GB2150278A

GB2150278A - Cooling cabins of parked aircraft

Info

Publication number: GB2150278A
Application number: GB08428965A
Authority: GB
Inventors: Richard Axel Haglund; Robert Edward Tupack
Original assignee: Teledyne Industries Inc
Current assignee: TDY Industries LLC
Priority date: 1983-11-18
Filing date: 1984-11-16
Publication date: 1985-06-26
Also published as: MX161927A; GB2150278B; CA1291643C; KR920007845B1; AU3548984A; FR2555131A1; IT8449175A0; KR850004066A; NZ210198A; SG6388G; IT8449175A1; ES537719A0; DE3442001A1; ES8606167A1; AU575355B2; GB8428965D0; FR2555131B1; IT1178241B

Abstract

A system 10 for cooling aircraft passenger cabins is located external to the aircraft and comprises a cooling unit 14, a heat exchanger 16 and a blower 18 which reduce the temperature of the air at outlet 22 to such a level that the air entering the aircraft inlet is below 35 DEG F. The air leaves the heat exchanger at 25 DEG F and, after passing through a flexible hose, enters the aircraft at 30 DEG F. The cooling unit includes a condenser 44 and a bypass valve 50 to enable de-icing of the heat exchanger. The cold air supplied to the aircraft has a low humidity and enables a reduced flow rate to be used compared with prior art systems. <IMAGE>

Description

SPECIFICATION Improved apparatus and method of air-conditioning parked aircraft Background of the invention This invention relates to aircraft air-conditioning system, and, more particularly, to apparatus and method of cooling the passenger cabins of parked aircraft.

A number of systems have been developed over the years to satisfy the requirement of maintaining the temperature of the passenger cabin of modern day aircraft at a level comfortable to the passengers during the time the aircraft is parked. In such aircraft, the high density of passengers, the interior lighting, the large number of windows, and the heavily insulated fuselage all contribute to raising the temperature of the cabin of the parked aircraft to uncomfortable levels. Accordingly, it has been found necessary to provide a cooling system to lower the aircraft cabin temperature, even when the aircraft is parked in locations with relatively cold outside ambient temperatures.

One type of prior art system for cooling the cabin of a parked aircraft utilizes an on-board auxiliary power unit which is generally a small, jet-fueled turbine. The turbine, which is operated when the aircraft is parked, is used to power the on-board cooling system. This same cooling system is powered by the main engines during flight.

Another type of prior art system for cooling the cabin of a parked aircraft utilizes one or more on-board air cycle machines which are specialpurpose heat pumps. These machines cool the cabin air when they are supplied with a source of highpressure, high temperature air. During flight, the source of air is an on-board compressor driven by the main engines. When the aircraft is parked, a ground-based air compressor is connected to the airplane to drive the heat pumps. This connection is made using a hose which links the compressor to a heat pump connector provided on the outer surface of the aircraft fuselage.

Yet another type of system for cooling the cabin of a parked aircraft utilizes a ground-based air conditioner unit which provides cool air under pressure directly into the cabin air-conditioning duct system.

This ground-based air conditioner, which may be fixed in location or portable, is connected to the parked airplane using a flexible hose. This hose links the air conditioner to a connector, provided on the exterior of the fuselage, which communicates directly with the cabin ducts. In this mechanization, there is no need to operate the on-board cooling system when the aircraft is parked.

Of the previously described types of cooling systems, the ground-based air conditioner unit is generally recognized as being the most energy efficient. Typically, prior art ground-based air conditioner units require from one-fifth to one-tenth the energy of those systems employing on-board auxiliary power units, and from one-half to one-fourth the energy of those systems employing on-board air cycle machines.

Even though ground-based air conditioner systems are generally more efficient than many other types of cooling systems, they still require large amounts of power for their operation. For example, electrically operated air conditioner systems for large commercial jet aircraft may require in excess of three hundred and fifty kilowatts of powerfortheir operation.

Further, prior art ground-based air conditioner systems typically employ very large and powerful blowers in order to generate sufficient air flow to maintain the desired cabin temperature. These blowers, some of which may be rated in excess of one hundred and fifty brake horsepower, generate substantial levels of noise adjacent the air conditioner unit. In addition, these large blowers cause the cool air to exit the cabin air ducts at sufficiently high velocities to produce noticeable cabin noise.

Yet another drawback to prior art ground-based air conditioner systems is the high moisture content of the cool air delivered to the cabin air ducts. This moisture increases cabin humidity, causing mist formation and contributing to passenger discomfort.

Accordingly, it is an object of the present invention to provide new and improved apparatus and methods for cooling the cabins of parked aircraft.

It is another object of the present invention to reduce the power consumption of ground-based aircraft air conditioning systems.

It is yet another object of the present invention to improve the cabin environment of parked aircraft by reducing the noise and humidity produced by the air conditioning system.

Summary of the invention The foregoing and other objects of the invention are accomplished by providing a ground-based air conditioning system for parked aircraft which departs from conventional mechanizations of such air conditioning systems by supplying to the aircraft air which is cooled below the freezing point of water.

