Heat transfer device for an aircraft, fuel conditioning system and aircraft

Abstract

The present invention provides a heat transfer device for an aircraft, a fuel conditioning system and an aircraft. The present invention relates to a heat transfer device for an aircraft, in particular a heat transfer device for providing heat to fuel of a fuel conduit. The present invention further relates to a conditioning system comprising a heat transfer device thereof, an aircraft comprising a heat transfer device of a fuel conditioning system thereof and a method for conditioning fuel of an aircraft.

Description

Technical Field

[0001] This invention relates to heat transfer devices for aircraft, and particularly to heat transfer devices for supplying heat to fuel in fuel conduits. The invention also relates to a regulating system including such a heat transfer device, an aircraft including such a heat transfer device with a fuel regulating system, and a method for regulating the fuel of an aircraft. Background Technology

[0002] The ongoing global push for decarbonization is a significant driver of development in the aircraft industry. As the industry seeks to reduce its carbon footprint, hydrogen has emerged as a particularly promising alternative fuel. Unlike conventional fossil fuels, hydrogen produces almost only water vapor when burned, resulting in a very low nitrogen oxide fraction, making it an attractive option for minimizing gaseous emissions. This shift towards hydrogen as a primary fuel source introduces new technological challenges, particularly in the design and operation of aircraft systems such as auxiliary power units (APUs).

[0003] In aircraft applications, hydrogen is typically stored in its cryogenic liquid form (LH2). This form is preferred due to hydrogen's high energy density and ability to be stored at extremely low temperatures, which is essential for maintaining its liquid state. However, before hydrogen can be used in the combustion process within an APU, it must undergo a phase transition from its liquid (LH2) to its gaseous (GH2) state at ambient temperature. This conditioning process is not only critical but also technically demanding, given the need to manage extreme temperature variations while ensuring efficient and safe heat transfer.

[0004] The conversion of hydrogen from the liquid phase to the gas phase and its temperature regulation involve complex thermal management systems operating under different conditions, both during steady-state operation and during the initial startup phase of the APU. These systems are designed to include multiple components, such as heat exchangers, evaporators, valves, and recirculation loops, all working together to ensure that hydrogen is properly and safely regulated and delivered at the appropriate temperature and pressure for combustion.

[0005] During steady-state operation, this process allows for the use of a consistent external heat source within the aircraft to facilitate hydrogen conditioning. For example, a gas turbine or engine such as an APU can serve as the primary heat source, with the exhaust system of the gas turbine or engine releasing high-energy combustion gases. In this case, the hot exhaust gases exchange heat with a secondary fluid, which then transfers that heat to the liquid hydrogen, enabling the fuel to transition to its gaseous state.

[0006] Several existing technologies and patent applications have addressed specific challenges associated with regulating liquid hydrogen to gaseous hydrogen, employing different methods to ensure efficient heat transfer and effective hydrogen regulation for automotive applications, highlighting the versatility of this technology across various transportation sectors. Other technologies are specifically designed for aircraft applications, achieving efficient heat exchange even under extreme conditions while maintaining system operational integrity.

[0007] Beyond these specific technologies, other heat exchanger designs are commonly employed in cryogenic applications, each offering distinct advantages. Shell-and-tube heat exchangers are widely used for gas-to-liquid and gas-to-gas heat transfer, particularly in high-temperature and high-pressure environments. These are especially effective when scaling is a problem or when other types of heat exchangers are unsuitable due to operating conditions. Plate heat exchangers, such as plate-frame, microchannel, and extended surface / plate-fin exchangers, also play a crucial role in cryogenic applications. For example, plate-frame exchangers are valued for their high heat transfer coefficient and compact design, making them suitable for space-constrained environments. Microchannel or printed circuit heat exchangers (PCHEs) comprise stacked plates with photochemically processed grooves to form flow paths, providing safe operation at pressures up to 600 bar.

[0008] However, their operating temperature range (73 K to 1073 K) may limit their application in hydrogen vaporization processes. Extended surface or plate-fin heat exchangers increase heat transfer surface density by adding fins, thereby improving heat exchange efficiency. This technology is exemplified by the brazed aluminum plate-fin heat exchanger (BAHX) used in cryogenic applications, which is known for its high thermal conductivity and strength at low temperatures.

[0009] One of the most challenging operating scenarios for hydrogen conditioning systems occurs in emergency situations where the APU must start up rapidly to provide critical electrical and / or aerodynamic power to the aircraft. In this scenario, the hydrogen conditioning system, which is typically at cryogenic temperatures when the APU is inactive, must rapidly heat the hydrogen to ensure a quick APU start-up.

[0010] Therefore, there is a need in the art for an electrically powered device or system capable of evaporating liquid hydrogen and heating it to gaseous hydrogen quickly and efficiently enough to enable its implementation in an APU during emergency situations. Summary of the Invention

[0011] This invention provides heat transfer devices, fuel regulation systems, aircraft, and methods for regulating the fuel of an aircraft according to various main aspects of the invention. Specific embodiments of the invention are disclosed in the appended aspects.

[0012] In a first aspect, the present invention provides a heat transfer device for an aircraft, the heat transfer device having a first inlet and a first outlet, the heat transfer device comprising:

[0013] - A fuel conduit having a first end and a second end, the first end being fluidly connected to a first inlet of a heat transfer device, and the second end being fluidly connected to a first outlet of a heat transfer device;

[0014] - A temperature sensor, located at the second end of the fluid conduit and configured to monitor the temperature of the fuel within the fuel conduit; and

[0015] - Heat exchanger, used to provide heat to fuel in fuel conduits.

[0016] in,

[0017] - The heat exchanger is integrated with the following:

[0018] ○ A heat source, including a working fluid, which is fluidly connected to the heat exchanger and configured to supply heat to the heat exchanger; and

[0019] ○ A heating device connected to a power source, which is configured to provide power to the heating device;

[0020] in,

[0021] The heat exchanger also includes a heating device connected to a power source, which is configured to provide power to the heating device;

[0022] The heat exchanger is configured to be used for:

[0023] In the first operating mode, heat is supplied from the heat source to the fuel in the fuel conduit.

