Patent Application
20250087713
This application claims the benefit of European Patent Application Number 23197056.7 filed on Sep. 13, 2023, the entire disclosure of which is incorporated herein by way of reference.
The present invention relates to a pressure stable electrode, more specifically the invention relates to a carrier structure for electrodes of a fuel cell, a fuel cell setup, a fuel cell arrangement, an energy supply system, an aircraft and a method for providing a carrier structure.
Fuel cells that convert chemical to electrical energy may be deployed to power a wide range of vehicle systems. However, certain vehicle systems, like aircrafts, have challenges in deploying fuel cells in terms of their stability to withstand possible physical conditions that may occur during operation of an aircraft and in terms of leakage of the fuel cell. The fuel cell design for handling of these requirements may result in too heavy fuel cell arrangements that may render the use of fuel cells in aircrafts inefficient.
There may thus be a need for a more stable fuel cell suitable for aircrafts.
This object of the present invention may be solved by the subject-matter of one or more embodiments described herein. It should be noted that the following described aspects of the invention apply also for the carrier structure for electrodes of the fuel cell, for the fuel cell setup, for the fuel cell arrangement, for the energy supply system, for the aircraft and for the method for providing a carrier structure.
According to the present invention, a carrier structure for electrodes of a fuel cell is provided. The structure comprises a duct wall and a tubular ducting volume. The duct wall forms the tubular ducting volume and comprises an outer surface facing a surrounding and an inner surface facing the tubular ducting volume. The tubular ducting volume is configured to conduct a first supply flow comprising an oxidant. The duct wall is configured to provide a second supply flow within the duct wall, the second supply flow comprising a reductant. The duct wall separates the first supply flow in the tubular ducting volume from the second supply flow within the duct wall and the surrounding of the carrier structure. A primary power coating layer is applied on the inner surface of the duct wall for being arranged between the first supply flow and the second supply flow. The primary power coating layer is configured for generating electrical energy from the first supply flow and the second supply flow. The duct wall is configured to withstand pressure loads resulting from a pressure difference between the tubular ducting volume and the surrounding. The pressure in the tubular ducting volume is at least twice as large as the pressure in the surrounding.
As an advantage, a lighter and more stable fuel cell is yielded.
As an advantage, high pressure differences can be handled between the inner and outer gas compartment of the tube.
As an advantage, a tremendous weight reduction for the surrounding compartment of the fuel cell stack is achieved because the pressure difference between the reactant air and the environmental atmosphere of the aircraft is fully captured by the cells itself.
As a further advantage, a fuel cell with a higher gravimetric power density is provided.
According to an example, the duct wall is based on an open-cellular structure. The open-cellular structure is configured to enhance interconnection within the duct wall to provide for its mechanical stability. The outer surface and the inner surface of the duct wall are formed from more dense cell regions of the open-cellular structure that are configured to separate the second supply flow from the first supply flow and the surrounding. The open-cellular structure comprises less dense cell regions within the duct wall to conduct the second supply flow.
According to an example, the open-cellular structure comprises a metal foam.
According to an example, a secondary power coating layer is applied on the outer surface of the duct wall for being arranged between the second supply flow and the surrounding providing an auxiliary source of oxidant to react with the reductant of the second supply flow. The secondary power coating layer is configured for providing electrical energy from the second supply flow and the auxiliary source of oxidant.
According to the present invention, also a fuel cell setup is provided. The fuel cell setup comprises at least one carrier structure according to one of the previous examples and electric terminals. The electric terminals comprise inner electric terminals that are in electric contact with the primary power coating layer. The electric terminals are configured to establish an electric power circuit by operating the carrier structure with an oxidant flow and a reductant flow.
According to the present invention, also a fuel cell arrangement is provided. The fuel cell arrangement comprises a housing and at least one fuel cell setup according to the previous examples. The least one fuel cell setup is encased by the housing. A gap between the at least one fuel cell setup and the housing forms a fluid receiving compartment for a fluid. The fluid prevents a contact of the at least one fuel cell setup with a surrounding atmosphere of the housing.
