RU2458824C2 - Method and system for cooling aircraft onboard device - Google Patents

Abstract

FIELD: transport.

SUBSTANCE: set of invention relates to water distribution for cooled drinking water supply for airliner passengers. Cooled drinking water distribution system comprises evaporator made up of drinking water tank to receiving water to be evaporated. Said evaporator communicates with drinking water feed line to receive water therefrom and valve to bleed cooled water from evaporator. Besides, proposed system incorporates first absorber with medium to absorb drinking water evaporated in evaporator, second absorber with medium to absorb drinking water evaporated in evaporator, and control system to establish or shut off communication between evaporator and first and/or second absorber.

EFFECT: distribution with reliable and continuous cooling.

12 cl, 4 dwg

Description

FIELD OF THE INVENTION

The present invention relates to a cooling system, as well as to a method for cooling a device on board an aircraft.

State of the art

On board the aircraft there are a large number of technical devices that generate heat and which must be cooled in order to guarantee safe operation. In addition, on board the aircraft there are a variety of enclosed spaces, the so-called compartments, in which the temperature must be kept lower than the temperature in the cockpit. For this reason, a variety of cooling systems are provided on board the aircraft.

For example, according to patent document DE 4105034 A1, an autonomous cooling device is provided for each kitchen in which cold air is used as the cooling medium and which is equipped with its own compression type refrigeration machine (air cooler).

As an alternative, patent document DE 4340317 C2 describes a centralized compression type refrigeration machine, the refrigerating capacity of which is distributed on board an aircraft through a refrigerant line. The disadvantage of cooling systems equipped with a compression type refrigeration machine is that during operation of this machine there is a lot of noise, which is heard in the passenger cabin of the aircraft, and therefore is perceived as a hindrance. Moreover, due to the presence of rotating parts, systems of this kind are characterized by low reliability.

In addition, according to patent document DE 3812739 C1, a refrigerating chamber provided in the aircraft kitchen is located near the outer skin of the aircraft, and a cold air chamber is provided between the refrigerating chamber and the outer skin of the aircraft. A cold air chamber exchanges heat with atmospheric air through the outer skin. The disadvantage of this type of heat exchanger is that atmospheric air cannot be used as a heat sink at high ambient temperatures. As a consequence, it is not possible to provide sufficient cooling capacity when the aircraft is on the ground on hot days.

Disclosure of invention

An object of the present invention is to provide a cooling system, as well as a method of cooling a device on board an aircraft that allows reliable and continuous cooling of fuel and other devices on board the aircraft.

This problem is solved by using a cooling system to cool a device on board an aircraft having the features of paragraph 1 of the claims, and also a method of cooling a device on board an aircraft having the features of paragraph 9 of the claims.

According to the invention, a cooling system for cooling a device on board an aircraft includes an evaporator for receiving a vaporization fluid. According to the invention, one or more evaporators can be used in the cooling system depending on the need for cooling energy. For example, the evaporator may be in the form of a plate filled with an evaporated fluid. The evaporator or evaporators can completely or partially enclose the refrigerated volume, or they can be placed in a specific place or in certain places of the refrigerated volume. Alternatively, the evaporator itself may be a storage of a cooled fluid, which will be explained in more detail later. As the vaporized fluid supplied to the evaporator, for example, water or alcohol can be used.

According to the invention, the cooling system includes a first absorber that contains a medium for absorbing the fluid evaporated in the evaporator. In addition, a second evaporator is provided, which also contains a medium for absorbing the fluid evaporated in the evaporator. As the absorbing medium, it is preferable to use finely porous material, such as, for example, activated carbon, zeolite, silica gel or the like. When the vaporization of the fluid evaporated in the evaporator by the absorbing medium, the absorption of the gaseous fluid occurs in several molecular layers of the absorbing medium. During the course of this physical-energy process, which corresponds to condensation, the heat of condensation is released, therefore, to regenerate the first and second absorbers, that is, to separate the absorbed fluid molecules from the absorbing medium, it is necessary to communicate the regeneration energy to the first and second absorbers. As a result, during the regeneration of the absorber, it is not able to absorb the fluid evaporated in the evaporator.