For air conditioning purposes, the prior art has for the most part rejected the use of air cooled below forty degrees Fahrenheit on the basis that such cold air results in an inefficient system and in user discomfort. However, in the present invention there are developed air conditioning configurations which cool the air entering the aircraft below forty degrees Fahrenheit (preferably below thirty-two degrees Fahrenheit) to provide a system for cooling parked aircraft which consumes less power, produces less outside and cabin noise, and provides a drier and more comfortable cabin environment than prior art systems of comparable cooling capacity.

Several embodiments are described for providing air at sub-freezing temperatures while overcoming the problem of excess frost buildup on the cooling elements.

Other features, objects, and advantages of the invention will become apparent from a reading of the specification taken in conjunction with the drawings, in which like reference numerals refer to like elements in the several views.

Brief description ofthe drawings Figure lisa block diagram of a ground-based air conditioning system of the type used in the present invention for cooling a parked aircraft; Figure2 is a schematic diagram of a direct expansion type of cooling configuration which may be used in the air conditioning system of Figure 1 to practice the present invention; Figure 3 is a schematic diagram of a chilled liquid type of cooling configuration which may be used in the air conditioning system of Figure 1 to practice the present invention; and Figure 4 is a schematic diagram of a combination chilled liquid and direct expansion type of cooling configuration which may be used in the air conditioning system of Figure 1 to practice the present invention.

Description of the preferred embodiment Referring to Figure 1, there is shown a block diagram of a ground-based air conditioning system 10 used to cool the cabin of a parked aircraft 12. The system 10 includes a cooling unit 14 which provides a source of cold fluid which is circulated through a heat exchanger 16. A blower 18 is used to force ambient air, entering through inlet 20, over the surfaces of the heat exchanger 16, whereby the air is cooled to the desired temperature when it exits from outlet 22. The heat exchanger 16 and the blower 18 are generally housed in a common enclosure which is located adjacent the airplane parking area. This enclosure may be fixed in location or may be portable. The cooling unit 14 may be located in that same area or may be remotely located as part of a central airport cooling system.In such instance, the cooling unit 14 is connected to the heat exchanger 16 using suitable piping. Electrical power to operate the blower 18 and the cooling unit 14 may be provided by a portable generator (typically driven by a diesel engine), or by the airport power utility using fixed power lines.

The air conditioning system air outlet 22 communicates with one end of a flexible hose 24. The other end of the hose 24 is attached to a connector 26 provided on the outside surface of the airplane 12.

The connector 26, in turn, communicates with a network of air conditioning ducts 28 distributed throughout the passenger cabin of the aircraft 12.

In order to provide a comfortable environment in the passenger cabin of the parked aircraft, it is desirable to maintain cabin temperature at a nominal seventy-five degrees Fahrenheit, even under worst case conditions of maximum cabin heat load.

Factors influencing this heat load are outside ambient temperature, sunlight radiating through the windows, interior cabin lights, and the number of passengers in the cabin.

For the most part, prior art air conditioning systems for parked aircraft accomplish the cooling task by providing air at the heat exchanger outlet 22 which has been cooled to between forty and fifty degrees Fahrenheit. Typically, the air flowing through the flexible hose 24 undergoes a temperature rise of about five degrees Fahrenheit. Accordingly, the temperature of the air entering the airplane at the connector 26 is between forty-five and fiftyfive degrees Fahrenheit in prior art systems. The blower 18 is sized to provide a sufficient rate of cool airflow to maintain the desired cabin temperature under conditions of maximum cabin heat load.

Until the present invention, those skilled in the art had for the most part rejected the concept of providing air at the heat exchanger outlet 22 which is colder than forty degrees Fahrenheit. These beliefs are based in part on the technical information accumulated over the years relating to the air conditioning of residential and commercial buildings.

Building air conditioning systems are characterized by the employment of very large air ducts having a low pressure drop. Air is cooled by cooling units to between forty and fifty-five degrees Fahrenheit and is distributed through the building duct system at very low flow rates. Generally, air pressure of only one to three inches of water is needed to distribute the cool air throughout the building. Accordingly, the power consumed by the blowers employed to move the air is quite small compared to the power needed to cool the air.

Further, the very low air pressure used in these systems means that the blowers do not contribute significant heat to the air as the result of air compression.

In general, air cooling apparatus is less efficient when called upon to cool the air below forty degrees Fahrenheit. Further, air at these cold temperatures results in an uncomfortably chilly atmosphere in a building environment. It has also been found that air at these cold temperatures is sufficiently low in humidity that it causes an uncomfortably dry environment for the building occupants. Another factor to be considered is that the cooling of air below approximately thirty-five degrees Fahrenheit requires the use of heat exchangers having subfreezing surfaces temperatures. These sub-freezing temperatures cause icing and frost buildup problems which do not occur in the prior art airconditioning systems.Thus, the prior art has generally rejected the use of air cooled below forty degrees Fahrenheit in air conditioning systems, based on energy inefficiency, hardware mechanization problems, and on user discomfort.

In contrast to the prior art teachings, the present invention employs air temperatures below forty degrees Fahrenheit (preferably below the freezing point of water) in ground-based air conditioner systems for parked aircraft with a resultant decrease in power consumption and an increase in passenger comfort. This surprising result may be shown to be related to a combination of factors which are peculiar to aircraft air conditioning systems, as outlined below.