As an advantage, a more efficient thermal insulation for a fuel cell setup is provided.
As an advantage, a more secure and lighter fuel cell arrangement is yielded.
According to the present invention, also an energy supply system is provided. The energy supply system comprises at least one fuel cell arrangement according to the previous examples and a fuel reservoir. The fuel reservoir is connected to the at least one fuel cell arrangement to supply the second supply flow and the at least one fuel cell arrangement is configured to provide electric energy to power consuming loads.
As an advantage, a more secure and reliable energy supply system is yielded.
According to the present invention, also an aircraft is provided. The aircraft comprises at least one energy supply system according to the previous example and at least one power consuming load. The least one power consuming load comprises at least one of the group of: a propulsion system, electric avionic equipment and onboard electric devices for a cabin area. The least one power consuming load is powered by the at least one energy supply system.
As an advantage, a more secure and reliable aircraft is yielded.
As an advantage, leakages of fuel into the surrounding atmosphere of the fuel cell can be more effectively detected.
As an advantage, a lighter aircraft is yielded.
According to the present invention, also a method is provided. The method comprises the following steps:
The primary power coating layer is configured for generating electrical energy from the first supply flow and the second supply flow. The duct wall is configured to withstand pressure loads resulting from a pressure difference between the tubular ducting volume and the surrounding. The pressure in the tubular ducting volume is at least twice as large as the pressure in the surrounding.
According to an aspect, the fuel cell comprises a metal supported tubular cell with a metal foam as mechanical backbone, or support, which is also functioning as a fuel gas channel. The mechanical backbone allows high pressure differences between the inside and outside of the tube as well as a higher shock resistivity.
According to an aspect, a fuel cell deploys an electrode wall that protects an inner oxidant fluid stream and an inner reductant fluid stream from surroundings of the fuel cell. The wall is tube-shaped and provides the fuel fluid supply within the wall structure itself. Further the electrode wall provides a separation of the oxidant fluid stream and the reductant fluid stream. The electrode wall also enhances the mechanical stability of the fuel cell to withstand a higher mass flow of a pressurized oxidant fluid stream and a pressurized reductant fluid stream.
These and other aspects of the present invention will become apparent from and be elucidated with reference to the embodiments described hereinafter.
Exemplary embodiments of the invention will be described in the following with reference to the following drawings:
Certain embodiments will now be described in greater details with reference to the accompanying drawings. In the following description, like drawing reference numerals are used for like elements, even in different drawings. The matters defined in the description, such as detailed construction and elements, are provided to assist in a comprehensive understanding of the exemplary embodiments. Also, well-known functions or constructions are not described in detail since they would obscure the embodiments with unnecessary detail. Moreover, expressions such as “at least one of”, when preceding a list of elements, modify the entire list of elements and do not modify the individual elements of the list.
The carrier structure can also be referred to as support, hull, skeleton, backbone, framework, base, tubular framework, scaffold, matrix, column, spine, base, supporting device, supporting framework, support body, supporting membrane, membrane body, membrane device, framework device, membrane support, base framework, base membrane, base support, base cylinder, base reactor, base structure, base unit.
The term “primary” can also be referred to as first and vice versa.
The term “secondary” can also be referred to as second and vice versa.
In an example, the carrier structure 10 comprises metal.
In an example, the carrier structure 10 is made by additive manufacturing.
In an example, the carrier structure 10 is made by additive manufacturing from metal powder.
The term “electrodes” relates to units that can extract electrons from atoms, donate electrons to atoms or transfer electrons between atoms.
The term “fuel cell” relates to a unit that converts chemical energy into electric energy using a reducing and oxidizing substance.