Therefore, according to the invention, the cooling system includes a control system that is configured to establish or interrupt the flow connection between the evaporator and the first and / or second absorber / absorbers. The flow connection between the evaporator and one of the two absorbers can be interrupted by the control system so that the absorber, which is no longer connected upstream to the evaporator, can be regenerated by supplying it with regeneration energy. The control system can connect the evaporator to another absorber during the regeneration phase of the absorber in order to guarantee continuous operation of the cooling system according to the invention.

For example, a control system may interrupt the flow connection between the evaporator and one of the two absorbers if the partial pressure of the fluid evaporated in the evaporator in the absorber corresponds to the partial pressure of the fluid in the evaporator. However, if necessary, the control system can at any time establish or interrupt the flow connection between the evaporator and the first and / or second absorber / absorbers. The control system may also be configured to control the volumetric flow rate of the fluid evaporated in the evaporator in the direction of the first and / or second absorber / absorbers. Due to this, you can set the desired temperature and / or the desired mode of operation of the device on board the aircraft, which is cooled using a cooling system.

In the cooling system according to the invention, the fluid evaporated in the evaporator absorbs the heat generated by the device to be cooled on board the aircraft, and during this process changes its state of aggregation. Therefore, the cooling system can work without moving parts, which allows you to get rid of the inconvenient noise of the machine and increase the overall reliability of the system. Moreover, the system can be relatively easily mounted on board the aircraft and during the evaporation process can supply cooling energy regardless of the power supply system on board the aircraft. Finally, since the system does not use fluorocarbons (HFC) as a refrigerant, it is completely safe from an environmental point of view and allows you to adjust the specific heat, as well as regulate the specific energy consumption.

In one preferred embodiment of the cooling system according to the invention, the first and / or second absorber / absorbers are included / included in the cooling circuit or energy supply system that provides the energy required to regenerate the first and / or second absorber / absorbers. For example, the energy necessary for the regeneration of the first and / or second absorber / absorbers can be taken from the spent cabin air, which as a result is cooled to a lower temperature. Higher overall aircraft performance is obtained by combining the cooling system of the invention with other systems on board the aircraft. Moreover, you can get a gain in weight. In the cooling system of the invention, the regeneration of the absorber can be isolated from the cooling function of the system. For this reason, the regeneration energy communicated to the absorber does not affect the device cooled by the cooling system.

The first and / or second absorber / absorbers are preferably attached to a fluid removal device that is configured to remove fluid released from the first and / or second absorber / absorbers during the regeneration of the first and / or second absorber / absorbers. Therefore, in the cooling system according to the invention, the fluid released from the absorbing medium in the first and / or second absorber / absorbers is not returned directly to the evaporator. For this reason, the cooling system according to the invention is extremely flexible in use. A device for discharging a fluid may, for example, include a first bypass line connected to the first absorber, as well as a second bypass line connected to the second absorber. In the first and / or second bypass line / lines, appropriate control valves may be provided for controlling the discharge of fluid released from the first and / or second absorber / absorbers. The first and second bypass lines can go into a common prefabricated bypass line.

A device for draining the fluid can, for example, be connected to a refrigerator, which serves to cool the fluid released from the absorbing medium in the first and / or second absorber / absorbers to the desired temperature. The refrigerator is preferably connected downstream to the fluid inlet of the evaporator in order to obtain a closed cooling system. In a cooling system that includes several evaporators, the fluid inlet in each evaporator is preferably connected to a separate supply line in which there is a control valve for controlling the flow of fluid from the refrigerator to the corresponding evaporator. Separate supply lines may exit to a combined supply line connected to a refrigerator.

A device for discharging a fluid in a cooling system according to the invention is preferably connected to a wastewater system on board an aircraft. In this embodiment, the systems in the evaporator use water as the vaporized fluid. Water that has been released from the absorbent medium in the first and / or second evaporator / s and is present in the form of steam is withdrawn from the first and / or second evaporator / s by means of a fluid removal device into the wastewater system on board the aircraft and supplied, for example in the water storage tank.

The fluid inlet port in the evaporator may be connected to the aircraft water supply system in order to obtain a half-open cooling system included in the aircraft water supply system.