Due to space limitations, aircraft cabin air conditioning ducts are necessarily small in cross section.

Further, the high passenger density in modern day aircraft, in conjunction with other heat producing factors previously mentioned, result in a heat load which requires a substantial rate of cooling airflow to maintain the desired cabin temperature. The combined requirement of high air flow rate and small duct cross-section results in the need for substantial air pressure to force the cool air into the cabin at the required flow rate.

The need for substantial air pressure is met in prior art systems by employing large and powerful blowers which consume a substantial portion of the overall energy consumed by the system. By way of example, in some prior art parked aircraft air conditioning systems, the blower consumes in excess of forty percent of the overall system power consumption. This is as opposed to building air conditioning systems where the blower represents only a few percent of the overall power consumption.

The need for large blowers to produce the required air flow rates further contributes to system inefficiency because these blowers add heat to the air. This heat, which must be removed by the cooling system, results from the compression of the air which occurs when it is pressurized.

In the present invention, it has been found that a reduction in the temperature of the air delivered to the airplane from that of prior art systems enables a reduction in the airflow rate necessary to maintain the desired cabin temperature. Such a temperature reduction (typically, to a temperature level below the freezing point of water) does result in a reduction in the efficiency of operation of the cooling apparatus.

However, the ability to reduce the air flow rate provides major system power savings because it both reduces the size of the blower and reduces the cooling requirements of the cooling apparatus. An overall power savings in excess of thirty percent is not uncommon for parked aircraft air conditioning systems built in accordance with the teachings of the present invention. The following examples are presented to more fully illustrate the features of the invention.

Example! This example compares the performance of prior art electrically operated ground-based air conditioner systems with a comparable system built in accordance with the teachings of the present invention when used to cool the cabin of a narrow body jet aircraft such as the Boeing Aircraft Co. Model 727-200.

Under the conditions of an outside ambienttemperature of one hundred degrees Fahrenheit, bright sunlight, the interior cabin lights turned on, and 134 occupants on board, the cabin heat load for the above model aircraft is approximately 85,940 BTU per hour. The goal of the air conditioning system is to maintain the cabin temperature at seventy-five degrees Fahrenheit at this heat load.

Referring briefly to Figure 1, prior art groundbased air conditioning systems generally provide air at no lower than forty degrees Fahrenheit at the outlet 22 of the heat exchanger. A typical five degree temperature rise in the hose 24 results in a minimum air temperature of forty-five degrees Fahrenheit at the airplane connector 26. Using the above figures, it may be shown that the cooling air flow rate required to achieve the desired cooling is about 200 pounds per minute. At this flow rate, the blower 18 must develop air pressure of about thirty-four inches of water.Of this pressure, about five inches of water are attributable to the restriction in the heat exchanger 16 and related manifolds, about ten inches of water are attributable to the restriction imposed by the hose 24 and its related connections, and the remaining nineteen inches of water are attributable to the restrictions imposed by the cabin ducting 28.

Assuming a typical blower efficiency of sixty-two percent and a blower motor efficiency of ninety percent, it may be shown that a blower rated at twenty-three brake horsepower is required to provide the necessary air pressure. A blower of this size consumes about 19.2 kilowatts of electric power. It may also be shown that the cooling unit 14 must be sized to provide cooling at the rate of 327,600 BTU per hour (about 27.3 tons) in order to process 200 pounds per minute of air and achieve the necessary temperature reduction to forty degrees Fahrenheit at the heat exchanger outlet 22. Further, the cooling unit 14 must also remove the heat contributed by the blower 18 in compressing the air.

The twenty-three brake horsepower blower contributes heat at the rate of about 58,512 BTU per hour (4.9 tons). Accordingly, the cooling unit 14 must be sized to supply a total of 32.2 tons of cooling. A typical cooling unit 14 might employ direct expansion type refrigeration apparatus. A well designed electrically operated air cooled refrigeration unit of this type which is configured to cool air to forty degrees Fahrenheit may be expected to consume about 1.6 kilowatts per ton of cooling capacity.

Accordingly, the prior art cooling unit described above would consume about 51.5 kilowatts which, when combined with the blower power consumption, yields a total prior art system power consumption of 70.7 kilowatts.

We turn now to a system configured in accordance with the teachings of the present invention to provide the same cabin temperature of seventy five degrees Fahrenheit under the same heat load of 85,940 BTU per hour. The present system is designed to provide air at the heat exchanger outlet 22 at a temperature of twenty-five degrees Fahrenheit, which is well below the freezing point of water (thirty-two degrees Fahrenheit). Allowing for a five degree Fahrenheit rise in the hose 24, the air temperature at the connector 26 is thirty degrees Fahrenheit.

Using the above figures, it may be shown that the cooling air flow rate requirement to achieve the desired cooling is only 133 pounds per minute, which is 33.5 percent less than the comparable prior art system air flow rate. At this lower flow rate, the blower 18 need only develop air pressure of about thirteen inches of water. Of this pressure, about three inches of water are attributable to the restriction in the heat exchanger 16 and related manifolds, about five inches of water are attributable to the restriction imposed by the hose 24 and its related connections, and the remaining five inches of water are attributable to the restrictions imposed by the cabin ducting 28.

