• 专利附录
  • 专利说明
  • 权利要求
  • 类似技术
  • 同族专利
  • 引用文献
  • 法律状态
  • 优先权
    • 专利摘要:
    Systems and methods for generating electricity for an aircraft are provided. In an exemplary embodiment, an aircraft power generation system (100) includes a thermionic generator (120) arranged to receive heat (112, 115) from at least one heat source (110). The thermionic generator (120) is adapted to generate electricity for the onboard system (s) (142, 144) at least partially from the heat (112, 115) received from the source (s) ) of heat (110). The power generating system (100) further includes a thermoelectric generator (130) arranged to receive residual heat (122) from the thermionic generator (120). The thermoelectric generator (130) is adapted to generate electricity to generate electricity for one or more edge systems (142, 144) at least partially from the heat (112, 115) received from the heat source (s) (110).
    公开号:FR3043255A1
    申请号:FR1660116
    申请日:2016-10-19
    公开日:2017-05-05
    发明作者:John Xiaozhong Wang
    申请人:GE Aviation Systems LLC；
    IPC主号:
    专利说明:

    1 Hybrid Thermoionic and Thermoelectric Hybrid Generator
    The present invention relates generally to power generation systems for aircraft.
    Electricity generation for on-board systems is often performed by generators driven mechanically by motors (eg gas turbine engines). These energy sources may require kerosene to be burned to produce electricity. The higher combustion of kerosene can exert on the engine an additional overload to the needs for the propulsion of the aircraft. Generating electricity from energy sources that do not require burning more kerosene may be desirable for some aircraft such as unmanned aerial vehicles.
    Thermoelectric generators have been used to produce electricity for aircraft. Thermoelectric generators are designed to convert heat from a heat source (eg solar heat, pick-up air, etc.) into electricity to operate on-board systems.
    Aspects and advantages of embodiments of the present invention will be set forth in part in the description below or may be apparent from the practice of the embodiments.
    A first exemplary aspect of the present invention relates to an aircraft power generation system. The power generation system includes a thermionic generator configured to receive heat from at least one heat source. The thermionic generator may be configured to generate electricity for one or more onboard systems at least partially from the heat received from the heat source (s). The system further includes a thermoelectric generator adapted to receive residual heat from the thermionic generator. The thermoelectric generator is adapted to generate electricity for one or more edge systems at least partially from residual heat received from the thermionic generator.
    Another exemplary aspect of the present invention relates to a method of generating electricity for one or more onboard systems. The method comprises receiving, in a thermionic generator, heat supplied by a heat source and generating electricity with the thermionic generator for the onboard system (s), at least partially from the heat received from the source (s) of heat. The method further comprises receiving, in a thermoelectric generator, residual heat emanating from the thermionic generator and generating electricity with the thermoelectric generator for the onboard system (s), at least partially from residual heat. received from the thermionic generator.
    Yet another example of an aspect of the present invention relates to an aircraft. The aircraft may include a heat source and an electricity distribution bus configured to distribute electricity to one or more onboard systems. The aircraft may include a thermionic generator designed to receive heat from the heat source. The thermionic generator may be designed to generate electricity for one or more onboard systems, at least partially from the heat received from the heat source (s). The system further includes a thermoelectric generator adapted to receive residual heat from the thermionic generator. The thermoelectric generator is adapted to generate electricity for one or more on-board systems, at least partially from residual heat received from the thermionic generator.
    Variations and modifications can be made to these exemplary aspects of the present invention.
    These features, aspects and advantages of various embodiments will become more apparent with reference to the following description and appended claims. The accompanying drawings, which form an integral part of this specification, illustrate embodiments of the present invention and, together with the description, serve to explain the related principles. The invention will be better understood from the detailed study of some embodiments taken by way of nonlimiting examples and illustrated by the appended drawings in which: FIG. 1 represents an overall view of an exemplary system of aircraft power generation according to exemplary embodiments of the present invention; FIG. 2 represents an example of an aircraft power generation system according to exemplary embodiments of the present invention; and FIG. 3 is a flowchart of an exemplary method according to exemplary embodiments of the present invention.
