Energy conversion arrangement for an aircraft, energy system and aircraft

Abstract

An energy conversion arrangement, an energy system 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 a fuel conversion device (11), in particular a fuel cell system (70), for converting at least one fuel into electrical and / or mechanical energy, and at least one exhaust gas outlet (13) for discharging exhaust gas (E) produced by the fuel conversion in the fuel conversion device (11), and at least one mixing assembly (42) configured to merge a flow of further exhaust gas (G) of the fuel conversion device (11) with at least one flow of exhaust gas (E) from the at least one exhaust gas outlet (13).

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, particularly energy systems for powering propulsion units used to propel aircraft, and to aircraft including energy conversion arrangements and / or energy systems. 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: a fuel conversion device, particularly a fuel cell system, for converting at least one fuel into electrical and / or mechanical energy; at least one exhaust outlet for discharging exhaust gas generated by fuel conversion in the fuel conversion device; and at least one mixing component configured to merge a flow of another exhaust gas from the fuel conversion device with at least one flow of exhaust gas from at least one exhaust outlet.

[0015] An energy system is provided, specifically for powering a propulsion unit used in a propelled aircraft. The energy system includes 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 aircraft.

[0016] An aircraft is provided, which includes a corresponding energy conversion arrangement structure and / or a corresponding energy system.

[0017] The mixing process of the two exhaust streams is not straightforward. Typically, one exhaust stream can be supplied as the effluent from the thermal management system (TMS), which is significantly larger than the fuel conversion unit's stream. This fuel conversion unit's stream can then be supplied as the effluent from the air supply system (ASP), which supplies air to the fuel conversion unit for fuel conversion. Nevertheless, the two streams should be mixed as uniformly as possible. Otherwise, some flow zones may still retain relatively high humidity and therefore pose a risk of condensation.

[0018] Another exhaust stream, such as the exhaust from the thermal management system, should be mixed with the air supply exhaust stream as completely as possible. If the thermal management exhaust stream is mixed with the cold ambient air before mixing with the exhaust stream, such as the air supply system exhaust stream, its effectiveness may be reduced or even lost. Furthermore, compactness is a crucial goal in aero-engine design. Therefore, the usable mixing length between the two streams may be quite short.

[0019] The proposed solution can mix one exhaust gas into another, or vice versa, as desired or required. A uniform and complete mixing process can be achieved by mixing another exhaust gas into exhaust gas from at least one exhaust outlet. The exhaust gas and the other exhaust gas streams can be beneficially merged to achieve the desired mixing behavior.

[0020] 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.

[0021] According to an embodiment of the energy conversion arrangement, at least one mixing component is arranged in the flow path of another exhaust gas. Thus, depending on the desired or required mixing process, one exhaust gas can be combined with another, or vice versa. This can help provide an efficient way to mix exhaust gas with another exhaust gas in a preferably uniform and complete manner.

[0022] According to an embodiment of the energy conversion arrangement, at least one mixing component is configured to envelop at least one exhaust outlet in another exhaust. Thus, the other exhaust can engulf exhaust along its path to at least one exhaust outlet, or exhaust can engulf another exhaust along its path to at least one exhaust outlet. This can further contribute to providing an efficient method for mixing exhaust with another exhaust in a preferably uniform and complete manner.

[0023] According to an embodiment of the energy conversion arrangement, at least one exhaust outlet is configured as at least a portion of a mixing device comprising at least one mixing component. The mixing device can be arranged such that exhaust gas and / or another exhaust gas can be directed to and / or bypassed from the mixing device. This facilitates providing an efficient manner for selectively mixing exhaust gas with another exhaust gas according to desired and / or required conditions.

[0024] According to the implementation of the energy conversion arrangement structure, the mixing device is configured to introduce a flow of exhaust gas into another flow of exhaust gas. Alternatively or additionally, a flow of exhaust gas may be introduced into another flow of exhaust gas. By introducing the flows into each other, shear forces and / or turbulence can be adjusted to a desired and / or required level in a certain mixing region to enable a balance between mixing mass and pressure loss during the mixing process.

[0025] According to an embodiment of the energy conversion arrangement, the mixing device includes at least one slotted nozzle having an elongated opening for discharging exhaust gas in a direction at least partially facing the flow direction of another exhaust gas. In other words, the elongated opening can be at least partially open, thus having a virtual surface normal pointing towards the flow direction of the other exhaust gas. Thus, the exhaust gas and the other exhaust gas can flow in substantially the same or at least similar directions in the mixing zone. The slotted nozzle can contribute to generating a uniform flow of exhaust gas, so as to uniformly distribute the exhaust gas when mixing with the other exhaust gas. This can further contribute to providing an efficient way to mix the exhaust gas with the other exhaust gas in a preferably uniform and complete manner, while minimizing pressure loss.

[0026] According to one embodiment of the energy conversion arrangement, the manifold of the mixing device leads to at least two slotted nozzles, which are arranged in a row extending substantially perpendicular to the flow direction of another exhaust. A plurality of slotted nozzles may be arranged in a row along the flow path of the exhaust and / or another exhaust. This improves the process of merging exhaust streams with another exhaust stream, providing an efficient way to mix the exhaust with another exhaust in a preferably uniform and complete manner, while minimizing pressure loss.

