Abstract:
This patent is directed to an external air conditioning system connected to a parked airplane. The system has multiple refrigeration units. Each refrigeration unit has a controller. Each refrigeration unit&#39;s controlled is linked to a common controller. A single stream of air flows through all of the evaporators in series. Each of the refrigeration units has multiple compressors. Additional compressors are activated or deactivated based on refrigerant pressure. The activation or deactivation pressures are staggered across the refrigeration units, thus coordinating operation of the multiple refrigeration units.

Description:
BACKGROUND 
     The present invention relates generally to systems for providing fresh air to aircraft when parked at a location on the ground. More particularly, the invention relates to a system that can adaptively regulate its operation during periods of considerable thermal load to maintain operation at a reduced level rather than interrupting operation completely. 
     Various air conditioning systems have been developed for providing conditioned air to aircraft. During flight, power plants (engines) used to drive the aircraft also generate power that can drive on-board conditioned air circulation systems. When parked on the ground, however, conditioned air may be supplied by external means. Air conditioning or refrigeration units may be provided adjacent to such aircraft and coupled to the aircraft by air conduits. Such refrigeration systems, may be either electrically powered or engine-driven. The thermal load encountered by the refrigeration systems, however, can vary greatly, depending upon the part of the world in which the aircraft is operating, the season and environmental temperatures, the size of the aircraft, and the air temperature and flow rates demanded of the refrigeration systems. 
     A drawback of conventional aircraft conditioned air supply systems, particularly of refrigeration systems, is their reaction to variable thermal loads caused by high or low ambient conditions. Single or multiple refrigeration systems have been provided to allow for reacting to increased loads, and various flow rates, while still maintaining a desired air temperature. However, when external temperatures rise significantly, adding to the thermal load on the refrigeration units, excessive refrigerant pressures may be encountered that force the units to shut down, significantly reducing or interrupting the flow of conditioned air to the aircraft. While the flow of air may be maintained by blowers, the temperature within the aircraft may significantly increase due to the interrupted operation of one or more of the refrigeration system. 
     There is a need, therefore, for improved approaches to providing conditioned air to parked aircraft. There is a particular need for approaches that will allow continued operation, even if at less than optimal temperatures or flow rates, but that will avoid the shut down of one or more refrigeration units completely. 
     BRIEF DESCRIPTION 
     The present invention provides a novel approach to aircraft conditioned air supply designed to respond to such needs. The invention may be applied in a wide range of settings, including in commercial airlines, military and private settings, and so forth. Moreover, the technique may be used with refrigeration systems having redundant refrigeration units or with a single refrigeration unit. 
     In accordance with certain aspects of the technique, a refrigeration system for supplying air to a parked aircraft is provided that includes parallel compressors, one or more of which can be operated at any time based upon temperatures and actual temperatures of air being supplied to the aircraft, and upon the thermal load. Moreover, the system may include multiple fans for one or more condensers, which may be individually controlled based upon refrigerant pressures. As thermal loads increase, pressures may be monitored or pressure switches may be set and controlled to interrupt operation of one of the compressors, thereby reducing the heat-removal capacity of the system, while maintaining system operation. 
     In particular embodiments described below, one or more air conditioning systems in a unit may be provided that include generally similar refrigeration circuitry provided with a common blower. The circuitry may function generally similarly, but in a redundant fashion, with certain of the refrigeration units being called into play depending upon the thermal load. As thermal load further increases, beyond the limits of one or more of the refrigeration units, the fans and compressors of each unit may be controlled to maintain refrigerant pressures within design limits, while maintaining some operation of the systems for providing conditioned air to the aircraft, albeit at slightly higher temperatures than desired, or at target temperatures but with reduced flow rates. 
    
    
     
       DRAWINGS 
       These and other features, aspects, and advantages of the present invention will become better understood when the following detailed description is read with reference to the accompanying drawings in which like characters represent like parts throughout the drawings, wherein: 
         FIG. 1  is a diagrammatical representation of an air conditioning system for a parked aircraft in accordance with certain aspects of the present technique; 
         FIG. 2  is a more detailed diagrammatical representation of the air conditioning system including several redundant air conditioning units designed to operate in accordance with the invention; and 
         FIG. 3  is a flow chart illustrating exemplary logic for operating the air conditioning system of the previous figures to maintain operation within design limits in response to excessive thermal loads. 
     
