Aircraft galley compartment, aircraft galley system and aircraft

Abstract

The invention relates to an aircraft galley compartment, an aircraft galley system and an aircraft. The aircraft galley compartment (3) comprises at least one port (13, 15) accessible from the interior of the compartment (3) and configured to be connected to a compartment temperature regulation unit (17). The aircraft galley system (1) comprises: an aircraft galley (25); an aircraft galley compartment (3); a compartment temperature regulation unit (17) for cooling the interior of the compartment (3) and connected to at least one port (13, 15) of the compartment (3); and a waste heat conduit (9) configured to distribute waste heat from the compartment temperature regulation unit (17) to at least one specific location of the aircraft galley (25) different from the compartment (3). The aircraft (27) comprises an aircraft galley compartment (3) or an aircraft galley system (1).

Description

Technical Field

[0001] The present invention relates to an aircraft galley compartment, an aircraft galley system including the compartment, and an aircraft including the aircraft galley compartment or the aircraft galley system. Background Art

[0002] Common aircraft galleys include an aircraft galley structure that includes system interfaces such as electrical interfaces, cooling interfaces, water interfaces, wastewater interfaces, and air ventilation interfaces. In addition, storage space is provided by means of a trolley integrated in the galley and aircraft galley compartments. Electric galley insert units are permanently installed in the respective aircraft galley compartments, and each aircraft galley compartment has a dedicated purpose, such as cooling meals or heating meals. Such electric galley insert units can be refrigerators, freezers, or ovens, which are all fully functional standalone units, i.e., they are fully operable units whether they are installed in the respective aircraft galley compartments or removed from the respective aircraft galley compartments. Each of these specific units has specific cooling / heating requirements such as selectable temperature, achievable temperature range, etc., insulation level requirements such as refrigerator-grade insulation, freezer-grade insulation, or oven-grade insulation, and space requirements.

[0003] These specific units are heavy, expensive, and once installed in the respective aircraft galley compartments, they are part of the galley whether needed or not. Summary of the Invention

[0004] The problem to be solved is to improve the known aircraft galley compartment, the aircraft galley system including the compartment, and the aircraft including the aircraft galley compartment or the aircraft galley system - particularly in terms of its efficient and cost-effective usefulness.

[0005] This problem is solved by the subject matter of the main aspects.

[0006] The problem to be solved by the present invention is particularly solved by the following technical teachings: (1)

[0008] An aircraft galley compartment, comprising: at least one port that is accessible from the interior of the compartment and configured to connect to at least one compartment temperature regulation unit. Thus, the compartment can be equipped with a compartment temperature regulation unit for cooling or heating in a simple and cost-effective manner. This allows each such compartment to be used for storing goods, such as meals, at ambient temperature or for changing the temperature of the compartment according to current needs, which can be cooling the goods or heating the goods. If needed, each such compartment can be turned into a refrigerator, freezer, or oven. The at least one port can be configured to power and control the at least one compartment temperature regulation unit. The size of the compartment is adjustable, allowing for flexible catering and optimizing the energy consumption of the aircraft galley and the aircraft interior. (2)

[0010] The aircraft galley compartment according to the teachings of part (1), wherein the at least one port provides a connection to at least one of a circuit, a communication system, and / or a temperature regulation loop in which a heat exchanger fluid circulates. The circuit enables the operation of a compartment temperature regulation unit, such as a thermoelectric device like a Peltier element or a fan that is part of the compartment temperature regulation unit. The power and polarity of the compartment temperature regulation unit can be controlled by the circuit. The communication system allows data such as the current operating state, temperature, etc. from the compartment temperature regulation unit to be transmitted to a control unit, for example, a control unit configured to control the temperature in the compartment and / or in a plurality of such compartments. The control unit can be integrated in the human-machine interface unit described below. The temperature regulation loop can provide a fluid that has been cooled or heated, and the compartment temperature regulation unit can further cool or heat the fluid to increase the desired cooling or heating effect. (3)

