most preferably about 5 mm. Outlet length l 13 The total length can be at least between 80 mm and 120 mm, preferably at least between 90 mm and 110 mm, and most preferably about 100 mm.

[0314] According to this example, the illustration shows how droplet source 407 evolves at the contact point where the warm and humid exhaust flow from fuel conversion device 11 meets the cold and dry air A from atmosphere 7, where uniform nucleation occurs and droplets C and D form. A portion of droplet source 407 can be observed falling into the recirculation region 410, indicated by corresponding eddy lines. The extended residence time of droplet D in this region leads to further growth of droplet D, which is beneficial in reducing the total number of droplets by producing relatively large and / or condensed droplets C. If the average distance between adjacent droplets is sufficiently small, the relatively large and / or condensed droplets C can be formed primarily by additional condensation and possibly also partially by condensation.

[0315] Figure 32A schematic diagram of an embodiment of an exhaust assembly 400 including a spoiler device 420 is shown, the spoiler device 420 may at least partially provide an outer trailing edge 408. The spoiler device 420 may include a spoiler element 421, which may be configured to have a corresponding variable spoiler height h. S The spoiler moves between the retracted position U and the extended position O, and the spoiler height h S Adjustments can be made using the control system 50 and corresponding actuators (not shown) as described above to avoid condensation formation or at least minimize the effects of unwanted condensation. For example, the spoiler element 421 may be provided with a hinge axis 422 that allows the spoiler element 421 to be rotatably moved between the retracted position U and the deployed position O in the manner of a spoiler baffle or the like.

[0316] At the retracted position U, the spoiler height h S It can be essentially zero, therefore the lip height h is not increased in the collapsed position U. S,U Therefore, this lip height can be considered as the minimum lip height h. L,MIN At the deployed position O, the spoiler height h S,O It can be increased to the minimum lip height to provide a maximum lip height or an open lip height h. L,O The lip margin 404. The outer posterior margin 408 is therefore raised and / or moved away from the lower posterior margin 409 to widen and / or open the mixing zone 406.

[0317] Figure 33 A schematic diagram of another embodiment of an exhaust assembly 400 including a spoiler device 420 is shown. The spoiler device 420 may include a lip segment 423, which may be at least segmentally shaped to provide a cavity 424 having a cavity depth d. The cavity 424 may enhance the formation of the outer trailing edge 408 and / or the inner trailing edge 409, and thus enhance the formation of the mixing zone 406. For example, the lip segment 423 may be shaped such that the lip segment 423 extends at least partially recessed between the outer trailing edge 408 and the inner trailing edge 409.

[0318] The lip segment 423 can be configured to at least segmentally accommodate a corresponding variable spoiler height h. D The spoiler moves between the retracted position U and the extended position O, and the spoiler height h D Adjustments can be made using the control system 50 and corresponding actuators (not shown) as described above to prevent condensation formation or at least minimize the effects of unwanted condensation. The maximum spoiler height h at the deployed position O. D,O This can result in the corresponding unfolding depth d of the lip segment 423. OThis results in an increase in the corresponding unfolding depth d of the cavity 424 formed by the lip segment 423. O For example, in the retracted position U, the lip segment 423 may provide a convex profile that potentially integrates the trailing edges 408, 409, in order to provide a single trailing edge for reducing drag and preferably to provide laminar flow adhering to the wall portion 401. In the extended position O, the lip segment 423 may be lowered to form a cavity 424 and establish a mixing zone 406 having the mixing effect between air A and exhaust E as described above.

[0319] According to this exemplary embodiment, the spoiler device 420 may be any component or arrangement including an active or passive spoiler element 421, a lip segment 423, and / or a cavity 424 that allow and / or enhance the formation of a mixing zone 404. The spoiler device 420 may help to turbulent and / or deflect the flow of ambient air A and / or exhaust gas E. In particular, the spoiler device 420 may promote corresponding flow stall, resulting in the formation of a mixing zone 404 that may occur in the formation of air vortices 411 and / or exhaust vortices 412.

