Temperature regulating system for a galley compartment of an in-flight kitchen

Abstract

A temperature regulating system for at least one galley compartment for an in-flight kitchen which is intended for installing in a transport apparatus or vehicle, especially in an aircraft, includes a controllable cooling and heating element, which is designed for selectively cooling or heating a specified section of the cooling and heating element, and a heat-insulating partitioning wall, which at least partially adjoins an encompassing side edge of the cooling and heating element and encloses the specified section of the cooling and heating element. The heat-insulating partitioning wall is designed for separating an interior space of the galley compartment from an interior of a section of a fluid duct which extends in the in-flight kitchen.

Claims

1. A temperature regulating system for at least one galley compartment for an in-flight kitchen which is intended for installing in a transport apparatus or vehicle, wherein the temperature regulating system comprises: a controllable cooling and heating element, which is configured for selectively cooling or heating a specified section of the cooling and heating element, the cooling and heating element comprising at least a thermoelectric element or a refrigerating machine; a heat-insulating partitioning wall, which at least partially adjoins an encompassing side edge of the cooling and heating element and encloses the specified section of the cooling and heating element; a delivery fan configured to control a speed at which a first fluid, present in the galley compartment, is delivered via the section of the cooling and heating element; and a controller configured to control temperature inside of the at least one galley compartment; the galley compartment having a heat-insulating door for closing off an opening of the galley compartment, wherein a first presetting device, in communication with the controller, is on, or in a proximity of, the heat-insulating door for presetting a setpoint temperature for the interior space of the galley compartment; wherein the heat-insulating partitioning wall is configured for separating an interior space of the galley compartment from an interior of a section of a fluid duct which extends in the in-flight kitchen; and either of: wherein the controller is configured to control temperature inside of the at least one galley compartment based on readings from radio frequency tags stored in the at least one galley compartment; wherein the controllable cooling and heating element is a thermoelectric element and the controller is configured for applying a variable voltage to the thermoelectric element and changing a polarity of the voltage; or wherein the controllable cooling and heating element is a refrigerating machine with two heat exchangers, ducts for a cooling medium and at least one valve in the ducts, wherein the controller is configured for controlling the at least one valve of the refrigerating machine so that the cooling medium is selectively ducted through one of the two heat exchangers for heat absorption or heat release.

2. The temperature regulating system according to claim 1, wherein the delivery fan is on a side of the partitioning wall facing the interior space of the galley compartment.

3. The temperature regulating system according to claim 1, further comprising: a first heat exchanger, which is on a side of the cooling and heating element facing the section of the fluid duct; and/or a second heat exchanger, which is on a side of the cooling and heating element facing the interior space of the galley compartment.

4. The temperature regulating system according to claim 1, wherein the transport apparatus or vehicle comprises an aircraft.

Description

BRIEF DESCRIPTION OF THE DRAWINGS

(1) All aspects, variants, examples of a temperature regulating system, of a galley compartment and of an in-flight kitchen which are described above are not be considered as being isolated from each other. Rather, all these aspects, variants, examples, etc. can be combined in any way with each other. Preferred embodiments of the disclosure herein are now explained in more detail with reference to the attached schematic and example drawings. In the drawings:

(2) FIG. 1 shows an in-flight kitchen, which is equipped with a first embodiment of a temperature regulating system;

(3) FIGS. 2A and 2B show a perspective view of a temperature regulating system; and

(4) FIGS. 3A through 3C show an alternative embodiment of an in-flight kitchen, which is equipped with a temperature regulating system.

DETAILED DESCRIPTION

(5) FIG. 1 shows an in-flight kitchen generally designated 100, which is suitable especially for installing in a passenger cabin of a passenger aircraft. The in-flight kitchen 100 comprises a body 102 with a substructure 104 and also upper compartments 106 which are arranged above the substructure 104. Stored in the upper compartments 106 are kitchen appliances such as coffee machines, water boilers, etc., and also drinks and foodstuff. Arranged in the substructure 104 of the in-flight kitchen 100, on the other hand, is a trolley compartment for accommodating mobile trolleys which are loaded with objects such as drinks and foodstuffs which are provided for handing out to the passengers in the passenger cabin of the passenger aircraft. A cooling system generally designated 10 serves for cooling the trolley compartment which is arranged in the substructure 104 of the in-flight kitchen 100.