[0012] The aircraft galley compartment according to the teachings of one of the foregoing parts, further comprising: a closed state in which the compartment is not accessible from the outside; and an open state in which the compartment is accessible from the outside; wherein, in the closed state, the compartment provides at least one of refrigerator-class insulation, freezer-class insulation, and / or oven-class insulation. The insulation can avoid unnecessary energy losses and improve safety, for example, avoid unnecessary energy losses and improve safety when the compartment is used as an oven. (4)

[0014] The aircraft galley compartment according to the teachings of one of the foregoing parts, wherein the compartment is configured to be temporarily divided into sub-compartments by removable partition walls. This solution can reduce energy consumption when cooling or heating the goods in the compartment because the size of the compartment to be cooled or heated can be adjusted according to the quantity and volume of the goods to be cooled or heated. (5)

[0016] An aircraft galley compartment according to the teachings of one of the foregoing sections further includes: at least one compartment temperature regulation unit for cooling the interior of the compartment; and at least one compartment temperature regulation unit for heating the interior of the compartment. A compartment having such a configuration can be used for both cooling and heating. This allows meals to be cooled in the same compartment as in a refrigerator or freezer and heated as in an oven, without having to move those foods from one compartment to another. (6)

[0018] An aircraft galley compartment according to the teachings of parts (4) and (5), wherein at least one compartment temperature regulation unit for cooling is arranged to cool a first sub-compartment, and wherein at least one compartment temperature regulation unit for heating is arranged to heat a second sub-compartment. This configuration allows a multi-functional compartment that can be cooled and heated to be divided into more energy-efficient but dedicated sub-compartments that can only be cooled or heated. (7)

[0020] An aircraft galley compartment according to the teachings of one of the foregoing sections further includes: at least one compartment temperature regulation unit, which is one or a combination of a skin heat exchanger, a heat pipe assembly, or a thermoelectric device such as a Peltier element. Depending on the situation, one can be selected instead of the others. For example, a skin heat exchanger can be provided with a thermoelectric device and a fan to form an efficient heat exchanger. (8)

[0022] An aircraft galley compartment according to the teachings of one of the foregoing sections further includes: at least one temperature sensor configured to measure the temperature in the compartment. Information from the sensor can be used to control the temperature of the compartment, for example, by controlling the operation of a compartment temperature regulation unit provided in the compartment.

[0023] Alternatively or additionally, the aircraft galley compartment can include an adaptable exhaust according to the operation and an adaptable control of the temperature / airflow according to the operation, such as door opening, different meals, etc. (9)

[0025] An aircraft galley compartment according to the teachings of one of the foregoing sections further includes: at least one humidity sensor configured to measure the humidity in the compartment. Information from the sensor can be used to control the humidity of the compartment, for example, by controlling the operation of a heat exchanger provided in the compartment. (10)

[0027] An aircraft galley system, comprising: an aircraft galley; an aircraft galley compartment according to one of the foregoing teachings; and a human-machine interface unit, the human-machine interface unit being connected to at least one port and configured to communicate with a compartment temperature regulation unit connected to the at least one port. For this purpose, the human-machine interface unit may include a control unit. The human-machine interface unit / control unit may be configured to control the connected compartment temperature regulation unit, for example, based on the output from at least one of the foregoing sensors. Thus, for example, meal storage and meal preparation can be controlled. The criteria for such control may be at least one of minimum peak power consumption, the time to remove meals / drinks from the compartment, and quality-related criteria such as required temperature, air flow, and / or humidity. The connection between the human-machine interface unit / control unit and at least one port / multiple ports of at least one aircraft galley compartment in the aircraft galley may be remote.

[0028] Additionally or alternatively, the aircraft galley compartment may include a sensor for sensing the open state and / or closed state of the compartment. Of course, the sensor may output a signal to the human-machine interface unit / control unit, and the human-machine interface unit / control unit may use this input for the above purposes.