[0024] In the second operating mode, heat is supplied from the heating device to the fuel in the fuel conduit, and

[0025] In the third operating mode, heat is supplied to the fuel in the fuel conduit from the heat source and heating device;

[0026] and

[0027] The temperature sensor is also connected to a power source and is configured to activate the power source by means of a control and processing device if the temperature of the fuel in the fuel conduit is lower than a predetermined target temperature.

[0028] This invention provides a heat transfer device for an aircraft that facilitates heating fuel in a fuel conduit to a predetermined target temperature, which is the optimal temperature for further injection into the engine and combustion. In some embodiments, the heated fuel is consumed by the engine of an auxiliary power unit.

[0029] Heat transfer devices advantageously integrate the heat source and heating device into a heat exchanger, that is, into a single element.

[0030] Advantageously, the present invention allows for the supply of heat to fuel in a fuel conduit under three possible operating conditions. In particular, in emergency situations, the device of the present invention is a faster and more efficient solution for supplying a greater amount of heat to fuel in a fuel conduit than solutions known in the prior art, resulting in heating the fuel to its predetermined target temperature in a shorter time period.

[0031] Emergency situations occur during flight operations, such as startup or under overload conditions, where the APU must start up quickly to provide critical electrical and / or aerodynamic power to the aircraft.

[0032] In a first aspect of the invention, the heat transfer device of the present invention includes a fuel conduit, a heat exchanger integrating a heat source and a heating device for heating the fuel in the fuel conduit, and a temperature sensor.

[0033] The fuel conduit includes a first end and a second end. The first end is fluidly connected to a first inlet of a heat transfer device, and the second end is fluidly connected to a first outlet of the heat transfer device, so that fuel is conveyed from the first end to the second end of the fuel conduit. Furthermore, the device of the present invention ensures that the temperature of the fuel in the fuel conduit at the first outlet of the heat transfer device is higher than the temperature of the fuel in the fuel conduit at the first inlet of the heat transfer device. In embodiments, the heat transfer device also ensures that the fuel in the fuel conduit changes phase as it is conveyed from its first inlet to its first outlet. In a particular embodiment, the fuel in the fuel conduit changes from a liquid phase at the first inlet of the heat transfer device to a gaseous phase at the first outlet of the heat transfer device.

[0034] A temperature sensor is located at the second end of the fluid conduit and is configured to monitor the temperature of the fuel within the fuel conduit, such that the sensor provides an accurate measurement of the fuel temperature in the fuel conduit downstream of the heat exchanger. The temperature sensor is preferably located downstream of the heat exchanger within the heat transfer device. In an alternative embodiment, the temperature sensor is located downstream of the heat exchanger outside the heat transfer device.

[0035] A heat source is connected to a heat exchanger in fluid communication, and the heat source includes a working fluid that has been preheated by the heat source. The heated working fluid is conveyed toward the heat exchanger via a closed loop between the heat source and the heat exchanger. Then, as the heated working fluid is conveyed from the heat source to the heat exchanger, the heat exchanger is able to provide heat from the heated working fluid to fuel in the fuel conduit.

[0036] In this implementation, the working fluid is nitrogen (N2), helium (He) or a mixture of nitrogen (N2) and helium (He), carbon dioxide, hydrogen (H) and / or ethylene glycol water (EGW).

[0037] Furthermore, the power source connected to the heating device is configured to provide power to the heating device. In a particular aspect of the invention, the heat exchanger advantageously integrates the heat source and the heating device into a single element to enhance control over the heat of the fuel transferred to the fuel conduit.

[0038] In the first operating mode, the heat exchanger is able to supply heat to the fuel in the fuel conduit solely from the heat source via a previously heated working fluid.

[0039] In the second operating mode, the heat exchanger is able to supply heat to the fuel in the fuel conduit solely from the heating device connected to the power source.

[0040] In the third operating mode, the heat exchanger is able to supply heat to the fuel in the fuel conduit from both the heat source and the heating device.

[0041] In the implementation, the first operating mode corresponds to steady-state operation, in which the heat exchanger requires only constant and effective heat provided solely by the heat source.

[0042] In this implementation, the second operating mode corresponds to an operating state where the heat exchanger requires only a certain amount of heat, provided solely by the heating device. This operating mode corresponds to two possible scenarios: one where startup occurs only with heat transfer from the heating device, i.e., only the electric heating device, and the other where the heat source is replaced in case of heat source failure. In this implementation, the heat from the working fluid of the heat source may be zero at certain stages due to failures during steady-state periods or design limitations during the startup phase.

[0043] In this implementation, the third operating mode corresponds to an emergency operation that requires a larger volume of heat from the heat exchanger, a combination of heat from the heat source and additional heat from the heating device. This emergency operating mode operates at high efficiency to heat the fuel in the fuel conduit within a shorter timeframe.

[0044] The temperature sensor of the heat transfer device of the present invention is connected to a power source and is also configured to actuate the power source by means of a control and processing device when the temperature of the fuel in the fuel conduit is lower than a predetermined target temperature. In an embodiment, when the predetermined target temperature is reached at the first outlet, the fuel in the fuel conduit has changed phase relative to its state when it enters the first inlet of the heat transfer device.

[0045] The control and processing unit is connected to both the temperature sensor and the power supply to activate the power supply as quickly as possible to provide power to the heating device in emergency situations, such as when the target temperature has not been reached, or in cases of overload or extreme conditions. When the control and processing unit activates the power supply, enabling the heating device to deliver a larger amount of additional heat to the heat exchanger, the fuel in the fuel conduit reaches the predetermined target temperature within a shorter time period.

[0046] Advantageously, the heat transfer device also helps reduce the weight and corresponding volume within the aircraft, two key factors in this field. This effect is primarily achieved by integrating both the heat source and the heating device into a single component within the heat exchanger.

[0047] In this embodiment, the heating device is an induction heating device.