Assuming the same blower efficiencies as in the prior art system description above, it may be shown that the blower in the present system need only be rated at 5.9 brake horsepower. Such a blower typically consumes 4.9 kilowatts of power, which is about seventy five percent less power than that consumed by the blower in the prior art system.

The reduced airflow rate results in a reduction in the cooling requirements of the cooling unit 14to 268,128 BTU per hour (about 22.3 tons). The additional heat contributed by the smaller blower is only 15,010 BTU per hour (1.3 tons). Accordingly, the cooling unit 14 in the present system need only be sized to supply 23.6 tons of cooling, which is about twenty-seven percent less than the cooling requirement for the prior art system.

As explained earlier, cooling units such as the direct expansion type refrigeration unit are less energy efficient when designed to provide cooling below about forty degrees Fahrenheit, which is the case for the present system. Such a cooling unit may be expected to consume on the order of 1.85 kilowatts per ton of cooling capacity, which is about sixteen percent less efficient than the prior art cooling unit. Accordingly, the sub-freezing cooling unit would consume about 43.7 kilowatts which, when combined with the blower power consumption, yields a total system power consumption of 48.6 kilowatts.

Comparing the total power consumption figures for the two previously described systems, it will be appreciated that, in spite of the less efficient cooling unit, the system of the present invention consumes 22.1 kilowatts less than comparable prior art systems, resulting in a power savings of over 31 percent.

Example II This second example compares the performance of prior art electrically operated ground-based air conditioner systems with a comparable system built in accordance with the teachings of the present invention when used to cool the cabin of a wide body jet aircraft such as the Boeing Aircraft Co.

Model 747-200.

Under the conditions of an outsideambienttem- perature of one hundred degrees Fahrenheit, bright sunlight, the interior cabin lights turned on, and 511 occupants on board, the cabin heat load for the above model aircraft is approximately 305,305 BTU per hour. The goal of the air conditioning system is to maintain the cabin temperature at seventy-five degrees Fahrenheit at this heat load.

The prior art ground-based air conditioning system provides air at forty degrees Fahrenheit at the outlet 22 of the heat exchanger. A typical five degree temperature rise in the hose 24 results in an air temperature of forty-five degrees Fahrenheit at the airplane connector 26. Using the above figures, it may be shown that the cooling air flow rate required to achieve the desired cooling is about 706 pounds per minute. At this flow rate, the blower 18 must develop air pressure of about seventy-three inches of water. Of this pressure, about five inches of water are attributable to the restriction in the heat exchanger 16 and related manifolds, about fifteen inches of water are attributable to the restriction imposed by the hose 24 and its related connections, and the remaining fifty-three inches of water are attributable to the restriction imposed by the cabin ducting 28.

Assuming a typical blower efficiency of sixty percent and a blower motor efficiency of ninety percent, it may be shown that a blower rated at one hundred and eighty brake horsepower is required to provide the necessary air pressure. A blower of this size consumes about one hundred and fifty kilowatts of electric power. The cooling unit 14 must be sized to provide cooling at the rate of 1,156,428 BTU per hour (about 96.4 tons) in order to process 706 pounds per minute of air and achieve the necessary temperature of forty degrees Fahrenheit at the heat exchanger outlet 22. Further, the cooling unit 14 must also remove the heat contributed by the blower 18 in compressing the air.

The one hundred and eighty brake horsepower blower contributes heat at the rate of about 457,920 BTU per hour (38.2 tons). Accordingly, the cooling unit must be sized to supply a total of 134.6 tons of cooling. As described in the previous example, a direct expansion refrigeration unit configured to cool air to forty degrees Fahrenheit may be expected to consume on the of order of 1.6 kilowatts per ton of cooling capacity. Accordingly, the prior art cooling unit described above would consume about 215.4 kilowatts which, when combined with the blower power consumption, yields a total prior art system power consumption of 365.4 kilowatts.

We turn now to a system configured in accordance with the teachings of the present invention to provide the same cabin temperature of seventy-five degrees Fahrenheit under the same heat load of 305,305 BTU per hour. The present system is designed to provide air at the heat exchanger outlet 22 at a temperature of twenty-five degrees Fahrenheit. Allowing for a five degree Fahrenheit rise in the hose 24, the airtemperature at the connector 26 is thirty degrees Fahrenheit.

Using the above figures, it may be shown that the air flow rate requirement to achieve the desired cooling is only 471 pounds per minute, which is 33.3 percent less than the comparable prior art system air flow rate. At this lower flow rate, the blower 18 need only develop air pressure of about forty-six inches of water. Of this pressure, about four inches of water are attributable to the restriction in the heat exchanger 16 and related manifolds, about ten inches of water are attributable to the restriction imposed by the hose 24 and its related connections, and the remaining thirty-two inches of water are attributable to the restriction imposed by the cabin ducting 28.

Assuming the same blower efficiencies as in the prior art system described above, it may be shown that the blower in the present system need only be rated at 75 brake horsepower. Such a blower typically consumes 62.5 kilowatts of power, which is about fifty-eight percent less power than that consumed by the blower in the prior art system.