[0027] According to embodiments of the energy conversion arrangement, the mixing device includes multiple exhaust outlets arranged in the form of blades, teeth, forks, and / or combs. The exhaust outlets can be formed as several elongated openings. The exhaust outlets can be at least segmented and enclosed by another exhaust stream. For example, such exhaust outlets providing outlet openings for discharging exhaust gas can be arranged within the mixing device, for example, near an outlet leading to a mixing region. This can further improve the process of merging exhaust streams with another exhaust stream to provide an efficient way to mix the exhaust gas with another exhaust gas in a preferably uniform and complete manner, while minimizing pressure loss.

[0028] According to an embodiment of the energy conversion arrangement, the mixing device is configured to provide a total mixing angle of less than 45°, preferably less than 30°, and most preferably less than 15°, at which the exhaust flow enters the flow of another exhaust. The mixing angle can be adjusted to provide a smooth merging of the corresponding flows of exhaust and another exhaust. This can further improve the process of merging the exhaust flow with another exhaust flow, providing an efficient way to mix the exhaust with another exhaust in a preferably uniform and complete manner, while minimizing pressure loss.

[0029] According to the implementation of the energy conversion arrangement, the mixing angle is configured to provide at least one exhaust flow and another exhaust flow substantially parallel, at least sectionwise. Thus, the exhaust flow can meet the other exhaust flow at an acute angle. This can help regulate the process of blowing the flows into each other in a way that provides an optimal balance between shear force and turbulence on the one hand, and coherence force and uniformly distributed flow on the other. Therefore, the mixing result can be balanced against any pressure drop and resulting efficiency losses. This can further contribute to providing an efficient way to mix the exhaust with the other exhaust in a preferably uniform and complete manner.

[0030] According to an embodiment of the energy conversion arrangement, the mixing component includes a throttling device configured to throttle the flow of exhaust gas and / or another exhaust gas. The throttling device can be configured to throttle the flow of exhaust gas, another exhaust gas, and / or any exhaust gas mixture. The throttling device can facilitate adjusting the mixing ratio of exhaust gas and another exhaust gas as desired or required. For example, the final device can function as a control valve, which can be controlled by means of a control unit, control device, and / or control system. Thus, the throttling device facilitates the controlled mixing of exhaust gas into another exhaust gas or the mixing of another exhaust gas into exhaust gas.

[0031] According to embodiments of the energy conversion arrangement, the throttling device includes a baffle configured to open and close at least one exhaust outlet and / or another exhaust outlet for another exhaust. The position of the baffle can be controlled by means of a control unit, control device, and / or control system. The baffle can particularly advantageously allow the direction of another exhaust towards the exhaust guide while controlling the amount of the other exhaust mixed with it, or the baffle can particularly advantageously allow the direction of exhaust towards another exhaust while controlling the amount of exhaust mixed with it. This can further contribute to providing an efficient manner of mixing the exhaust with the other exhaust in a preferably uniform and complete manner.

[0032] According to an embodiment of the energy conversion arrangement, the throttling device is configured to guide the flow of another exhaust gas toward the flow of exhaust gas from at least one exhaust outlet, at least in an intermediate position between the open and closed positions of the throttling device. In the closed position of the throttling device, the amount of the other exhaust gas supplied to the mixing assembly can be zero or substantially zero. In the open position of the throttling device, substantially all of the available other exhaust gas can be mixed with the exhaust gas. At least in the intermediate position, the baffle can guide the flow of the other exhaust gas at the exhaust gas flow in a manner that provides an optimal balance between shear force and turbulence on the one hand, and coherence force and laminar flow on the other hand. This can further contribute to providing an efficient way to mix the exhaust gas with the other exhaust gas in a preferably uniform and complete manner.

[0033] Furthermore, it should be noted that, with respect to mass flow, the expression "mixing one flow into another flow" can depend on the corresponding amounts of the available exhaust gas and / or the other exhaust gas. Therefore, on the one hand, when the amount of exhaust gas is less than the amount of the other exhaust gas, the expression "mixing" can be interpreted as causing the exhaust gas to mix into the other exhaust gas. On the other hand, when the amount of the other exhaust gas is less than the amount of exhaust gas, the expression "mixing" can be interpreted as causing the other exhaust gas to mix into the exhaust gas. Therefore, since in this example, the throttling device can be configured to throttle the exhaust gas and / or the other exhaust gas flow at least within a certain range of the throttling device's open position, the other exhaust gas can be considered to be mixed into the exhaust gas, possibly until the amount of the other exhaust gas significantly exceeds the amount of exhaust gas.

[0034] However, the expression "mixing" can also be interpreted as indicating, in terms of impulse, which flow is entrained by another flow. Therefore, a flow with a relatively low impulse can be considered to be entrained by a flow with a relatively high impulse. In any case, the expression "mixing" should not be considered as excluding any setup or arrangement that allows exhaust gases to mix with each other, especially if the amount to be mixed can be adjusted and / or controlled as desired or required.