In an example, the fuel cell is provided as solid oxide fuel cell, SOFC. The solid oxide fuel cell provides an oxide ion conducting solid state electrolyte between an anode layer site and a cathode layer site. The anode layer site extracts electrons from a reducing substance, i.e., hydrogen, that are transferred via an electric circuit to the cathode layer site. At the cathode layer site these electrons reduce an oxidant, i.e., oxygen, to oxide ions. The oxide ions are transferred via the oxide ion conducting solid state electrolyte to the anode layer site, where they match up with the converted reducing substance, i.e., protons, to form water and close the electric circuit. To provide for the mobility of the oxide ions in the oxide ion conducting solid state electrolyte, the SOFC needs to be operated at elevated temperatures, i.e., at over 600° C.
In an example, the fuel cell is configured to convert the chemical energy of hydrogen to electricity.
In an example, the fuel cell is configured to convert the chemical energy of molecular hydrogen to electricity.
In an example, the fuel cell is configured to convert the chemical energy of molecular ammonia to electricity.
In an example, the fuel cell is configured to convert the chemical energy of a hydrocarbon to electricity.
In an example, the fuel cell is configured to convert the chemical energy of methane to electricity.
In an example, the fuel cell is configured to convert the chemical energy of methanol to electricity.
The term “duct wall” relates to a physical barrier for molecules of a fuel for a fuel cell, but which is permeable for the reaction products of the energy converting reaction of the fuel cell, for example for oxide ions, electrons, or protons, to enable the reaction in the fuel cell. The duct wall 14 prevents the permeation of the molecules from an inner lumen enclosed by the duct wall 14 to the outside, the surrounding 20 of
In an example, the duct wall 14 is a membrane.
In an example, the duct wall 14 is a metallic membrane.
In an example, the duct wall 14 is a ceramic membrane.
In an example, the duct wall 14 is a tubular membrane duct.
In an example, the duct wall 14 is a membrane duct.
In an example, the duct wall 14 is configured to allow for diffusion of reaction products between the first supply flow 24 and the second supply flow 26.
The term “tubular ducting volume” relates to the inner lumen formed by a tube or a pipe that can conduct a mass flow of, i.e., a fluid, and predetermine the direction of the mass flow.
The term “outer surface” relates to the face that encloses a tube or a pipe and is in contact to the environment of the tube or pipe, the surrounding 20 of
In an example, the outer surface 18 of the tube is coated with an electrochemically inactive gas tight layer.
In an example, the outer surface 18 provides for thermal insulation.
In an example, the outer surface 18 provides for electric insulation.
The term “surrounding” relates to a space in a vehicle, such as an aircraft, or can also relate to a space enclosed by a housing or a chamber. The surrounding 20 can also be the external environment outside the vehicle.
The term “inner surface” relates to the face of a tube or pipe that is in contact to the inner lumen of the tube or pipe that is not in contact to the environment of the tube or pipe.
The term “supply flow” relates to a mass flow of molecules. The supply flow can be provided by a tank and compressors.
The first supply flow 24 can also be referred to as supply flow or first flow.
The second supply flow can also be referred to as supply flow or second flow.
In an example, the supply flow is provided to the carrier structure 10 by supply lines and the supply lines are attached to the carrier structure 10 by dedicated adapters.
In an example, the supply flow comprises pressurized fluid.
The term “oxidant” relates to a substance that can accept electrons.
In an example, the oxidant can be oxygen and/or hydrogen peroxide and/or nitrogen oxides.
The term “within the duct wall” relates to a property of the duct wall 14 in providing a radial cross section that is able to conduct a mass flow, as shown in
In an example, there are channels, pores, holes or cavities within the duct wall 14 that form an empty volume space to conduct a fluid.
The term “reductant” relates to a substance that donates electrons.
The reductant can also be referred to as fuel, reducing agent or reducer.
In an example, the fuel comprises hydrogen.
In an example, the fuel comprises molecular hydrogen.
In an example, the fuel comprises molecular ammonia.
In an example, the fuel comprises a hydrocarbon.
In an example, the fuel comprises methane.
In an example, the fuel comprises methanol.