    Embodiments of the invention will now be considered in detail, of which one or more examples are illustrated in the drawings. Each example is provided as an explanation of the invention, not to limit the invention. In fact, it will be apparent to those skilled in the art that various modifications and variations can be made to the present invention without departing from the scope and spirit of the invention. For example, features illustrated or described as falling within one embodiment may be used with another embodiment to provide yet another embodiment. It is therefore understood that the present invention covers such modifications and variations as falling within the scope of the appended claims and their equivalents.
    Examples of aspects of the present invention relate to the generation of electricity for one or more aircraft system (s) in an aircraft. More particularly, an electricity generating system may include a thermionic generator designed to produce electricity using heat received from a heat source. The power generation system may further include a thermoelectric generator. The thermoelectric generator can receive residual heat that is not converted into electricity by the thermionic generator and can use the waste heat to produce more electricity for the aircraft.
    In this way, the combined thermionic generator and thermoelectric generator can increase power output and efficiency compared to prior art aircraft power generation systems employing thermoelectric generators. In addition, the thermoelectric generator may be a semiconductor device. As a result, the thermoelectric generator does not require moving members during operation, which can improve safety.
    In some embodiments, the thermoelectric generator may be a silicon carbide (SiC) metal oxide-semiconductor (MOSFET) field effect transistor thermoelectric generator. The use of a SiC MOSFET thermoelectric generator may require very little current for unblocking, while delivering much more current to excite an electrical load such as one or more onboard systems. Compared with silicon, SiC can withstand much higher voltages (eg a voltage 10 times higher) than silicon, carrying much stronger currents (eg with intensity 5 times higher) than silicon, have a much higher thermal conductivity (eg a thermal conductivity approximately 3 times greater) than silicon and can operate up to 400 ° C, against 150 ° C for silicon. Therefore, the use of a SiC MOSFET thermoelectric device can offer significant advantages for high temperature applications such as powering engine control systems for aircraft engines. In addition, SiC has a greater energy band gap than silicon and is more robust (more resistant) in the event of disturbances such as heat, radiation or intense electromagnetic fields in commercial and military aeronautics.
    In an exemplary implementation, the thermionic generator can receive heat from a heat source, in particular solar heat or heat associated with the sampling air or the exhaust gases of a combustion engine. 'aircraft. The heat supplied to the thermionic generator can cause a cathode (eg a hot cathode) of the thermionic generator to emit electrons, crossing an energy potential barrier, to an anode (eg a cooler electrode) producing electricity for a power distribution system of an aircraft. Residual heat (eg heat not converted to electrical energy by the thermionic generator) can be transferred from the anode of the thermionic generator to the thermoelectric generator. In some embodiments, the thermoelectric generator may also receive heat from the heat source. The thermoelectric generator can produce Seebeck effect electricity from the residual heat. The electricity produced by the thermionic generator and the thermoelectric generator can be supplied to an electricity distribution bus to power one or more on-board systems such as engine control systems, de-icing systems and other systems. on board.
    In one embodiment, the combined thermionic generator and thermoelectric generator can be used to power an integrated anti-icing system including an anti-icing system and a de-icing system. The aircraft anti-icing system may be configured to operate prior to the occurrence of icing-promoting conditions and may be designed to prevent frost formation on one or more parts of the aircraft. Anti-icing systems may include electrical heating elements incorporated into structural elements of aircraft subject to icing in order to maintain a surface temperature above the freezing point. The deicing system can be configured to remove ice after it has begun to accumulate on the aircraft. For example, the de-icing system may include electrical heating elements that can be energized during exposure to icing-promoting conditions to remove frost from parts of the aircraft.
    The thermionic generator and thermoelectric generator combined according to exemplary embodiments of the present invention may be particularly useful in unmanned aerial vehicles. For example, the combined thermionic and thermoelectric generator can reduce a thermal signature by enhancing the stealth of the unmanned aerial vehicle. More particularly, the combined thermionic and thermoelectric generator can receive heat from the sampling air and / or the exhaust gas from the propulsion engine, by reducing the infrared radiation emitted by these heat sources. In addition, the acoustic signature of the unmanned aerial vehicle can be reduced by producing electricity using semiconductor components, thermal and solar energy. This reduces the noise emanating from aircraft propulsion engines. In addition, the efficient use of heat due to solar energy can lead to greater flight distance and longer flight times for unmanned aerial vehicles.