[0320] Figure 34 A schematic diagram of droplet formation parameters provided according to an embodiment of the exhaust assembly 400 is shown. In this example, the corresponding exhaust height h of the exhaust outlet 13, illustrated by the horizontal dotted line, is shown. 13 The total is 70 mm. The normalized droplet diameter distribution downstream of plume 6 is represented by a corresponding scale, such as a grayscale scale, which indicates the number of droplets C and D classified by their respective size, i.e., diameter. It should be noted that after the implementation of recirculation zone 410, many small droplets D in the lower left corner of the figure are no longer present because they have grown. Therefore, the average Sauter diameter d... 32 exist Figure 34 The exemplary cases without the mixing region 406 are depicted by corresponding vertical dashed lines, and the exemplary cases involving the mixing region 406 are depicted by corresponding vertical solid lines.

[0321] Therefore, the application of the proposed exhaust assembly 400 shifts the droplet spectrum toward larger droplet C sizes while reducing the total number of droplets. This effect is achieved by, according to, as... Figure 30 The computational fluid dynamics (CFD) simulation applied in the simulated flow domain modeled by the exhaust assembly implementation illustrated in the figure has been successfully demonstrated. In the simulation domain, a rectangular overall shape is assumed to be defined by the atmosphere 7 and the plane of symmetry s, with a small rectangular indentation on its lower left side. The small rectangular indentation is represented by the wall portion 401 between the external ambient air A and the exhaust E in the form of an example of the internal flow from the air supply system 41.

[0322] From the bottom left to the top left, there are two inlets to the simulation domain: a cold, dry flow of air A from atmosphere 7 and a warm, humid flow of exhaust gas E. The walls are assumed to be no-slip walls. The top far-field boundary is set far enough from the main flow to ensure it does not affect the simulation results. The bottom boundary condition is the symmetric plane s. The right boundary condition is the domain outlet, which is also far enough to ensure undisturbed flow.

[0323] The obtained simulated flow is Figure 31 The diagram shows the application boundary conditions used for the simulation.

[0324] - Ambient air A:

[0325] - Static temperature: 228 K

[0326] - Static pressure: 37601 Pa

[0327] - Water vapor mass fraction: 0.0

[0328] - Mach 0.5

[0329] - Exhaust gas E and / or exhaust gas mixture M:

[0330] - Total temperature: 320 K

[0331] - Total pressure: 38300 Pa

[0332] - Water vapor mass fraction: 0.191

[0333] Furthermore, for the simulation, for both non-recirculation and recirculation cases, the variable lip height h... L Set the values ​​to between 1 mm and 5 mm respectively. Outlet length l 13 Set to 70 mm. Figure 34 The simulated droplet formation parameters shown in the figure were generated at the outlet of the simulation domain, approximately 15 m away from the corresponding exemplary embodiment of the exhaust assembly 400.

[0334] Possible implementations of the proposed exhaust assembly can be categorized, for example, by the corresponding implementation of the spoiler device 420, as passive or active flow control devices. Any passive flow control device is relatively easy to implement and should not significantly increase the complexity / weight of the system. An increase in thickness at the end of the wall portion 401 can be considered a passive measure. Alternatively or additionally, vortex plates, such as fixed spoiler element 421, can be arranged at the end of the wall portion 401. Furthermore, blunt ends of the wall portion 401 and / or cavities 424 that facilitate the formation of the recirculation region 410 can be implemented.

[0335] The active flow control device allows the exhaust assembly 400 to be selectively enabled / disabled as needed, using the control system 50 and corresponding actuators (not shown) as described above, to avoid condensation formation or at least minimize undesirable condensation effects, while improving the overall efficiency of the aircraft 1. For example, a baffle-like device, such as the described spoiler element 421, can be located at the wall portion 401 and can be configured in a mixing and / or recirculation configuration in the deployed position O or a drag-reducing configuration in the retracted position U when the mixing zone 406 is not required. Furthermore, flow injection to facilitate the formation of the mixing zone 406 and / or the recirculation zone 410 is conceivable.