(6) The cooling system 10 comprises a cooling device 11 with a cooling medium circuit 12 which is exposed to throughflow by a cooling medium, for example a two-phase refrigerant. An evaporator 14 and a condenser 16 are arranged in the cooling medium circuit 12. When flowing through the evaporator 14, the cooling medium which flows through the cooling medium circuit 12 absorbs heat and in the process transfers from the liquid into the gaseous aggregate state. In contrast to this, the cooling medium which flows through the cooling medium circuit 12 is cooled when flowing through the condenser 16 as a result of release of heat energy and is converted from the gaseous back into the liquid aggregate state again. The cooling device 11 is integrated into an intermediate wall 17 which divides the substructure 104 of the in-flight kitchen 100 into a first and a second section. Alternatively, the cooling device 11 can also be installed in a sidewall of the in-flight kitchen 100 or in a rear wall 26 of the in-flight kitchen.

(7) The cooling device 11 comprises a first fluid duct generally designated 38 and a second fluid duct generally designated 18 which in each case are thermally connected to the cooling medium circuit 12 of the cooling device 11. The fluid flows which are created by the cooling device 11, for example in the first cooling-device fluid duct 38 or second cooling-device fluid duct 18 and also in ducts which are arranged downstream of the cooling device 11, can be used for a temperature regulating system generally designated 200. Shown in FIG. 1 by way of example is such a temperature regulating system 200 which is arranged in a section 42 of the first cooling-device fluid duct 38. The temperature regulating system 200 serves for temperature regulation in the interior space of a galley compartment 106b.

(8) To this end, the temperature regulating system, as is shown in detail in FIGS. 2A and 2B, has a cooling and heating element 210 and a heat-insulating partitioning wall 220 which at least partially adjoins an encompassing side edge of the cooling and heating element 210 and encloses a specified section of the cooling and heating element. As a result, the heat-insulating partitioning wall 220 separates an interior space of the galley compartment 106b from the interior of the section 42 of the first cooling-device fluid duct 38. The cooling and heating element 210 of flat design therefore has a side facing the interior of the first cooling-device fluid duct 38 and a side facing the interior space of the galley compartment 106b.

(9) In the embodiment variant shown in FIG. 2A, the cooling and heating element 210a is a thermoelectric element 210a. The thermoelectric element 210a, when a voltage is applied, creates a heat flow from one side (for example from the side facing the interior of the first cooling-device fluid duct 38) to an opposite side (for example to the side facing the interior space of the galley compartment 106b).

(10) Alternatively to this, the cooling and heating element 210 can also be designed in the form of a refrigerating machine generally designated 210b, as is shown by way of example and schematically as a sectional view in FIG. 2B. The refrigerating machine 210b comprises a delivery device 260 for a cooling medium of the refrigerating machine 210b (such as compressor), a restrictor valve or expansion valve 261, a first heat exchanger 262, a second heat exchanger 263 and at least one valve 264 (for example a (multi) directional valve) for altering the direction of the cooling medium volumetric flow downstream of the at least one valve 264. Via the at least one valve 264, a volumetric flow of the cooling medium which is moved by the delivery device 260 in the refrigerating machine 210b can be controlled so that the refrigerating medium flows from the delivery device 260 either to the first heat exchanger 262 (first valve position) or the second heat exchanger 263 (second valve position). Correspondingly, the refrigerating medium flows from the first heat exchanger 262 to the restrictor valve 261 in the first valve position, and in the second valve position flows from the second heat exchanger 263 to the restrictor valve 261.