    Figure 1 illustrates an exemplary power generation system 100 for an aircraft 50 according to exemplary embodiments of the present invention. The aircraft 50 can be any suitable aircraft, such as an unmanned aerial vehicle, a commercial aircraft, a military aircraft or other aircraft. The electricity generating system 100 can be used to supply electricity to various on-board systems present in the aircraft 50. In Figure 1, the power generating system 100 may include a heat source 110, a thermionic generator 120 and a thermoelectric generator 130. The thermionic generator 120 and the thermoelectric generator 130 may be designed to produce electricity, such as direct current, to be distributed to one or more onboard systems via a distribution bus. electricity 140. The electricity distribution bus 140 may, for example, be a DC bus.
    The present invention is presented, for purposes of illustration and discussion, with reference to a thermionic generator 120 and a thermoelectric generator 130 producing direct current. In some embodiments, the thermionic generator 120 and / or the thermoelectric generator 130 may be coupled to a current converter (eg an inverter) designed to convert the DC produced by the thermionic generator 120 and / or the AC thermoelectric generator 130 for supplying one or more AC loads to the aircraft 50, for example via a DC distribution bus.
    The heat source 110 may be any heat source for the operation of the thermionic generator 120 and may be on the aircraft 50 or away from it. In some embodiments, the heat source 110 may be pickup air and / or exhaust gas from a propulsion engine for the aircraft 50, such as a gas turbine engine. The thermionic generator 120 may be disposed in the aircraft 50 to receive heat from the sampling air and / or the exhaust gases from the propulsion engine. For example, in some embodiments, the sample air may be associated with the high temperature for supplying heat to the thermionic generator 120, as discussed in detail below.
    In some embodiments, the heat source 110 may be solar heat intercepted by the thermionic generator 120. For example, the solar energy may be intercepted, concentrated (e.g. several optical devices such as one or more reflectors, lenses, collimators, etc.) and supplied to the thermionic generator 120. Other suitable heat sources may be used without departing from the scope of the present invention.
    The thermionic generator 120 can convert the heat supplied to the thermionic generator 120 into electricity by emitting towards an anode, from a cathode receiving heat from the heat source 110, electrons crossing an energy potential barrier. The electricity produced by the thermionic generator 120 can be supplied to the electricity distribution bus 140.
    Residual heat 122 from the thermionic generator 120 can be supplied to the thermoelectric generator 130. The thermoelectric generator 130 can convert to electricity, by the Seebeck effect, at least a portion of the residual heat 122. In some embodiments, the thermoelectric generator 130 may also receive heat 115 from the heat source 110. The electricity produced by the thermoelectric generator 130 may be supplied to the electricity distribution system 140.
    The electricity distribution bus 140 can supply the electricity produced by the thermionic generator 120 and the thermoelectric generator 130 to power one or more edge systems. For example, the electricity distribution bus 140 can supply electricity to a motor control system 142. The engine control system 142 may provide one or more control instructions to various engine components (eg, a throttle, a relief valve, vanes, etc.) to control the operation of the engine aircraft. The electricity distribution bus 140 may also provide electricity, for example, to a frost protection system 144. The frost protection system 144 may comprise resistive elements with electric heating forming part of anti-icing systems. and de-icing systems which serve to limit and / or prevent frost formation on various aircraft components.
    The power distribution bus 140 may provide power to other onboard systems without departing from the scope of the present invention. For example, the electricity distribution bus 140 can provide power to an avionics system, a display system, a flight control system, digital control systems, throttle systems, systems, and the like. inertial reference systems, flight instrument systems, auxiliary power systems, fuel control system, engine vibration monitoring systems, communication systems, flap control systems, flight acquisition of flight data and other systems.
    Figure 2 is an overview of the operation of the power generating system including a thermionic generator 120 and a thermoelectric generator 130 combined according to exemplary embodiments of the present invention. The thermionic generator comprises a cathode (eg a hot cathode) 124 and an anode (eg a cold anode) 126 separated by a gap. Vapors such as cesium vapors can be introduced into the gap between cathode 124 and anode 126. Heat energy in the form of heat 112 from heat source 110 is supplied to cathode 124 to be at a higher temperature T1 with respect to a temperature T2 of the anode 126. This can cause the cathode 124 to emit, towards the anode 126, elections crossing an energy barrier of potential. The resulting current may be used to power the power distribution bus 140. For example, the cathode 124 may be electrically coupled to a positive terminal of the power distribution bus 140 and the anode 126 may be electrically coupled to a negative terminal of the electricity distribution bus 140.