[0336] Figure 35 A schematic diagram of an embodiment of an exhaust assembly 400 is shown, configured to generate a mixing zone 406 comprising a premixing zone 406a and a main mixing zone 406b. A relatively small amount of exhaust gas E can be branched, diverted, or separated by a branching path 405a or a pre-path leading from the outlet passage 405 to another exhaust outlet 13, while the main stream of exhaust gas E can be guided through the main passage 406b, which can be configured as a continuation of the outlet passage 405. The corresponding branch streams of exhaust gas E can be guided through a side passage 425, which can be at least partially provided by the branching path 405a.

[0337] A branch flow of exhaust gas E may generate a premixing zone 406a at another exhaust outlet 13 in the branch flow path 405a and / or side passage. Such at least one other exhaust outlet 13 may be located in the outer wall section 402. At at least one other exhaust outlet 13, the premixing zone 406a may preferably be formed upstream of the main mixing zone 406b in the direction of travel F.

[0338] Any relatively small droplets D formed in the premixing zone 406a can travel to the main mixing zone 406b. In the main mixing zone 406b, relatively large droplets C can be formed by the additional condensation of relatively small droplets D, for example, by means of water vapor from exhaust gas E entering the main mixing zone 406b from the main passage 405b through the corresponding exhaust outlet 13, under the formation of vortices as described above. In many cases, additional droplets can be formed in the main mixing zone 406b. However, the number of additional droplets formed in the main mixing zone 406b can be significantly less than in the case where the premixing zone 406a is not implemented.

[0339] Figure 36A schematic diagram of another embodiment of the exhaust assembly 400 is shown, configured to generate a mixing zone 406 comprising a premixing zone 406a and a main mixing zone 406b. The diagram illustrates a diversion path 405a that can be formed between a sleeve 426 and a wall portion 401, particularly an inner wall segment 403 of the wall portion 401. The sleeve 426 can be provided as a bushing-like insert, which can form a nozzle providing the main passage 405b and can protrude from the wall portion 401 in a direction opposite to the direction of travel F.

[0340] The corresponding branch passage 405a and / or field passage 425 can lead to another exhaust outlet 13, at the end of which a premixing zone 406a can be generated. A main mixing zone 406b can be generated again at the end of the main passage 405b. Because the sleeve 426 can protrude from the outlet passage 405, a stepped lip 404 or at least two lips 404 can be formed for potential vortex generation. Therefore, a corresponding number of stepped inner trailing edges 408 and outer trailing edges 409 can be provided at the two lips, for example, at the corresponding edges of the wall portion 401 and the sleeve 426.

[0341] Figure 37 A schematic diagram of droplet formation parameters according to an embodiment of an exhaust assembly 400 configured to generate a mixing zone 406 comprising a premixing zone 406a and a main mixing zone 406b is shown. In this example, the corresponding exhaust height h of the exhaust outlet 13, illustrated by a horizontal dashed line, is shown. 13 The total diameter is 70 mm. Based on the CFD results shown in the figure, the normalized droplet diameter distribution downstream of plume 6 is represented by a grayscale bar indicating the number of droplets of the corresponding size. It should be noted that many small droplets in the lower left corner of the figure are absent after implementing the proposed solution. This is because droplets are introduced from the premixing zone into the main mixing zone. Therefore, in Figure 37 The average Sotter average diameter d is depicted by a corresponding vertical dashed line for the exemplary case without premixing zone 406a and by a corresponding vertical solid line for the exemplary case involving premixing zone 406a. 32 A significant increase, which is beneficial.

[0342] The presented embodiment of the mixing component 400 introduces a premixing zone 406a, where a small portion of the warm, humid flow from the exhaust gas E mixes with the cold, dry ambient air. This results in the formation of relatively small droplets D after the premixing zone. These droplets are then conveyed to a main mixing zone 406b, where the majority of the remaining warm, humid flow mixes with the cold, dry ambient air A. Here, the earlier formed droplets D provide a phase boundary where condensation will occur. The condensation and associated latent heat release reduce the supercooling of the water vapor. Therefore, the nucleation rate of new droplets in the main mixing zone 406b is much lower than in the case without the premixing zone 406a.