In one preferred embodiment of the cooling system of the invention, a water storage tank that is involved in the water distribution system is used as an evaporator. In water distribution systems that are currently used on board aircraft to supply passengers with drinking water, it is common practice to cool the tank for storing drinking water with active cooling means, for example, using a compression type refrigeration machine. Therefore, the present invention provides an integrated water distribution / cooling system. Drinking water that enters the water storage tank is evaporated and supplied to the first and / or second absorber / absorbers if the temperature of the water entering the water storage tank exceeds the required value. As a result, cooling energy is released, due to which the non-evaporated water remaining in the water storage tank is cooled.

During normal operation of the drinking water distribution system used on board the aircraft, a certain overpressure is maintained in the drinking water storage tank in order to provide the pressure head required for withdrawing drinking water from the drinking water storage tank. However, in order to initiate the evaporation process described above, a reduced pressure must be created in the water storage tank. Therefore, the water storage tank is preferably connected to a pressure control system which, in accordance with the requirements, creates a reduced or overpressure in the water storage tank.

In a method of cooling a device on board an aircraft according to the invention, fluid is evaporated in the evaporator and a flow connection is established between the evaporator and the first absorber so that the vaporized fluid in the evaporator is absorbed by the medium contained in the first absorber. At a predetermined point, for example, when the partial pressure of the fluid evaporated in the evaporator in the first absorber becomes equal to the partial pressure of the fluid in the evaporator, the flow connection between the evaporator and the first absorber is interrupted and a flow connection is established between the evaporator and the second absorber so that the fluid evaporated in the evaporator was absorbed by the medium contained in the second absorber. The regeneration energy is reported to the first absorber while the evaporator is connected to the second absorber. In the method according to the invention, the flow connection between the evaporator and the second absorber can be interrupted accordingly, and instead a flow connection between the evaporator and the first absorber is established, while regeneration energy is reported to the second absorber. Thus, the present invention provides a method for continuous adsorption cooling of a device on board an aircraft.

The method according to the invention implements a continuous process of cooling the device on board the aircraft by alternately using the first and second absorbers.

The energy required for the regeneration of the first and / or second absorber / absorbers is preferably provided by the cooling circuit or an energy source available on board the aircraft, which includes the first and / or second absorber / absorbers. Such an energy source can be, for example, air taken from a power plant.

Fluid generated during the regeneration of the first and / or second absorber / absorbers can be removed from the first and / or second absorber / absorbers using a fluid removal device connected to the first and / or second absorber / absorbers.

For example, the fluid evolved during the regeneration of the first and / or second absorber / absorbers can be fed to a refrigerator through a fluid removal device, which in turn is connected to a fluid inlet in the evaporator.

The fluid released during the regeneration of the first and / or second absorber / absorbers can be supplied to the wastewater system on board the aircraft by means of a fluid removal device.

In one preferred embodiment of the method of cooling a device on board an aircraft according to the invention, water is supplied to a fluid inlet in the evaporator from the aircraft water supply system.

The water storage tank that is involved in the water distribution system on board the aircraft is preferably used as an evaporator.

The pressure in the water storage tank can be adjusted using a pressure control system connected to the water storage tank.

In the method for cooling a device on board an aircraft according to the invention, the cooling efficiency of the device on board an aircraft is preferably not reduced.

Brief Description of the Drawings

Preferred embodiments of the invention are explained in detail using the attached schematic diagrams, where:

Figure 1 shows the basic structure of a device cooling system according to the invention on board an aircraft;

Figure 2 shows a system for cooling a device on board an aircraft in accordance with the invention in the form of a closed system;

Figure 3 shows a device cooling system according to the invention on board an aircraft, made in the form of a half open system; and

4 shows a cooling system according to the invention, in which a water storage tank provided on board an aircraft in a water distribution system is used as an evaporator.

The implementation of the invention

Figure 1 shows a system 10 for cooling a device 12 on board an aircraft, which system includes three evaporators 14, 16, 18 that are housed in a cooled device 12 on board an aircraft. Fluid F, for example alcohol or water, enters each evaporator. This fluid is intended for evaporation in the evaporator 14, 16, 18 and the supply of cooling energy released when its aggregate state changes, into the cooled device 12 on board the aircraft.