    Residual heat 122 from the anode 126 of the thermionic generator 120 may be supplied to the thermoelectric generator 130. In some embodiments, the thermoelectric generator 130 may further receive heat 115 from the heat source 110. The generator thermoelectric may comprise a first conductor 132 and a second conductor 134. The first conductor 132 may have a temperature T3 greater than a temperature T4 of the second conductor 134 due to the residual heat 122 and / or heat 115 emanating from the source of heat 110.
    As illustrated in FIG. 2, the thermoelectric generator 130 may comprise a SiC MOSFET structure between the first conductor 132 and the second conductor 134. Portions 137 of the SiC MOSFET structure 135 may be of N-doped semiconductor material and portions thereof. 138 of the SiC MOSFET structure 135 may be of P-doped semiconductor material. When a current is supplied to the second conductor 134, electrons may flow into the SiC MOSFET structure 135 in the directions indicated by arrows 136 due to the difference in temperature between the first conductor 132 and the second conductor 134. In this way, electricity can be produced by the thermoelectric generator 130 and supplied to the electricity distribution bus 140 as a result of the application of heat residual 122 to the first conductor 132 of the thermoelectric generator 130 from the anode of the thermionic generator 120.
    Figure 3 shows a flowchart of an exemplary method 200 for generating electricity for one or more edge systems according to exemplary embodiments of the present invention. The method 200 can be implemented using the thermionic generator 120 and the thermoelectric generator 130 presented with reference to FIGS. 1 and 2. In addition, FIG. 3 indicates, for the purpose of illustration and discussion, steps performed in a particular order. Those of ordinary skill in the art, using the innovations presented herein, will understand that various steps of any of the methods described herein may be omitted, amplified, rearranged, modified and / or adapted in a variety of ways without departing from the scope of the present invention.
    In 202, the method comprises receiving, in a thermionic generator, heat emanating from one or more heat sources. For example, heat 112 from heat source 110 may be received at cathode 124 of thermionic generator 120. In 204 of Figure 3, electricity is generated with thermionic generator 120 from heat 112. received at the cathode 124 of the thermionic generator 120. More particularly, the heat 112 received at the cathode 124 can cause the emission of electrons from the cathode 124 to the anode 122 to produce electricity.
    In 206 of FIG. 3, the method comprises the reception of residual heat of the thermionic generator in the thermoelectric generator. For example, residual heat 122 emanating from the anode 126 of the thermionic generator 120 can be received in the thermoelectric generator 130 in order to increase the temperature of the first conductor 132 of the thermoelectric generator 130 with respect to the temperature of the second conductor 134 of the thermoelectric generator 130. thermoelectric generator 130. Optionally, heat may also be received from the heat source in the thermoelectric generator, as shown at 208 of FIG. 3. For example, heat 115 may be received in first conductor 132 of thermoelectric generator 130 .
    In 210, the process may include generating electricity with the thermoelectric generator. For example, the thermoelectric generator 130 may produce electricity due to a temperature difference between the first conductor 132 and the second conductor 134, caused by the application of residual heat 122 and / or heat 115 from the source 110 to the thermoelectric generator 130.
    At 212, the method may comprise supplying the electricity produced by the thermionic generator and / or the thermoelectric generator to an electricity distribution bus for supplying one or more edge systems. For example, electricity can be supplied to the electricity distribution bus 140 from the thermionic generator 120 and the electrical generator 130 to power onboard systems such as a motor control system 142, a control system frost protection 144 and other systems.
    Although specific details of various embodiments may be shown in some drawings and not others, it is only for convenience. According to the principles of the present invention, any detail of a drawing may be cited and / or claimed in combination with any detail of any other drawing.