    
    
     DETAILED DESCRIPTION 
     Turning now to the drawings, and referring first to  FIG. 1 , an aircraft air conditioning system  10  is illustrated diagrammatically. The system made to be designed as a stationary or mobile system that can be run electrically from a connection to the power grid, or by an integrated or separate power supply. In many applications, the system can be designed as a cart which can approach an aircraft  12  and supply conditioned air by a conduit  14  which is coupled between the air conditioning system and the aircraft. 
     In the embodiment illustrated in  FIG. 1 , the system is operated by power provided by an engine-driven generator set. An internal combustion engine  16 , such as a gasoline or diesel engine drives a generator  18  which will typically be associated with appropriate control circuitry for providing output power for the air conditioning units. The air conditioner itself may include one or a series of air conditioning or refrigeration units as indicated by reference numerals  20 ,  22  and  24  in  FIG. 1 . As described more fully below, the air conditioning units may be operated simultaneously or may be switched in and out of operation separately based upon thermal load and their individual operating parameters. The air conditioning units may be separately controlled, or their control may be coordinated by a common controller as indicated by reference numeral  26 . As noted below, depending upon the instrumentation and control scheme adopted for the refrigeration units, the controller  26  may perform basic functions or may be adapted for more complete integrated control of operation of the various components of the air conditioning units, as well as control of coordinated operation of the units to accommodate the thermal load encountered. 
     In general, the air conditioning units will provide a flow of conditioned air at a desired temperature to the aircraft. Because aircraft engines will not be available for the refrigeration and circulation of cool air within the aircraft, the air conditioning units are operated to provide the desired airflow. The temperature of the air is typically set at a desired level, as is the airflow rate. Larger aircrafts will typically require a greater air flow rate, and thermal load on the air conditioning units and on the system in general will be determined by such factors as the air flow rate, the desired temperature of the supplied air, and the environmental conditions reigning internally and externally of the aircraft (e.g., outside air temperature), and so forth. 
       FIG. 2  illustrates the air conditioning units shown in  FIG. 1  in somewhat greater detail. In a presently contemplated embodiment, several such units are provided to offer redundancy in air cooling, and to accommodate various levels of thermal load. Individual components of air conditioning unit  20  are labeled with reference numerals in view of  FIG. 2 , and will be described in detail below, although similar components are included in air conditioning units  22  and  24 , respectively. 
     As illustrated in  FIG. 2 , each of the air conditioning or refrigeration units may include a plurality of compressors, as indicated by reference numerals  28  and  30  in  FIG. 2  for unit  20 , arranged in parallel to compress a refrigerant. Compressed refrigerant is directed from the compressors to a condenser  32 . In a presently contemplated embodiment, multiple fans  34  and  36  are provided for each condenser, and may be operated based upon thermal load as described below. The fans draw heat from the pressurized refrigerant and expel hot air stream  38 . An expansion valve  40  is provided downstream of the condenser  32 . An evaporator coil  42  is provided in the circuit downstream of the expansion valve  40 , and draws environmental heat into the refrigerant by evaporation of the refrigerant. Following such phase change, the refrigerant is recirculated to the compressors to complete the refrigeration cycle. 
     In the embodiment illustrated in  FIG. 2 , the refrigeration system may be regulated by the controller  26 , as may the parallel refrigeration systems  22  and  24 . However, the refrigeration systems are preferably coupled to a common plenum and blower arrangement as indicated in  FIG. 2  so as to draw incoming air  44  from the surrounding environment. A blower  46  is driven by an electric motor (not shown) and output flow rate from the blower may be regulated by a damper plate  48  which is, itself, controlled by an actuator  50 . The actuator  50  is also controlled by the common controller  26 . Thus, one or more of the refrigeration or air conditioning units may be operated as described below, and a desired flow rate of air through the parallel systems may be generated and controlled by appropriate regulation of the blower  46  and damper plate  48 , under the control of the actuator  50  and controller  26 . 
     In the illustrated embodiment, several parameters are sensed and used for control purposes. In the illustrated embodiment, pressure transducers are utilized to control operation of the compressors and the overall refrigeration units, as well as to operate fans used to draw heat from the condenser  32 . As shown in  FIG. 2 , the units utilize one pressure transducer  54  and one pressure switch  56  upstream of compressors  28  and  30  and one pressure transducer  52  and a pressure switch  83  on the downstream side of the compressors. Moreover, temperature of the air stream is detected at an inlet side as illustrated by temperature sensor  58  in  FIG. 2  and downstream of the refrigeration units (not shown in the figures). As described below, the pressure transducers are employed to appropriately control the compressors and fans to react to thermal loads, while the pressure switches are employed as back up devices for control in the event, for example, that the pressure transducers fail, while the temperature sensor is used to provide control of the compressors as well. The temperature sensor may also be used to regulate and coordinate operation of the various refrigeration units. The fans, compressors and their associated motors are also preferably controlled by the central controller  26 . 
     As described below, the compressors of each refrigeration unit may be controlled to respond to temperatures sensed for the system, which will be indicative of the thermal load. The fans associated with the condenser may also be controlled based upon the thermal load. Moreover, the overall system operation, that is, which and how many air conditioning units are employed at any one time may be controlled based upon the thermal load or factors indicative of the thermal load. 