[0035] 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; at least one exhaust outlet for discharging exhaust gas generated by fuel conversion in the fuel conversion device; and at least one mixing component configured to mix another exhaust gas from the fuel conversion device with exhaust gas from at least one exhaust outlet.

[0036] According to an embodiment of the energy conversion arrangement, at least one mixing component is arranged in the flow path of another exhaust gas. Thus, depending on the desired or required mixing process, one exhaust gas can be mixed with another exhaust gas, or vice versa. This can help provide an efficient way to mix exhaust gas with another exhaust gas in a preferably uniform and complete manner.

[0037] According to an embodiment of the energy conversion arrangement, at least one mixing component is configured to allow another exhaust gas to pass through at least one exhaust outlet. Thus, the other exhaust gas can entrain exhaust gas along its path along at least one exhaust outlet, or exhaust gas can entrain another exhaust gas along its path along at least one exhaust outlet. This can further contribute to providing an efficient method for mixing exhaust gas with another exhaust gas in a preferably uniform and complete manner.

[0038] According to an embodiment of the energy conversion arrangement, at least one exhaust outlet is configured as at least a portion of a mixing device comprising at least one mixing component. The mixing device can be arranged such that exhaust gas and / or another exhaust gas can be directed to and / or bypassed from the mixing device. This facilitates providing an efficient manner for selectively mixing exhaust gas with another exhaust gas according to desired and / or required conditions.

[0039] According to an embodiment of the energy conversion arrangement, the mixing device is configured to blow a stream of one exhaust gas into another. Alternatively or additionally, the exhaust gas stream can be blown into another exhaust gas stream. By blowing the streams into each other, shear forces and / or turbulence can be generated in a certain mixing region and the mixing process can be enhanced.

[0040] According to embodiments of the energy conversion arrangement, the mixing device is configured as at least one slotted nozzle. The slotted nozzle can help generate a wide exhaust flow to uniformly distribute the exhaust when mixing it with another exhaust. For example, the slotted nozzle can extend substantially laterally along the flow path of the exhaust and / or the other exhaust. This can further contribute to providing an efficient way to mix the exhaust with the other exhaust in a preferably uniform and complete manner.

[0041] According to one embodiment of the energy conversion arrangement, the manifold of the mixing device leads to at least two slotted nozzles. Several slotted nozzles can be arranged along the flow paths of one exhaust and / or another. This can improve the process of blowing flow into each other, thereby generating shear forces and / or turbulence in a certain mixing region and enhancing the mixing process.

[0042] According to embodiments of the energy conversion arrangement, the mixing device includes guiding elements in the form of blades, teeth, forks, and / or combs. For example, such guiding elements can be arranged within the mixing device, such as near the outlet of the mixing device leading to the mixing region. This can further improve the process of blowing the flow into each other, thereby generating shear forces and / or turbulence in a certain mixing region and enhancing the mixing process.

[0043] According to an embodiment of the energy conversion arrangement, the mixing device is configured to provide a mixing angle at which the flow of one exhaust gas enters the flow of another exhaust gas. The mixing angle can be adjusted to provide a beneficial collision between the respective flows of the exhaust gas and the other exhaust gas. This can further improve the process of blowing the flows into each other, thereby generating shear forces and / or turbulence in a certain mixing region and enhancing the mixing process.

[0044] According to the implementation of the energy conversion arrangement, the total mixing angle is less than 90°. Thus, the exhaust flow can meet another exhaust flow at an acute angle. This helps to regulate the process of blowing the flows into each other in a way that provides an optimal balance between shear force and turbulence on the one hand, and coherence force and uniformly distributed flow on the other. Therefore, the mixing result can be balanced against any pressure drop and resulting efficiency losses. This can further contribute to providing an efficient way to mix exhaust with another exhaust in a preferably uniform and complete manner.

[0045] According to embodiments of the energy conversion arrangement, the mixing component includes a throttling device configured to throttle a flow of another exhaust gas. Alternatively or additionally, the throttling device may be configured to throttle a flow of exhaust gas and / or any exhaust gas mixture. The throttling device can help allow adjustment of the mixing ratio of exhaust gas and another exhaust gas as desired or required. For example, the final device can be used as a control valve, which can be controlled by means of a control unit, control device, and / or control system. Thus, the throttling device helps to mix exhaust gas into another exhaust gas or mix another exhaust gas into exhaust gas in a controlled manner.

[0046] According to an embodiment of the energy conversion arrangement, the throttling device includes a baffle configured to open and close another exhaust outlet for another exhaust. The position of the baffle can be controlled by means of a control unit, control device, and / or control system. The baffle can particularly advantageously allow the other exhaust to be directed toward the exhaust guide while controlling the amount of the other exhaust mixed with it, or the baffle can particularly advantageously allow the exhaust to be directed toward the other exhaust while controlling the amount of the exhaust mixed with it. This can further contribute to providing an efficient way to mix the exhaust with the other exhaust in a preferably uniform and complete manner.

