Abstract:
One embodiment of the present invention is a unique airborne electrical power and thermal management system. Another embodiment is a unique aircraft. Other embodiments include apparatuses, systems, devices, hardware, methods, and combinations for aircraft and electrical power and thermal management systems. Further embodiments, forms, features, aspects, benefits, and advantages of the present application will become apparent from the description and figures provided herewith.

Description:
CROSS REFERENCE 
       [0001]    The present application claims the benefit of U.S. Provisional Patent Application No. 61/468,387, filed Mar. 28, 2011, which is incorporated herein by reference. 
     
    
     FIELD OF THE INVENTION 
       [0002]    The present invention relates to aircraft, and more particularly, to an aircraft having an airborne electrical power and thermal management system. 
       BACKGROUND 
       [0003]    Airborne systems that effectively provide electrical power and manage thermal energy remain an area of interest. Some existing systems have various shortcomings, drawbacks, and disadvantages relative to certain applications. Accordingly, there remains a need for further contributions in this area of technology. 
       SUMMARY 
       [0004]    One embodiment of the present invention is a unique airborne electrical power and thermal management system. Another embodiment is a unique aircraft. Other embodiments include apparatuses, systems, devices, hardware, methods, and combinations for aircraft and electrical power and thermal management systems. Further embodiments, forms, features, aspects, benefits, and advantages of the present application will become apparent from the description and figures provided herewith. 
     
    
     
       BRIEF DESCRIPTION OF THE DRAWINGS 
         [0005]    The description herein makes reference to the accompanying drawings wherein like reference numerals refer to like parts throughout the several views, and wherein: 
           [0006]      FIG. 1  illustrates an aircraft employed in accordance with an embodiment of the present invention. 
           [0007]      FIG. 2  schematically illustrates an electrical power and thermal management system operating to provide electrical power to and manage thermal energy for a system in accordance with an embodiment of the present invention. 
           [0008]      FIG. 3  schematically illustrates a non-limiting example of some aspects of an electrical power and thermal management system in accordance with an embodiment of the present invention. 
           [0009]      FIG. 4  schematically illustrates a non-limiting example of some aspects of an electrical power and thermal management system in accordance with an embodiment of the present invention. 
           [0010]      FIG. 5  schematically illustrates a non-limiting example of some aspects of an electrical power and thermal management system in accordance with an embodiment of the present invention. 
       
    
    
     DETAILED DESCRIPTION 
       [0011]    For purposes of promoting an understanding of the principles of the invention, reference will now be made to the embodiments illustrated in the drawings, and specific language will be used to describe the same. It will nonetheless be understood that no limitation of the scope of the invention is intended by the illustration and description of certain embodiments of the invention. In addition, any alterations and/or modifications of the illustrated and/or described embodiment(s) are contemplated as being within the scope of the present invention. Further, any other applications of the principles of the invention, as illustrated and/or described herein, as would normally occur to one skilled in the art to which the invention pertains, are contemplated as being within the scope of the present invention. 
         [0012]    Referring to  FIG. 1 , there are illustrated some aspects of a non-limiting example of an aircraft  10  employed in accordance with an embodiment of the present invention. Aircraft  10  includes a fuselage  12 , wings  14 , an empennage  16 , four gas turbine engine propulsion systems  18  and two external pods  20 . In one form, aircraft  10  is a multi-engine military turboprop aircraft. In other embodiments, aircraft  10  may be any fixed-wing aircraft, including turbofan aircraft, turbojet aircraft and turboprop aircraft. In still other embodiments, aircraft  10  may be a rotary-wing aircraft or a combination rotary-wing/fixed-wing aircraft. In various embodiments, aircraft  10  may have a single propulsion engine or a plurality of propulsion engines. In addition to propulsion engines, aircraft  10  may include one or more gas turbine auxiliary power units. In addition, in various embodiments, aircraft  10  may employ any number of wings  14 . Empennage  16  may employ a single or multiple flight control surfaces. 