[0048] Advantageously, induction heating devices facilitate the direct generation of heat relative to the fuel conduit, rather than relying on indirect radiation, convection, or thermal conduction. Induction heating devices allow for more efficient heat transfer in a faster manner, resulting in temperature increases over short periods. Specifically, electricity is transferred from the power source to the heat exchanger body via induced current (eddy current or Foucault current) and from the heat exchanger body via conduction to the interface or exchange surface of the fuel conduit and convection to the fuel.

[0049] Also advantageously, the change in the thermal setting of the induction heating device is instantaneous, and this feature helps the entire heat transfer device to react in emergency situations.

[0050] In one implementation, the induction heating device is an induction coil wound around a heat exchanger.

[0051] In this embodiment, the induction heating device is an induction box inserted into the heat exchanger.

[0052] In an embodiment of a heat transfer device

[0053] The induction heating device is an induction coil wound around a heat exchanger, and

[0054] It also includes multiple ferromagnetic devices inserted into corresponding slots in the heat exchanger.

[0055] This embodiment is intended for situations where the material of the heat exchanger is not ferromagnetically effective or incompatible. This is the case when the fuel is hydrogen, because the compatible steel of the heat exchanger is not ferromagnetic. Advantageously, a ferromagnetic device allows induced current to be transferred to the heat exchanger body, whereas if the heat exchanger body is ferromagnetic, a ferromagnetic device is not required. Therefore, for example, it is also necessary if the heat exchanger body is aluminum.

[0056] In those embodiments where the heating device is an induction heating device, ferromagnetic devices are distributed within the heat exchanger to increase the efficiency of the induction phenomenon and to make the heat uniform and / or conduct the heat, thereby preventing stress, deformation or thermal fatigue phenomena that would jeopardize the structural and safety integration of the heat exchanger.

[0057] In implementations, the working fluid conduit and / or heat exchanger comprises ferrous metals, such as cast iron or stainless steel.

[0058] In some implementations, the working fluid conduit and / or heat exchanger are made of ferrous metals such as cast iron or stainless steel.

[0059] In one embodiment, the induction heating device consists of multiple induction boxes inserted into corresponding slots within a heat exchanger.

[0060] Advantageously, this implementation offers a high degree of modularity for component replacement and inspection, maintainability, and repairability. If any type of failure occurs, replacing the damaged sensor box is sufficient.

[0061] In another embodiment, each of the plurality of sensor boxes includes:

[0062] A ferromagnetic housing, the ferromagnetic housing having an induction coil housed inside the ferromagnetic housing, and

[0063] The cover is used to operate the sensor box and also serves as a stop for placing the sensor box in the corresponding slot.

[0064] In addition to providing high modularity for component replacement and inspection, maintainability and repairability, this implementation also provides easy handling of the sensor box when inserting or removing it from the slot.

[0065] Preferably, there is a separation distance between the induction coil itself and the ferromagnetic outer shell, so that the induction coil does not come into contact with the ferromagnetic outer shell.

[0066] In addition, the cover includes a connector that can supply power to the induction coil.

[0067] In this embodiment, the heating device is a resistance heating device.

[0068] Advantageously, resistance heating devices contribute to a fast response and compactness for the entire heat transfer system. Furthermore, the variety of sizes available for resistance heating devices facilitates their integration within heat exchangers.

[0069] In a particular implementation, the resistance heating device consists of multiple resistance boxes inserted into corresponding slots within a heat exchanger.

[0070] Advantageously, this implementation offers a high degree of modularity for component replacement and inspection, maintainability, and repairability. If any type of failure occurs, replacing the damaged resistor box is sufficient.

[0071] In another embodiment, each of the plurality of resistor cells includes:

[0072] Resistance, and

[0073] The cover is used to operate the resistor box and also serves as a stop for placing the resistor box in the corresponding slot.

[0074] In addition to providing high modularity for component replacement and inspection, maintainability and repairability, this implementation also provides easy handling of the resistor box when inserting or removing it from the slot.

[0075] In one embodiment, the heat exchanger also includes an isolation device configured to confine heat within the heat exchanger.

[0076] Advantageously, the isolation device, by limiting and retaining the heat within the heat exchanger, helps to improve the heating phenomenon provided by the heating device, more specifically when the heating device is an induction heating device.

[0077] In this implementation, the insulating device is a conventional thermal insulator that allows the heat provided by the heating device to be confined and concentrated within the heat exchanger, and prevents the formation of high-temperature spots on the outer surface of the heat exchanger. Advantageously, including a thermal insulator helps reduce the risk of fire, because in the event of a fuel leak, and more specifically when the fuel is hydrogen, the formation of hot spots can be an ignition source.

[0078] In embodiments where the heating device is an induction heating device, the isolation device is a magnetic flux control device, which helps to increase the effectiveness of induction and thus reduce the size required for the induction heating device.

[0079] In embodiments where the heating device is an induction heating device and the induction heating device is an induction coil wound around a heat exchanger, an isolation device is located on the outer side of the induction coil in order to concentrate the magnetic field into the heat exchanger.

[0080] In embodiments where the heating device is an induction heating device and the induction heating device is an induction box inserted into the heat exchanger, the isolation device is located on the outer side of the heat exchanger.

[0081] In this implementation, the fuel flow in the fuel conduit and the working fluid flow in the heat source are countercurrent.

[0082] The fuel flow and working fluid flow in the fuel conduit are countercurrent, such that most of the heat is supplied by the working fluid near the outlet of the heat exchanger, where the fuel in the fuel conduit requires the most heat to reach a predetermined target temperature. As the working fluid temperature decreases, the fuel temperature gradually increases because the working fluid continuously transfers heat to the fuel in the fuel conduit, thus promoting a phase change and performing this phase change in a less abrupt manner. The working fluid remains in contact with the fuel conduit until it reaches the inlet of the heat exchanger, where the fuel temperature in the fuel conduit is lowest; furthermore, the temperature of the working fluid at the point of contact with the fuel at the heat exchanger inlet is lower than its temperature at the point of contact with the fuel at the heat exchanger outlet.

