Abstract:
A heat exchange system for an aircraft includes an aircraft controller for controlling an operation of an aircraft, a thermoelectric device having a low temperature side and a high temperature side, an inlet line that carries fluid through the low temperature side of the thermoelectric device and to the aircraft controller; and an outlet line that carrier the fluid away from the and aircraft controller through the high temperature side of the thermoelectric device. Heat is transferred away from the inlet line to the outlet line through the thermoelectric device when a predetermined condition is met.

Description:
BACKGROUND OF THE INVENTION 
       [0001]    The present disclosure relates to a heat exchanger for an aircraft and, in particular, to using a thermoelectric device to regulate the heat of fuel used to cool a controller of the aircraft. 
         [0002]    An aircraft has a number of electronic controllers used to control an operation of the aircraft. One such controller manages the function of the aircraft engines and is commonly known as a Full Authority Digital Engine Control or FADEC. The FADEC is generally installed in an environment of the aircraft susceptible to both very high temperatures and very low temperatures. For example, the FADEC may be installed in the engine bay where large amounts of heat are generated during flight conditions. In these conditions, the FADEC requires a substantial amount of cooling to regulate its operating temperature. When the aircraft is not in flight, however, the engine bay may be extremely cold when ambient air temperature is low. At these conditions, the FADEC requires very little, if any, cooling. 
         [0003]    The FADEC, like many aircraft controls, is composed of electronic components that require moderate and uniform temperatures for optimal operation. The large temperature swings experienced by the FADEC is not conducive to the best performance of these temperature sensitive components. While there are electronic components that are capable of performing at the extreme temperature conditions of the aircraft, these components are generally very expensive and have relatively low performance (memory, process, reliability, or speed) compared to most modern electronics. 
         [0004]    A need therefore exists for an assembly and technique that maintains the electronics of an aircraft controller within their designed operating temperatures. 
       SUMMARY OF THE INVENTION 
       [0005]    According to one embodiment, a heat exchange system for an aircraft control is disclosed. The system includes an aircraft controller for controlling an operation of an aircraft, a thermoelectric device having a low temperature side and a high temperature side, an inlet line that carries fluid through the low temperature side of the thermoelectric device and to the aircraft controller and an outlet line that carries the fluid away from the and aircraft controller through the high temperature side of the thermoelectric device. In this embodiment, heat is transferred away from the inlet line to the outlet line through the thermoelectric device when a predetermined condition is met. 
         [0006]    According to another embodiment, an aircraft including any of the heat exchanger systems or heat exchange methods contained herein is disclosed. 
         [0007]    According to yet another embodiment, a method of cooling a Full Authority Digital Engine Control (FADEC) of an aircraft is disclosed. The method includes: pumping fuel from a fuel tank via an input line to the FADEC through a low temperature side of a thermoelectric device; pumping the fuel from the FADEC via an output line through a high temperature side of the thermoelectric device back to the fuel tank; applying an electrical signal to the thermoelectric device to cause heat from fluid in the input line to be transferred to fluid in output line. 
         [0008]    Additional features and advantages are realized through the techniques of the present disclosure. Other embodiments and aspects of the disclosure are described in detail herein. For a better understanding of the disclosure with the advantages and the features, refer to the description and to the drawings. 
     
    
     
       BRIEF DESCRIPTION OF THE DRAWINGS 
         [0009]    The subject matter which is regarded as the invention is particularly pointed out and distinctly claimed in the claims at the conclusion of the specification. The foregoing and other features, and advantages of the invention are apparent from the following detailed description taken in conjunction with the accompanying drawings in which: 
           [0010]      FIG. 1  shows a high level block diagram of heat exchange system where engine fuel is used as a cooling liquid to cool a FADEC; 
           [0011]      FIG. 2  shows a more detailed depiction of an example of a thermoelectric device that may be utilized in one embodiment; and 
           [0012]      FIG. 3  shows a more detailed version of a system according to one embodiment. 
       
    
    