[0029] The human-machine interface unit / control unit, which may be a thermal management unit, may be modular and / or installed inside the electrical panel of the aircraft galley system. Additionally or alternatively, the human-machine interface unit / control unit may be configured as a centralized thermal management unit for multiple compartments to achieve optimal energy efficiency. (11)

[0031] An aircraft galley system, comprising: an aircraft galley; an aircraft galley compartment according to one of the foregoing teachings; a compartment temperature regulation unit for cooling the interior of the compartment and connected to at least one port of the compartment; and a waste heat conduit configured to distribute waste heat from the compartment temperature regulation unit to at least one specific location in the aircraft galley different from the compartment. This is an energy-saving configuration that allows the reduction of the necessary heat generation at at least one specific location by utilizing waste heat. (12)

[0033] The aircraft galley system according to the teaching of part (10), wherein the specific location in the aircraft galley is at least one of another aircraft galley compartment to be heated, another compartment temperature regulation unit for heating the aircraft galley compartment, and / or the kitchen floor. This reduces the energy required to operate the aircraft galley. (13)

[0035] The aircraft galley system taught by part (10) or part (11) further includes: a human-machine interface unit configured to control the distribution of waste heat from the compartment temperature regulation unit to at least one specific location in the aircraft galley. This is an effective and intuitive way to direct waste heat to the desired location. (14)

[0037] An aircraft includes an aircraft galley compartment taught by one of parts (1) to (9) or an aircraft galley system taught by one of parts (10) to (12). Since weight is important in an aircraft, an aircraft having such an aircraft galley system can be made lighter and thus more efficient. BRIEF DESCRIPTION OF THE DRAWINGS

[0038] The foregoing summary, as well as the following detailed description, will be better understood when read in conjunction with the accompanying drawings. For the purpose of illustrating the present disclosure, the preferred embodiments are shown in the drawings. However, it should be understood that the invention is not limited to the specific embodiments disclosed, and reference is made to the claims for this purpose. In the

[0039] In the drawings:

[0040] Figure 1 An aircraft galley system for regulating the temperature in a galley compartment is shown;

[0041] Figure 2 is shown Figure 1 a modification of one of the compartments shown in;

[0042] Figure 3 is shown Figure 1 the cross-section A-A indicated in; and

[0043] Figure 4 An aircraft galley of the aircraft galley system in an aircraft is shown. DETAILED DESCRIPTION

[0044] Figure 1 An aircraft galley system 1 for regulating the temperature in a galley compartment 3 is shown.

[0045] In this embodiment, the aircraft galley system 1 includes a temperature regulation loop 5 in which a heat exchange fluid circulates. The temperature regulation loop 5 includes fluid pipelines, which may include a single pipeline or two pipelines, such as a cold pipeline 7 and a hot pipeline 9. The cold pipeline 7 and the hot pipeline 9 Figure 1 in Figure 1 a plane orthogonal to the plane shown in and are thus covered by each other. The hot pipeline 9 may also be referred to as a waste heat conduit 9. In Figure 1In this case, the fluid circulates in the temperature control circuit 5 in a clockwise direction by means of the pump 11. The temperature control circuit 5 can be integrated in the kitchen, for example, integrated in the kitchen panel and / or the kitchen worktop and can also include a reservoir (not shown) for the fluid.

[0046] The output port 13 and the input port 15 can be provided inside the kitchen compartment 3 and are configured to be connected to at least one compartment temperature control unit 17. The ports 13, 15 can provide a connection to at least one of a circuit (not shown), a communication system (not shown), and / or the temperature control circuit 5. The ports 13, 15 can be arranged in and / or around the kitchen compartment 3. An aircraft cabin trolley can form such a kitchen compartment 3. Instead of the two ports 13, 15 shown, only one port or more than two ports can be provided. Therefore, at least one port 13, 15 must be provided. The at least one port can be configured for simultaneously powering (power transmission) and controlling (data transmission) at least one compartment temperature control unit.

