METHOD AND APPARATUS FOR AIRCRAFT GALLEY COOLING
Described in this application for patent is a novel method and apparatus for providing cooling to an aircraft galley. The aircraft galley is cooled by means of a central aircraft cooling line, including a phase change cooling system and a ram air heat exchanger.
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The present invention relates to a configurable cooling apparatus, and more specifically to a heat exchanger circuit for use in cooling one or more aircraft galley monuments.
Galleys in private or commercial aircraft are very common. These areas store food and beverages for aircraft passengers on long flights and have become a staple of the airline industry. These galleys often incorporate parking areas (or galley cooling units) where a food transport cart can be stored. The galley cooling units include a cooling element for keeping the food at a temperature lower than the surrounding environment.
One method of providing cooling to these galley cooling units is the use of a central aircraft cooling line that provides cooling throughout the aircraft and a heat exchanger between the central aircraft cooling line and the galley cooling unit. A fan module may also be provided for circulating the cool air into or over the galley cooling unit to provide cooling.
The central aircraft cooling line contains a fluid which may have a high specific heat, that is, the fluid is able to absorb large amounts of heat without a significant change in temperature. This allows the fluid of the central aircraft cooling line to maintain a relatively stable temperature while absorbing heat from multiple locations.
The central aircraft cooling line is typically a closed system where the cooling fluid (or coolant) is cycled through the cooling line to draw heat from various components. Therefore, whatever heat is absorbed by the coolant must be extracted to maintain cooling.
The central aircraft cooling line is currently cooled by use of a phase change circuit that utilizes a refrigerant in a separate and closed evaporator/condenser fluid line to cool the central aircraft cooling line, and therefore the coolant contained therein. This process is well known to those in the art and generally includes a compressor for compressing a gas, a condenser for converting the gas into a liquid, and an evaporator for converting the liquid into a gas to thereby draw heat from the surrounding environment.
The compressor of a phase change cooling circuit produces heat in excess of that absorbed by the evaporator and this heat is dissipated through the condenser. As the gas is condensed into a liquid, heat is released and preferably removed by means of a tertiary closed-circuit cooling line.
The tertiary closed-circuit cooling line generally cycles between a first heat exchanger a second heat exchanger. The first heat exchanger is in thermal communication with the tertiary line and the condenser and the second heat exchanger is in thermal communication with the tertiary line and the ram air. Ram air is air that is drawn from the boundary layer (or near boundary layer) of the outside of the aircraft and passed through a heat exchanger matrix. Ram air at approximately 35,000 feet is typically −55° C. (−67° F.), and may vary by up to 20° C. (36° F.) depending on weather conditions.
The current method of providing cooling to the galley cooling units requires a number of phase change coolers to provide adequate cooling for the central aircraft cooling line. A cooling method and apparatus that would remove one or more of the phase change coolers would reduce the weight of the aircraft and improve efficiency.
SUMMARYDescribed herein is a novel method for cooling the galley of an aircraft. The method includes the steps of providing a preferred temperature for a cooling line, and the cooling line includes a coolant, a heat source, a phase change cooler, and a heat exchanger. Heat from the heat source is collected by means of the coolant which is then transferred to the heat exchanger. The heat is transferred from the heat exchanger to the air source and the output temperature of the coolant from the heat source is determined. If the output temperature is higher than the preferred temperature, than the phase change cooler is engaged to provide supplemental cooling of the coolant.
Also described herein is an apparatus for aircraft galley cooling. The apparatus comprises a central cooling line, a galley monument, and a preferred temperature for the central cooling line. The cooling line further includes a phase change cooling system, a ram heat exchanger and a galley heat exchanger in thermal communication with the galley monument. If an output temperature of the heat exchanger is less than or equal to the preferred temperature, then the phase change cooling system may be disengaged.
Also described herein is a method for regulating temperature in a central aircraft cooling line. The method includes the steps of providing a phase change cooling system and a heat exchanger, both in thermal communication with the central aircraft cooling line. The heat loss through the heat exchanger is determined and the phase change cooling system is selectively engaged or disengaged based on this heat loss.
