Aircraft galley system and aircraft

Abstract

The invention discloses an aircraft galley system and an aircraft. The aircraft galley system (1, 1 ', 1' ') comprises: a temperature regulation circuit (5) in which a heat exchanger fluid circulates; the invention relates to an aircraft (25) having an aircraft galley (23) comprising a galley system (1, 1 ', 1' '), a temperature regulating unit (19, 19', 19 '') configured to cool fluid in a temperature regulating circuit (5), and a compartment (3) configured to be cooled by a heat exchanger (17) supplied with fluid from the temperature regulating circuit (5). The aircraft (25) has an aircraft galley (23) comprising a galley system (1, 1 ', 1' ').

Description

Technical Field

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

[0002] A typical aircraft galley comprises an aircraft galley structure including system interfaces such as electrical, cooling, water, wastewater, and air ventilation. The cooling function is achieved via a central cooling system that generates cold air for trolley cooling.

[0003] Above the worktop, there is a galley compartment with fully functional, standalone electric galley plug-in units—i.e., fully operational units, whether installed in or removed from the corresponding aircraft galley compartment. Such electric galley plug-in units can be refrigerators, freezers, or wine coolers. Each of these specialized units has specific cooling requirements, such as selectable temperatures, freezing temperatures, etc.; insulation requirements, such as refrigerator-grade insulation or freezer-grade insulation; and space requirements.

[0004] These specific units are heavy, expensive and - once installed in the corresponding aircraft galley compartment - become part of the galley, whether needed or not. Summary of the Invention

[0005] The problem to be solved is to improve the known aircraft galley system and an aircraft having an aircraft galley comprising such an aircraft galley system—in particular with regard to its efficient and cost-effective utility.

[0006] This problem is solved by the technical solution according to the main aspects of the present invention.

[0007] The problem to be solved by the present invention is solved in particular by the following technical teachings:

[0008] (1) An aircraft galley system comprising: a temperature regulation circuit in which a heat exchanger fluid circulates; a temperature regulation unit configured to cool the fluid in the temperature regulation circuit; and

[0009] A compartment is configured to be cooled by a heat exchanger supplied with fluid from a temperature control circuit. Thus, further individual cooling of the compartment is possible based on the already cooled fluid in the temperature control circuit. For this purpose, the compartment, for example its walls and doors, may be provided with refrigerator-grade insulation and / or freezer-grade insulation.

[0010] (2) An aircraft galley system according to part (1), wherein the temperature regulating unit is a pre-cooling compartment. This can be provided by, for example, a compartment filled with dry ice. This solution is simple and cost-effective.

[0011] (3) The aircraft galley system according to part (1) or (2), wherein the temperature regulation unit is a trolley with an active cooling unit. If the cooling unit of the trolley is insufficient to meet the cooling requirements or the trolley malfunctions, it can be easily replaced with another trolley.

[0012] (4) The aircraft galley system according to one of the preceding parts, wherein the temperature regulation unit is a heat exchanger unit configured to be positioned adjacent to the aircraft fuselage. In cold weather on the ground and in any weather during normal flight altitudes, ambient air may be sufficient to cool the fluid in the temperature regulation circuit. This solution is also simple and cost-effective.

[0013] (5) The aircraft galley system according to one of the preceding parts, wherein at least one heat exchanger is incorporated in the rear wall, side wall, bottom wall, top wall or door of the compartment. This enables better utilization of the space occupied by the galley. In addition, it allows a heat exchanger to be arranged between two adjacent compartments to cool both compartments.

[0014] (6) The aircraft galley system according to one of the preceding parts, wherein at least one heat exchanger is located inside the compartment. This allows for easier maintenance and higher efficiency compared to the incorporated solution.

[0015] (7) The aircraft galley system according to one of the preceding parts, wherein the temperature regulation circuit includes ports configured to connect at least one heat exchanger to the temperature regulation circuit. Thus, the heat exchangers can be placed only in the compartments where they are needed. In addition, adjustable or optimized heat exchangers can be selected according to the needs of a particular compartment.