[0083] Advantageously, arranging the fuel flow and working fluid flow in the fuel conduit in countercurrent provides optimized heat transfer between the working fluid and the fuel in the fuel conduit.

[0084] In an embodiment, the heat transfer device of the first aspect of the invention further includes a second inlet and a second outlet, wherein the second inlet is configured to introduce an inert gas, and the second outlet is configured to conduct the inert gas to the outside of the heat transfer device and to conduct any possible leaks, such as fuel, along with the inert gas.

[0085] Advantageously, introducing an inert gas into the heat transfer device facilitates the introduction of a flow that ventilates the internal volume of the heat transfer device, thereby removing any remaining fuel trapped within the device due to leakage. Furthermore, this helps maintain the temperature within the heat transfer device at specific conditions below the temperature of the fuel at the outlet of the heat transfer device. Therefore, hot spots that could act as ignition sources within the heat transfer device are avoided, and the integrity of the components within the heat transfer device is ensured.

[0086] Inert gas is introduced through the second inlet and output from the heat transfer device through the second outlet.

[0087] In the implementation method, the inert gas is enriched with nitrogen or helium.

[0088] In the context of this disclosure, nitrogen-rich or helium-rich is understood to be a gas or gas mixture with a majority content of >50% nitrogen or helium.

[0089] Advantageously, enriching the nitrogen or helium increases the effect of ventilating the internal volume of the heat transfer device, thereby removing any final fuel that may have remained inside the device due to leakage.

[0090] In an embodiment of the heat transfer device of the first aspect of the present invention:

[0091] - The heat exchanger and heating device are enclosed, or

[0092] - The heat exchanger, heating device, and heat source are enclosed, or

[0093] - The heat exchanger, heating device, and power supply are encapsulated, or

[0094] - The heat exchanger, heating device, heat source, and power supply are encapsulated, or

[0095] - The heat exchanger, heating device, heat source, control and processing device, and power supply are encapsulated.

[0096] In the context of this disclosure, encapsulation is understood as the placement of components of a heat transfer device within a protective housing. Such encapsulation protects the components from physical damage and environmental factors, and ensures the durability and reliability of the components throughout their lifespan and during operation.

[0097] Encapsulation is achieved by introducing inert gas through a second inlet and a second outlet. This encapsulation enhances safety, for example, regarding the eventual leakage of any components of a heat transfer device located within the encapsulated area.

[0098] Advantageously, encapsulating some components of the heat transfer device ensures that the rest of the aircraft components are protected from hazards such as fire.

[0099] In this implementation, the fluid in the fluid conduit is hydrogen (H2). That is, the fluid in the fluid conduit is pure hydrogen.

[0100] In one embodiment, the fluid in the fluid conduit includes hydrogen gas.

[0101] In this embodiment, the fluid in the fluid conduit is a mixture of hydrogen and fuels such as methane, propane, butane, etc. In the specific case where the fluid in the fluid conduit is a mixture, hydrogen is the main component of the mixture.

[0102] Specifically, under ambient pressure, approximately 101325 Pa, the heat transfer device requires a power supply of approximately 1 kW per 1 kg / h of fuel, particularly hydrogen, to evaporate the fuel due to heating provided by the heat exchanger of the heat transfer device. In the special case of hydrogen, the fuel temperature rises to approximately 15 ºC of ambient temperature.

[0103] In an embodiment, the heat transfer device also includes a testing device configured to monitor and inspect the functional status of each of its components.

[0104] In a second aspect of the invention, the present invention provides a fuel conditioning system that includes a heat transfer device according to any embodiment of the first aspect of the invention.

[0105] In a second aspect of the invention, the heat source is connected in fluid communication to a recovery loop configured to provide external heat to the working fluid of the heat source.

[0106] In this implementation, the recovery loop provides external heat recovered from the aircraft or exhaust gases.

[0107] In a third aspect of the invention, the present invention provides an aircraft comprising a heat transfer device according to any embodiment of the first aspect of the invention or a fuel regulation system according to any embodiment of the second aspect of the invention.

[0108] In a fourth aspect of the invention, the present invention provides a method for regulating the fuel of an aircraft, the method comprising the following steps:

[0109] a) Provide a heat transfer device according to any embodiment of the first aspect of the invention or a conditioning system according to any embodiment of the second aspect of the invention.

[0110] b) Providing heat from a heat source or heating device to the heat exchanger.

[0111] c) Providing heat to the fuel from the heat exchanger to the fuel conduit.

[0112] d) Monitor the temperature of the fuel at the second end of the fluid conduit within the fuel conduit using a temperature sensor, and

[0113] e) When the temperature of the fuel in the fuel conduit is lower than the predetermined target temperature, the power source, the heat source, or both the power source and the heat source are actuated by means of a control and processing device.

[0114] In this implementation, when the temperature of the fuel is monitored and is above a predetermined target temperature, the heat transfer device can operate the heat exchanger using only one heat source, that is, without providing heat from another heat source.

[0115] In this implementation, steps d) and e) operate as a control loop that is repeated multiple times as needed until the temperature of the fuel in the fuel conduit is at least equal to a predetermined temperature. Advantageously, the control loop helps to improve the accuracy of the fuel temperature and ensures that optimal fuel conditions are achieved.

[0116] In a fourth aspect of the invention, the control device is configured to actuate the power supply to provide heat to the fuel in the fuel conduit within a range of 30 milliseconds to 70 milliseconds, preferably within about 50 milliseconds.

[0117] Advantageously, the control device ensures that additional heat is rapidly supplied to the heat exchanger in emergency situations due to its short response time, and thus to the fuel conduit. Attached Figure Description

[0118] Referring to the accompanying drawings, and in view of the detailed description of the invention which makes it readily apparent from the preferred embodiments thereof, these and other features and advantages of the invention will be clearly understood. The preferred embodiments are given by way of example only and are not limited thereto.

[0119] Figures 1 to 5 These figures illustrate different embodiments of the heat transfer device according to the present invention.