[0047] At least one compartment temperature control unit 17 for regulating the temperature in the kitchen compartment 3 can be provided for the respective kitchen compartment 3. The compartment temperature control unit 17 can be directly connected to the circuit, the communication system, and / or the temperature control circuit 5 (see Figure 1 I and II therein) or indirectly connected to the circuit, the communication system, and / or the temperature control circuit 5 via the ports 13, 15, for example (see Figure 1 IV and V therein). In addition, the compartment temperature control unit 17 can be integrated in at least one of the rear wall (see Figure 1 I therein), the side wall (see Figure 1 II therein), the bottom wall (see Figure 1 II therein), the top wall (not shown), or the door (not shown) of the compartment 3. The specific form of the integration can be that the respective compartment temperature control unit 17 forms the entire respective wall or the inner door surface of the compartment 3. This will allow for even more efficient temperature regulation. In addition, one compartment temperature control unit 17 arranged between two adjacent compartments 3 can be configured to serve both compartments 3, i.e., heating or cooling both compartments 3. Alternatively or additionally, the compartment temperature control unit 17 can be located inside the compartment 3 and is, for example, removably connected to the circuit, the communication system, and / or the temperature control circuit 5 via the ports 13, 15 (see Figure 1 IV and V therein). In this case, the compartment temperature control unit 17 can extend along at least one of the rear wall (see Figure 1 IV therein), the side wall, the bottom wall, the top wall (see Figure 1 V therein), or the door of the compartment 3. The ports 13, 15 can be accessed from the inside of the compartment 3 since they extend into the compartment 3 (see Figure 1in IV and V). However, ports 13, 15 can be flush with one of the walls or doors of compartment 3, or they can even be recessed into one of the aforementioned walls or doors of compartment 3. The flush configuration and the recessed configuration increase the space available within compartment 3. The recessed configuration can also make it easier to connect the compartment temperature regulation unit 17 to ports 13, 15, because the recesses for ports 13, 15 can help to locate ports 13, 15 in compartment 3. The walls and doors of the compartment can provide at least one of refrigerator-grade insulation, freezer-grade insulation, and / or oven-grade insulation, such as oven-grade insulation for temperatures above 100 °C. This modularity allows the compartment temperature regulation unit 17 to be replaced during flight or on the ground according to the desired configuration. Compartment 3 with multiple compartment temperature regulation units 17 can be configured to include at least one compartment temperature regulation unit 17 for cooling and at least one compartment temperature regulation unit 17 for heating (see Figure 1 and Figure 2 in II). Thus, a compartment 3 that can only cool or heat can be provided, and a compartment 3 that can cool and heat can also be provided. The selection of the optimal compartment temperature regulation unit 17 for cooling depends, for example, on:

[0048] · the duration of the cooling requirement (short-range or long-range flight);

[0049] · only freezing or cooling (refrigeration); and

[0050] · the cooling (refrigeration) temperature accuracy.

[0051] Finally, the selection of the optimal cooling unit is a trade-off between complexity and cooling requirements. Since the compartment temperature regulation unit 17 can be attached to compartment 3 in an interchangeable manner, this can be easily customized even between different flights.

[0052] In Figure 1 :

[0053] · I is compartment 3 in which the compartment temperature regulation unit 17 is integrated into the rear wall of compartment 3;

[0054] · II is compartment 3 in which the compartment temperature regulation unit 17 is integrated into the side wall and the bottom wall of compartment 3; one or both of the compartment temperature regulation units 17 can be configured to also cool or heat the adjacent compartments 3 represented by I and III;

[0055] · III is compartment 3 that does not have any compartment temperature regulation unit 17 but has ports 13, 15 for connecting the compartment temperature regulation unit 17; of course, compartment 3 can have multiple such ports 13, 15 on different walls and / or doors for connecting multiple compartment temperature regulation units 17;

[0056] · Compartment IV is similar to Compartment III, with the difference that the compartment temperature regulation unit 17 is arranged inside Compartment 3 and connected to ports 13 and 15, and the compartment temperature regulation unit 17 extends along the rear wall of Compartment 3; and

[0057] · Compartment V is similar to Compartment IV, with the difference that the compartment is larger and configured to receive an aircraft cabin trolley, and the compartment temperature regulation unit 17 extends along the top wall of Compartment 3.