         [0013]    Referring to  FIG. 2 , aircraft  10  includes an airborne electrical power and thermal management system  22 , which is configured to provide electrical power and manage thermal loads for a system  24 . In one form, system  24  is a directed energy weapon system, such as a high power laser system, a high power microwave system and/or a high power millimeter wave system. In other embodiments, system  24  may include other aircraft electrical and thermal loads. As illustrated in  FIG. 2 , in one form, system  22  is configured to provide electrical power to system  24 , and to receive thermal energy from system  24 , e.g., heat energy rejected by system  24 . In various embodiments, system  22  is partially or completely disposed within an external pod  20 , which, for example, may be retrofitted from use as an external fuel tank pod. In one form, external pod  20  is configured to appear similar to a conventional external fuel tank pod, e.g., in order to avoid altering of the appearance of aircraft  10  or to minimize any alteration of the appearance of aircraft  10  due to the inclusion of airborne electrical power and thermal management system  22  and/or system  24 . 
         [0014]    Referring to  FIG. 3 , a non-limiting example of some aspects of an electrical power and thermal management system  22  in accordance with an embodiment of the present invention is schematically depicted. In one form, electrical power and thermal management system  22  includes a combustor  26 , a turbine  28 , a generator  30 , a refrigerant compressor  32 , a condenser  34 , an expansion valve  36  and an evaporator  38  that is configured to chill a fluid, e.g., water. In some embodiments described herein, combustor  26  and turbine  28  (via combustor  26 ) are supplied with pressurized air from one or more gas turbine engine propulsion systems  18  in order to produce power to drive generator  30 , refrigerant compressor  32  and/or other components. In some embodiments, electrical power and thermal management system  22  may include a complete gas turbine engine  39  disposed within pod  20 , wherein engine  39  includes a compressor (not shown) in fluid communication with combustor  26 , and turbine  28  in fluid communication with combustor  26 . The compressor of engine  39  may be supplied with ambient air, e.g., ram air, for example, via one or more openings (not shown) in pod  20 , and/or may be supplied with pressurized air from a bleed air port of one or more gas turbine engine propulsion systems  18 , e.g., a compressor bleed port. Refrigerant compressor  32 , condenser  34 , expansion valve  36  and evaporator  38  are parts of a refrigeration system configured to handle the thermal loads of system  24 , e.g., by extracting heat from one or more components of system  24 . 
         [0015]    In some embodiments, electrical power and thermal management system  22  may include one or more other cooling systems to handle the thermal loads of system  24  in addition to or in place of a refrigeration system. For example, a cooling fluid may be circulated through or in proximity to one or more system  24  components to absorb heat from the system  24  components. The cooling fluid may then be circulated through one or more heat exchangers, e.g., air cooled heat exchangers disposed within external pod  20 , for removal of the heat from aircraft  10 . Although many or all components of the refrigeration system and/or other cooling system (e.g., one or more heat exchangers) may be disposed within external pod  20 , some such components may be located elsewhere in aircraft  10 , i.e., not in external pod  20 , including, for example and without limitation, one or more refrigerant and/or cooling fluid return pumps. Although components of electrical power and thermal management system  22  are depicted in certain locations and orientations within external pod  20  in  FIG. 3  (and in  FIGS. 4  and  5 ), it will be understood that in various embodiments, components of electrical power and thermal management system  22  and/or other components may be disposed in any desired locations and orientations within external pod  20 . 
         [0016]    In one form, combustor  26 , turbine  28 , generator  30 , refrigerant compressor  32 , condenser  34 , expansion valve  36  and evaporator  38  are located within external pod  20 . It will be understood that an electrical power and thermal management system  22  and/or components thereof may be mounted in each external pod  20 , and that the output of both may be combined in order to meet electrical power and thermal management demands of aircraft  10  and/or any weapon system installed therein and/or mounted thereon. In some embodiments, one or more of combustor  26 , turbine  28 , generator  30 , refrigerant compressor  32 , condenser  34 , expansion valve  36  and evaporator  38  may be mounted in other locations. 