[0047] According to an embodiment of the energy conversion arrangement, the throttling device is configured to guide the flow of another exhaust gas to the flow of exhaust gas from at least one exhaust outlet, at least in an intermediate position between the open and closed positions of the throttling device. In the closed position of the throttling device, the amount of the other exhaust gas supplied to the mixing assembly can be zero or substantially zero. In the open position of the throttling device, substantially all of the other exhaust gas available can be mixed to the exhaust gas. At least in the intermediate position, the baffle can guide the flow of the other exhaust gas at the exhaust gas flow in a manner that provides an optimal balance between shear force and turbulence on the one hand, and coherence force and laminar flow on the other hand. This can further contribute to providing an efficient way to mix the exhaust gas with the other exhaust gas in a preferably uniform and complete manner.

[0048] Furthermore, it should be noted that, with respect to mass flow, the expression "mixing one flow into another" can depend on the corresponding amounts of the available exhaust gas and / or the other exhaust gas. Therefore, on the one hand, when the amount of exhaust gas is less than the amount of the other exhaust gas, the expression "mixing" can be interpreted as causing the exhaust gas to mix into the other exhaust gas. On the other hand, when the amount of the other exhaust gas is less than the amount of exhaust gas, the expression "mixing" can be interpreted as causing the other exhaust gas to mix into the exhaust gas. Therefore, since in this example, the throttling device can be configured to throttle the flow of the other exhaust gas at least within a certain range of the throttling device's open position, the other exhaust gas can be considered to be mixed into the exhaust gas, possibly until the amount of the other exhaust gas significantly exceeds the amount of the exhaust gas.

[0049] However, the expression "mixing" can also be interpreted as indicating, in terms of impulse, which flow is entrained by another flow. Therefore, a flow with a relatively low impulse can be considered to be entrained by a flow with a relatively high impulse. In any case, the expression "mixing" should not be considered as excluding any setup or arrangement that allows exhaust gases to mix with each other, especially if the amount to be mixed can be adjusted and / or controlled as desired or required.

[0050] According to an alternative or additional solution, a method 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 comprising 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.

[0051] 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.

[0052] According to one aspect, a computer-readable data carrier having a corresponding control program stored thereon is provided.

[0053] 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.

[0054] 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.

[0055] According to one aspect, an aircraft including a corresponding energy conversion arrangement structure is provided.

[0056] 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.

[0057] 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.

[0058] 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.

[0059] The proposed solution offers a reduction in condensation formation for all types of aircraft, including but not limited to fuel cell aircraft. This includes energy systems for the aircraft, including fuel cells used 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 mitigating the potential drawbacks of fuel cell-powered aircraft by reducing their contribution to condensation formation and thus increasing their environmental friendliness.

[0060] 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 impact area, 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 expected negative climate impact, even when condensation may not be possible or may be acceptable.

[0061] 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.

[0062] 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.

[0063] 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.

[0064] 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.

[0065] 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.

[0066] 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.

[0067] According to an embodiment of the energy conversion arrangement structure, the energy conversion arrangement structure 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 structure, and the at least one second control valve is configured to mix the other exhaust gas from the energy conversion arrangement structure with the exhaust gas from the fuel conversion device. The control valves may be provided in the form of throttling devices configured 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.

[0068] 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.

[0069] 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.

[0070] 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.

[0071] 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).

[0072] 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.

[0073] 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.

[0074] 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.

[0075] 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.

[0076] 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.

[0077] 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.

[0078] 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.

[0079] 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.

[0080] 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.

[0081] 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.

[0082] 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.

[0083] 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.

[0084] 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.

[0085] 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.

[0086] 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.

[0087] 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.

[0088] 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.

[0089] 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.

[0090] 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.

[0091] 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.

[0092] 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.

[0093] 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.

[0094] 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.

[0095] 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 reduces the amount of ice crystals that may form and thus reduces the effects of condensation. In principle, a corresponding solution could utilize any heat source to provide another exhaust stream.

[0096] 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.

[0097] 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.

[0098] 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.

[0099] 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.

[0100] 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.

[0101] 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.

[0102] 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.

[0103] 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.

[0104] 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.

[0105] 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.

[0106] 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.

[0107] 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.

[0108] 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.

[0109] 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.

[0110] 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.

[0111] 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.

[0112] 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.

[0113] 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.

[0114] 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.

[0115] 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.

[0116] 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.

[0117] 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.

[0118] 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.

[0119] 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.

[0120] 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.

[0121] 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.

[0122] 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.

[0123] 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.

[0124] 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.

[0125] 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.

[0126] 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.

[0127] 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.

[0128] 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.

[0129] 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.

[0130] 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.

[0131] 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.

[0132] 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.

[0133] 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.

[0134] 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.

[0135] 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.

[0136] According to one aspect of the energy conversion arrangement, the energy conversion arrangement also includes a control unit configured to regulate 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.

[0137] 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.

[0138] 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

[0139] 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:

[0140] 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.