The term “separates” relates to the function of the duct wall 14 in preventing the direct contact of the first supply flow 24 and the second supply flow 26, such that, e.g., the reductant and the oxidant do not mix and react in
The term “primary power coating layer” relates to an entity that enables the power converting function of the fuel cell. The primary power coating layer 28 comprises a cathode layer an electrolyte layer and an anode layer. The primary power coating layer 28 is electrochemically active in
The primary power coating layer 28 can also be referred to as primary coating layer, primary layer, first power coating layer, or first layer.
In an example, the cathode layer is attached to the electrolyte layer and the electrolyte layer is attached to the anode layer in a sandwich structure of the primary power coating layer 28.
In an example, the primary power coating layer 28 can be applied to the inner surface 22, such that the inner surface 22 has different structural orientations towards the sandwiched structure of the primary power coating layer 28.
In an example, the inner surface 22 is provided in the cathode layer.
In a further example, the inner surface 22 is provided between the cathode layer and the electrolyte layer.
In a further example, the inner surface 22 is provided in the electrolyte layer.
In a further example, the inner surface 22 is provided between the electrolyte layer and the anode.
In a further example, the inner surface 22 is provided at the anode layer.
In an example, the duct wall 14 comprises a structural contact area enlargement to enhance the contact surface to the primary power coating layer 28.
In an example, the duct wall 14 comprises channels to allow permeation of the reaction products in the first supply flow 24 and the second supply flow 26 through the primary power coating layer 28.
In an example, the duct wall 14 is made from the primary power coating layer 28.
In an example, the duct wall 14 comprises the anode layer.
In an example, to enhance the number of conversions of molecules in the fuel cell and the production of electric energy of the fuel cell, the pressure of the first and second supply flow 26 is enhanced.
In an example, the pressure of the first and second supply flow 26 is enhanced by a compressor, not shown in
In an example the pressure in the tubular ducting volume 16 can be at around 4 bar and the pressure in the surrounding 20 can be at around 0.3 bar.
In an example the pressure in the tubular ducting volume 16 can be at around 4 bar and the pressure in the surrounding 20 can be at around 1 bar.
In an example, the pressure difference is in a range of about 3.7 bar.
In an example, not show in
In an example, the pressure of the first supply flow 24 is at around 4 bar, the pressure of the second supply flow 26 is at around 2 bar and the pressure in the surrounding 20 is at around 0.3 bar.
In an example, the pressure of the first supply flow 24 is at around 4 bar, the pressure of the second supply flow 26 is at around 2 bar and the pressure in the surrounding 20 is at around 1 bar.
In an example, the environmental atmosphere of the aircraft is used at its low pressure level within the surrounding 20. This way heat losses can be reduced and thermal insulation works more efficiently as the density and heat conductivity of the surrounding 20 atmosphere is reduced compared to pressurized conditions.
In an example, the structure of the carrier structure 10 is adjusted to withstand the pressure gradient between first flow supply, second flow supply and the surrounding 20.
As an advantage, heat losses of a fuel cell can be reduced and thermal insulation works more efficiently.
In an example of
The term “more dense cell regions” relates to regions of the open cellular structure that are less permeable or impenetrable for molecules, than the “less dense cell regions”.
In an example, the “more dense cell regions” comprise more matter per volume than the “less dense cell regions”.
In an example, the primary power coating layer 28 covers at least a part of the inner surface 22 formed by the dense cell region of the open-cellular structure 32.
In an example, the duct wall 14 is based on a porous structure. The pore walls enhance the mechanical stability of the duct wall 14 through their interconnections. The outer surface 18 and the inner surface 22 of the duct wall 14 are formed from sealed pore regions of the porous structure that are configured to separate the second supply flow 26 from the first supply flow 24 and the surrounding 20. The porous structure comprises open pore regions within the duct wall 14 to conduct the second supply flow 26.
In an example, the open-cellular structure 32 comprises a honeycomb structure, connecting the inner surface 22 to the outer surface 18 of the wall. The honeycomb structure is configured to conduct the second supply flow 26 along the duct wall 14.