The reduced airflow rate results in a reduction in the cooling requirements of the cooling unit 14 to 949,536 BTU per hour (about 79.1 tons). The additional heat contributed by the smaller blower is only 190,800 BTU per hour (15.9 tons). Accordingly, the cooling unit 14 in the present system need only be sized to supply 95 tons of cooling, which is about twenty-nine percent less than the cooling requirement for the prior art system.

Using the energy consumption factor of 1.85 kilowatts per ton of cooling capacity established earlier, the sub-freezing cooling unit would consume about 175.8 kilowatts which, when combined with the blower power consumption, yields a total system power consumption of 238.3 kilowatts.

Comparing the total power consumption figures for the two previously described systems for widebody aircraft, it will be appreciated that in spite of the less efficient cooling unit, the system of the present invention consumes 127.1 kilowatts less than comparable prior art systems, resulting in a power savings of about thirty-five percent.

In addition to power savings, air conditioning systems constructed in accordance with the teachings of the present invention offer other advantages over prior art systems. For example, the air cooled to forty-five degrees Fahrenheit at the aircraft connector in prior art systems is generally extremely high in moisture content, resulting in a relative humidity in the aircraft cabin in the range of 70 to 80 percent, which is considered uncomfortable. On the other hand, in the present invention, by cooling the air to sub-freezing temperatures, a great deal of moisture is removed by condensation. Accordingly, the air entering the cabin is much lower in humidity than in prior art systems and a cabin relative humidity of less than fifty percent may be expected.

It will be appreciated that the air entering the cabin in the present system is colder than that of prior art systems. From the prior art teachings related to building air conditioning, one might expect passenger discomfort at these lower temperatures. On the contrary, it has been found that the high cabin heat load, the high density of passengers, the relatively short time during which the airplane is parked with passengers aboard, and the rapid mixing of air due to its relatively high duct exit velocity, all contribute to obviate passenger discomfort.

It is interesting to note that the low humidity of the cabin air produced using the present invention could enable the cabin temperature to be increased several degrees above the commonly selected seventy-five degrees Fahrenheit, while maintaining the same or greater level of passenger perceived comfort. It is well known to those skilled in the art that such perceived comfort is a function both of temperature and humidity.

Another feature of the present invention is the reduction of cabin noise. Using the present invention, air is delivered into the cabin at a flow rate which is about thirty-three percent less than that of prior art systems. This reduced airflow rate decreases wind noise to less than half that of prior art systems. Noise produced outside the airplane in the vicinity of the blower 18 is also reduced by practicing the present invention. The use of smaller, less powerful blowers results in blower noise which is about six to ten decibels less than that of prior art systems.

Installation and operating costs of systems constructed in accordance with the teachings of the present invention are greatly reduced over these same costs for prior art systems. For example, the reduction in system electrical power enables a reduction in airport wiring costs for fixed installation ground-based systems. Since an air conditioning system is generally provided at each gate in an airport, this installation savings is significant.

Returning to Figure 1, the cooling of air to sub-freezing temperatures in the present invention presents the problem of frost buildup on the surfaces of the heat exchanger 16. It will be appreciated that to achieve the low air temperatures used in the present invention, it is necessary to cool at least some portion of the surfaces of the heat exchanger 16 belowe the freezing point of water. The buildup of frost on these surfaces is the result of the freezing of moisture which has been condensed from the air.

Excess frost accumulation can block the heat exchanger airflow passages and reduce system cooling efficiency. Figures 2 through 4 show various air conditioning configurations which have been developed as part of the present invention to overcome the frost problem.

Figure 2 is a schematic diagram of a ground-based air conditioning system 10 employing a direct expansion type cooling unit 14. The heat exchanger 16 includes first and second sections 30 and 32, respectively, which are typically formed of coiled copper tubing. The section 30 is positioned closest the blower 18, while the section 32 is positioned adjacent the heat exchanger outlet 22. The sections 30 and 32 are interconnected so that a compressible fluid refrigerant, such as Freon (R.T.M), may flow through the section 32 from an inlet 34 to an outlet 36 and then through section 30 from an inlet 38 to an outlet 40. It will be appreciated that the flow of fluid is from a location closest the outlet 22 to a location closest the blower 18 in the heat exchanger 16.This flow pattern establishes a temperature gradient in the heat exchanger 16 whereby the air flowing from the blower 18 to the outlet 22 is made progressively colder.

The outlet 40 is connected to an inlet of a compressor 42 used to compress the fluid. An outlet of the compressor 42 is connected to an inlet of a condenser 44 which may be air cooled by a fan 46 in order to liquifythe compressed fluid. An outlet of condenser 44 is connected to an inlet of an expansion valve 48, the outlet of which is connected to the inlet 34 of the section 32. The expansion valve 48 is used to cause the fluid to expand and evaporate in the coils of the sections 30 and 32, thus lowering the temperature of the heat exchanger surfaces. An electrically operated bypass valve 50 is connected between the outlet of the compressor 42 and the inlet 34 of the heat exchanger section 32. The normally open valve 50 is closed in response to an electrical signal applied on line 52.