[0016] (8) The aircraft galley system according to part (7), wherein the ports are configured to be accessible from the inside of the compartment. Thus, the heat exchangers can be easily added to or removed from the compartment.

[0017] (9) The aircraft galley system according to one of the preceding parts,

[0018] wherein the heat exchanger includes a thermoelectric device, such as a Peltier element, attached to the heat exchanger and configured to increase the cooling effect of the fluid from the temperature regulation circuit. Thus, starting from the temperature of the fluid entering the thermoelectric device, the thermoelectric device can raise or lower the temperature of the fluid to better meet the temperature requirements of the corresponding compartment.

[0019] (10) An aircraft galley system according to one of the foregoing portions, wherein at least one temperature sensor is provided in at least one compartment, heat exchanger, and / or temperature regulating unit to control the fluid flow of the temperature regulating circuit. These sensors can assist in distributing fluid and / or energy according to the temperature required for each compartment.

[0020] (11) An aircraft having an aircraft galley including an aircraft galley system according to one of the foregoing portions. Since weight is important in an aircraft, an aircraft having such an aircraft galley system can be made lighter and thus more efficient. Description of the Drawings

[0021] The foregoing summary of the invention, 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 present invention is not limited to the specific embodiments disclosed, and reference is made to the claims for this purpose. In the drawings:

[0022] Figure 1 An aircraft galley system for regulating the temperature in a galley compartment according to a first embodiment is shown;

[0023] Figure 2 An aircraft galley system for regulating the temperature in a galley compartment according to a second embodiment is shown;

[0024] Figure 3 An aircraft galley system for regulating the temperature in a galley compartment according to a third embodiment is shown; and

[0025] Figure 4 An aircraft galley in an aircraft having an aircraft galley system is shown. Detailed Description

[0026] Figure 1 An aircraft galley system 1 for regulating the temperature in a galley compartment 3 according to a first embodiment is shown.

[0027] In this embodiment, the aircraft galley system 1 includes a temperature regulating circuit 5 in which heat exchanger fluid circulates. The temperature regulating circuit 5 includes fluid lines, which may include a single line or two lines, such as a cold line 7 and a hot line 9, which Figure 1 in a plane Figure 1 orthogonal to the plane shown and thus are covered by each other. The fluid is caused to flow in the temperature regulating circuit 5 by means of a pump 11 Figure 1in a clockwise direction. The temperature regulation circuit 5 can be integrated in the kitchen, for example in the kitchen panel and / or the kitchen worktop, and can also include a reservoir (not shown) for the fluid.

[0028] The temperature regulation circuit 5 includes an output port 13 and an input port 15 for the fluid, the output port 13 and the input port 15 being arranged in and / or around the kitchen compartment 3. Each of the ports 13, 15 can be opened and closed to allow the fluid to be output from or input into the temperature regulation circuit 5.

[0029] The temperature regulation circuit 5 is connected to or configured to be connected to a heat exchanger 17 for regulating the temperature in the kitchen compartment 3. Here, the heat exchanger 17 is used to cool the compartment 3. The heat exchanger 17 can be directly connected to the temperature regulation circuit 5 (see Figure 1 I and II in Figure 1 or indirectly connected to the temperature regulation circuit 5 via the ports 13, 15 for example (see Figure 1 IV and V in Figure 1 ). In addition, the heat exchanger 17 can be integrated in at least one of the rear wall (see Figure 1 I in Figure 1 ), side wall (see Figure 1 II in Figure 1 ), bottom wall (see Figure 1 II in