(11) For example, as shown in FIG. 2B, the refrigerating machine 210b can comprise two valves 264. In a first position of the valves 264, the cooling medium flows from the delivery device 260 through the lower valve 264 (at the bottom in FIG. 2B) into the first heat exchanger 262. From the upper end of the heat exchanger 262, the cooling medium flows further into the upper valve 264, from there flows towards the restrictor valve or expansion valve 261, through the lower valve 264, and also flows from the bottom upwards through the second heat exchanger 263. In the upper valve 264, the flows of the cooling medium therefore cross over, whereas in the lower valve 264 the cooling medium flows flow past each other in parallel. In the reverse position of the valves 264 (second valve position), the cooling medium flows from the heat exchangers 262, 263 flow past each other in parallel in the upper valve 264 and in the lower valve 264 cross over.

(12) The heat exchangers 262 and 263 therefore achieve the same function as the two sides of the thermoelectric element 210a from FIG. 2A. Instead of changing the polarity of the voltage which is applied to the thermoelectric element 210a, in the case of the refrigerating machine 210b, by controlling (changing the valve positions) of the at least one valve 264, the direction of a heat flow between the two heat exchangers 262, 263 can be reversed.

(13) A first heat exchanger 215 and a second heat exchanger 217 can be arranged on one of or both of these sides of the cooling and heating element 210. The temperature regulating system 200 can also comprise a delivery device 230 which is arranged on a side of the cooling and heating element 210 facing the interior space of the galley compartment 106b. The delivery device 230 is designed or configured for delivering a first fluid, which is present in the galley compartment 106b, via the cooling and heating element 210 and/or via the heat exchanger 217 which is attached on this side of the cooling and heating element 210. Since a fluid flow, created by the cooling device, exists on the side of the cooling and heating element 210 facing away from the interior space of the galley compartment 106b, a separate delivery device is unnecessary on the side of the cooling and heating element 210 facing this fluid flow. This allows a saving of weight and space of the temperature regulating system 200.

(14) The temperature regulating system 200 can also comprise a control unit 240 which can apply a variable voltage to the thermoelectric element 210 and can change the polarity of this voltage. Alternatively, the control unit 240 can control the delivery device 260 of the refrigerating machine 210b and/or the at least one valve 264. As a result, a heat flow between the two sides of the cooling and heating element can be controlled in its value and direction. Depending on the polarity of the voltage or position of the at least one valve 264, by the cooling and heating element 210 heat from the interior of the section 42 of the first cooling-device fluid duct 38 is therefore transported into the interior space of the galley compartment 106b or in the reverse direction.

(15) As is shown in FIG. 1, the first cooling-device fluid duct 38 is exposed to throughflow by a second fluid. In the exemplary embodiment shown in FIG. 1, the second fluid is air. The first cooling-device fluid duct 38 is thermally connected via the condenser 16 to the cooling medium circuit 12 of the cooling device 11 in order to transfer heat from the cooling medium which circulates in the cooling medium circuit 12 to the fluid which flows through the first cooling-device fluid duct 38. The second fluid is therefore used for the cooling of cooling medium which circulates in the cooling medium circuit 12.

(16) The first cooling-device fluid duct 38 comprises a first section 40 which is integrated in an installation-space saving manner into a worktop 22 of the in-flight kitchen 100. The worktop 22 separates the substructure 104 of the in-flight kitchen 100 from the upper compartments 106 of the in-flight kitchen 100. A second section 42 of the first cooling-device fluid duct 38 adjoins (upstream) the first section 40 and extends for example adjacent to a rear wall 26 of the in-flight kitchen 100. The second section 42 of the first cooling-device fluid duct 38 is provided with one, or a plurality of, fluid inlet(s) 42a. Such a fluid inlet 42a can be formed adjacent to the rear wall 26 of the in-flight kitchen 100. Additionally or alternatively, a fluid inlet 42a can be arranged adjacent to a front side of the in-flight kitchen 100 which lies opposite the rear wall 26 of the in-flight kitchen 100 and via a third section 44 of the first cooling-device fluid duct 38 can be connected to the second section 42. Also alternatively or additionally, a fluid inlet 42a can be arranged in a roof area of the in-flight kitchen 100. Also alternatively or additionally, a fluid inlet (not shown) can also open into a further galley compartment, as a result of which air discharged from the galley compartment. Each of the possible air inlets 42a can be provided with an air filter in order to reduce or to avoid contamination of the adjoining fluid duct sections.