The sections 30 and 32 are sized so that when the blower 18 forces ambient air over these sections, the section 30 reduces the temperature of the air until it is only a few degrees above freezing. At this temperature, a large percentage of the moisture in the air is removed without any freezing of this moisture occurring on the surfaces of the section 30.

The condensed moisture which drips from the surfaces of the section 30 is removed from the exchanger 16 using a suitable drain 54. The chilled air then passes over the surfaces of the second section 32 where it is cooled to the desired subfreezing temperature. Because most of the moisture has already been removed by section 30 (only about 0.004 pounds of moisture remain per pound of dry air), the rate of ice formation on the surfaces of section 32 is relatively slow.

The ice which does form on the surfaces of the section 32 is periodically removed by opening the bypass valve 50. Opening this valve 50 causes hot refrigerant gas (at approximately 150 to 200 degrees Fahrenheit) from the compressor 42 to enterthe section 32 tubing and rapidly melt the ice. The melted ice is drained away using drain 56. The valve 50 may be operated on a periodic basis by an electrical timer to automatically defrost the section 32. It has been found that operation of the valve 50 for about two minutes every twenty minutes is adequate to prevent excess frost buildup.

During this short defrost cycle, the temperature of the air exiting the exchanger 16 will rise to about sixty degrees Fahrenheit. However, the large thermal mass provided by the hose 24 and the duct system 28 acts to maintain the temperature of the air entering the cabin at very nearly the desired temperature during this time. Accordingly, the defrost cycle has negligible effect on the overall cabin temperature.

Figure 3 is a schematic diagram of a ground-based air conditioning system employing a chilled liquid type cooling unit 14. The heat exchanger 16 includes first and second sections 58 and 60, respectively, which are typically formed of copper tubing. The section 58 is positioned closest the blower 18, while the section 60 is positioned adjacent the heat exchanger outlet 22. The sections 58 and 60 are interconnected so that a liquid having a freezing point below that of water may flow through the section 60 from an inlet 62 to an outlet 64 and then through section 58 from an inlet 66 to an outlet 68. It will be appreciated that the flow of liquid (which may be a mixture of glycol and water) is from a location closest the outlet 22 to a location closest the blower 18 in the heat exchanger 16.

The outlet 68 is connected to an inlet of a pump 70 used to pump the liquid through the heat exchanger.

An outlet of the pump 70 is connected to an inlet of a chiller 72, and an outlet of the chiller is connected to the inlet 62 of the section 60. The chiller 72 may be any one of a number of apparatus configurations which is able to cool the liquid to a temperature below the freezing point of water (for example, to twenty degrees Fahrenheit).

The sections 58 and 60 are sized so that when the blower 18 forces ambient air over these sections, the section 58 reduces the temperature of the air until it is only a few degrees above freezing. As in the previously described configuration, a large percentage of moisture is removed without any frost occurring on the surfaces of the section 58. Condensed moisture drains via drain 74. The chilled air passes from the section 58 to the section 60, where it is cooled to the desired sub-freezing temperature, and the air then exits through the outlet 22. The rate of ice formation on the surfaces of the section 60 is relatively slow, because most of the moisture in the air has already been removed in the section 58.It should be noted that the flow of chilled liquid through the heat exchanger 16 from the outlet 22 toward the blower 18 aids in establishing the section 60 as the coldest of the two sections and provides the desired cooling gradient.

The frost which does form on the surfaces of the section 60 is periodically removed by stopping the pump 70, which stops the flow of cold liquid through the heat exchanger 16. The warm ambient air being drawn in by the blower 18 and forced over the heat exchanger surfaces acts to quickly defrost the section 60. Condensed moisture drains from the section 60 via drain 76. It has been found that by stopping the pump 70 for two minutes every twenty minutes, the section 60 is adequately defrosted. As in the previous system description, the short defrost interval does not produce any significant increase in airplane cabin temperature because of the large thermal mass of the hose 24 and duct system 28.

Figure 4 is a block diagram of a ground-based air conditioning system employing both chilled liquid and direct expansion cooling. The heat exchanger 16 includes first and second sections 78 and 80, respectively, which may be formed of copper tubing or the like. The section 78 is positioned closest the blower 18, and includes an inlet 82 and outlet 84.

The section 78 is connected as part of a chilled liquid system comprising a pump 86 and a chiller 88.

The pump 86 circulates a liquid, which may be water, through the chiller 88 and through the section 78 from the inlet 82 to the outlet 84. Connected between the pump 86 and the chiller 88 is a heat exchanger coil 90 which is part of a condenser 92 further described below.

The section 78 is designed to cool the incoming ambient air to a temperature slightly above the freezing point of water Accordingly, the liquid flowing through the section 78 need not be chilled below the freezing point of water. In fact, the chiller 88 may be part of a central airport cooling system for generating cold water, and a portion of this water can be routed to flow through the section 78.

Condensed moisture collecting on the surfaces of this section is drained via drain 94.

The section 80 is designed to cool the already chilled air from the section 78 to the sub-freezing temperature desired at the outlet 22. The section 80 is connected as part of a direct expansion refrigeration system similar in operation to that described above for the mechanization shown in Figure 2.