The phase change cooling system 114 is generally shown in
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Finally, the central aircraft cooling line 112 is passed through the ram heat exchanger 120 which includes a serpentine arrangement similar to heat exchangers previously described. Heat is drawn from the ram heat exchanger 120 by means of ram air 144 that passes over the heat exchanger 120. This ram air is significantly cold at altitude (for example, −55° C. at 35,000 feet) to provide sufficient cooling for the cold air system.
As shown in
The system is preferably automated to maintain a preferred temperature within the system. Because of the electrical draw and increased heat generated by the phase change coolers 114, it is desirable to reduce the time that these systems are in use. Therefore, a system as illustrated in the flowchart of
As shown in
The output temperature (TOUT) of the ram heat exchanger 120 is next compared against a known preferred temperature (TPREF) of the cooling line. This preferred temperature (TPREF) may be a constant or determined based on the amount of cooling required. For example, if fewer galley cooling units 116 are in use, the temperature of the central aircraft cooling line 112 does not need to be as cool as less heat is being introduced into the line 112. The preferred temperature (TPREF) is typically within a range from a minimum preferred temperature (TMIN) to a maximum preferred temperature (TmAx). When a temperature is referred to as “equal to” the preferred temperature (TPREF), this means that the temperature is within the acceptable range between the minimum (TMIN) and maximum (TmAx) preferred temperatures. A temperature referred to as “below” or “lower than” the preferred temperature (TPREF) is a temperature that is below the minimum preferred temperature (TMIN). A temperature referred to as “above” or “higher than” the preferred temperature (TPREF) is a temperature that is above the maximum preferred temperature (TMAX).
If the output temperature (TOUT) of the ram heat exchanger 120 is above the preferred temperature (TPREF), then the ram heat exchanger 120 is not dissipating enough heat to cool the central aircraft cooling line 112 on its own, and supplemental cooling from the phase change coolers 114 must be introduced. Based on the temperature difference between the ram heat exchanger 120 output (TOUT) and the preferred temperature (TPREF), one or more phase change coolers 114 may be engaged to produce the desired cooling. Alternatively, phase change coolers 114 may be engaged in sequence to progressively step down the temperature in the central aircraft cooling line 112.
The output temperature (TOUT) of the ram heat exchanger 120 may also be below the preferred temperature (TPREF) for the central aircraft cooling line 112. In this case, the phase change coolers 114 do not need to be engaged, and control of the system will shift to the temperature sensor 154 that measures the combined temperature (TCOMB).
The combined temperature (TCOMB) is the temperature of the fluid from the ram heat exchanger 120 and bypass path 156 modified by the proportion diverted by the diverter valve 158. The combined temperature (TCOMB) may be modified by adjusting the diverter valve 158 to allow more or less flow through the bypass path 156. The fluid flowing through the bypass path 156 maintains the same high temperature (TOUT) as the input fluid to the ram heat exchanger 120, and therefore is used to raise the temperature of the central aircraft heating line 112 to prevent the combined temperature (TCOMB) from falling below the preferred temperature (TPREF).
The combined temperature (TCOMB) may be either lower than, equal to, or higher than the preferred temperature (TPREF). If the combined temperature is below the preferred temperature (TPREF), then the diverter valve 158 may be adjusted to increase the flow through the bypass path 156 so that the combined temperature (TCOMB) reaches the preferred temperature (TPREF). This is preferably maintained by a positive feedback control system that monitors and adjusts the diverter valve 158 to maintain the preferred temperature (TPREF).
If the combined temperature (TCOMB) is higher than the preferred temperature (TPREF) (and the output temperature (TOUT) is less than the preferred temperature (TPREF)), then the diverter valve 158 must be adjusted to reduce the flow through the bypass path 156 to thereby reduce the temperature (TCOMB) of the combined fluid.
If the combined temperature (TCOMB) is equal to the preferred temperature (TPREF) (and the output temperature (TOUT) is less than the preferred temperature (TPREF)), then the flow through the bypass path 156 is appropriate and should be maintained.
It may be appreciated by those having skill in the art that the bypass path 156 and diverter valve 158 may be combined with any of the heat exchanger matrices in the above described system, and a control system may be devised to monitor input, output, and combined temperatures within the central aircraft cooling line 112. For example, sensors (not shown) may detect the temperature or presence of galley carts 153 in one or more of the galley cooling units 116 and selectively allow flow through the heat exchanger 146 of the galley cooling unit 116 to conserve energy.