(17) Via the one, or the plurality of, fluid inlet(s) 42a, air can therefore be discharged from an environment of the in-flight kitchen 100 and be ducted as the second fluid through the first cooling-device fluid duct 38. The air surrounding the in-flight kitchen can originate for example from a cabin area 52, to which is fed cold climatization air from an aircraft climatization system 54 at a temperature of approximately 12° C. Therefore, the fluid flow in the first cooling-device fluid duct 38 has a corresponding temperature and is well suited as a heat sink.

(18) The first cooling-device fluid duct 38 also comprises a fourth section 48 which, with regard to the flow direction of the second fluid through the first cooling-device fluid duct 38, is arranged downstream of the first section 40 and consequently connects the first section 40 of the first cooling-device fluid duct 38 to the cooling device 11, i.e. to a section of the first cooling-device fluid duct 38 which is thermally connected to the cooling medium circuit 12 of the cooling device 11. In the arrangement according to FIG. 1, the fourth section 48 of the first cooling-device fluid duct 38 opens into the cooling device 11 in the region of the upper side 30 of the cooling device 11 facing the worktop 22.

(19) For delivering the second fluid through the first cooling-device fluid duct 38, a delivery device 50 can be designed in the form of a fan. For delivering the second fluid through the first cooling-device fluid duct 38, the delivery device 50 is integrated into the cooling device 11 in the exemplary embodiment shown here. By this delivery device 50, a separate delivery device for the temperature regulating system 200 is not required, as a result of which space and weight are saved.

(20) The first cooling-device fluid duct 38, with regard to the flow direction of the fluid, i.e. the air, through the first cooling-device fluid duct 38, is continued downstream of the thermal connection of the first cooling-device fluid duct 38 to the cooling medium circuit 12 of the cooling device 11 by a waste heat fluid duct 56. The waste heat fluid duct 56 can be connected to a cabin area 52 of the aircraft which accommodates the in-flight kitchen 100 in order to feed warmed air to the cabin area 52 by heat transfer of the cooling medium which circulates in the cooling medium circuit 12 of the cooling device 11. The warm air which flows through the first cooling-device fluid duct 38 can therefore be used for heating the cabin area 52.

(21) To this end, the waste heat fluid duct 56 branches into a first section 56a and a second section 56b. The first section 56a of the waste heat fluid duct 56 opens into an air outlet 58 which is arranged in the region of a front side of the in-flight kitchen 100, via which outlet the warm air which flows through the waste heat fluid duct 56 can be ducted into the cabin area 52 close to the floor. Via the second section 56b, the waste heat fluid duct 56 can be connected on the other hand to a cargo area 60 of the aircraft so that the warm air which flows through the waste heat fluid duct 56 can also be fed to the cargo area 60 of the aircraft. A valve 62 is arranged in the waste heat fluid duct 56 in the region of the branch of the waste heat fluid duct 56 into the first and the second sections 56a, 56b. The valve 62 is designed or configured for conducting the volumetric flow of the warm air which flows through the waste heat fluid duct 56 into the cabin area 52 which accommodates the in-flight kitchen 100 and/or into the cargo area 60, as desired. In the embodiment shown in FIG. 1, the valve 62 is designed in the form of a flap which can be operated by a controllable actuator 64. Depending on the position of the valve 62, the warm air which flows through the waste heat fluid duct 56 can be selectively ducted either just into the cabin area 52 or just into the cargo area 60. Alternatively to this, the airflow which flows through the waste heat fluid duct 56 can, however, also be divided by the valve 62 into partial volumetric flows which, depending on requirement, can then be fed to the cabin area 52 and to the cargo area 60.

(22) The second cooling-device fluid duct 18 is exposed to throughflow by a third fluid, which is to be cooled, by the cooling device 11. In the exemplary embodiment shown in FIG. 1, the third fluid is air, i.e. the cooling device 11 is designed in the form of an air chiller. The second cooling-device fluid duct 18 is thermally connected via the evaporator 14 to the cooling medium circuit 12 of the cooling device 11 in order to transfer heat from the third fluid, which flows through the second cooling-device fluid duct 18, to the cooling medium which circulates in the cooling medium circuit 12. The third fluid is therefore cooled to a desired low temperature when flowing through the evaporator 14.