In an example, the open-cellular structure 32 comprises a metal foam.
In an example, at least a part of the metal foam is coated with an anode layer.
In an example, at least a part of the metal foam is coated with the primary power coating layer 28.
In an example, the metal foam separates the reactant air with a high pressure, 1-10 bar, at the inside of the tube from the environmental surrounding air at the outside of the tube, which has a very low pressure at high flight altitudes.
In an example, the fuel, i.e., the first supply flow 24, is fed to the porous metal foam, the reactant air, i.e., the second supply flow 26, to the tubular ducting volume 16. The outer surface 18 of the metal foam is covered with a gas-tight and electrochemically inactive layer.
As an advantage, by the metal foam the fuel cell is capable of handling higher mechanical and shock loads because of its more elastic properties compared to ceramic support structures.
In an example of
In an example, the duct wall 14 is a mantle structure, as shown in
In an example, the first tubular wall 34 is configured to provide an exchange of reaction products with the flow space between the two walls.
In an example, the second supply flow 26 flows in-between the first tubular wall 34 and a second tubular wall 36.
In an example, the first tubular wall 34 and the second tubular wall 36 form an annular interspace for receiving the second supply flow 26, as shown in
In an example, at least a part of the spacers is covered with the primary power coating layer 28.
In an example, at least a part of the spacers is covered with an anode layer.
In an example, the primary power coating layer 28 covers at least a part of the inner surface 22 formed by the first tubular wall 34.
In an example of
The term “secondary power coating layer” relates to an entity that enables the power converting function of the fuel cell. The secondary power coating layer 38 comprises a cathode layer an electrolyte layer and an anode layer.
The secondary power coating layer 38 can also be referred to as secondary coating layer, secondary layer, second power coating layer, or second layer.
In an example, the cathode layer is attached to the electrolyte layer and the electrolyte layer is attached to the anode layer in a sandwich structure.
In an example, the secondary power coating layer 38 can be applied to the outer surface 18, such that the outer surface 18 has different structural orientations towards the sandwiched structure of the primary power coating layer 28.
In an example, the outer surface 18 is provided in the cathode layer.
In a further example, the outer surface 18 is provided between the cathode layer and the electrolyte layer.
In a further example, the outer surface 18 is provided in the electrolyte layer.
In a further example, the outer surface 18 is provided between the electrolyte layer and the anode.
In a further example, the outer surface 18 is provided at the anode layer.
In an example, the cathode layer is applied facing away from the anode layer of the primary power coating layer 28.
In an example, the cathode layer of the secondary power coating layer 38 faces to the surrounding 20 of the carrier structure 10.
In an example, the secondary power coating layer 38 reacts with the air of the atmosphere in the surrounding 20 of the carrier structure 10 that acts as the auxiliary source of oxidant.
As an advantage, a fuel cell with an auxiliary power source can be provided.
In an example, the inner electric terminals 114a, 114b are in contact to an anode layer and a cathode layer of the primary power coating layer 128. The carrier structure 110 is configured to establish an electric power circuit via the inner terminals by operating the at least one carrier structure 110 with an oxidant flow and a reductant flow.
In an example of
The oxidant flow can also be referred to as first supply flow 24 comprising an oxidant.
The reductant flow can also be referred to as second supply flow 26 comprising a reductant.
In an example, the outer surface 18 of the tube is coated with an electrochemically active layer, which can be used as power boost during take-off conditions of the aircraft when more power is needed. This could be an add on functionality. Additional terminals, like the at least one outer electric terminal 140, for the outer cathode of the secondary power coating layer 138 would have to be implemented to either utilize the power during take-off conditions as well as applying a small short-cut current at cruise conditions.
As an advantage, a fuel cell with an auxiliary electric power circuit can be provided.
In an example, the at least one outer electric terminal 140 is further configured for short-circuiting at the secondary power coating layer 138 to form at least one short circuit unit. The at least one short circuit unit is configured for a depletion of an auxiliary source of oxidant of a surrounding 20.