Using the connecting line 20, the evaporators 14, 16, 18 are connected to the control system 22, which is made in the form of a three-way valve. Using the control system 22, the evaporators 14, 16, 18 can be connected to the first 24 or second 26 absorbers or separated from the first 24 and / or second 26 absorbers.

The control system 22 is made in the form of a three-way valve with a variable flow cross-section in order to be able to control the flow of fluid from the evaporators 14, 16, 18 to the first 24 and / or second 26 absorbers / absorbers.

The first 24 and second 26 absorbers contain a finely porous absorbent medium 28, for example, activated carbon, zeolite, or silica gel. The absorption medium 28 has a large surface so that the absorption of the fluid F evaporated in the evaporators 14, 16, 18 occurs in only a few molecular layers of the absorption medium 28.

The process of absorption by the absorbing medium 28 of the fluid evaporated in the evaporators 14, 16, 18 is accompanied by the release of energy. Therefore, for the reverse process, that is, the release of molecules from the absorbing medium 28, it is necessary to provide energy supply. In this regard, the first 24 and second 26 absorbers are connected to an energy supply device 30, 32, by means of which regeneration energy can be communicated to the first 24 and second 26 absorbers.

The sequence of operation of the cooling system 10 is explained below. As already mentioned, during operation of the cooling system 10, the fluid F entering the evaporators 14, 16, 18 evaporates. The cooling energy released during this process is supplied to the cooling device 12 on board the aircraft. The fluid F exiting the evaporators 14, 16, 18 in a gaseous state is fed through the control system 22 to the first absorber 24 so that the fluid molecules are absorbed by the surface of the absorbing medium 28 in the first absorber 24.

If the partial pressure of the fluid F evaporated in the evaporators 14, 16, 18 becomes equal to the partial pressure of the fluid in the first absorber 24, then the absorption medium 28 in the first absorber 24 has become “saturated” and needs to be regenerated. To this end, thermal energy is reported to the first absorber 24 by means of an energy supply device 30. As a result, fluid molecules absorbed by the surface of the absorbing medium 28 are released, and as a result, the absorbing medium 28 is again ready to accept new fluid molecules.

During the regeneration of the absorption medium 28 in the first absorber 24, the control system 22 interrupts the flow connection between the evaporators 14, 16, 18 and the first absorber 24. At the same time, a flow connection is established between the evaporators 14, 16, 18 and the second absorber 26. Therefore during the regeneration of the absorption medium 28 in the first absorber 24, the fluid F evaporated in the evaporators 14, 16, 18 enters the second absorber 26, where it is absorbed by the absorption medium 28.

Similarly, during the regeneration of the absorbing medium 28 in the second absorber, the flow connection between the evaporators 14, 16, 18 and the second absorber 26 can be interrupted, and instead the flow connection between the evaporators 14, 16, 18 and the first absorber 24 can be restored. Thus, a continuous operation of the cooling system 10 is provided. Moreover, the cooled device 12 on board the aircraft is isolated from the power supply devices 30, 32 that supply the regeneration energy to the first and second absorbers 24, 26, as a result of which the regeneration energy communicated to the first and second absorbers 24, 26 does not affect the device 12.

During operation of the cooling system 10, a reduced pressure is maintained in the evaporators 14, 16, 18 and in the first 24 and / or second 26 absorbers, which are connected to the evaporators 14, 16, 18. The cooling capacity of the cooling system 10 is controlled by a control system 22, which controls the volumetric flow rate of the fluid supplied by the evaporators 14, 16, 18 to the first 24 and / or second 26 absorber / absorbers. Therefore, the temperature of the cooled device 12 on board the aircraft can be set by adjusting the volumetric flow rate of the fluid coming from the evaporators 14, 16, 18 in the direction of the first 24 and / or second 26 absorbers / absorbers, using the control system 22 in the form of a three-way valve with variable flow cross-section. Due to this, the cooling system 10 provides active control of heat consumption.