(23) The second cooling-device fluid duct 18 comprises a first section 20 which is integrated in an installation-space saving manner into the worktop 22 of the in-flight kitchen 100. The first section 20 of the second cooling-device fluid duct 18 is provided with a plurality of fluid inlets which are formed in an underside of the worktop 22 facing the substructure 104 of the in-flight kitchen 100. The first section 20 of the second cooling-device fluid duct 18 is connected to a second section 28 of the second cooling-device fluid duct 18 which opens into the cooling device 11 in the region of an upper side 30 of the cooling device 11 facing the worktop 22 and as a result creates a connection between the first section 20 of the second cooling-device fluid duct 18 and a section of the second cooling-device fluid duct 18 which is thermally connected via the evaporator 14 to the cooling medium circuit 12 of the cooling device 11.

(24) A cooling fluid duct 32 connects the cooling device 11 to a fluid outlet 34 which opens into the substructure 104 of the in-flight kitchen 100. The third fluid which is cooled by the cooling device 11 can therefore be ducted via the cooling fluid duct 32 into an area of the substructure 104 close to the floor and via the first section 20 and then the second section 28 of the second cooling-device fluid duct 18 can be recirculated into the cooling device 11. The flow direction of the third fluid, which is cooled by the cooling device 11, through the cooling fluid duct 32 and the second cooling-device fluid duct 18 can also be reversed, however.

(25) A delivery device 36 delivering the third fluid through the cooling fluid duct 32 and the second cooling-device fluid duct 18 can be designed or configured for example in the form of a fan and is integrated into the cooling device 11 in the exemplary embodiment shown here. In particular, the delivery device 36 for delivering the third fluid through the cooling fluid duct 32 and the second cooling-device fluid duct 18 is arranged downstream of the thermal connection of the second cooling-device fluid duct 18 to the evaporator 14 of the cooling device 11 with regard to the flow direction of the third fluid.

(26) A temperature regulating system 200 can be arranged in any section of the above-described first cooling-device fluid duct 38, second cooling-device fluid duct 18, waste heat fluid duct 56 and cooling fluid duct 32. In other words, the cooling and heating element 210 of the temperature regulating system 200 can use any of the fluid flows provided in these fluid ducts as a heat source or heat sink or in order to cool or to heat a galley compartment 106b or another area of the in-flight kitchen 100.

(27) In the exemplary embodiment shown in FIG. 1, a galley compartment 106b is arranged in an upper compartment 106 of the in-flight kitchen 100. In this case, the temperature regulating system 200 by its partitioning wall 220 forms a rear side of the galley compartment 106b. As can be gathered from FIG. 1, the temperature regulating system 200 could alternatively or additionally form a part of a floor of the galley compartment 106b, wherein the cooling and heating element 210 would lie in the section 40 of the first cooling-device fluid duct 38. By the same token, the temperature regulating system 200 can be arranged at any further optional location of the galley compartment 106b.

(28) Furthermore, an additional temperature regulating system 200 can also be arranged in the in-flight kitchen and cools or heats the same galley compartment 106b but is thermally connected to another section of the fluid duct or to another fluid duct. For example, the cooling and heating element 210 of a first temperature regulating system 200 for heating a galley compartment 106b can lie in the section 40 of the first cooling-device fluid duct 38, whereas a cooling and heating element 210 of a second temperature regulating system (not shown in FIG. 1) for cooling the galley compartment 106b lies in the section 20 of the second cooling-device fluid duct 18. Alternatively or additionally, a pure heating element (for example an electric heating element) can also be installed for heating the galley compartment 106b.

(29) By the same token, the temperature regulating system 200 in the substructure 104 of the in-flight kitchen 100 can cool or heat a galley compartment (not explicitly shown). For this, the cooling and heating element 210 can be arranged in/on one of the sections 48, 28 of the first or second cooling-device fluid ducts 38, 18 or also in/on one of the sections of the waste heat fluid duct 56 and cooling fluid duct 32.