[0058] The compartment temperature regulation unit 17 can be a skin heat exchanger or a flat heat pipe assembly. The skin heat exchanger can directly heat or cool Compartment 3, for example, by means of a fan (not shown), or indirectly heat or cool the compartment by means of a thermoelectric device attached thereto, such as a Peltier element, which can also include a fan (not shown). The Peltier element / skin heat exchanger is preferably integrated in Compartment 3, preferably on the back of Compartment 3, to optimize space and simplify system integration. Thus, starting from the temperature of the fluid entering the thermoelectric device, the thermoelectric device can even further increase or decrease the temperature of the fluid to better meet the temperature requirements of the corresponding Compartment 3. In addition, at least one temperature sensor and / or humidity sensor (not shown) can be provided in the corresponding Compartment 3, and at least one temperature sensor and / or humidity sensor can be wireless.

[0059] Therefore, Compartment 3 can be configured for cooling by the following units:

[0060] · A passive cooling unit, such as a dry ice battery, and optionally having a distribution unit, such as a fan and / or a duct; and / or

[0061] · An active cooling unit, such as a thermoelectric device, and optionally having a distribution unit, such as a fan and / or a duct.

[0062] Compartment 3 can be configured for heating by the following units:

[0063] · An active heating unit, such as a thermoelectric device, and optionally having a distribution unit, such as a fan and / or a duct.

[0064] In the case of active cooling via a Peltier element, the Peltier element can be attached to a flat skin heat exchanger or a flat heat pipe assembly for disposing of waste heat, so that the flat skin heat exchanger or the flat heat pipe assembly serves as a radiator in the cooling compartment 3. Heat transfer in the heat exchanger can be achieved by a heat transfer / two-phase heat transfer fluid distributed within the temperature regulation loop 5. A component including a Peltier element, a fan, and a skin heat exchanger or a flat heat pipe can be provided. Preferably, both the Peltier element and the fan are attached to one side of the skin heat exchanger or the flat heat pipe. Alternatively, the component can be interchanged with a heating module or can be used for heating by alternating the current and heat flow.

[0065] In other words, in the case where refrigeration is not required, the compartment cooling compartment temperature regulation unit 17 can be directly integrated into the side wall of the compartment. This can be combined with the compartment heating compartment temperature regulation unit 17 at the rear wall of the compartment 3 to achieve a combined function of cooling and heating.

[0066] Another feature of this solution is that, compared with a conventional design having an electric kitchen insertion unit, fewer electronic components are required. Only one display may be needed to control the temperature in the compartment 3. The AC / DC conversion can also be centralized. This results in lower costs, fewer electronic components, lighter weight, and easier control of the temperature in the compartment 3. The human-machine interface unit 19 (see Figure 3 )), such as a touch screen device, can be provided as part of the aircraft kitchen system 1. A control unit (not shown), which can be part of the human-machine interface unit 19, can be configured to determine, for example, calculate algorithmically, the most cost-effective way to prepare food, such as cooling or heating, according to customizable criteria, such as by reducing power, avoiding power peaks, etc. This will minimize power consumption and optimize the workload of the crew, since the current standard is to operate each electric kitchen insertion unit, such as an oven, individually. The human-machine interface unit 19 can be configured to perform any combination of the following functions:

[0067] a) Visualize the compartment 3;

[0068] b) Identify the cooling compartment 3 and the heating compartment 3 and visualize the cooling compartment 3 and the heating compartment 3;

[0069] c) Visualize the position and / or type of the compartment temperature regulation unit 17 provided in the compartment 3;

[0070] d) Set and / or control the temperature in the compartment 3;

[0071] e) Control the operation of the compartment temperature regulation unit 17;

[0072] f) Control the distribution of waste heat from the temperature regulation unit 17 of the cooling compartment; and

[0073] g) Select when the meals in compartment 3 are ready to be served and prepare the meals accordingly by automatically operating the compartment temperature regulation unit 17.