[0141] Figure 2 It is a schematic diagram of the energy conversion arrangement structure including the condensation reduction device.

[0142] Figure 3 This is a schematic diagram of another embodiment of the energy conversion arrangement structure equipped with a heating device.

[0143] Figure 4 yes Figure 3 The diagram shows a schematic of an energy conversion arrangement, in which the heating device includes a catalytic converter.

[0144] Figure 5 yes Figure 3 and Figure 4 The diagram shows an energy conversion arrangement, in which the heating device includes a combustion chamber.

[0145] Figure 6 yes Figures 3 to 5 The diagram shows an energy conversion arrangement, in which the heating device includes a heat exchange device.

[0146] Figure 7 yes Figures 3 to 6 The diagram shows an energy conversion arrangement, in which the heating device includes an electric heating element and is provided with a bypass pipe.

[0147] Figure 8 This is a schematic diagram of a thermal management system for any embodiment of the energy conversion arrangement structure shown in this document.

[0148] Figure 9 This is a schematic diagram showing the mixing lines of plumes in the atmosphere.

[0149] Figure 10 This is a schematic diagram of the relative humidity within a plume when it mixes in the atmosphere.

[0150] Figure 11 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.

[0151] Figure 12 This is a schematic top view of an aircraft, which includes control devices for monitoring and controlling the properties of exhaust components.

[0152] Figure 13This 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.

[0153] Figure 14 This is a schematic diagram of possible steps in a method for operating an energy conversion arrangement structure.

[0154] Figure 15 This is a schematic perspective view of an implementation of the hybrid component.

[0155] Figure 16 This is a schematic perspective view of another embodiment of the hybrid component.

[0156] Figure 17 This is a schematic perspective view of another embodiment of the hybrid component.

[0157] Figure 18 yes Figure 17 Another schematic perspective view of an embodiment of the hybrid component shown.

[0158] Figure 19 yes Figure 17 and Figure 18 The diagram shows a schematic semi-transparent perspective view of an embodiment of the hybrid component.

[0159] Figure 20 yes Figures 17 to 19 A schematic perspective view showing details of an implementation of the hybrid component. Detailed Implementation

[0160] 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.

[0161] Figure 1A 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.

[0162] Figure 2 A 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.

[0163] 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 ).

[0164] 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.

[0165] 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 .

[0166] 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... E There 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.

[0167] Figure 3 A 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.

[0168] 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 .

[0169] Figure 4 It shows Figure 3The 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 5. 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 ).

[0170] Figure 5 It shows Figure 3 and Figure 4 The 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.

[0171] Figure 6 It shows Figures 3 to 5 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 8 ).

[0172] Figure 7 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.

[0173] 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.

[0174] 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.

[0175] 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.

[0176] Figure 8A 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.

[0177] 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.

[0178] Figure 9 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.

[0179] 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.

[0180] exist Figure 9 In the diagram, an exemplary condition for this flow is represented by point III.

[0181] 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).

[0182] Figure 10 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 2In 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.

[0183] 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.

[0184] Other alternative and / or additional implementations of the proposed solution may involve different air supply architectures, such as blowers replacing compressors, air from the cabin 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, cabin systems, thermal management system 40, and / or air supply system 41.

[0185] 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 adapted to different droplet sizes, constant mode, active mode, etc. Heating and / or cooling devices 30 can be used to adapt to the liquid water temperature to achieve smaller droplet sizes.

[0186] Figure 11A 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.

[0187] 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 12 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.

[0188] Figure 12 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 2, configured to supply electricity e to the vehicle 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 vehicle 1, energy system 2, propulsion unit 5, fuel conversion arrangement 10, and / or fuel conversion device 11 may be incorporated into the vehicle 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.

[0189] 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.

[0190] 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.

[0191] 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.

[0192] 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.

[0193] 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.

[0194] Another air H can be used in the thermal management system 40 to cool the coolant K, which is then selectively 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.

[0195] Figure 13 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.

[0196] 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.

[0197] 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.

[0198] Figure 14 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 can 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 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 can be mixed with another exhaust gas G and / or in a fourth step S4, another exhaust gas G can be mixed with exhaust gas. 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.

[0199] 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.

[0200] 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.

[0201] 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, thereby enhancing 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.

[0202] 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.

[0203] 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.

[0204] Figure 15A schematic perspective view of an embodiment of the mixing component 42 of the energy conversion arrangement structure 10 is shown. Here, the thermal management system 40, air supply system 41, and mixing component 42 of the energy conversion arrangement structure 10 are illustrated. The thermal management system 40 has an air inlet 12 that is substantially oriented towards the direction of travel F to draw in another air H. A corresponding flow path 14 for the other air H can be provided by an air duct 25 in the form of a ram air passage, which guides the other air H to a heat exchanger unit 45 including at least one heat exchanger element of the thermal management system 40. The other air H exits the heat exchanger unit 45 along with another exhaust gas G flowing along the corresponding flow path 15.