A compressible fluid refrigerant, such as Freon (R.T.M.) flows through the section 80 from an inlet 96 to an outlet 98. The outlet 98 is connected to an inlet of a compressor 100 designed to compress the fluid.

An outlet of the compressor 100 is connected to an inlet of the condenser 92 which is designed to condense the fluid to a liquid. The heat exchanger 90, which is connected as part of the chilled water system described above, provides cooling for the condenser 92 in lieu of air cooling. An outlet of the condenser 92 is connected to an inlet of an expan sion valve 102, and an outlet of the expansion valve 102 is connected to the inlet 96 of the section 80. The expansion valve 102 causes the fluid to expand and evaporate in the coils of the section 80, thus lowering the temperature of the heat exchanger surfaces to achieve the desired air temperature.

An electrically operated bypass valve 104 is connected between the outlet of the compressor 100 and the inlet 96 of the section 80. The valve 104 is operated periodically to provide hot compressed fluid to the section 80 in order to defrost the surfaces of this section. As in the previous mechanizations, a two minute defrost interval every twenty minutes has been found to be adequate. Melted ice is drained from the section 80 using drain 106.

While there have been shown and described preferred embodiments of the invention, it is to be understood that various other adaptations and mod ifications may be made within the spirit and scope of the invention. It is thus intended that the invention be limited in scope only by the appended claims.

Claims

1. In a method of air conditioning a parked aircraft having an external air inlet, the method including the steps of reducing the temperature of a portion of the ambient air external to the aircraft to a first level of temperature using a cooling system located external to the airplane, and providing the reduced temperature air under pressure to the aircraft external air inlet at a second level of temperature, the improvement comprising the step of reducing the temperature of the portion of the ambient air sufficiently to lower the second level of temperature below th i rty-five degrees Fahrenheit.

2. The improvement of claim 1 in which the step of reducing the temperature of the portion of the ambient air includes reducing the temperature of the portion of the ambient air sufficiently to lower the first and second levels of temperature to or below the freezing point of water.

3. The improvement of claim 2 in which the step of reducing the temperature of the portion of the ambient air sufficiently to lower the second level of temperature to or below the freezing point of water includes the steps of: providing a heat exchanger having first and second sections of coiled tubing; circulating a fluid through the second and first sections, respectively, of the heat exchanger; cooling the fluid entering the second heat exchanger section below the freezing point of water; forcing the portion of ambient air past the first and second heat exchanger sections, respectively, where the air exiting the first heat exchanger section is slightly above the freezing point of water and has most of its moisture removed, and the air exiting the second heat exchanger section, which is at the first level of temperature, is below the freezing point of water; and interrupting the circulation of the fluid through at least the second heat exchanger section for a predetermined interval of time on a periodic basis to enable the forced portion of ambient air to defrost the second heat exchanger section.

4. The improvement of claim 2 in which the step of reducing the temperature of the portion of the ambient air sufficiently to lower the second level of temperature to or below the freezing point of water includes the steps of: providing a heat exchanger having first and second sections of coiled tubing; connecting the first and second heat exchanger sections to provide fluid flow from an inlet of the second section to an outlet of the first section; providing a compressible fluid within the heat exchanger tubing; compressing the fluid exiting the first heat exchan ger section; condensing the compressed fluid into a liquid; expanding the liquid as it flows into the inlet of the second heat exchanger section; providing a compressible first fluid circulating through the second heat exchanger section; compressing the first fluid which exits the second heat exchanger;; condensing the compressed fluid into a liquid; expanding the liquid as it flows into the inlet of the second heat exchanger section; circulating a second fluid through the first heat exchanger section; cooling the second fluid entering the first heat exchanger section; forcing the portion of ambient air past the first and second heat exchanger sections, respectively, where the air exiting the first heat exchanger section is slightly above the freezing point of water and has most of its moisture removed, and the air exiting the second heat exchanger section, which is at the first level of temperature is below the freezing point of water; and forcing the portion of ambient air past the first and second heat exchanger sections, where the air exiting the first heat exchanger section is slightly above the freezing point of water and has most of its moisture removed, and the air exiting the second heat exchanger section, which is at the first level of temperature is below the freezing point of water; and circulating the compressed, but not condensed or expanded, fluid through at least the second heat exchanger section for a predetermined interval of time on a periodic basis to enable the compressed fluid to defrost the second heat exchanger section.

5. The improvement of claim 2 in which the step of reducing the temperature of the portion of the ambient air sufficiently to lower the second level of temperature to or below the freezing point of water includes the steps of: providing a heat exchanger formed of first and second sections of coiled tubing, each section having an inlet and outlet; circulating the compressed, but not condensed or expanded, first fluid through the second heat exchanger section for a predetermined interval of time on a periodic basis to enable the compressed first fluid to defrost the second heat exchanger section.

6. In a system of air conditioning parked aircraft having an external air inlet, the system including cooling means located external to the airplane for reducing the temperature of a portion of the ambient air external to the aircraft to a first level of temperature, and transport means for providing the reduced temperature air under pressure to the aircraft external air inlet at a second level of temperature, the improvement comprising apparatus included as part of the cooling means for reducing the second level of temperature belowthirty-five degrees Fahrenheit.