[0074] The temperature of the fluid in the temperature regulation circuit 5 is controlled by the temperature regulation unit 21. Here, the temperature regulation unit 21 is configured as a radiator, i.e., configured to cool the fluid circulating in the temperature regulation circuit 5. Ports 13, 15 can be configured to allow for quick connection and disconnection of the temperature regulation unit 21 to and from the temperature regulation circuit 5, even during flight. For this purpose, quick couplings can be used. The temperature regulation unit 21 includes a heat exchange unit, shown in a W-shape, for cooling the fluid in the temperature regulation circuit 5. However, ports 13, 15 can additionally or alternatively be configured to allow for quick connection and disconnection of the compartment temperature regulation unit 17 to and from a circuit (not shown) and / or a communication system (not shown) in general.

[0075] Here, the temperature regulation unit 21 is a well-insulated pre-cooling compartment that can be filled with ice, for example, before or at the start of a flight. As Figure 1 shown, the temperature regulation unit 21 can be fixedly connected to the galley. For example, the temperature regulation unit 21 can be located in an inaccessible area of the galley, where dry ice can be inserted into the dry ice compartment via a chute from outside the galley. Alternatively, the dry ice compartment can be part of a trolley, which allows for quick replacement of one trolley that is no longer sufficiently pre-cooled, e.g., whose dry ice volume has decreased below a threshold, with another trolley that is sufficiently pre-cooled, e.g., whose dry ice volume is at or above the threshold. This solution covers both the ground phase and the flight phase on an aircraft. Alternatively, the temperature regulation unit can be a trolley with an active cooling function (not shown), e.g., with a vapor cycle, that serves as a ground support device and is only installed on the ground to cover the pull-down on the ground. This solution covers the ground phase on an aircraft. Alternatively, the temperature regulation unit can be a heat exchanger unit that is positioned adjacent to the aircraft fuselage (both not shown) to serve as a radiator during flight. This solution covers the flight phase on an aircraft and can be combined with the previous solution to cover both the ground phase and the flight phase of the aircraft.

[0076] Figure 2 Shows Figure 1 a modification of compartment 3, denoted by II herein, which is hereby referred to as compartment II'. Here, compartment II' is divided by a partition wall 23, e.g., an insulating partition wall 23 in this case, into a left sub-compartment 3l and a right sub-compartment 3r. Thereby, the temperatures of the two compartments 3l, 3r can be set separately. In fact, this modification is related toFigure 1 It is also different in that a compartment temperature regulation unit 17c is integrated in the side wall of the left sub-compartment 3l forming the compartment II', and a compartment temperature regulation unit 17h is integrated in the side wall of the right sub-compartment 3r forming the compartment II'. However, each of the compartment temperature regulation units 17c, 17h may be located inside the compartment 3. The first compartment temperature regulation unit 17c is configured to cool the left sub-compartment 3l, while the second compartment temperature regulation unit 17h is configured to heat the right sub-compartment 3l. For this purpose, the first compartment temperature regulation unit 17c may be supplied with fluid from the temperature regulation circuit 5 and output the fluid to the second compartment temperature regulation unit 17h. Thus, the waste heat from cooling the first compartment temperature regulation unit 17c can be used to heat the second compartment temperature regulation unit 17h.

[0077] Figure 3 shows Figure 1 the cross-section A-A indicated therein. Here, the kitchen floor 23 is heated by the waste heat from a cooling compartment temperature regulation unit (not shown) in one of the aircraft kitchen system 1 or the compartment 3. Specifically here, the fluid from the hot pipeline 9 is used to heat the kitchen floor 23 and then return the cooled fluid to the temperature regulation unit 21 to be even further cooled and re-introduced into the aircraft kitchen system 1 for cooling the compartment 3.