[0205] Air supply system 41 provides an air inlet 12, also substantially oriented in the direction of travel F, for drawing in air A to be directed to fuel conversion unit 11. In this example, air A is compressed by a compressor 16 driven by a turbine 19, which can be powered by exhaust gas E, which is configured as the effluent from fuel conversion unit 11. After leaving the turbine, exhaust gas E flows along its corresponding flow path 15.

[0206] The mixing assembly 42 includes a mixing device 44. In this example, the mixing device 44 is provided in the form of a slotted nozzle 80, which has a longitudinal outlet opening 81 for exhaust gas E. The outlet opening 81 extends substantially perpendicular to the flow path of the other exhaust gas G, as it extends along the entire outlet passage 82, which leads to another outlet opening 83 for the other exhaust gas G, which is substantially oriented in the opposite direction to the direction of travel F. The dimensions of the outlet passage 82 and / or the other outlet opening 83 can be controlled at least in part by means of a first control valve 43a, implemented in this example as a throttling device 84.

[0207] The throttling device 84 may be provided in the form of a baffle 85 and / or include a baffle 85, which may be hinged at at least one hinge point 86. The baffle 85 may rotate about the hinge point 85 to move between a closed position and an open position. Figure 15 In the open position shown, the top wall portion 87 moves away from the outlet 13 of the other exhaust gas G from the heat exchange unit 45. The lateral sidewall portion 88 of the baffle 85 laterally defines and thus defines the outlet passage 82 in the open position. In the closed position, the baffle 84 can at least segmentally cover the outlet opening 81, such that the baffle 84 can be used to close the outlet passage 81 for the exhaust gas E.

[0208] Another exhaust gas G exits from the heat exchange unit 45 through its outlet 13 and is directed toward the mixing device 44, specifically the outlet opening 81 of the slotted nozzle 80. As the other exhaust gas G passes through the outlet opening 81, it mixes with the exhaust gas E exiting the outlet opening 81. The respective flows of exhaust gas E and the other exhaust gas G are directed such that they meet each other at a mixing angle α. Thus, exhaust gas E and the other exhaust gas G mix together to produce an exhaust gas mixture M, which exits the mixing assembly via the exhaust outlet 13, which constitutes the combined exhaust gas outlet for the exhaust gas mixture M.

[0209] Figure 16 A schematic perspective view of another embodiment of the mixing assembly 42 and mixing device 44 is shown. Here, the mixing device 44 includes at least one manifold 89 adapted to guide exhaust gas E to a plurality of slotted nozzles 80. Thus, the outflow of exhaust gas E from the air supply system 41 is separated to be compatible with the above-mentioned... Figure 15 The embodiment of the mixing component 42 illustrated in the figure exits the corresponding outlet opening 81 in a similar manner to that described. A manifold 89 is arranged in the flow path 15 of the exhaust gas E exiting the turbine 19 and guides the exhaust gas to the outlet opening 81 provided by the slotted nozzle 80. For example, the manifold 89 is arranged in the flow path 15 of the exhaust gas E between the turbine 19 and the exhaust outlet 13, particularly the combined exhaust outlet.

[0210] Figure 17 This is a schematic perspective view of another embodiment of the mixing assembly 42. Here, the mixing device 44 includes at least one manifold 89 adapted to guide exhaust gas E to a plurality of slotted nozzles 80. Thus, the outflow of exhaust gas E from the air supply system 41 is separated to be mixed with the above-mentioned... Figure 15 and Figure 16 The embodiment of the mixing component 42 illustrated in the figure exits the corresponding outlet opening 81 in a similar manner to that described. A manifold 89 is arranged in the flow path 15 of the exhaust gas E exiting the turbine 19 and guides the exhaust gas to the outlet opening 81 provided by the slotted nozzle 80. For example, the manifold 89 is arranged in the flow path 15 of the exhaust gas E between the turbine 19 and the exhaust outlet 13, particularly the combined exhaust outlet.

[0211] The outlet opening 81 is elongated, extending into another outlet opening 83 for another exhaust gas G. Thus, the other exhaust gas G can enclose the outlet opening 81. This may be particularly advantageous for merging the flow of the other exhaust gas G with the flow of exhaust gas E from the outlet opening 81 of the exhaust outlet 13 used as exhaust gas E.

[0212] Figure 18 yes Figure 17Another schematic perspective view of an embodiment of the mixing component 42 shown. It becomes apparent here that the elongated outlet opening 81 provided by the slotted nozzle 80 is substantially oriented towards the flow direction of the other exhaust gas G. A mixing zone 46 is provided at a corresponding gap between the slotted nozzles 80. The other exhaust gas G can flow through the gap to merge with the exhaust gas E exiting the outlet opening 81.

[0213] Figure 19 yes Figure 17 and Figure 18 The diagram shows a schematic semi-transparent perspective view of an embodiment of the mixing assembly. Another exhaust gas G is guided through the mixing device 44, specifically through the gap between the outlet openings 81 of the slotted nozzle 80. As the other exhaust gas G passes through the outlet openings 81 from the rear, it mixes with the exhaust gas E exiting the outlet openings 81. The respective flows of exhaust gas E and the other exhaust gas G are guided such that they meet each other at a mixing angle α. Therefore, exhaust gas E and the other exhaust gas G mix with each other to produce an exhaust gas mixture M, which exits the mixing assembly 42 via an exhaust outlet 13 that constitutes the combined exhaust gas outlet for the exhaust gas mixture M.