[0120] Figures 6 to 8 These figures illustrate a heat exchanger with an induction heating device according to an embodiment of the heat transfer device of the present invention.

[0121] Figures 9A to 9B These figures show, in perspective, details of a heat exchanger and some ferromagnetic devices according to the same embodiment of the heat transfer device.

[0122] Figure 10 The figure shows a three-dimensional cross-sectional view of a heat exchanger, which also shows in cross-section the induction cylinder with a ferromagnetic shell and the induction coil inside the ferromagnetic shell.

[0123] Figure 11 The diagram shows the relationship with Figure 10 The same details as the sensor cylinder.

[0124] Figure 12 This figure shows a perspective view of an embodiment having a sensing cylinder before it is inserted into the corresponding slot.

[0125] Figures 13A to 13B: This figure shows details of the induction cylinder with a ventilation device.

[0126] Figure 14 This figure shows a bottom view of a heat exchanger with a bottom cover.

[0127] Figure 15 The figure shows a three-dimensional cross-sectional view of an embodiment of the heat exchanger, which shows the resistor box and resistors.

[0128] Figure 16 This figure shows a perspective view of an embodiment with a resistor box before it is inserted into the corresponding slot.

[0129] Figure 17 This figure shows a bottom view of a heat exchanger with the same embodiment having a bottom cover.

[0130] Figure 18 This figure shows a horizontal cross-sectional view of an embodiment of a heat exchanger with multiple resistors.

[0131] Figure 19 The diagram shows Figure 18 A three-dimensional cross-sectional view of a heat exchanger, showing details of the multiple resistors inserted in the heat exchanger.

[0132] Figure 20 The diagram depicts Figure 18 The same three-dimensional cross-sectional view of the heat exchanger without resistance is shown, and multiple housings of the heat exchanger are also shown.

[0133] Figure 21 This figure shows a detailed view of a region in the bottom side portion of the bottom cover of the same embodiment.

[0134] Figure 22 The figure shows an aircraft including a heat transfer device according to an embodiment of the present invention. Detailed Implementation

[0135] Figures 1 to 5 An embodiment of the heat transfer device 1 for an aircraft 100 according to the present invention is described.

[0136] In these implementations, from Figures 1 to 5 The heat transfer device 1 has a first inlet 2 and a first outlet 3. The heat transfer device 1 also includes a fuel conduit 4 having a first end 4.1 and a second end 4.2. The first end 4.1 is fluidly connected to the first inlet 2 of the heat transfer device 1, and the second end 4.2 is fluidly connected to the first outlet 3 of the heat transfer device 1.

[0137] Figures 1 to 5 The heat transfer device 1 also includes a temperature sensor 11 located at the second end 4.2 of the fluid conduit 4. The temperature sensor helps monitor the temperature of the fuel within the fuel conduit 4. In one embodiment, the temperature sensor is located within the heat transfer device 1, downstream of the heat exchanger. In an alternative embodiment, the temperature sensor is located outside the heat transfer device, downstream of the heat exchanger.

[0138] In addition, the heat transfer device 1 includes: a heat exchanger 8 integrated as a single element; a heat source 6 including a working fluid; and a heating device 9 connected to a power source 5.

[0139] Heat source 6 is connected to heat exchanger 8 in fluid communication and is configured to provide heat to heat exchanger 8. Figures 1 to 5The arrows depicted indicate the direction of each fluid flow. Furthermore, the power supply 5 connected to the heating device 9 is configured to provide power to the heating device 9.

[0140] Furthermore, the heat exchanger 8 is configured to operate in three different operating modes. In the first operating mode, the heat exchanger 8 supplies heat from the heat source 6 to the fuel in the fuel conduit 4. In the second operating mode, the heat exchanger 8 supplies heat from the heating device 9 to the fuel in the fuel conduit 4. Finally, in the third operating mode, the heat exchanger 8 supplies heat from both heat sources—the heat source 6 and the heating device 9—to the fuel in the fuel conduit 4.

[0141] In addition, the temperature sensor 11 is connected to the power supply 5 and is also configured to actuate the power supply 5 by means of the control and processing device 10 when the temperature of the fuel in the fuel conduit 4 is lower than a predetermined target temperature.

[0142] Because of the heat transfer device 1, the condition of the fuel in the fuel conduit 4 at the first outlet 4.2 is continuously monitored, and the heat transfer device 1 ensures that the fuel is output from the heat transfer device 1 at an optimal temperature that is at least equal to or higher than a predetermined target temperature.

[0143] In an implementation, the first operating mode is a steady-state operation in which the heat exchanger 8 requires only a constant and effective amount of heat provided by the heat source 8.

[0144] In the implementation, the second operating mode is an operating state in which the heat exchanger 8 only needs heat provided by the heat source 8.

[0145] In this implementation, the third operating mode is an emergency operation requiring a larger amount of heat from the heat exchanger 8, a combination of heat from the heat source 6 and additional heat from the heating device 9. This emergency operating mode operates at high efficiency to heat the fuel in the fuel conduit 4 within a shorter time period.

[0146] In the implementation, when the predetermined target temperature is reached at the first outlet 3, the fuel in the fuel conduit 4 has changed phase relative to its state when it enters the first inlet 2 of the heat transfer device 1.

[0147] The control and processing device 10 is connected to both the temperature sensor 11 and the power supply 5 to actuate the heating device 9 as quickly as possible in emergency situations, such as when the target temperature has not been reached, or in cases of overload or extreme conditions. Because the control and processing device 10 actuates the power supply 5, enabling the heating device 9 to deliver a greater amount of additional heat to the heat exchanger 8, the fuel in the fuel conduit 4 reaches the predetermined target temperature within a shorter timeframe.

[0148] Advantageously, the heat transfer device 1 also helps to reduce the weight and volume occupied within the aircraft 100. This effect is primarily provided by integrating both the heat source and the heating device 9 into a single element in the heat exchanger 8.

[0149] In this implementation, the fuel flow in the fuel conduit 4 and the working fluid flow in the heat source 6 are countercurrent.

[0150] In this embodiment, the fluid in the fluid conduit 4 is hydrogen (H2).