         [0017]    Combustor  26  is in fluid communication with turbine  28 . During the operation of system  22 , combustor  26  is supplied with pressurized air from a bleed port  40  of one or more gas turbine engine propulsion systems  18 , e.g., a compressor bleed port. Combustor  26  includes one or more fuel injectors (not shown), which are supplied with fuel from a fuel tank  42 , e.g., an aircraft  10  fuel tank. Combustor  26  is configured to mix the fuel with pressurized air received from bleed port  40  and to ignite the mixture using one or more igniters (not shown). Combustor  26  is configured to contain the combustion process, and to discharge the pressurized air, heated by the combustion process, into turbine  28 . Turbine  28  is coupled to both generator  30  and refrigerant compressor  32 , and is operative to power both generator  30  and refrigerant compressor  32  by extracting energy from the hot gases discharged from combustor  26 . In one form, generator  30  and refrigerant compressor  32  operate at the same rotational speed as turbine  28 . In other embodiments, one or more gearboxes may be interposed between turbine  28  and generator  30  and/or refrigerant compressor  32  to drive generator  30  and/or refrigerant compressor  32  at a different speed of rotation than turbine  28 . 
         [0018]    Condenser  34  is fluidly coupled to the output of refrigerant compressor  32 . Condenser  34  is operative to condense the refrigerant discharged by refrigerant compressor  32  during the operation of turbine  28 . In one form, ambient air, e.g., including ram air, is used as a coolant for extracting heat from condenser  34 . In one form, an inlet scoop (not shown), e.g., a ram scoop (not shown) is employed to provide ambient air, e.g., ram air, for extracting heat from condenser  34 . In other embodiments, air and/or one or more other fluids may be employed to extract heat from condenser  34  via one or more other means. Expansion valve  36  is fluidly coupled to the outlet of condenser  34 , and is configured to expand the liquid refrigerant received from condenser  34 , e.g., adiabatic expansion, which reduces the temperature of the liquid refrigerant. In other embodiments, other means may be employed in addition to or in place of expansion valve  36  to expand the liquid refrigerant received from condenser  34 . 
         [0019]    Evaporator  38  is in fluid communication with condenser  34  via expansion valve  36 . In particular, the refrigerant inlet of evaporator  38  is fluidly coupled to expansion valve  36 , and is operative to receive the refrigerant from expansion valve  36 . The refrigerant outlet of evaporator  38  is fluidly coupled to the inlet of refrigerant compressor  32 , and returns refrigerant vapor to the inlet of refrigerant compressor  32 . Evaporator  38  is configured to chill fluid for delivery to a fuselage  12  mounted chilled fluid manifold  44 . The chilled fluid outlet of evaporator  38  is in fluid communication with chilled fluid manifold  44 . A recirculation pump (not shown) circulates a fluid, e.g., water and/or one or more other suitable fluids through evaporator  38  and chilled fluid manifold  44 , transmitting heat in the fluid from chilled fluid manifold  44  to evaporator  38 . Chilled fluid manifold  44  is in fluid communication with a plurality of heat sources  46 ,  48  and  50 , and is configured to distribute chilled fluid to heat sources  46 ,  48  and  50 . Heat sources  46 ,  48  and  50  may be, for example and without limitation, system  24  components, such as a high power microwave module, a modulator and an antenna module. In other embodiments, other components of aircraft systems, weapon systems, propulsion systems and system  22  may be cooled using the fluid chilled by evaporator  38 , in addition to or in place of those heat sources mentioned herein. The fluid outlets of heat sources  46 ,  48  and  50  are in fluid communication with evaporator  38 . Chilled fluid from chilled fluid manifold  44  is employed to extract heat from heat sources  46 ,  48  and  50  to cool those components. The fluid heated by heat sources  46 ,  48  and  50  is then circulated through and re-chilled by evaporator  38 . 
         [0020]    Generator  30  is electrically coupled to one or more power conditioning units  52 , e.g., located in fuselage  12 , for providing power in a desired form for one or more electrically powered devices  54 , only one of which is illustrated for the sake of clarity. Conditioning unit  52  may be, for example and without limitation, a DC/DC converter or any signal conditioning or power converting component. Device  54  may be, for example and without limitation, a component of system  24 , such as a gyrotron or a cathode heater, high power microwave module, a modulator and/or an antenna module or other directed energy weapon system component, or may be any electrical component. In some embodiments, electrical power and thermal management system  22  may include systems for storing energy and/or generating electrical power, in addition to or in place of generator  30 , in order to supply power to one or more devices  54 . For example and without limitation, one or more batteries (not shown) and/or flywheel/motor/generator systems (not shown) and/or fuel cell systems may be employed to provide and/or store energy for use by one or more devices  54 , e.g., to handle peak loads and/or to provide electrical power to one or more devices  54  during startup of electrical power and thermal management system  22 . In various embodiments, such systems for storing energy may be disposed completely or partially within external pod  20  or elsewhere within or on aircraft  10 . 
