Patent Application
20130209901
The present disclosure relates generally to heat transfer systems and, more particularly, to methods and systems for transferring heat produced by a fuel cell module positioned onboard an aircraft.
Known aircraft include a plurality of engines that generate lifting power. At least some known aircraft include electrical components that require electricity to operate. To provide electricity to such electrical components, at least some known aircraft extract power from the engines. However, supplying electricity from the engines to the electrical components increases an overall fuel consumption of the engine. To facilitate reducing electrical demand from the engines, at least some known aircraft include fuel cells that generate power for use in powering onboard electrical components. However, at least some known aircraft do not efficiently utilize electricity and/or byproducts generated by the fuel cell.
In one aspect, a method is provided for transferring heat produced by a fuel cell module positioned onboard an aircraft. The method includes coupling a loop heat pipe (LHP) module to the fuel cell module. The LHP module includes a first fluid that absorbs the heat from the fuel cell module and is channeled through the LHP module.
In another aspect, a power generation system is provided for use on an aircraft. The power generation system includes a fuel cell module configured to produce heat and a LHP module coupled to the fuel cell module. The LHP module includes a first fluid that absorbs the heat from the fuel cell module and is channeled through the LHP module.
In yet another aspect, a system is provided. The system includes an aircraft and an electronic device positioned onboard the aircraft. A fuel cell module is coupled to the electronic device. The fuel cell module is configured to produce electricity and heat. The electricity is transmitted to the electronic device. A LHP module is coupled to the fuel cell module. The LHP module includes a first fluid that absorbs the heat from the fuel cell module and is channeled through the LHP module.
The features, functions, and advantages described herein may be achieved independently in various embodiments of the present disclosure or may be combined in yet other embodiments, further details of which may be seen with reference to the following description and drawings.
Although specific features of various embodiments may be shown in some drawings and not in others, this is for convenience only. Any feature of any drawing may be referenced and/or claimed in combination with any feature of any other drawing.
The subject matter described herein relates generally to heat transfer systems and, more particularly, to methods and systems for transferring heat produced by a fuel cell module positioned onboard an aircraft. In one embodiment, a power generation system onboard an aircraft includes a fuel cell module configured to produce heat and electricity. A loop heat pipe (LHP) module is coupled to the fuel cell module. The LHP module includes a first fluid (i.e., a working fluid) that absorbs the heat from the fuel cell module and is channeled through the LHP module. As such, the LHP module facilitates cooling the fuel cell module.
As used herein, the term “load” or “external load” refers to any device and/or machine that utilizes electricity, heat, water, and/or any other byproduct generated, created, and/or produced by another device and/or machine. An element or step recited in the singular and proceeded with the word “a” or “an” should be understood as not excluding plural elements or steps unless such exclusion is explicitly recited. Moreover, an element or step recited in the singular and proceeded with the word “a” or “an” should be understood as not excluding plural elements or steps unless such exclusion is explicitly recited. Moreover, references to “one embodiment” of the present invention and/or the “exemplary embodiment” are not intended to be interpreted as excluding the existence of additional embodiments that also incorporate the recited features.
In the exemplary embodiment, system 200 includes a heat transfer module or loop heat pipe (LHP) module 218. In the exemplary embodiment, LHP module 218 includes an evaporator 220, a condenser 222, and a heat transfer loop 224. In the exemplary embodiment, evaporator 220 includes a fine pore wick structure for capillary pumping of the fluid and circulation inside LHP module 218. In the exemplary embodiment, evaporator 220 is coupled directly to fuel cell module 202 to absorb heat generated by fuel cell module 202. Alternatively, evaporator 220 may have any configuration and/or be coupled to any device and/or element that enables system 200 to function as described herein.
In the exemplary embodiment, heat transfer loop 224 includes a vapor line 226 that channels vapor from evaporator 220 towards condenser 222, and a liquid line 228 that channels liquid from condenser 222 towards evaporator 220. That is, in the exemplary embodiment, LHP module 218 is a two-phase heat transfer device that uses capillary action to remove heat from fuel cell module 202 and passively transfer the heat to condenser 222.
In the exemplary embodiment, a load 230 is coupled to condenser 222 such that the heat may be used onboard aircraft 100. For example, load 230 may be an appliance including, but not limited to, a coffee maker, a hot water faucet, and/or an oven. Alternatively, load 230 may be any other appliance and/or device that enables system 200 to function as described herein.