[0030] ), top wall (not shown) or door (not shown) of the compartment 3. The specific form of integration can be such that the respective heat exchanger 17 forms the entire respective wall or inner door surface of the compartment 3. This will allow for even more efficient temperature regulation. In addition, a heat exchanger 17 arranged between two adjacent compartments 3 can be configured to serve both compartments 3, i.e. to cool both compartments 3. Alternatively or additionally, the heat exchanger 17 can be located inside the compartment 3 and connected to the temperature regulation circuit 5 in a removable manner via the ports 13, 15 for example (see Figure 1 IV and V in ). In this case, the heat exchanger 17 can extend along at least one of the rear wall (see Figure 1 IV in ), side wall, bottom wall, top wall (see Figure 1 V in ), or door of the compartment 3. The ports 13, 15 can be accessed from the inside of the compartment 3 as they extend into the compartment 3 (see Figure 1 IV and V in ). However, the ports 13, 15 can be flush with one of the walls or the door of the compartment 3, or they can even be recessed into one of the above-mentioned walls or the door of the compartment 3. The flush and recessed configurations increase the available space inside the compartment 3. The recessed configuration can further make it easier to connect the heat exchanger 17 to the ports 13, 15 as the recesses for the ports 13, 15 can help to locate the ports 13, 15 in the compartment 3. The walls and doors of the compartment can provide refrigerator-grade insulation and / or even freezer-grade insulation.

[0030] In Figure 1 :

[0031] · I is compartment 3, in which the heat exchanger 17 is incorporated in the rear wall of compartment 3;

[0032] · II is compartment 3, in which the heat exchanger 17 is incorporated in the side wall and the bottom wall of compartment 3; one or both of the heat exchangers 17 may be configured to also cool the adjacent compartments 3 represented by I and III;

[0033] · III is compartment 3, which does not have any heat exchanger 17, but has ports 13, 15 for connecting the heat exchanger 17; of course, compartment 3 may have a plurality of such ports 13, 15 on different walls and / or doors for connecting a plurality of heat exchangers 17;

[0034] · IV is a compartment 3 similar to III, except that the heat exchanger 17 is arranged inside compartment 3 and is connected to the ports 13, 15, wherein the heat exchanger 17 extends along the rear wall of compartment 3; and

[0035] · v is a compartment 3 similar to IV, except that this compartment is larger and is configured to receive an aircraft cabin trolley, and the heat exchanger 17 extends along the top wall of compartment 3.

[0036] The heat exchanger 17 may be a skin heat exchanger or a flat heat pipe assembly. The skin heat exchanger can directly cool the compartment 3, for example, by means of a fan, or indirectly cool the compartment by means of a thermoelectric device attached thereto, such as a Peltier element. Thus, starting from the temperature of the fluid entering the thermoelectric device, the thermoelectric device can even further increase the temperature of the fluid or, in this case, further decrease the temperature of the fluid to better meet the temperature requirements of the corresponding compartment 3. In addition, at least one temperature sensor (not shown) may be provided in the corresponding compartment 3, heat exchanger 17 and / or temperature regulation unit 19 to control the fluid flow of, for example, the pump 11 in the temperature regulation loop 5. The at least one temperature sensor may be connected to a control unit (not shown), which is configured to control the temperature inside each compartment 3 by controlling at least one of the pump 11, the fluid flowing through the heat exchanger 17, such as by changing the degree of opening / closing of the ports 13, 15, the speed of the fan of the heat exchanger 17, and / or the power and polarity of the thermoelectric device. The ports 13, 15 may have an integrated communication port such that not only can fluid be input into and output from the heat exchanger 17, but also communication signals can be transmitted between the heat exchanger 17 and the control unit.

[0037] The temperature of the fluid in the temperature regulation circuit 5 is controlled by the temperature regulation unit 19. Here, the temperature regulation unit 19 is configured as a radiator, i.e., for cooling the fluid circulating in the temperature regulation circuit 5. The ports 13, 15 can be configured to allow for quick connection and disconnection of the temperature regulation unit 19 to and from the temperature regulation circuit 5, even in flight. For this purpose, quick connectors can be used. The temperature regulation unit 19 includes a heat exchange unit shown in a W shape for cooling the fluid in the temperature regulation circuit 5.