[0214] Figure 20 yes Figures 17 to 19 A schematic perspective view showing details of an embodiment of the mixing assembly 42. It becomes apparent here that the gap between the slotted nozzles 80 provides a corresponding mixing zone 46. Another exhaust gas G exits the gap and merges with the exhaust gas E exiting the outlet opening 81 in the mixing zone 46. Alternatively, additionally, the exhaust gas E and the other exhaust gas G can mix at their respective top ends protruding into the outlet channel 82 of the slotted nozzle 80. In other words, when the slotted nozzle 80 protrudes into the outlet channel 82, the slotted nozzle 80 can be enveloped by the other exhaust gas G.

[0215] According to this example, one or more elongated slotted nozzles 80, each with a corresponding outlet opening 81, are arranged in a comb-like pattern to introduce exhaust gas E, such as ASP exhaust gas, into another exhaust gas G, such as a ram air channel flow. The outlet opening 81 can provide a relatively large combined opening cross-section, thus allowing the exhaust gas E to have a relatively low flow velocity. This helps reduce pressure loss in the energy conversion arrangement 10, particularly the ASP, and also avoids droplet formation, while the outlet opening 81 can occupy only a relatively small portion of the corresponding cross-section of the outlet channel 82, and thus obstruct the flow of the other exhaust gas, such as the ram air channel flow. This, in turn, helps reduce pressure loss in the flow of the other exhaust gas G, such as the TMS air flow.

[0216] Furthermore, the flow of another exhaust gas G can pass through the mixing device 44 between the outlet openings 81. This helps to improve the process of mixing exhaust gas E with the other exhaust gas G, because the shear layer between the two flows can be relatively long, due to the adjacency of the slotted nozzle 80 with the outlet channel 82, the mixing zone can extend along the entire outer circumference of the slotted nozzle 80. The outlet openings 81, and therefore exhaust gas E, can be enveloped by the other exhaust gas E to merge with it, thereby forming an exhaust mixture M.

[0217] In this example, an air duct 25 in the form of a ram air channel is used, in which cold ambient air H is used as a radiator for the heat obtained from the fuel cell system 70. A heat exchanger unit 45, as part of the thermal management system 10, is used to transfer heat from the coolant K toward the cold air flow. After the heat exchanger unit 45, another exhaust gas G, in the form of a warm and still dry air flow, passes through a mixing device 44, specifically through the slotted nozzle 80 of the mixing device 44. Here, exhaust gas E from the energy conversion device 11 is introduced into the ram air channel in the form of humidified exhaust air from the air supply system 41. The mixing device 44 ensures effective and uniform mixing of the two flows. After the mixing device 44, the exhaust gas mixture M composed of the two flows is discharged to the surrounding environment, i.e., the atmosphere 7, through a combined exhaust outlet 13.

[0218] 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.

[0219] List of reference numerals

[0220] 1 aircraft

[0221] 2 Energy System

[0222] 3 fuselage

[0223] 4. Outer shell

[0224] 5 propulsion units

[0225] 6 plumes

[0226] 7 atmospheres

[0227] 8 satellites

[0228] 9 ground stations / control stations

[0229] 10 Energy Conversion Arrangement Structure

[0230] 11 Fuel Conversion Unit

[0231] 12 air inlets

[0232] 13 exhaust outlets

[0233] 14. Flow path (air)

[0234] 15. Flow path (exhaust)

[0235] 16 compression units

[0236] 17 Expansion Device

[0237] 18 transmission lines

[0238] 19 turbines

[0239] 20 condensation reduction device

[0240] 21 Water supply lines / pipelines

[0241] 25 air ducts

[0242] 30 heating devices

[0243] 31 Catalytic converter

[0244] 32 sensors

[0245] 33 Combustion Chamber

[0246] 34 heat exchange devices

[0247] 35 Electric heating element

[0248] 36 Bypass pipes

[0249] 37 Flow connector

[0250] 38 Switching valve / discharge valve

[0251] 39 control unit

[0252] 40 Thermal Management System

[0253] 41 Air Supply System

[0254] 42 Hybrid Components

[0255] 43 Control valve / Switching valve

[0256] 43a First Control Valve

[0257] 43b Second control valve

[0258] 44 Mixing device

[0259] 45 Heat Exchanger Units / Components

[0260] 46 Mixed Zone

[0261] 50 control system

[0262] 51 Computing System

[0263] 52 Fuel Storage System

[0264] 53 Energy Storage System / Power Storage Device / Battery

[0265] 54 control devices

[0266] 55 Transmission lines / communication lines / data connectors

[0267] 56 processing units

[0268] 57 Interface Module

[0269] 58 storage modules

[0270] 59 control elements

[0271] 60 computing devices

[0272] 61 Control Program / Computer Program

[0273] 62 Computer-readable data carriers

[0274] 63 Computer-readable media

[0275] 64 data carrier signals

[0276] 70 fuel cell system

[0277] 71 fuel cell units

[0278] 72 fuel cell elements

[0279] 80 grooved nozzle

[0280] 81 Exit Opening

[0281] 82 Exit Channel

[0282] 83 Another exit opening

[0283] 84 throttling device

[0284] 85 baffle

[0285] 86 hinge points

[0286] 87 Top Wall Section

[0287] 88 side wall section

[0288] 89 manifold

[0289] I warm, dry flow

[0290] II. Two exhaust mixtures

[0291] III. Moisturize and expel air.