In the exemplary embodiment, a second heat transfer module 232 is coupled to LHP module 218. In the exemplary embodiment, second heat transfer module 232 includes a heat spreader 234, a radiator 236, and a fluid line 238 extending therebetween. In the exemplary embodiment, heat spreader 234 is configured to absorb heat from condenser 222 and transfer the heat to fluid channeled through fluid line 238. In the exemplary embodiment, second heat transfer module 232 includes a pump 240 such that fluid is actively channeled through fluid line 238. Alternatively, second heat transfer system 232 may be a passive system such that heat is passively transferred between heat spreader 234 and radiator 236. In the exemplary embodiment, radiator 236 is positioned such that heat may be transferred to the ambient environment.
During operation, fuel cell module 202 receives fuel 204 and air 206 and generates and/or produces electricity 208, water 210, air 212, and/or heat. In the exemplary embodiment, water 210 is channeled through conduit 214, and water purifier 216 makes water 210 potable.
In the exemplary embodiment, evaporator 220 absorbs heat from fuel cell module 202 as fluid is channeled through heat transfer loop 224. More specifically, in the exemplary embodiment, liquid channeled through evaporator 220 absorbs heat from fuel cell module 202 to enable the liquid to change into a vapor. That is, in the exemplary embodiment, heat absorbed at evaporator 220 enables the liquid to convert into vapor through a phase-change process. In the exemplary embodiment, the vapor is discharged from evaporator 220 and channeled through vapor line 226 towards condenser 222. As such, in the exemplary embodiment, heat is transported to condenser 222. In the exemplary embodiment, heat is transferred from condenser 222 towards load 230 and/or heat spreader 234 to enable the vapor to change into a liquid. That is, in the exemplary embodiment, the phase-change process takes place after the vapor gives out its latent heat. In the exemplary embodiment, the liquid is discharged from condenser 222 and channeled through liquid line 228 towards evaporator 220.
In the exemplary embodiment, second heat transfer module 232 is selectively operated to transfer heat from LHP module 218 into the ambient environment. That is, in the exemplary embodiment, pump 240 is not activated when the heat is being used by load 230, and is activated when the heat is not being used by load 230.
In the exemplary embodiment, condenser 222 is positioned within a container 246 configured to channel water therethrough. More specifically, in the exemplary embodiment, container 246 includes an inlet 248 configured to receive water, and an outlet 250 configured to discharge water. In the exemplary embodiment, water is channeled through container 246 to facilitate cooling condenser 222 and/or fluid channeled through LHP module 218.
System 500 is generally similar to system 200, but, instead of LHP module 218, a liquid-to-liquid heat exchanger 502 is coupled to conduit 214 to facilitate absorbing, using, and/or dissipating heat generated by fuel cell module 202. In the exemplary embodiment, heat exchanger 502 includes a conduit 504 extending therethrough that channels cold water into heat exchanger 502, wherein the water absorbs heat from conduit 214 and/or water 210 within conduit 214 such that hot water may be discharged from heat exchanger 502 through conduit 504.
System 600 is generally similar to system 200, but, instead of LHP module 218, a liquid-to-air heat exchanger 602 is coupled to conduit 214 to facilitate absorbing, using, and/or dissipating heat generated by fuel cell module 202. In the exemplary embodiment, heat exchanger 602 includes a conduit 604 extending therethrough that channels cold air into heat exchanger 602, wherein the air absorbs heat from conduit 214 and/or water 210 within conduit 214 such that hot air may be discharged from heat exchanger 602 through conduit 604.
The embodiments described herein relate generally to heat transfer systems and, more particularly, to methods and systems for transferring heat produced by a fuel cell module positioned onboard an aircraft. The embodiments described herein facilitate increasing fuel cell efficiency for use in an airplane galley and/or decreasing a quantity of airplane generated power required to operate the airplane during flight. As such, the embodiments described herein facilitate decreasing an amount of power used by galleys through energy storage, use of combined heat and power from fuel cells, and efficient transfer of the heat from the fuel cell to galley insert loads.
Exemplary embodiments of methods and systems for transferring heat in an aircraft environment are described above in detail. The methods and systems are not limited to the specific embodiments described herein, but rather, components of systems and/or steps of the method may be utilized independently and separately from other components and/or steps described herein. Each method step and each component may also be used in combination with other method steps and/or components. Although specific features of various embodiments may be shown in some drawings and not in others, this is for convenience only. Any feature of a drawing may be referenced and/or claimed in combination with any feature of any other drawing.
This written description uses examples to disclose the embodiments, including the best mode, and also to enable any person skilled in the art to practice the embodiments, including making and using any devices or systems and performing any incorporated methods. The patentable scope of the disclosure is defined by the claims, and may include other examples that occur to those skilled in the art. Such other examples are intended to be within the scope of the claims if they have structural elements that do not differ from the literal language of the claims, or if they include equivalent structural elements with insubstantial differences from the literal language of the claims.