(30) On a front side of the galley compartment 106b facing the in-flight kitchen 100, provision is made for a door 107 for closing off an opening of the galley compartment 106b. As a result of heat insulation properties of the door 107, the interior space of the galley compartment 106b can be temperature-regulated by the temperature regulating system 200 in an energy-efficient manner. The remaining parts of the galley compartment 106b, such as sidewalls, floor or ceiling, can be formed by partitioning elements 108 of the in-flight kitchen 100. Alternatively to this, the galley compartment 106b can comprise a complete body which rests on a partitioning element 108 which forms a bottom of the upper compartment 106.

(31) In both cases, the galley compartment 106b and/or the temperature regulating system 200 comprises an electric connecting element generally designated 250. This electric connecting element 250 serves for connecting the temperature regulating system 200 to an electric current source (not shown) and/or to a control device 70.

(32) For controlling the temperature regulating system 200, a first presetting unit 66 is arranged on, or in the proximity of, the door 107. By this presetting unit 66, a setpoint temperature for the interior space of the galley compartment 106b can be preset (adjusted) by a user. The presetting unit 66 can be put into effect by pushbuttons, rotary selector switches, an indicator element and the like.

(33) In an alternative or additional embodiment, an individual or second presetting unit 68 in the form of a manually operable interface is attached at an optional position on the front side of the in-flight kitchen 100. By this interface, parameters of the cooling system 10 can be selected and/or set by a user, e.g. for presetting a setpoint temperature in the trolley area 104. For the case in which the presetting unit 68 is the single presetting device, a setpoint temperature for the interior space of the galley compartment 106b can additionally also be preset by the presetting unit 68.

(34) Furthermore, a temperature sensor 260 can be arranged in the interior space of the galley compartment 106b. This temperature sensor 260 measures an actual temperature of the first fluid in the interior space of the galley compartment 106b.

(35) Signals emitted from the first presetting device 66, the second presetting unit 68 and/or the temperature sensor 260 are fed to an electronic control unit 70. The electronic control unit 70 is designed or configured for controlling the operation of the temperature regulating system 200 and also of the cooling device 11. As a result, the temperature regulating system 200 can be integrated as a (further) control element of the controlling of the cooling system 10, as a result of which only a data or signal line (bus) is required between the control unit 70 and the temperature regulating system 200.

(36) Alternatively, the temperature regulating system 200 can also be equipped with a separate control unit 240. In this case, the control unit 240 would receive corresponding signals from the first presetting device 66, from the second presetting device 68 and/or from the temperature sensor 260 and correspondingly control the cooling and heating element 210 in order to set a desired setpoint temperature in the interior space of the galley compartment 106b.

(37) The control unit 70 and/or the control unit 240 can also control the valve 62 which is arranged in the waste heat fluid duct 56 and the operation of the delivery device 50 for delivering the second fluid through the first cooling-device fluid duct 38 in dependence of signals which are emitted to the presetting device 66 and/or the presetting device 68, that is to say in dependence of the established setpoint temperature in the galley compartment 106b. Depending on the arrangement of the temperature regulating system 200, a suitable volumetric flow of the fluid, which serves as a heat source or heat sink for the cooling and heating element 210, can consequently be set.

(38) The in-flight kitchen 100 shown in FIG. 3 differs from the arrangement according to FIG. 1 especially by the fact that the waste heat fluid duct 56 comprises a third section 56c and also a fourth section 56d. The third section 56c of the waste heat fluid duct 56 leads in the floor region of the in-flight kitchen 100 to its rear wall 26, whereas the fourth section 56d of the waste heat fluid duct 56 leads upwards adjacent to the rear wall 26 of the in-flight kitchen 100. Arranged next to the first valve 62a, which can be controlled by the actuator 64a, is a second valve 62b, for example in the form of a flap which can be controlled by a second actuator 64b. The second valve 62b is preferably mirror-symmetrical to the first valve 62a and can be moved separately or together with the first valve 62a. As a result, at least a partial volumetric flow of the fluid flow in the waste heat fluid duct 56 can be ducted into the third section 56c and therefore also into the fourth section 56d of the waste heat fluid duct 56.