Figure 2 shows the cooling system 10, made in the form of a closed system that can be used on board the aircraft to cool the kitchen. In the cooling system 10, the first 24 and second 26 absorbers are included in the cooling circuit (not shown in detail in FIG. 2) so that the regeneration energy communicated to the first 24 and second 26 absorbers in the regeneration step can be taken from the spent cabin air, removed from the cockpit of the aircraft. As a result of this, an operation mode of the cooling system 10 that is particularly effective, from the point of view of energy saving, can be ensured, which makes it possible to increase the overall level of aircraft efficiency.

The first 24 and second 26 absorbers of the cooling system 10 are connected to a fluid removal device 34, with which it is possible to remove from the first 24 and second 26 absorbers a fluid F in a gaseous state, which is released from the absorbing medium 28 in the first 24 at the regeneration step and second 26 absorbers. The fluid discharge device 34 includes a first bypass line 36 connected to the first absorber 24, and a second bypass line 38 connected to the second absorber 26. Corresponding valves 40, 42 are provided in the first 36 and second 38 bypass lines for controlling the outlet fluid from the first 24 and second 26 absorbers.

The first 36 and second 38 bypass lines exit to the collection branch pipe 44, which is connected to the refrigerator 46. The refrigerator 46 is cooled to the desired temperature of the fluid F, taken from the first 24 and second 26 absorbers at the stage of regeneration of the first 24 and second 26 absorbers.

A hole 48 for discharging fluid in the refrigerator 46 is connected to the supply lines 52, 54, 56 through the prefabricated supply line 50, through which the fluid F cooled in the refrigerator 46 can be directed to evaporators 14, 16, 18. In the supply lines 52, 54 56, corresponding valves 58, 60, 62 are provided for controlling the flow of fluid from the refrigerator 46 to the individual evaporators 14, 16, 18.

The cooling system 10 shown in FIG. 3, which can be similarly used to cool the kitchen, is different from the system shown in FIG. 2. The difference is that it is designed as a half open system. A distinctive feature of the cooling system 10 of FIG. 3 is, in particular, that it is included in the water supply system, or wastewater system on board the aircraft, which is not shown in detail. For this purpose, water from the aircraft’s water supply system is directed to the evaporators 14, 16, 18 through the combined supply line 50 and the supply lines 52, 54, 56 as a fluid F, which must be turned into a gaseous state in the evaporators 14, 16, 18 .

The first 24 and second 26 absorbers by means of a device 34 for draining the fluid connected to the wastewater system on board the aircraft, for example, with a tank for storing water. Otherwise, the structure and operation mode of the cooling system 10 shown in FIG. 3 corresponds to the structure and operation mode of the system of FIG. 2.

Figure 4 shows a special application of the cooling system 10, in which the evaporator 14, which serves the evaporation fluid F, is a water storage tank that is part of a drinking water distribution system for supplying passengers with chilled drinking water on board an aircraft. The evaporator 14 in the form of a tank for storing water is connected via a line 64 for supplying drinking water with a drinking water distribution system, which is not shown in detail. A valve 65 is provided in the line 64 for supplying drinking water, by which the supply of drinking water to the evaporator 14 is regulated in the form of a water storage tank. The evaporator 14 in the form of a tank for storing water, in addition, includes a tap 66 of drinking water for the selection of chilled drinking water. The selection of drinking water through the tap 66 drinking water regulate using a valve 67.

The evaporator 14 is additionally connected to a pressure control system 68, which serves to control the pressure in the evaporator 14 in the form of a potable water tank. The pressure control system 68 via a valve 70 is connected to the evaporator 14 and can additionally create a reduced pressure or overpressure in the evaporator 14.

The first 24 and second 26 absorbers of the cooling system 10 are connected to the wastewater system on board the aircraft using the water drainage device 34, as in the case of the system shown in FIG. 3.

The sequence of operation of the system 10 shown in FIG. 4 is explained below. After cooling the water entering the evaporator 14 in the form of a tank for storing drinking water to the desired distribution temperature, overpressure is maintained in the evaporator 14 using the pressure control system 68 in order to provide the supply pressure in the drinking water tap 66 required for the selection of drinking water water from the evaporator 14.

On the other hand, if the temperature of the drinking water in the evaporator 14 exceeds the required sampling temperature, a reduced pressure is created in the evaporator, using the pressure control system 68, so that the drinking water entering the evaporator can transition to a gaseous state of aggregation. The cooling energy released in this case can be used to cool the remaining drinking water in the evaporator 14. Otherwise, the structure and operation of the cooling system 10 of FIG. 4 correspond to the structure and operation of the cooling system shown in FIG.