         [0021]    During operation, one or more devices  54  are powered by electrical power and thermal management system  22 , and one or more heat sources, such as heat sources  46 ,  48  and  50  are cooled by electrical power and thermal management system  22 . 
         [0022]    Referring to  FIG. 4 , a non-limiting example of some aspects of an electrical power and thermal management system  122  in accordance with an embodiment of the present invention is schematically depicted. Electrical power and thermal management system  122  employs many of the same components for the same operations as set forth above with respect to electrical power and thermal management system  22 , and hence, the description of such components, interconnections and operations is also applicable to electrical power and thermal management system  122 . 
         [0023]    In addition to combustor  26 , turbine  28 , generator  30 , refrigerant compressor  32  and condenser  34 , electrical power and thermal management system  122  includes a refrigerant receiver  124 , a refrigerant circulation pump  126 , an expansion valve  128 , an evaporator  130  and a thermal energy storage (TES) system  132 . TES  132  may be any type of system configured to store thermal energy, e.g., using one or more gases, liquids, solids and/or eutectic mixtures. Refrigerant receiver  124  is in fluid communication with the outlet of condenser  34 , and is operative to receive liquid refrigerant from condenser  34 . Recirculation pump  126  is in fluid communication with the outlet of refrigerant receiver  124  and the inlet of expansion valve  128 . The outlet of expansion valve  128  is in fluid communication with the fluid inlet of evaporator  130 . The vapor outlet of evaporator is in fluid communication with the inlet of refrigerant compressor  32 . 
         [0024]    Recirculation pump  126  is configured to pump liquid refrigerant to expansion valve  128 . Expansion valve  128  is configured to expand the liquid refrigerant. In other embodiments, other means may be employed in addition to or in place of expansion valve  128  to expand the liquid refrigerant received from condenser  34 . Evaporator  130  is configured to remove heat from TES  132 . TES  132  is configured to remove heat from a plurality of heat sources  134 ,  136  and  138 , which may be, for example and without limitation, system  24  components, such as a high power microwave module, a modulator and an antenna module. In other embodiments, other components of aircraft systems, weapon systems, propulsion systems and system  122  may be cooled by evaporator  130  and TES  132 , in addition to or in place of those heat sources mentioned herein. It will be understood that an electrical power and thermal management system  122  may be mounted in each external pod  20 , and that the output of both may be combined in order to meet electrical power and thermal management demands of aircraft  10  and/or any weapon system installed therein and/or mounted thereon, such as system  24 . 
         [0025]    Referring to  FIG. 5 , a non-limiting example of some aspects of an electrical power and thermal management system  222  in accordance with an embodiment of the present invention is schematically depicted. Electrical power and thermal management system  222  employs many of the same components for the same operations as set forth above with respect to electrical power and thermal management systems  22  and  122 , and hence, the description of such components, interconnections and operations is also applicable to electrical power and thermal management system  222 . 
         [0026]    In addition to combustor  26 , turbine  28 , generator  30 , refrigerant compressor  32 , condenser  34 , refrigerant circulation pump  126 , expansion valve  128 , evaporator  130  and TES  132 , electrical power and thermal management system  222  includes a refrigerant receiver  224 , an expansion valve  226 , an evaporator  228 , a heat exchanger  230 , an expansion valve  232 , an evaporator  234 , a controller/rectifier  236  for generator  30 , an expansion valve  238  and an evaporator  240 . Refrigerant receiver  224  is configured to separate liquid refrigerant and refrigerant vapor, to return refrigerant vapor to the inlet of refrigerant compressor  32 , and to supply liquid refrigerant to recirculation pump  126 . Recirculation pump  126  is operative to circulate liquid refrigerant to the expansion valve and evaporator associated with each item to be cooled. For example, expansion valve  226  is in fluid communication with recirculation pump  126  and operative to receive liquid refrigerant from recirculation pump  126 . Evaporator  228  is in fluid communication with expansion valve  226  for receiving liquid refrigerant therefrom, and is in fluid communication with refrigerant receiver  224  for supplying refrigerant vapor thereto. Recirculation pump  126  supplies liquid refrigerant to expansion valve  226 , which is expanded and supplied to evaporator  228  for extracting heat from heat exchanger  230 . In one form, heat exchanger  230  is a turbine  28  lube oil cooler, from which heat is extracted by evaporator  228 . In other embodiments, heat exchanger  230  may be employed for cooling one or more other mediums and/or components in addition to or in place of turbine  28  lube oil. The refrigerant vapor exiting evaporator  228  is returned to refrigerant receiver  224 , from where it is supplied to the inlet of refrigerant compressor  32 . 