In an example, the at least one outer electric terminal 140 is further configured to connect to the anode layer of the secondary power coating layer 138 to form at least one short circuit unit in order to close an electric circuit between the anode layer and the cathode layer of the second tubular membrane wall. The at least one short circuit unit is configured at the outer surface 18 facing a surrounding 20 for depletion of oxidant from the surroundings 20.
In an example, oxygen molecules are reduced at the outer surface 18 to oxide ions that are absorbed by the secondary power coating layer 138.
In an example, the outer surface 18 of the tube is coated with an electrochemically active layer, which could be used to create an inert-gas atmosphere around the tubular cells during cruise conditions of an aircraft. A small short-cut current is applied between the negative potential of the anode, i.e., anode layer, at the metal support and the outer cathode. The required electrical short-cut connection between these two electrodes can be implemented within the outer anode/electrolyte/cathode layer. The closed outer gas compartment of the cell is thus gradually depleted from oxygen to create an inert-gas atmosphere.
As an advantage, a more secure fuel cell is yielded.
The housing can also be referred to as chamber, envelope, case, box or compartment.
In an example, due to the rigid design of the carrier structure 110 of the fuel cell setup 210, a lighter housing can be chosen.
In an example, the housing 202 comprises a thermal insulation.
In an example, a reduced pressure of the fluid provides for thermal insulation of the fuel cell setup 210 in the housing 202.
In an example, the surrounding compartment, i.e., the housing 202 of the fuel cell arrangement 200 faces a minimum of pressure difference between the inside of the housing 202 and the environmental conditions. The mechanical housing, i.e., housing 202 can be constructed with thin walls and consequently light-weight designs. The low pressure level within the surrounding compartment, i.e., housing 202, furthermore reduces heat losses because the thermal insulation applied to the inner surface of the compartment works more efficiently as the gas density and heat conductivity within the insulation material is reduced compared to pressurized conditions.
In an example, the housing 202 comprises supply ports for the first and second supply flow 24, 26 to the at least one fuel cell setup 210.
In an example of
In an example, the fuel cell setup 210 comprises the secondary power coating layer 38 or the short circuit unit at the outer surface 18. The fuel cell setup 210 is encased in the housing 202 that comprises the fluid. Due to levelling of the pressure of the fluid with the surrounding atmosphere 216 of the housing 202, the fluid contains oxidant, like, i.e., oxygen. When the fuel cell setup 210 is operated in the housing 202 it will gradually convert the oxidant, i.e., oxidant in the fluid of the housing 202, such that all oxidant is removed from the fluid in the housing 202. This way an inert atmosphere is created in the housing 202. The levelling of the pressure might occur in a situation where the fuel cell arrangement 200 is aboard an aircraft, and the aircraft is on ground after being on a flight mission. At flight mission, pressure in the housing 202 is at around 0.3 bar. At an aircraft on ground condition, pressure in the housing 202 is at around 1 bar. Moreover, this provides, in the case of the secondary power coating at the outer surface 18, auxiliary electric power that can be used in a case where additional power is required, e.g., when the aircraft takes off.
In an example, at aircraft cruise conditions, the surrounding atmosphere 216 of the fuel cell set ups can be depleted from oxygen to create an inter-gas atmosphere which provides additional safety in case of fuel, like hydrogen, leakages into the stack compartment.
In an example, the secondary power coating layer 138 has an electrochemically active outer cathode, where the fuel is fed to the porous metal foam, i.e., the duct wall 14, the reactant air to the tubular ducting volume 16, and the housing 202 with air at environmental conditions. The housing 202 here is designed as a closed housing 202 with a small connection to the environment atmosphere to enable a levelling of the outer and inner pressure of the mechanical housing 202. The outer active cathode is suited with some electrical short circuit connections, between the outer cathode and the metal foam which has the anodic potential. The short circuit connection is designed in the way that only a small, short circuit current will gradually deplete the air inside the housing 202 from oxygen to create an inert gas atmosphere around the fuel cell setup 210. Additional safety in case of fuel, hydrogen, leakages into the stack compartment, i.e., housing 202, is realized by the inter-gas atmosphere. Consequently, a small portion of hydrogen is consumed during the start-up of the cells. Once the oxygen is fully depleted from the stack compartment, the short circuit current and hydrogen consumption via the outer active cell area, i.e., at the secondary power coating layer 138, would be interrupted naturally.