[0078] Figure 4 shows the aircraft kitchen 25 of the aircraft kitchen system 1 in the aircraft 27.

[0079] Each embodiment provides at least one of the following advantages:

[0080] · Reduced weight;

[0081] · Optimized design, such as less electronics for control, power efficiency, etc.;

[0082] · Fewer number of parts;

[0083] · Reduced cost;

[0084] · Higher reliability;

[0085] · Improved space efficiency; and

[0086] · Higher customization flexibility.

Claims

1. An aircraft galley compartment (3), comprising: At least one port (13, 15) that is accessible from the interior of the compartment (3) and configured to connect to at least one compartment temperature control unit (17).

2. The aircraft galley compartment (3) according to claim 1, Among them, The at least one port (13, 15) provides a connection to at least one of an electrical circuit, a communication system, and / or a temperature control loop (5) in which a heat exchanger fluid circulates.

3. The aircraft galley compartment (3) according to one of the preceding claims, further comprising: A closed state in which the compartment (3) is not accessible from the outside; And An open state in which the compartment (3) is accessible from the outside; Wherein, in the closed state, the compartment (3) provides at least one of refrigerator-class insulation, freezer-class insulation, and / or oven-class insulation.

4. The aircraft galley compartment (3) according to one of the preceding claims, Among them, The compartment (3) is configured to be temporarily divided into sub-compartments (3l, 3r) by a removable partition wall (23).

5. The aircraft galley compartment (3) according to one of the preceding claims, further comprising: At least one compartment temperature control unit (17) for cooling the interior of the compartment (3); And At least one compartment temperature control unit (17) for heating the interior of the compartment (3).

6. The aircraft galley compartment (3) according to claims 4 and 5, Among them, The at least one compartment temperature control unit (17) for cooling is arranged to cool a first sub-compartment (3l), and Wherein, the at least one compartment temperature control unit (17) for heating is arranged to heat a second sub-compartment (3r).

7. The aircraft galley compartment (3) according to one of the preceding claims, further comprising: At least one compartment temperature control unit (17), which is one or a combination of a skin heat exchanger, a heat pipe assembly, or a thermoelectric device such as a Peltier element.

8. The aircraft galley compartment (3) according to one of the preceding claims, further comprising: At least one temperature sensor configured to measure the temperature in the compartment (3).

9. The aircraft galley compartment (3) according to one of the preceding claims, further comprising: At least one humidity sensor configured to measure the humidity in the compartment (3).

10. An aircraft galley system (1), comprising: An aircraft galley (25); The aircraft galley compartment (3) according to one of the preceding claims; And A human-machine interface unit (19) that is connected to the at least one port (13, 15) and configured to communicate with the compartment temperature control unit (17) connected to the at least one port (13, 15).

11. An aircraft galley system (1), comprising: An aircraft galley (25); An aircraft galley compartment (3) according to one of the preceding claims; A compartment temperature regulating unit (17) for cooling the interior of the compartment (3) and connected to at least one port (13, 15) of the compartment (3); And A waste heat conduit (9) configured to distribute waste heat from the compartment temperature regulating unit (17) to at least one specific location of the aircraft galley (25) different from the compartment (3).

12. The aircraft galley system (1) according to claim 10 or 11, Among them, The specific location of the aircraft galley (25) is at least one of another aircraft galley compartment (3) to be heated, another compartment temperature regulating unit (17) for heating the aircraft galley compartment (3), and / or the galley floor (23).

13. The aircraft galley system (1) according to one of claims 10 to 12, further comprising: A human-machine interface unit (19) configured to control the distribution of the waste heat from the compartment temperature regulating unit (17) to the at least one specific location of the aircraft galley (25).

14. An aircraft (27) comprising an aircraft galley compartment (3) according to one of claims 1 to 9 or comprising an aircraft galley system (1) according to one of claims 10 to 13.

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