[0292] IV. Ambient Air

[0293] d diameter

[0294] c communication channel

[0295] e-energy

[0296] g ground

[0297] A air

[0298] B fuel

[0299] C condensate droplets

[0300] D droplet

[0301] E exhaust

[0302] F direction of travel

[0303] G's other exhaust

[0304] H another air

[0305] I Mixing Threshold

[0306] M exhaust mixture

[0307] P-trace formation parameters

[0308] Q mixing ratio

[0309] K coolant

[0310] R is mixed under conditions of reduced condensation / mixing ratio.

[0311] S is mixed without being reduced.

[0312] V saturation pressure

[0313] W water

[0314] X-saturation line

[0315] Y-mixed line

[0316] Z-hybrid line

[0317] α Mixing Angle

[0318] S1 monitoring parameters

[0319] S2 assesses clot formation parameters / determines mixing ratio

[0320] S3 adjusts the first mixing ratio.

[0321] S4 adjusts the second mixing ratio.

[0322] S5 assesses condensation parameters / determines energy output

[0323] S6 increases output

[0324] S7 produces an imbalance

Claims

1. An energy conversion arrangement structure (10) for an aircraft (1), comprising: A fuel conversion device (11), particularly a fuel cell system (70), the fuel conversion device (11) being used to convert at least one fuel into electrical and / or mechanical energy, and At least one exhaust outlet (13) for discharging exhaust gas (E) generated by fuel conversion in the fuel conversion device (11); and At least one mixing component (42) configured to combine a flow of another exhaust gas (G) from the fuel conversion device (11) with at least one flow of exhaust gas (E) from the at least one exhaust outlet (13).

2. The energy conversion arrangement structure (10) according to claim 1, wherein, The at least one mixing component (42) is arranged in the flow path (15) of the other exhaust (G).

3. The energy conversion arrangement structure (10) according to claim 1 or 2, wherein, The at least one mixing component (42) is configured to enclose the at least one exhaust outlet (13) with the other exhaust (G).

4. The energy conversion arrangement structure (10) according to at least one of claims 1 to 3, wherein, The at least one exhaust outlet (13) is configured as at least a part of the mixing device (44) of the at least one mixing component (42).

5. The energy conversion arrangement structure (10) according to claim 4, wherein, The mixing device (44) is configured to introduce the flow of the exhaust gas (E) into the flow of the other exhaust gas (G).

6. The energy conversion arrangement structure (10) according to claim 4 or 5, wherein, The mixing device (44) includes at least one slotted nozzle (80) having an elongated outlet opening (81) for discharging the exhaust gas (E) in a direction at least partially facing the flow direction of the other exhaust gas (G).

7. The energy conversion arrangement structure (10) according to at least one of claims 4 to 6, wherein, The manifold (89) of the mixing device (44) leads to at least two slotted nozzles (80), which are arranged to extend substantially perpendicular to the flow direction of the other exhaust (G).

8. The energy conversion arrangement structure (10) according to at least one of claims 4 to 7, wherein, The mixing device (44) includes a plurality of exhaust outlets (13) arranged in the form of teeth, forks and / or combs.

9. The energy conversion arrangement structure (10) according to at least one of claims 4 to 8, wherein, The mixing device (44) is configured to provide a mixing angle (α) of less than 45°, preferably less than 30°, and most preferably less than 15°, at which the flow of the exhaust (E) enters the flow of the other exhaust (G).

10. The energy conversion arrangement structure (10) according to claim 9, wherein, The mixing angle (α) is configured to provide at least one stream of the exhaust (E) and a substantially parallel arrangement of the other exhaust (G) stream, at least in segments.

11. The energy conversion arrangement structure (10) according to at least one of claims 1 to 10, wherein, The mixing component (42) includes a throttling device (84) configured to throttle the flow of the exhaust (E) and / or the other exhaust (G).

12. The energy conversion arrangement structure (10) according to claim 11, wherein, The throttling device (84) includes a baffle (85) configured to open and close the at least one exhaust outlet (13) and / or another exhaust outlet (83) for the other exhaust (G).

13. The energy conversion arrangement structure (10) according to claim 11 or 12, wherein, The throttling device (84) is configured to direct the flow of the other exhaust (G) toward the flow of the exhaust (E) from the at least one exhaust outlet (13) at least in an intermediate position between the open and closed positions of the throttling device.

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

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

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