Claims (12)

1. A water distribution system for supplying passengers on board an aircraft with chilled drinking water, including
an evaporator (14), made in the form of a tank for storing drinking water, used to receive the drinking water to be evaporated; wherein the evaporator (14) is connected to a drinking water supply line (64) for supplying drinking water to the evaporator (14) and a drinking water tap (66) for collecting chilled drinking water from the evaporator (14);
a first absorber (24) containing a medium (28) for absorbing drinking water evaporated in an evaporator (14);
a second absorber (26) containing a medium (28) for absorbing drinking water vaporized in an evaporator (14); and
a control system (22) configured to establish or interrupt the flow connection between the evaporator (14) and the first (24) and / or second (26) absorber (s). 2. The water distribution system according to claim 1, characterized in that the first (24) and / or second (26) absorber (s) are included (included) in the cooling circuit or energy supply system, which provides the energy required for regeneration of the first (24) and / or the second (26) sink (s). 3. The water distribution system according to claim 1, characterized in that the first (24) and / or second (26) absorber (s) are connected (connected) to a device (34) for draining the fluid, which is configured to remove drinking water released from the first (24) and / or second (26) scavenger (s) during the regeneration of the first (24) and / or second (26) scavenger (s). 4. The water distribution system according to claim 3, characterized in that the device (34) for draining the fluid is connected to a refrigerator (46), which, in turn, is connected downstream with a hole for drinking water inlet in the evaporator (14), or a device (34) for draining the fluid is connected to the wastewater system on board the aircraft. 5. The water distribution system according to claim 1, characterized in that the water storage tank is connected to a pressure control system (68) in the water storage tank. 6. A method for distributing chilled drinking water to passengers on board an aircraft, the method comprising the following steps;
supply of drinking water to the evaporator (14), made in the form of a tank for storing drinking water, through the line (64) of the supply of drinking water;
the evaporation of part of the drinking water in the evaporator (14);
establishing a flow connection between the evaporator (14) and the first absorber (24) to ensure the absorption of drinking water evaporated in the evaporator (14) with the medium (28) contained in the first absorber (24);
interruption of the flow connection between the evaporator (14) and the first absorber (24);
establishing a flow connection between the evaporator (14) and the second absorber (26) to ensure the absorption of drinking water evaporated in the evaporator (14) by the medium (28) contained in the second absorber (26);
communication of regeneration energy to the first absorber (24) with the connection between the evaporator (14) and the second absorber (26),
and the selection of drinking water, cooled by the cooling energy released during the evaporation of part of the drinking water, from the evaporator (14) through the tap (66) of drinking water. 7. The method according to claim 6, characterized in that they implement a continuous cooling process by alternately using the first (24) and second (26) absorbers (absorbers). 8. The method according to claim 6, characterized in that the energy required for the regeneration of the first (24) and / or second (26) absorbers (absorbers) is provided by means of a cooling circuit or an energy source provided on the aircraft, which includes the first (24) and / or a second (26) absorber (s). 9. The method according to claim 6, characterized in that the drinking water released during the regeneration of the first (24) and / or second (26) scavenger (s) is removed from the first (24) and / or second (26) scavenger ( absorbers) using a device (34) for draining a fluid connected to the first (24) and / or second (26) absorber (s). 10. The method according to claim 9, characterized in that the drinking water released during the regeneration of the first (24) and / or second (26) scavengers (scavengers) is fed to a refrigerator (46) using a device for draining the fluid ), which, in turn, is connected downstream to the drinking water inlet in the evaporator (14), or drinking water released during the regeneration of the first (24) and / or second (26) scavenger (s), using the device (34) for discharging a fluid, it is supplied to a wastewater system on board an aircraft. 11. The method according to claim 6, characterized in that the pressure in the tank for storing drinking water is regulated using a pressure control system (68) connected to the tank for storing water. 12. The method according to claim 6, characterized in that the regeneration of the absorbers (24, 26) is carried out in such a way as to exclude a decrease in the efficiency of cooling drinking water.

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