The invention has been described as utilizing a ram heat exchanger in communication with an exterior air source to provide heat transfer from the central cooling line. However, the ram heat exchanger may be replaced with any heat exchanger in thermal communication with outside air. One example of such a heat exchanger is a series of cooling lines adjacent or near the skin of the aircraft that utilize conduction to transfer heat from the cooling line to the aircraft skin and then to the outside air.
The invention has been generally described with respect to a preferred embodiment. This embodiment is intended to be exemplary rather than limiting. Further, those skilled in the art will recognize that various modifications of the described embodiment may be made without departing from the scope of the invention. Any limitations will appear in the claims as allowed.
Claims
1. A method for cooling the galley of in an aircraft:
- providing a preferred cooling line temperature;
- providing a cooling line including: a coolant; a heat source; a phase change cooler; and a heat exchanger in thermal communication with an air source;
- drawing heat from said heat source with said coolant;
- transferring said coolant to said heat exchanger;
- transferring said heat from said coolant to said air source;
- determining an output temperature of said coolant as it exits said heat exchanger; and
- engaging said phase change cooler if said output temperature is higher than said preferred temperature.
2. The method of claim 1 wherein said air source is an atmosphere outside of the aircraft.
3. The method of claim 2 wherein said heat source is a heat exchanger in thermal communication with a galley.
4. The method of claim 3 wherein said air source comprises a ram air source.
5. The method of claim 4 wherein said cooling line further includes a bypass line.
6. The method of claim 5 wherein said cooling line further includes a diverter valve for diverting a first portion of said coolant through said bypass line and a second portion of said coolant through said heat exchanger, and wherein said first and second portions are combined after said second portion passes through said heat exchanger.
7. The method of claim 6 wherein said preferred cooling line temperature comprises a range between a minimum preferred temperature and a maximum preferred temperature.
8. The method of claim 7 further including the step of adjusting the diverter valve to maintain said preferred temperature.
9. An apparatus for aircraft galley cooling comprising:
- a central cooling line including: a phase change cooling system, a ram heat exchanger in thermal communication with an atmosphere including an output temperature, and a galley heat exchanger;
- a preferred temperature for said central cooling line; and
- a galley monument in thermal communication with said galley heat exchanger;
- wherein said phase change cooling system is disengaged if said output temperature is less than or equal to said preferred temperature.
10. The apparatus of claim 9 further comprising a fan adjacent said galley heat exchanger, said fan for aiding thermal communication between said galley heat exchanger and said galley monument.
11. The apparatus of claim 9 wherein said central cooling line further includes a coolant.
12. The apparatus of claim 11 further comprising a bypass line for diverting said coolant around said ram heat exchanger.
13. The apparatus of claim 12 further comprising a diverter valve for transferring all or a portion of said coolant through said bypass line.
14. A method of regulating temperature in a central aircraft cooling line comprising the steps of:
- providing a phase change cooling system in thermal communication with said central aircraft cooling line;
- providing a heat exchanger in thermal communication with an exterior of said aircraft and said central aircraft cooling line;
- determining a heat loss through said heat exchanger;
- selectively engaging or disengaging said phase change cooling system depending on said heat loss.
15. The method of claim 14 further comprising a heat source.
16. The method of claim 15 further comprising the step of determining a heat gain through said heat source.
17. The method of claim 16 further comprising determining a net heat gain based on said heat loss and said heat gain.
18. The method of claim 17 wherein said phase change cooling system comprises a plurality of refrigerators.
19. The method of claim 18 further comprising the step of engaging one or more of said plurality of refrigerators if said net heat gain is positive.
20. The method of claim 17 further comprising the step of diverting a portion of said coolant around said heat exchanger if said net heat gain is negative.
Type: Application
Filed: May 17, 2011
Publication Date: Nov 22, 2012
Applicant: THE BOEING COMPANY (Chicago, IL)
Inventors: Rodney Millar (Mukilteo, WA), Steve G. Mackin (Bellevue, WA)
Application Number: 13/109,693
International Classification: F25B 41/00 (20060101); F25D 17/06 (20060101);