[0151] In some embodiments of the present invention, such as Figures 1 to 5 In the embodiment shown, the heat transfer device 1 includes a second inlet 12 and a second outlet 13, wherein the second inlet 12 is configured to introduce an inert gas, and the second outlet 13 is configured to conduct the inert gas to the outside of the heat transfer device 1, and conduct any possible leaks, such as fuel leaks, together with the inert gas.

[0152] In this implementation, the inert gas is nitrogen-rich.

[0153] In implementation methods, such as Figure 1 In the embodiment shown, the heat exchanger 8 and the heating device 9 are encapsulated.

[0154] In implementation methods, such as Figure 2 In the embodiment shown, the heat exchanger 8, the heating device 9, and the heat source 6 are encapsulated.

[0155] In an embodiment not shown in the figure, the heat exchanger 8, the heating device 9, and the power supply 5 are encapsulated.

[0156] In an embodiment not shown in the figure, the heat exchanger 8, heating device 9, heat source 6, and power supply 5 are encapsulated.

[0157] In implementation methods, such as Figure 3 In the embodiment shown, the heat exchanger 8, heating device 9, heat source 6, control and processing device 10, and power supply 5 are encapsulated.

[0158] exist Figure 4 or Figure 5 In a specific embodiment not shown, the heat exchanger 8 and the induction heating device 9.1 or the resistance heating device 9.2 are encapsulated.

[0159] exist Figure 4 or Figure 5 In a specific embodiment not shown, the heat exchanger 8, the induction heating device 9.1 or the resistance heating device 9.2, and the heat source 6 are encapsulated.

[0160] exist Figure 4 or Figure 5In a specific embodiment not shown, the heat exchanger 8, the induction heating device 9.1 or the resistance heating device 9.2, and the power supply 5 are encapsulated.

[0161] In this embodiment, the heat exchanger 8, the induction heating device 9.1 or the resistance heating device 9.2, the heat source 6, and the power supply 5 are encapsulated.

[0162] In implementation methods, such as Figure 3 In the embodiment shown, the heat exchanger 8, the induction heating device 9.1 or the resistance heating device 9.2, the heat source 6, the control and processing device 10, and the power supply 5 are encapsulated.

[0163] Induction heating device 9.1, which serves as the heating device 9 for heat exchanger 8.

[0164] In such Figure 4 In the embodiment shown, the heating device 9 is an induction heating device 9.1.

[0165] exist Figures 6 to 9B In the illustrated embodiment, the induction heating device comprises an induction coil 9.1 wound around a heat exchanger 8 and a plurality of ferromagnetic devices 9.2 inserted into the heat exchanger 8. Specifically, as... Figure 7 and Figure 8 As shown, the induction heating device consists of an induction coil 9.1 wound around the heat exchanger 8 and a plurality of ferromagnetic devices 9.2 inserted into corresponding slots 9.3 provided in the heat exchanger 8.

[0166] Figure 7 Depicting Figure 6 The horizontal cross-sectional view of the embodiment shows details of a plurality of ferromagnetic devices 9.2 inserted into corresponding slots 9.3 of the heat exchanger 8, and an induction coil 9.1 wound around the heat exchanger 8.

[0167] Figure 8 Depicting Figure 6 A three-dimensional cross-sectional view of the heat exchanger 8, showing details of a plurality of ferromagnetic devices 9.2 inserted into corresponding slots 9.3 of the heat exchanger 8, and an induction coil 9.1 wound around the heat exchanger 8.

[0168] Figure 9A A three-dimensional diagram is depicted, showing the moment when multiple ferromagnetic devices 9.2 are inserted into their corresponding slots 9.3 in the heat exchanger 8 and before the induction coil 9.1 is wound.

[0169] In this embodiment, the number of corresponding slots 9.3 in the ferromagnetic device 9.2 and the heat exchanger 8 is four. Figure 9A and Figure 9B In another embodiment shown, the ferromagnetic device 9.2 is a rectangular plate.

[0170] Figure 9BDepicting Figure 6 and Figure 9A The horizontal cross-sectional view of the embodiment shows the slot 9.3 of the heat exchanger 8.

[0171] Figures 6 to 9B The embodiment shown has the advantage that the induction coil 9.1 almost completely covers the body of the heat exchanger 8.

[0172] This embodiment is intended for use where the material of the heat exchanger 8 is not ferromagnetically effective or compatible, particularly when the fuel is hydrogen, because the compatible steel of the heat exchanger 8 is not ferromagnetic or has very poor inductive properties. Advantageously, the ferromagnetic device 9.2 allows induced current to be transferred to the body of the heat exchanger 8. More specifically, the induction coil 9.1 generates an induced current in the ferromagnetic device 9.2, which is in turn heated by its ohmic resistance, and this heat is transferred to the non-ferromagnetic material of the heat exchanger 8 via thermal conduction.

[0173] In another embodiment, the induction heating device 9.1 comprises a plurality of induction boxes 9.4, which are inserted into corresponding slots 9.5 within the heat exchanger 8, such as... Figures 10 to 12 As shown.

[0174] Each of the plurality of induction boxes 9.4 includes: a ferromagnetic housing 9.6 having an induction coil 9.7 housed within the ferromagnetic housing 9.6; and a cover 9.8 for operating the induction box 9.4 and serving as a stop for placing the induction box 9.4 into a corresponding slot 9.5. Preferably, there is a gap between the induction coil 9.7 itself and the ferromagnetic housing 9.6, such that the induction coil 9.7 does not contact the ferromagnetic housing 9.6.

[0175] Figure 10 A three-dimensional cross-sectional view of the heat exchanger 8 is depicted, which also shows the ferromagnetic housing 9.6 in cross-section, in which the induction coil 9.7 is visible inside the ferromagnetic housing 9.6.

[0176] Figure 11 It shows Figure 10 Same details as the 9.4 induction box.

[0177] Figure 12 A three-dimensional view is depicted, showing multiple induction boxes 9.2 at the moment they are inserted into the corresponding slots 9.5 of the heat exchanger 8.