[0343] In general, the resulting droplet spectrum consists of fewer, larger droplets. This can help reduce unwanted condensation effects depending on the corresponding flight conditions. The capacity of the branch passage 405a, main passage 405b, and / or side passage 425 used to guide the exhaust gas to the premixing zone 406a can be regulated and / or controlled by means of the control system 50, in particular the control device 54, for example by means of a control valve (not shown) for controlling the amount of exhaust gas E guided through the branch passage 405a, main passage 405b, and / or side passage 425.

[0344] Although at least one exemplary embodiment of the invention has been disclosed herein, it should be understood that modifications, substitutions, and alternatives will be apparent to those skilled in the art and can be made without departing from the scope of this disclosure. This disclosure is intended to cover any modifications or variations of the exemplary embodiments. Furthermore, in this disclosure, the terms “comprising” or “including” do not exclude other elements or steps, the terms “a,” “an,” or “an” do not exclude a plural, and the term “or” means any or both. Moreover, unless otherwise implied by this disclosure or the context, the features or steps described may also be used in combination with other features or steps and in any order. This disclosure is incorporated herein by reference the full disclosure of any patent or application for which it claims a benefit or priority. List of reference numerals 1 aircraft 2 Energy System 3 fuselage 4. Outer shell 5 propulsion units 6 plumes 7 atmospheres 8 satellites 9 ground stations / control stations 10 Energy Conversion Arrangement Structure 11 Fuel Conversion Unit 12 air inlets 13 exhaust outlets 14. Flow path (air) 15. Flow path (exhaust) 16 compression units 17 Expansion Device 18 transmission lines 19 turbines 20 condensation reduction device 21 Water supply lines / pipelines 22 pumps 23 Injection Nozzle 25 air ducts 30 heating devices 31 Catalytic converter 32 sensors 33 Combustion Chamber 34 heat exchange devices 35 Electric heating element 36 Bypass pipes 37 Flow connector 38 Switching valve / discharge valve 39 control unit 40 Thermal Management System 41 Air Supply System 42 Hybrid Components 43 Control valve / Switching valve 43a First Control Valve 43b Second control valve 44 Mixing device 45 Heat Exchanger Units / Components 50 control system 51 Computing System 52 Fuel Storage System 53 Energy Storage System / Power Storage Device / Battery 54 control devices 55 Transmission lines / communication lines / data connectors 56 processing units 57 Interface Module 58 storage modules 59 control elements 60 computing devices 61 Control Program / Computer Program 62 Computer-readable data carriers 63 Computer-readable media 64 data carrier signals 70 fuel cell system 71 fuel cell units 72 fuel cell elements 130 Humidifier 131 First Humidification Stage 132 Second Humidification Stage 140 Intercooler Assembly 150 filter unit 151 particulate filter element 152 Chemical Filter Element 210 water separator 211 exhaust inlet 212 Wet Export 213 dry export 214 Enclosure / Housing 215 Separation Structure 216 permeable membrane 217 Capillary Component / Orifice Arrangement Structure 218 capillary elements / holes 300 motor 400 exhaust components 401 wall section 402 outer wall section 403 inner wall section 404 Lip Edge 405 Export Channel 405a branch path / pre-path 405b main path 406 Mixed Zone 406a premixing zone 406b Main Mixing Area 407 droplet source 408 outer trailing edge 409 inner posterior edge 410 Recirculation Area 411 Air Vortex 412 Exhaust Vortex 420 spoiler device 421 spoiler element 422 hinged axis 423 Lip border segment 424 chambers 425 side passage 426 Sleeve I warm, dry flow II. Two exhaust mixtures III. Moisturize and expel air. IV. Ambient Air d diameter c communication channel d cavity depth d O Depth of Expansion e-energy g ground h 13 Export height h D spoiler depth h L Lip height h M Mixing height h S spoiler height l 13 Export length s-symmetric plane A air B fuel C condensate droplets D droplet E exhaust F direction of travel G's other exhaust H another air I Mixing Threshold K coolant M exhaust mixture O Expand position P-trace formation parameters Q mixing ratio R is mixed under conditions of reduced condensation / mixing ratio. S is mixed without being reduced. Temperature value U Collapse position V saturation pressure W water X-saturation line Y-mixed line Z-hybrid line S1 monitoring parameters S2 assesses clot formation parameters / determines mixing ratio S3 adjusts the first mixing ratio. S4 adjusts the second mixing ratio. S5 assesses condensation parameters / determines energy output S6 increases output S7 produces an imbalance