[0038] Here, the temperature regulation unit 19 is a well-insulated pre-cooling compartment that can be filled with dry ice, for example, before flight or at the start of flight. As Figure 1 shown, the temperature regulation unit 19 can be fixedly connected to the galley. For example, the temperature regulation unit 19 can be located in an inaccessible area of the galley, where dry ice can be added to the dry ice compartment via a chute from the outside of the galley. Alternatively, the dry ice compartment can be part of a trolley that allows for quick replacement of one trolley that is no longer sufficiently pre-cooled, e.g., whose dry ice volume has dropped 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 the ground phase and the flight phase of the aircraft.

[0039] Figure 2 An aircraft galley system 1' for regulating the temperature in the galley compartment 3 according to a second embodiment is shown. This second embodiment differs from the first embodiment in its temperature regulation unit 19'. Here, the temperature regulation unit 19' is a trolley with an active cooling function, e.g., with a vapor cycle, which serves as ground support equipment and is only installed on the ground to cover the pull-down on the ground. This solution covers the ground phase of the aircraft.

[0040] Figure 3 An aircraft galley system 1'' for regulating the temperature in the galley compartment 3 according to a third embodiment is shown. This third embodiment differs from the first and second embodiments in its temperature regulation unit 19''. Here, the temperature regulation unit 19'' is a heat exchanger unit located adjacent to the aircraft fuselage 21 for use as a radiator during flight. This solution covers the flight phase of the aircraft and can be combined with the previous solutions to cover both the ground phase and the flight phase of the aircraft.

[0041] Figure 4 An aircraft galley 23 in the aircraft 25 with the aircraft galley systems 1, 1', 1'' is shown.

[0042] These embodiments provide at least one of the following advantages:

[0043] · Weight reduction;

[0044] · Reduction in the number of components;

[0045] · Improved kitchen design, e.g., fewer walls;

[0046] · Cost reduction;

[0047] · Higher reliability;

[0048] · Improved space efficiency; and

[0049] · Higher customization flexibility.

Claims

1. An aircraft galley system (1, 1', 1"), comprising: A temperature regulation circuit (5) in which a heat exchanger fluid circulates; A temperature regulation unit (19, 19', 19") configured to cool the fluid in the temperature regulation circuit (5); And A compartment (3) configured to be cooled by a heat exchanger (17) supplied with fluid from the temperature regulation circuit (5).

2. The aircraft galley system (1) according to claim 1, Among them, The temperature regulation unit (19) is a pre-cooling compartment.

3. The aircraft galley system (1') according to claim 1 or 2, Among them, The temperature regulation unit (19') is a trolley with an active cooling unit.

4. The aircraft galley system (1") according to one of the preceding claims, Among them, The temperature regulation unit (19") is a heat exchanger unit configured to be positioned adjacent to the aircraft fuselage (21).

5. The aircraft galley system (1, 1', 1") according to one of the preceding claims, Among them, At least one heat exchanger (17) is incorporated in the rear wall, side wall, bottom wall, top wall or door of the compartment (3).

6. The aircraft galley system (1, 1', 1") according to one of the preceding claims, Among them, At least one heat exchanger (17) is located inside the compartment (3).

7. The aircraft galley system (1, 1', 1") according to one of the preceding claims, Among them, The temperature regulation circuit (5) includes ports (13, 15) configured to connect at least one heat exchanger (17) to the temperature regulation circuit (5).

8. The aircraft galley system (1, , 1") according to claim 7, Among them, The ports (13, 15) are configured to be accessible from the inside of the compartment (3).

9. The aircraft galley system (1, 1', 1") according to one of the preceding claims, Among them, The heat exchanger (17) includes a thermoelectric device, such as a Peltier element, attached to the heat exchanger (17) and configured to enhance the cooling effect of the fluid from the temperature regulation circuit (5).

10. The aircraft galley system (1, 1', 1") according to one of the preceding claims, Among them, At least one temperature sensor is provided in at least one of the compartment (3), the heat exchanger (17) and / or the temperature regulation unit (19, 19', 19") to control the fluid flow in the temperature regulation circuit (5).

11. An aircraft (25) having an aircraft galley (23) including an aircraft galley system (1, 1', 1") according to one of the preceding claims.

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