7. The improvement of claim 6 in which the apparatus further includes means for lowering the second level of temperature to or below the freezing point of water.

8. The improvement of claim 7 in which the apparatus includes: heat exchanger means formed of first and second sections of coiled tubing; fluid; means for cooling the fluid below the freezing point of water; pump means for circulating the cooled fluid through the second and first heat exchanger sections, respectively; blower means for forcing the portion of ambient air past the first and second heat exchanger sections, respectively, where the air exiting the first heat exchanger section is slightly above the freezing point of water and has most of its moisture removed, and the air exiting the second heat exchanger section, which is at the first level of temperature is below the freezing point of water; and control means for periodically interrupting the circulation of the fluid through at least the second heat exchanger section for a predetermined interval of time to enable the forced portion of ambient air to defrost the second heat exchanger section.

9. The improvement of claim 8 in which the control means interrupts the circulation of fluid about every twenty minutes, and the predetermined interval of time is about two minutes.

10. The improvement of claim 7 in which the apparatus includes: heat exchanger means formed of first and second sections of coiled tubing and connected to provide fluid flow from an inlet of the second section to an outlet of the first section; a compressible fluid; a compressor having an inlet and an outlet for compressing the fluid; a condenser having an inlet and outlet for li quifying the fluid; an expansion valve having an inlet and outlet for causing the condensed fluid to evaporate in the heat exchanger; means for connecting the compressor inlet to the outlet of the first heat exchanger section; means for connecting the compressor outlet to the condensor inlet; means for connecting the condensor outlet to the expansion valve inlet; means for connecting the expansion valve outlet to the inlet of the second heat exchanger section;; blower means for forcing the portion of ambient air past the first and second heat exchanger sections, respectively, where the air exiting the first heat exchanger section is slightly above the freezing point of water and has most of its moisture removed, and the air exiting the second heat exchanger section, which is at the first level of temperature is below the freezing point of water; a bypass valve; means for connecting the bypass valve between the compressor outlet and the inlet of the second heat exchanger section; and control means for periodically opening the bypass valve for a predetermined interval of time to flow through and defrost the second heat exchanger section.

11. The improvement of claim 7 in which the apparatus includes: heat exchanger means formed of first and second sections of coiled tubing, each section having an inlet and outlet; a compressible first fluid flowing in the second heat exchanger section; a compressor having an inlet and an outlet for compressing the first fluid; a condensor having an inlet and outlet for liquifying the first fluid; an expansion valve having an inlet and outlet for causing the condensed first fluid to evaporate in the heat exchanger second section; means for connecting the compressor inlet to the outlet of the second heat exchanger section; means for connecting the compressor outlet to the condensor inlet; means for connecting the condensor outlet to the expansion valve inlet; means for connecting the expansion valve outlet to the inlet of the second heat exchanger section;; a second fluid flowing in the first heat exchanger section; means for cooling the second fluid; pump means for circulating the cooled second fluid through the first heat exchanger section; blower means for forcing the portion of ambient air past the first and second heat exchanger section, respectively, where the air exiting the first heat exchanger section is slightly above the freezing point of water and has most of its moisture removed, and the air exiting the second heat exchanger section, which is at the first level of temperature is below the freezing point of water; a bypass valve; ; means for connecting the bypass valve between the compressor outlet and the inlet of the second heat exchanger section, and control means for periodically opening the bypass valve for a predetermined interval of time to permit the compressed first fluid to flow through and defrost the second heat exchanger section.

12. The improvement of claim 11 in which the gondensor includes heat exchanger means which accommodates a coolant for cooling the first fluid, and in which the second fluid is provided to the heat exchange means as the coolant.

13. In a method of air conditioning a parked aircraft having an external air inlet, the method including the steps of reducing the temperature of a portion of the ambient air external to the aircraft to a first level of temperature using a cooling system located external to the airplane which has a blower for forcing the portion of ambient air over a surface of a heat exchanger which surface is cooled to reduce the temperature of the portion of ambient air, and providing the reduced temperature air under pressure to the aircraft external air inlet at a second level of temperature, the improvement comprising the step of reducing the temperature of at least a portion of the heat exchanger surface below the freezing point of water in order to lower the second level of temperature below thirty4ive degrees Fahrenheit.

14. In a system of air conditioning parked aircraft having an external air inlet, the system including cooling means located external to the airplane which has a blower for forcing the portion of ambient air over a surface of a heat exchanger, which surface is cooled to reduce the temperature of a portion of the ambient air external to the aircraft to a first level of temperature, and transport means for providing the reduced temperature air under pressure to the aircraft external air inlet at a second level of temperature, the improvement comprising apparatus included as part of the cooling means which reduces the temperature of at least a portion of the heat exchanger surface below the freezing point of water in order to reduce the second level of temperature belowthirty-five degrees Fahrenheit.

15. A method of air conditioning a parked aircraft substantially as described herein.

16. Equipmentfor air conditioning a parked aircraft substantially as described herein with reference to, and as shown in, the accompanying drawings.