     DETAILED DESCRIPTION OF THE INVENTION 
       [0013]    Embodiments described herein to closed loop cooling system for a FADEC. The FADEC may be part of an aircraft and, as such, embodiments disclosed herein may be implanted on an aircraft. The system may utilize thermoelectric (TE) device positioned between the inbound and outbound fuel lines providing cooling fuel to the FADEC. In one embodiment, the TE device is superlattice device. The TE cooler, when powered, “pumps” heat from the inbound fuel line and provides that heat to the hot, outbound fuel line. According to one embodiment, the TE device is sized to handle fuel temperatures up to 190° F. at flow rates currently used for FADEC cooling. Closed loop control is achieved when fuel temperature sensing is applied to the inbound flow. When temperatures exceed inbound limits, a controller adjusts power provided to the TE device to effect cooling of the fuel to keep inbound fuel temperatures at the desired level. 
         [0014]      FIG. 1  shows a high level block diagram of heat exchange system  100  where engine fuel is used as a cooling liquid to cool a FADEC. Most generally, the system includes a fuel tank  102 , one or more pump (shown as pump  103 ), a TE device  104  and electronics to be cooled  106 . In the following discussion the electronics may be referred to as a FADEC but is shall be understood that other electronics or even other non-electronic devices may be cooled in the manner disclosed herein. As such, while FADEC is used as a description, unless specifically required, the electronics to be cooled  106  are not limited to a FADEC. 
         [0015]    Engine fuel is stored in a reservoir or fuel tank  102 . The tank  102  may be a primary fuel tank used for all engines or an individual tank used for a single engine. Further, the tank  102  may be a portion of a larger tank. A pump  103  is provided that can pump fuel out of the tank  102 . This pump  103  may be a single pump or may include more than one pump. Regardless of the configuration, the pump  103  causes fuel form the tank  102  to be provided through an input line  110  to the FADEC  106 . The input line  110  passes through a low temperature heat source side  120  (referred to as “low temperature side” hereinafter) of the TE device  104  before being provided to the FADEC  106 . The fuel in the input line  110  passes through, around or near the FADEC  106  such that heat from the FADEC  106  is transferred to the fuel. The fuel then returns to the fuel tank  102  via return line  112 . Before returning the fuel tank  102  via return line  112 , the fuel passes through the high temperature heat sink side  122  (referred to as “high temperature side”) hereinafter of the TE device  104 . In general, to the extent that the TE device removed heat from the fuel as it passed through the low temperature side  120 , that heat is at least partially transferred to the fuel in the return line  112  as it passes through the high temperature heat sink side  122  of the TE device  104 . 
         [0016]    In operation, fuel enters the lower temperature side  120  of the TE device  104  at a first temperature T 1 . When operating, the energy (heat) is removed from the fuel by the TE device  104  such that it leaves the TE device at a second, lower temperature T 2 . The fuel then enters the FADEC  106  where it has heat transferred to it and leaves the FADEC at T 3 . It is assumed that in operation, T 3  is greater than T 2 . 
         [0017]    As mentioned above, as the fuel in the return line  112  is passed through the high temperature side  122  of the TE device  104 , heat removed from the fuel at the low temperature side  120  is added to the fuel such that it exits the TE device  104  at an even higher temperature T 4 . That is, T 4  is greater than T 3  when the TE device is operating. 
         [0018]    In one embodiment, the TE device  104  may be formed such that that application of a voltage and current causes heat in one location to be moved to another location. With reference to  FIG. 2 , application of a voltage V and current to the low temperature side causes heat from to move from one side of the TE device to the other. The direction of the travel is based on the polarity of the voltage and the rate is based on the magnitude of the current. As shown, the direction of heat travel is against the temperature gradient. 
         [0019]    As discussed above, and now with reference to  FIG. 3 , at times the TE device  104  may not be operating to remove heat from the input line  110 . Such a case may exist when T 1  is sufficiently low to cool the FADEC  106  without having heat removed from it. To that end, in one embodiment, the system  100  may include a temperature sensor  304  that measures the temperature of the fuel in the input line  110  after it exits the TE device  104 . Of course, the position of the sensor could be moved such that it is upstream (e.g., closer to the tank  102  than the TE device  104 ) of the TE device  104  in one embodiment. 
         [0020]    In such a system a sensor  302  is also provided that measures the temperature in or near the FADEC  106 . While shown in the FADEC itself, it shall be understood that the sensor need only be able to measure the temperature of the FADEC and does not have to necessarily be within it. Based on the two temperatures, a cooling controller  306  determines how much (if any) heat needs to be removed from the fuel such that T 2  is at a level that may effectively cool the FADEC  106 . In one embodiment, the TE device  104  may operate when the temperature of the fluid leaving it is over a predetermined level. In another embodiment, the operation of the TE device  104  may depend on a difference in the temperature measured by sensor  302  and that measured by the temperature sensor  304 . That is, the TE device may operate when a difference between a temperature of the fuel leaving the TE device  104  and a temperature of the FADEC  106  is below a limit difference. 
         [0021]    Regardless, the amount of change needed will determine the voltage polarity and current level provided on line  308  to set the rate at which the TE device  104  removes heat from the input line  110 . The exact manner in which voltage and current is applied will depend on the type/configuration of the TE device  104  used. 
         [0022]    The above description provides for a system  100  that works in a closed loop manner to control the cooling of a FADEC  106 . The “closed” refers to the means of controlling the temperature. For example, an open loop temperature control is one that sets temperature based on a table or some other condition that is fixed. As here, a closed loop system closes the control loop by measuring temperature and commanding a response (e.g., turning on the TE device). 
         [0023]    The terminology used herein is for the purpose of describing particular embodiments only and is not intended to be limiting of the invention. As used herein, the singular forms “a”, “an” and “the” are intended to include the plural forms as well, unless the context clearly indicates otherwise. It will be further understood that the terms “comprises” and/or “comprising,” when used in this specification, specify the presence of stated features, integers, steps, operations, elements, and/or components, but do not preclude the presence or addition of one more other features, integers, steps, operations, element components, and/or groups thereof. 
         [0024]    While the invention has been described in detail in connection with only a limited number of embodiments, it should be readily understood that the invention is not limited to such disclosed embodiments. Rather, the invention can be modified to incorporate any number of variations, alterations, substitutions or equivalent arrangements not heretofore described, but which are commensurate with the spirit and scope of the invention. 
         [0025]    Additionally, while various embodiments of the invention have been described, it is to be understood that aspects of the invention may include only some of the described embodiments. Accordingly, the invention is not to be seen as limited by the foregoing description, but is only limited by the scope of the appended claims.