         [0027]    Recirculation pump  126  also supplies liquid refrigerant to expansion valve  232 , which is expanded and supplied to evaporator  234  for extracting heat from controller/rectifier  236 . In other embodiments, evaporator  234  may be employed for cooling one or more other components in addition to or in place of controller/rectifier  236 . The refrigerant vapor exiting evaporator  234  is returned to refrigerant receiver  224 , from where it is supplied to the inlet of refrigerant compressor  32 . 
         [0028]    Recirculation pump  126  also supplies liquid refrigerant to expansion valve  238 , which is expanded and supplied to evaporator  240  for extracting heat from generator  30 . In other embodiments, evaporator  240  may be employed for cooling one or more other components in addition to or in place of generator  30 . The refrigerant vapor exiting evaporator  240  is returned to refrigerant receiver  224 , from where it is supplied to the inlet of refrigerant compressor  32 . 
         [0029]    Recirculation pump  126  also supplies liquid refrigerant to expansion valve  128 , which is expanded and supplied to evaporator  130  for extracting heat from TES  132  for providing cooling of heat sources  134 ,  136  and  138 . In other embodiments, evaporator  130  may be employed for cooling one or more other components in addition to or in place of heat sources  134 ,  136  and  138 . The refrigerant vapor exiting evaporator  130  is returned to refrigerant receiver  224 , from where it is supplied to the inlet of refrigerant compressor  32 . 
         [0030]    Embodiments of the present invention include an airborne electrical power and thermal management system, comprising: a turbine in fluid communication with a gas turbine engine bleed air source; a generator powered by the turbine and configured to provide power to an electrical load; a refrigerant compressor powered by the turbine; a condenser in fluid communication with the refrigerant compressor; and at least one evaporator in fluid communication with the condenser, wherein the at least one evaporator is configured to extract heat from at least one heat source. 
         [0031]    In a refinement, the electrical load includes a directed energy weapon system. 
         [0032]    In another refinement, the at least one heat source includes a directed energy weapon system. 
         [0033]    In yet another refinement, the system further comprises a combustor fluidly disposed between the turbine and the bleed air source, wherein the combustor is operative to mix fuel with air received from the bleed air source, combust the mixture, and discharge the combustion products to the turbine. 
         [0034]    In still another refinement, the at least one heat source is a plurality of heat sources, further comprising a chilled fluid manifold, wherein the at least one evaporator is configured to chill a fluid for delivery to the chilled fluid manifold; and wherein the chilled fluid manifold is configured to distribute chilled fluid to the plurality of heat sources. 
         [0035]    In yet still another refinement, the turbine, the generator, the refrigerant compressor and the condenser are disposed in an aircraft external pod. 
         [0036]    In an additional refinement, the system further comprises a gas turbine engine disposed within the external pod, wherein the turbine is a component of the gas turbine engine. 
         [0037]    In a further refinement, the system further comprises a refrigerant receiver; a thermal energy storage system; and an evaporator in fluid communication with the refrigerant receiver and operative to receive a liquid refrigerant from the refrigerant receiver and extract heat from the thermal energy storage system. 
         [0038]    In a yet further refinement, the system further comprises a refrigerant circulation pump configured to pump the liquid refrigerant to the thermal energy storage system. 
         [0039]    Embodiments of the present invention include an aircraft, comprising: a fuselage; a wing coupled to the fuselage; an empennage coupled to at least one of the fuselage and the wing; a gas turbine engine propulsion system coupled to the aircraft and having a bleed air port; an external pod coupled to the aircraft; and an electrical power and thermal management system at least partially disposed in the external pod, wherein the electrical power and thermal management system includes a turbine in fluid communication with the bleed air port; a generator powered by the turbine and configured to provide power to an aircraft electrical load; a refrigerant compressor powered by the turbine; a condenser in fluid communication with the refrigerant compressor; and at least one evaporator in fluid communication with the condenser, wherein the at least one evaporator is configured to extract heat from at least one heat source. 