[0178] In this embodiment, there are two sensing boxes 9.4, and each sensing box 9.4 has two ferromagnetic housings 9.6 and a cover 9.8 for the two ferromagnetic housings 9.6.

[0179] Furthermore, in a particular embodiment (not shown in the figures), the cover 9.8 includes a connector that can power the induction coil 9.7.

[0180] In other embodiments, all ferromagnetic housings 9.6 used in the heat exchanger 8 have only one cover 9.8.

[0181] The advantages of this implementation are its high degree of modularity, maintainability, and repairability for component replacement and inspection. In the event of any type of failure, replacing the damaged sensor box 9.4 is sufficient.

[0182] In another embodiment, a cover 9.8 is provided for each ferromagnetic housing 9.6 used in the heat exchanger 8. Advantageously, this embodiment provides greater modularity, maintainability, and repairability for component replacement and inspection. In the event of any type of failure in a particular induction housing 9.4, it is sufficient to replace the damaged induction housing.

[0183] In another embodiment, as shown in Figures 13A and 13B, each induction box 9.4 includes a ventilation device for maintaining the integrity of the induction coil 9.7 by generating air circulation between the induction coil 9.7 and the ferromagnetic housing 9.6. This can be achieved through natural convection or forced convection.

[0184] Preferably, each sensor box 9.4 includes at least one air inlet 9.9 on one side and at least one air outlet 9.10 on the opposite side. Alternatively, at least one air inlet 9.9 and at least one air outlet 9.10 are both on the same side of the sensor box 9.4.

[0185] In such Figure 14 In another embodiment shown, the heat exchanger 8 includes a bottom cover 14 for closing the side opposite to the side where the induction box 9.4 is inserted into the slot 9.5. This bottom cover 14 allows for no heat loss and avoids hot spots that could become ignition sources.

[0186] In embodiments compatible with any of the embodiments involving the induction heating device 9.1 as the heating device 9, the heat exchanger 8 further includes an isolation device (not shown) configured to confine heat within the heat exchanger 8.

[0187] Resistance heating device 9.1 serves as the heating device 9 for heat exchanger 8.

[0188] In such Figure 5 In the embodiment shown, the heating device 9 is a plurality of resistance heating devices 9.2.

[0189] In this embodiment, the resistance heating device 9.2 comprises multiple resistance boxes 9.11, which are inserted into corresponding slots 9.12 within the heat exchanger 8, such as... Figures 15 to 18 As shown.

[0190] Each of the multiple resistor boxes 9.11 includes a resistor 9.13 and a cover 9.14, the cover 9.14 being used to operate the resistor box 9.11 and serving as a stop for placing the resistor box 9.11 into a corresponding slot 9.12.

[0191] Furthermore, in a particular embodiment (not shown in the figures), cover 9.14 includes a connector that can supply power to resistor 9.13.

[0192] Figure 15 A three-dimensional cross-sectional view of the heat exchanger 8 is depicted, which also shows the resistor box 9.11 in cross-section, in which the resistor 9.13 is visible.

[0193] Figure 16 A three-dimensional view is depicted, showing multiple resistor boxes 9.11 at the moment they are inserted into the corresponding slots 9.12 of the heat exchanger 8.

[0194] In this embodiment, there are two resistor boxes 9.11, each resistor box 9.11 having two resistors 9.13 and a cover 9.14 for the two resistors 9.13.

[0195] In another embodiment, all resistors 9.13 used in heat exchanger 8 have only one cover 9.14.

[0196] The advantage of this implementation is its high degree of modularity, maintainability, and repairability for component replacement and inspection. In the event of any type of failure, replacing the damaged resistor box 9.11 is sufficient.

[0197] In another embodiment, each resistor 9.13 used in the heat exchanger 8 has a cover 9.8. Advantageously, this embodiment provides greater modularity for component replacement and inspection, maintainability, and repairability. In the event of any type of failure in a particular resistor box 9.11, it is sufficient to replace the damaged resistor box.

[0198] In such Figure 17 In another embodiment shown, the heat exchanger 8 includes a bottom cover 9.15 for closing the side opposite to the side where the resistor box 9.11 is inserted into the slot 9.12. This bottom cover 9.15 allows for no heat loss and avoids hot spots that could become ignition sources.

[0199] In embodiments compatible with any embodiment involving a resistance heating device 9.1 as a heating device 9, the heat exchanger 8 further includes an isolation device (not shown) configured to confine heat within the heat exchanger 8.

[0200] In such Figures 18 to 22 In the embodiment shown, the resistance heating device consists of a plurality of resistors 9.16, which are inserted into corresponding housings 9.18 disposed in the heat exchanger 8.

[0201] Figure 18 A horizontal cross-sectional view of the heat exchanger 8 is depicted, showing details of the multiple resistors 9.16 inserted into the corresponding housing 9.18 of the heat exchanger 8.

[0202] Figure 19 Depicting Figure 18 A three-dimensional cross-sectional view of the heat exchanger 8, showing details of the plurality of resistors 9.16 inserted in the corresponding housing 9.18 of the heat exchanger 8.

[0203] In one embodiment, the heat exchanger 8 includes 7 rows of resistors 9.16.

[0204] Figure 20 It depicts the situation without a 9.16 resistor. Figure 19 The same three-dimensional cross-sectional view of the heat exchanger 8 is shown, and it shows multiple housings 9.18 of the heat exchanger 8.

[0205] For ease of power supply, each resistor in resistors 9.16 includes one or more electrical connection pins 9.17, which mate with corresponding electrical connectors (not shown in the figure). Preferably, the electrical connectors are hermetically sealed. Therefore, by simply removing the electrical connectors, the electrical connection pins 9.17 of resistors 9.16 can be directly accessed for individual inspection or replacement.

[0206] In such Figure 21 In another embodiment shown, the heat exchanger 8 includes an opening for a bottom cover that is used to close the side opposite to the side where the resistor 9.16 is inserted into the slot 9.18.