Claims

1. An energy conversion arrangement structure (10) for an aircraft (1), comprising: At least one exhaust outlet (13) for discharging exhaust gas (E) generated by a fuel conversion device (11), particularly a fuel cell system (70), wherein the fuel conversion device (11) is used to convert at least one fuel into electrical and / or mechanical energy; as well as At least one exhaust assembly (400) configured to mix the flow of exhaust (E) from at least one of the exhaust outlets (13) with ambient air (A) from the surrounding environment (7) in at least one mixing zone (406) to promote the growth of water droplets by causing water vapor contained in the exhaust (E) to condense at least partially in the mixing zone (406).

2. The energy conversion arrangement structure (10) according to claim 1, wherein, The mixing zone (406) is configured to gradually mix the exhaust gas (E) into the ambient air (A).

3. The energy conversion arrangement structure (10) according to claim 1 or 2, wherein, The mixing zone (406) includes a premixing zone (406a) and a main mixing zone (406b), wherein at least one exhaust branch path (405a) of the exhaust assembly (400) guides a branch flow of exhaust (E) to the premixing zone (406a), and the main passage (405b) of the exhaust arrangement structure (10) guides the main flow of exhaust (E) to the main mixing zone (406b).

4. The energy conversion arrangement structure (10) according to claim 3, wherein, The diversion passage (405a) is formed as a side passage (425) within the wall portion (401) of the exhaust assembly (400) that at least partially separates the exhaust (E) from the ambient air (A) and / or between the sleeve (426) and the inner wall portion (403) of the main passage (405a).

5. The energy conversion arrangement structure (10) according to at least one of claims 1 to 4, wherein, The exhaust assembly (400) is configured to promote the formation of an exhaust vortex (412) of the exhaust gas (E) recirculated in the mixing zone (406).

6. The energy conversion arrangement structure (10) according to at least one of claims 1 to 5, wherein, The exhaust assembly (400) is configured to promote the formation of an air vortex (411) of ambient air (A) recirculated in the mixing zone (406).

7. The energy conversion arrangement structure (10) according to claims 5 and 6, wherein, The exhaust vortex (412) and the air vortex (411) come into contact with each other in the recirculation region (410) of the mixing zone (406).

8. The energy conversion arrangement structure (10) according to at least one of claims 1 to 7, wherein, The exhaust assembly (400) includes a lip (404) that provides at least one trailing edge configured to generate the mixing zone (406).

9. The energy conversion arrangement structure (10) according to claim 8, wherein, The lip margin (404) height (h) L ) and the outlet height (h) of the exhaust outlet (13) 13 The ratio of ) exceeds 0.05, preferably 0.06, and most preferably 0.

07.

10. The energy conversion arrangement structure (10) according to claim 8 or 9, wherein, The exhaust assembly (400) includes a spoiler device (420) configured to at least partially provide the lip (404).

11. The energy conversion arrangement structure (10) according to at least one of claims 1 to 10, wherein, The exhaust assembly (400) includes a concave lip segment (423) that provides a cavity (424) that at least partially provides the mixing zone (406).

12. The energy conversion arrangement structure (10) according to at least one of claims 1 to 11, wherein, The outlet passage (405) leading to the exhaust outlet (13) is configured to provide an outflow direction that extends substantially parallel to or at least at an acute angle to the flow direction of ambient air.

13. An energy system (2), particularly for providing power to a propulsion unit (5) used in a propulsion vehicle (1), the energy system (2) comprising an energy conversion arrangement structure according to at least one of claims 1 to 12.

14. A propulsion unit (5) for propelling an aircraft (1), the propulsion unit (5) comprising an energy conversion arrangement structure (10) according to at least one of claims 1 to 12 and / or an energy system according to claim 13.

15. An aircraft (1) comprising an energy conversion arrangement (10) according to at least one of claims 1 to 12, an energy system (2) according to claim 13, and / or a propulsion unit (5) according to claim 14.

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