         [0040]    In a refinement, the at least one heat source includes components of a directed energy weapon system. 
         [0041]    In another refinement, at least the turbine, the generator and the refrigerant compressor are disposed in the external pod. 
         [0042]    In yet another refinement, the condenser is disposed in the external pod. 
         [0043]    In still another refinement, the condenser is configured for cooling with ambient air supplied to the condenser from outside the external pod. 
         [0044]    In yet still another refinement, the condenser is configured for ram-air cooling. 
         [0045]    In an additional refinement, the aircraft further comprises a combustor fluidly disposed between the turbine and the bleed air port, wherein the combustor is operative to mix fuel with air received from the bleed air port, combust the mixture, and discharge the combustion products to the turbine. 
         [0046]    In a further refinement, the at least one heat source is a plurality of heat sources; wherein the at least one evaporator is a plurality of evaporators corresponding in number to the plurality of heat sources; and wherein each evaporator of the plurality of evaporators is configured to extract heat from a corresponding each heat source of the plurality of heat sources. 
         [0047]    In a yet further refinement, the aircraft further comprises a refrigerant circulation pump configured to pump liquid refrigerant to the plurality of evaporators. 
         [0048]    In a still further refinement, the aircraft further comprises a refrigerant receiver fluidly disposed between the condenser and the refrigerant circulation pump, wherein the refrigerant receiver is configured to accumulate liquid refrigerant. 
         [0049]    In a yet still further refinement, the refrigerant receiver is configured to separate liquid refrigerant from refrigerant vapor. 
         [0050]    In an additional refinement, the system further comprises a gas turbine engine disposed within the external pod, wherein the turbine is a component of the gas turbine engine. 
         [0051]    Embodiments of the present invention include an aircraft, comprising: a fuselage; a wing coupled to the fuselage; an empennage coupled to at least one of the fuselage and the wing; a gas turbine engine propulsion system having a bleed air port; and means for providing electrical power and thermal management, wherein the means for providing is in fluid communication with the bleed air port. 
         [0052]    In a refinement, the aircraft further comprises an external pod, wherein the means for providing is at least partially disposed in the external pod. 
         [0053]    In another refinement, the external pod is configured to appear similar to a conventional external fuel tank pod employed by the aircraft. 
         [0054]    Embodiments of the present invention include an aircraft, comprising: a fuselage; a wing coupled to the fuselage; an empennage coupled to at least one of the fuselage and the wing; a gas turbine engine propulsion system coupled to the aircraft for providing propulsive thrust to the aircraft; an external pod coupled to the aircraft; and an electrical power and thermal management system at least partially disposed in the external pod, wherein the electrical power and thermal management system includes a gas turbine engine disposed in the external pod; a generator powered by the gas turbine engine and configured to provide power to an aircraft electrical load; a refrigerant compressor powered by the gas turbine engine; a condenser in fluid communication with the refrigerant compressor; and at least one evaporator in fluid communication with the condenser, wherein the at least one evaporator is configured to extract heat from at least one heat source. 
         [0055]    In a refinement, the external pod is configured to appear similar to a conventional external fuel tank pod employed by the aircraft. 
         [0056]    While the invention has been described in connection with what is presently considered to be the most practical and preferred embodiment, it is to be understood that the invention is not to be limited to the disclosed embodiment(s), but on the contrary, is intended to cover various modifications and equivalent arrangements included within the spirit and scope of the appended claims, which scope is to be accorded the broadest interpretation so as to encompass all such modifications and equivalent structures as permitted under the law. Furthermore it should be understood that while the use of the word preferable, preferably, or preferred in the description above indicates that feature so described may be more desirable, it nonetheless may not be necessary and any embodiment lacking the same may be contemplated as within the scope of the invention, that scope being defined by the claims that follow. In reading the claims it is intended that when words such as “a,” “an,” “at least one” and “at least a portion” are used, there is no intention to limit the claim to only one item unless specifically stated to the contrary in the claim. Further, when the language “at least a portion” and/or “a portion” is used the item may include a portion and/or the entire item unless specifically stated to the contrary.