[0207] The opening allows access to the end of resistor 9.16 opposite to the electrical connection pin 9.17, facilitating their removal and allowing them to be pressed out if stuck. Furthermore, the bottom cover 14 for the opening prevents heat loss and avoids hot spots that could become ignition sources.

[0208] Figure 22 An aircraft 100 is depicted, including any embodiment of the heat transfer device 1 of the present invention.

[0209] Methods for regulating the fuel of aircraft

[0210] The present invention also provides a method for regulating the fuel of an aircraft 100, the method comprising the following steps:

[0211] a) Provide a heat transfer device 1 according to any embodiment of the heat transfer device 1 or a regulating system according to any embodiment of the regulating system.

[0212] b) Heat is supplied from heat source 6 or heating device 9 to heat exchanger 1.

[0213] c) Heat is supplied from heat exchanger 6 to fuel conduit 4.

[0214] d) The temperature of the fuel at the second end 4.2 of the fluid conduit 4 within the fuel conduit 4 is monitored by means of temperature sensor 11, and

[0215] e) When the temperature of the fuel in the fuel conduit 4 is lower than the predetermined target temperature, the power source 5 is actuated by means of the control and processing device 10, or the heat source 6 is actuated, or both the power source 5 and the heat source 6 are actuated.

[0216] In an embodiment of the method of the present invention, the control and processing device 10 is configured to actuate the power supply 5 to provide heat to the fuel in the fuel conduit 4 within a range of 30 milliseconds to 70 milliseconds, preferably within about 50 milliseconds.

Claims

1. A heat transfer device (1) for an aircraft, the heat transfer device (1) having a first inlet (2) and a first outlet (3), the heat transfer device (1) comprising: Fuel conduit (4) having a first end (4.1) and a second end (4.2), the first end (4.1) being fluidly connected to the first inlet (2) of the heat transfer device (1), and the second end (4.2) being fluidly connected to the first outlet (3) of the heat transfer device (1). A temperature sensor (11) is located at the second end (4.2) of the fluid conduit (4) and is configured to monitor the temperature of the fuel in the fuel conduit (4); as well as Heat exchanger (8), the heat exchanger (8) being used to provide heat to the fuel in the fuel conduit (4), in, The heat exchanger (8) is integrated with the following: A heat source (6) comprising a working fluid, the heat source (6) being fluidly connected to the heat exchanger (8) and configured to provide heat to the heat exchanger (8); as well as A heating device (9) is connected to a power source (5) configured to provide power to the heating device (9); The heat exchanger (8) is configured to: In the first operating mode, heat is supplied from the heat source (6) to the fuel in the fuel conduit (4). In the second operating mode, heat is supplied from the heating device (9) to the fuel conduit (4) for the fuel, and In the third operating mode, heat is supplied from the heat source (6) and the heating device (9) to the fuel conduit (4); and The temperature sensor (11) is also connected to the power source (5) and is configured to actuate the power source (5) by means of the control and processing device (10) if the temperature of the fuel in the fuel conduit (4) is lower than a predetermined target temperature.

2. The heat transfer device (1) according to the preceding claim, wherein, The heating device (9) is an induction heating device (9.1).

3. The heat transfer device (1) according to claim 2, wherein, The induction heating device is an induction coil (9.1) wound around the heat exchanger (8), and The induction heating device also includes a plurality of ferromagnetic devices (9.2) inserted into corresponding slots (9.3) provided in the heat exchanger (8).

4. The heat transfer device (1) according to claim 2, wherein, The induction heating device (9.1) consists of multiple induction boxes (9.4) inserted into the corresponding slots (9.5) of the heat exchanger (8).

5. The heat transfer device (1) according to claim 4, wherein, Each of the plurality of sensor boxes (9.4) includes: A ferromagnetic housing (9.6), the ferromagnetic housing (9.6) having an induction coil (9.7) housed within the ferromagnetic housing (9.6), and A cover (9.8) is used to operate the sensor box (9.4) and serves as a stop for placing the sensor box (9.4) in the corresponding slot (9.5).

6. The heat transfer device (1) according to claim 1, wherein, The heating device (9) is a resistance heating device (9.2).

7. The heat transfer device (1) according to claim 6, wherein, The resistance heating device consists of multiple resistance boxes (9.11) inserted into the corresponding slots (9.12) inside the heat exchanger (8).

8. The heat transfer device (1) according to claim 7, wherein, Each of the plurality of resistor cells (9.11) includes: Resistor (9.13), and A cover (9.14) is used to operate the resistor box (9.11) and serves as a stop for placing the resistor box (9.11) in the corresponding slot (9.12).

9. The heat transfer device (1) according to any one of the preceding claims, wherein, The heat exchanger (8) also includes an isolation device configured to confine heat within the heat exchanger (8).

10. The heat transfer device (1) according to any one of the preceding claims further includes a second inlet (12) and a second outlet (13), wherein, The second inlet (12) is configured to introduce inert gas, and the second outlet (13) is configured to conduct the inert gas to the outside of the heat transfer device (1) and conduct any possible leaks, such as fuel, along with the inert gas.

11. The heat transfer device (1) according to claim 10, wherein, The inert gas is enriched with nitrogen or helium.

12. The heat transfer device (1) according to any one of the preceding claims, wherein, The heat exchanger (8) and the heating device (9) are encapsulated, or The heat exchanger (8), the heating device (9), and the heat source (6) are encapsulated, or The heat exchanger (8), the heating device (9), and the power supply (5) are encapsulated, or The heat exchanger (8), the heating device (9), the heat source (6), and the power source (5) are encapsulated, or The heat exchanger (8), the heating device (9), the heat source (6), the control and processing device (10), and the power supply (5) are encapsulated.

13. The heat transfer device (1) according to any one of the preceding claims, wherein, The fluid in the fluid conduit (4) is hydrogen.

14. A fuel conditioning system comprising a heat transfer device (1) according to any one of the preceding claims.

15. An aircraft (100) comprising a heat transfer device (1) according to any one of claims 1 to 10 or a fuel regulation system according to any one of claims 11 or 12.

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