(39) A third valve 62c is also arranged at the end of the fourth section 56d of the waste heat fluid duct 56, as seen downstream. The third valve 62c, which for example can be designed as a rotatable flap, enables, in a first position shown in FIG. 3B, a connection between the fourth section 56d of the waste heat fluid duct 56 and the second section 42 of the first cooling-device fluid duct 38, as a result of which the first section 40 and second section 42 of the first cooling-device fluid duct 38 are isolated. In a second position, shown in FIG. 3c, of the third valve 62c, the fourth section 56d of the waste heat fluid duct 56 is closed and the first section 40 and second section 42 of the cooling-device fluid duct 38 are interconnected. The position of the third valve 62c can be altered by an actuator (not shown) which is controlled by the control unit 70 or control unit 240.

(40) Consequently, the second fluid which is heated in the cooling device 11 can be ducted from the waste heat fluid duct 56 into the second section 42 (and also third section 44) of the first cooling-device fluid duct 38 in the upper compartment 106 of the in-flight kitchen 100. The one, or the plurality of, fluid inlet(s) 42a shown in FIG. 1 would in this case serve as an air outlet, or outlets. Therefore, heated fluid (heated air) can be fed to a temperature regulating system 200 which is arranged in the section 42 of the first cooling-device fluid duct 38. As a result, an energy-efficient heating of the galley compartment 106b by the cooling and heating element 210 can be achieved. Depending on the position of the second valve 62b and the third valve 62c, cooler ambient air (or galley compartment exhaust air) or heated exhaust air of the cooling device 11 can therefore be ducted to the cooling and heating element 210.

(41) If the third valve 62c in its first position, shown in FIG. 3B, isolates the first section 40 from the second section 42 of the first cooling-device fluid duct 38, the first section 40 of the first cooling-device fluid duct 38 has to be connected via other fluid ducts and/or fluid inlets (not shown) to the environment of the in-flight kitchen 100 in order to be able to provide a sufficient volumetric flow for cooling of the cooling medium in the cooling medium circuit 12. For example, a plurality of second sections 42 of the first cooling-device fluid duct 38 can be arranged next to each other (above and below the plane of the illustration in FIG. 3) and all meet in the first section 40 of the first cooling-device fluid duct 38. The third valve 62c would isolated only one of these second sections 42 of the first cooling-device fluid duct 38 from the first section 40 so that via the remaining second sections 42 fluid can continue to be drawn in and conducted through the cooling device 11.

(42) The subject matter disclosed herein can be implemented in software in combination with hardware and/or firmware. For example, the subject matter described herein can be implemented in software executed by a computer processor or processing unit. In one exemplary implementation, the subject matter described herein can be implemented using a computer readable medium having stored thereon computer executable instructions that when executed by a processor of a computer control the computer to perform steps. Exemplary computer readable mediums suitable for implementing the subject matter described herein include non-transitory devices, such as disk memory devices, chip memory devices, programmable logic devices, and application specific integrated circuits. In addition, a computer readable medium that implements the subject matter described herein can be located on a single device or computing platform or can be distributed across multiple devices or computing platforms.

(43) While at least one exemplary embodiment of the present invention(s) is disclosed herein, it should be understood that modifications, substitutions and alternatives may be apparent to one of ordinary skill in the art and can be made without departing from the scope of this disclosure. This disclosure is intended to cover any adaptations or variations of the exemplary embodiment(s). In addition, in this disclosure, the terms “comprise” or “comprising” do not exclude other elements or steps, the terms “a”, “an” or “one” do not exclude a plural number, and the term “or” means either or both. Furthermore, characteristics or steps which have been described may also be used in combination with other characteristics or steps and in any order unless the disclosure or context suggests otherwise. This disclosure hereby incorporates by reference the complete disclosure of any patent or application from which it claims benefit or priority.