In an example, an electrochemically active outer cathode, i.e., the secondary power coating layer 138 is at the fuel cell setup 210. The fuel is fed to the porous metal foam, i.e., the duct wall 14, the first reactant air to the tubular ducting volume 16 and the stack compartment, i.e., housing 202 or compartment, with either the second reactant air at environmental conditions, the duct wall 14 and the tubular ducting volume 16 are not shown in detail in
As an advantage, a self-protecting fuel cell arrangement is provided.
As a further advantage, no heavy protection equipment is required at the fuel cell which saves weight.
As an advantage, not inert gas needs to be provided as the fluid beforehand.
As an advantage, at take-off operation of the aircraft the atmospheric pressure is around 1 bar and thus provides a sufficient oxygen partial pressure for fuel cell operation of the outer active area of the cell.
As an advantage, auxiliary electric power is provided by the fuel cell.
In an example, the energy supply system 300 is configured to consider the auxiliary electric power provided by the secondary power coating.
In an example, the aircraft 400 is on ground and the fuel cell arrangement 302 comprises surrounding atmosphere 216 in the housing 202. For taking off the aircraft 400 requires additional electrical power. This power is supplied by the fuel cell arrangement 302 converting the oxidant of the surrounding atmosphere 216 in its housing 202. On the flight mission all oxidant is used up in the housing 202 and the fuel cell setup 210 in the fuel cell arrangement 302 is immersed in an inert fluid stemming from the conversion of the oxidant of the surrounding atmosphere 216.
It has to be noted that embodiments of the invention are described with reference to different subject matters. In particular, some embodiments are described with reference to method type claims whereas other embodiments are described with reference to the device type claims. However, a person skilled in the art will gather from the above and the following description that, unless otherwise notified, in addition to any combination of features belonging to one type of subject matter also any combination between features relating to different subject matters is considered to be disclosed with this application. However, all features can be combined providing synergetic effects that are more than the simple summation of the features.
While the invention has been illustrated and described in detail in the drawings and foregoing description, such illustration and description are to be considered illustrative or exemplary and not restrictive. The invention is not limited to the disclosed embodiments. Other variations to the disclosed embodiments can be understood and effected by those skilled in the art in practicing a claimed invention, from a study of the drawings, the disclosure, and the dependent claims.
In the claims, the word “comprising” does not exclude other elements or steps, and the indefinite article “a” or “an” does not exclude a plurality. A single processor or other unit may fulfil the functions of several items re-cited in the claims. The mere fact that certain measures are re-cited in mutually different dependent claims does not indicate that a combination of these measures cannot be used to advantage. Any reference signs in the claims should not be construed as limiting the scope.
While at least one exemplary embodiment of the present invention(s) is disclosed herein, it should be understood that modifications, substitutions and alternatives may be apparent to one of ordinary skill in the art and can be made without departing from the scope of this disclosure. This disclosure is intended to cover any adaptations or variations of the exemplary embodiment(s). In addition, in this disclosure, the terms “comprise” or “comprising” do not exclude other elements or steps, the terms “a” or “one” do not exclude a plural number, and the term “or” means either or both. Furthermore, characteristics or steps which have been described may also be used in combination with other characteristics or steps and in any order unless the disclosure or context suggests otherwise. This disclosure hereby incorporates by reference the complete disclosure of any patent or application from which it claims benefit or priority.
| Number | Date | Country | Kind |
|---|---|---|---|
| 23197056.7 | Sep 2023 | EP | regional |