     An exemplary control scheme for regulating operation of the refrigeration units illustrated in  FIG. 2 , or one of these units, is shown in  FIG. 3 . Certain control logic, designated generally by reference numeral  60 , is illustrated in  FIG. 3  specifically for one of the units, although all of the units may operate similarly. As indicated at step  62 , temperatures are first sensed when conditioned air is desired, or when the overall system is placed in an operative state. Again, temperatures will typically be sensed upstream of the refrigeration system and downstream of the system. In a typical application, a set temperature for air exiting the system will be compared to a desired temperature set via a control interface or thermostat. At step  64 , then, one or more of the units is started. In a presently contemplated embodiment, one of the units, such as unit  20  will be started first, with one of the compressors being operative and one of the fans being turned on to extract heat from the condenser. 
     As indicated at step  66 , then, following a transition period to allow temperatures to reach a generally steady state level, it may be determined whether additional units are required to obtain the desired temperature of the air stream. If additional cooling is determined to be required, an additional unit may be started as indicated at step  68 . If such additional units are started, they may be started in a similar manner, that is, with a single compressor operative and a single fan. Alternatively, control may proceed by increasing the heat-removal capacity of a single one of the units, with a subsequent unit being called into play only as the first unit capacity is reached. 
     Steps  70 - 82  summarized in  FIG. 3  will typically be carried out for each of the units, although particular levels at which decisions occur (e.g., based upon pressures) may be staggered for each of the units to avoid similar responses of the units at specific pressures, and to ensure an orderly increase in heat removal capacity or, conversely, a decrease in capacity as the design limits of the units are reached. 
     At step  70 , the temperature sensed for the air stream is compared to a target temperature and, if the target temperature cannot be reached or maintained, a second compressor of the refrigeration unit is started. The starting of the second compressor, as indicated at step  72  will increase the heat removal capacity of the refrigeration unit. However, such increase in capacity is not required until and unless the target temperature cannot be reached. Continuously, then, pressures on the refrigeration system are measured by each pressure transducer, and if a desired higher pressure is reached, as indicated at step  74 , a second fan is started as indicated at step  76 . By way of example, in a presently contemplated embodiment, a refrigerant pressure of approximately 275 psi will cause the controller to start a second fan associated with the condenser  32  to extract more heat from the refrigerant. This should have the effect of reducing or stabilizing the refrigerant pressure and thus responding to the heat load. 
     If the heat load is still higher, or if the heat load increases, a higher pressure can be expected for the refrigerant exiting the compressors. Pressure transducer  54  (see  FIG. 2 ) is set to a pressure higher than that controlling the operation of the second fan, and as indicated at step  78  in  FIG. 3 , if this higher pressure is encountered, one of the two compressors of the refrigeration unit is switched off. In a presently contemplated embodiment, for example, this pressure may be approximately 350 psi. In the same presently contemplated embodiment, although one of the compressors is deactivated, both fans at least temporarily stay on to extract heat from the condenser. Stopping the compressor, as indicated at step  80  in  FIG. 3 , is preferably followed by reducing the overall air flow rate as indicated at step  82  in  FIG. 3 . Reducing the airflow at step  82  may be performed by adjusting the damper plate  48  (see  FIG. 2 ). Although the air flow rate does not necessarily need to be reduced, its reduction may aid in providing the desired temperature of air to the aircraft, albeit at a reduced flow rate. 
     The arrangement of  FIG. 2  includes additional pressure switches  83  and  56 . Pressure switch  83 , in the present embodiment, serves to avoid operation of either compressor in the event that incoming refrigerant pressure is too low. Thus, pressure switch  83  can avoid damage to the compressors in such situations. Pressure switch  56 , on the other hand, provides a high-pressure shutdown. At some elevated pressure, such as approximately 410 psi, pressure switch  56  will cause the unit to shut down, terminating operation of the refrigeration system. Even at this point, blower  46  may continue to supply a flow of air to the aircraft, albeit at a higher temperature. 
     It should be noted that the various pressure transducers, pressure switches, and temperature sensors discussed above with reference to unit  20  and steps  70 - 82  of  FIG. 3  may be replicated, although in certain embodiments offset from those of unit  20  for the additional units  22  and  24 . That is, the temperatures at which additional fans become operative in each unit, and the pressures at which additional compressors become operative and are then deactivated can be staggered to coordinate operation of the refrigeration units. 
     Pressure sensors or transducers will be coupled to the controller  26  and will provide inputs for logical operations performed by the controller similar to those discussed above with reference to  FIG. 3 . That is, the controller can command operation of an additional compressor if the thermal load is higher than anticipated, as indicated by temperatures that do not level off at the desired set points. Similarly, controller  26 , based upon detected pressures from the transducers, can control operation of additional fans for the condenser, and can activate and deactivate compressors as discussed above. Such coordinated control can also assist in bringing into operation additional refrigeration units as thermal load increases, and for shutting down compressors and refrigeration units in an organized fashion, cascading with respect to one another when elevated pressures are reached due to even higher thermal loads. 
     While only certain features of the invention have been illustrated and described herein, many modifications and changes will occur to those skilled in the art. It is, therefore, to be understood that the appended claims are intended to cover all such modifications and changes as fall within the true spirit of the invention. For example, the systems and methods of the invention may employ various refrigeration components and working fluids, including, for example, refrigerants commonly referred to in the field by the designations R22 and R407c. Moreover, it should be noted that, while the invention has been described in the context of portable aircraft conditioned air systems, it may be applied in a variety of settings, including permanent installations, such as for building cooling, as well as on various vehicles, and so forth.