    List of milestones 50 Aircraft 100 Power generation system 110 Heat source 112 Heat 115 Heat 120 Thermoionic generator 122 Residual heat 124 Cathode 126 Anode 130 Thermoelectric generator 132 First conductor 134 Second conductor
    135 SiC MOSFET Structure 136 Directional Arrows 140 Power Distribution Bus 142 Motor Control System 144 Frost Protection System 200 Process 202 Process Step 204 Process Step 206 Process Step 208 Process Step 210 Process Step 212 Process step
    权利要求:
    Claims (20)
    [1" id="c-fr-0001]
    CLAIMS 1 * Electricity generation system (100) for an aircraft (50), the power generation system (100) comprising: a thermionic generator (120) adapted to receive heat (112, 115) from at least one heat source (110), the thermionic generator (120) being configured to generate electricity for one or more edge systems (142, 144) at least partially from the heat (112, 115) received from the heat source (s) (110); a thermoelectric generator (130) adapted to receive residual heat (122) from the thermionic generator (120); the thermoelectric generator (130) being adapted to generate electricity for one or more onboard systems (142, 144) at least partially from the residual heat (122) received from the thermionic generator (130).
    [2" id="c-fr-0002]
    An electricity generating system (100) according to claim 1, wherein the thermoelectric generator (130) is a silicon carbide metal oxide-semiconductor field effect transistor thermoelectric generator (130).
    [3" id="c-fr-0003]
    An electricity generating system (100) according to claim 1, wherein the thermionic generator (120) and the thermoelectric generator are electrically coupled to an electricity distribution bus (140) for supplying electricity to one or more edge systems (142, 144).
    [4" id="c-fr-0004]
    The power generating system (100) of claim 1, wherein the thermoelectric generator (130) is adapted to receive residual heat (122) from an anode (126) of the thermionic generator (120).
    [5" id="c-fr-0005]
    The power generation system (100) of claim 1, wherein the thermoelectric generator (130) is adapted to receive heat (110, 115) from the heat source (s) (110).
    [6" id="c-fr-0006]
    The power generating system (100) of claim 1, wherein the heat source (s) (110) comprises / include bleed air or exhaust gas from a heat engine. 'aircraft.
    [7" id="c-fr-0007]
    The power generation system (100) of claim 1, wherein the heat source (s) (110) comprises / include solar heat.
    [8" id="c-fr-0008]
    The power generation system (100) according to claim 1, wherein the edge system (s) (142, 144) comprises / comprise a control system (142) for controlling one or more members of the aircraft (50).
    [9" id="c-fr-0009]
    The power generating system (100) of claim 1, wherein the onboard system (s) (142,144) includes / comprises an ice protection system (144) for the aircraft ( 50).
    [10" id="c-fr-0010]
    A method (200) for producing electricity for one or more onboard systems (242, 244), comprising: receiving (202), in a thermionic generator (130), heat (112, 115) emanating from at least one heat source (110); generating (204) electricity with the thermionic generator (120) for one or more edge systems (142, 144) at least partially from the heat (112, 115) received from the source (s) ( s) heat (110); receiving (206), in a thermoelectric generator (130), residual heat (122) emanating from the thermionic generator (120); and generating (210) electricity with the thermoelectric generator (130) for the at least one edge system (s) from the residual heat (122) received from the thermionic generator (120).
    [11" id="c-fr-0011]
    The method (200) of claim 10, wherein generating (210) electricity with the thermoelectric generator (130) comprises generating electricity with a thermoelectric generator (130) comprising a thermoelectric transistor generator (130). metal-oxide-semiconductor field effect with silicon carbide.
    [12" id="c-fr-0012]
    The method (200) of claim 10, wherein the receiving (206) of residual heat (122) from the thermionic generator (122) comprises receiving residual heat (122) from an anode (126) associated with the thermionic generator. (130).
    [13" id="c-fr-0013]
    The method (200) of claim 10, the method (200) comprising supplying (212) electricity generated by the thermionic generator (120) and the thermoelectric generator (130) to an electricity distribution bus ( 140) for supplying electricity to the onboard system (s) (142, 144).
    [14" id="c-fr-0014]
    The method (200) of claim 10, the method (200) comprising receiving, in the thermoelectric generator (130), heat (112, 115) from the heat source (110) and generating electricity. with the thermoelectric generator (130) at least partially from the heat (112, 115) received from the heat source (110).
    [15" id="c-fr-0015]
    15. Aircraft (50), the aircraft (50) comprising: a heat source (110); an electricity distribution bus (140) for distributing electricity to one or more on-board systems; and a thermionic generator (120) arranged to receive heat (112, 115) from the heat source (110), the thermionic generator (120) being adapted to generate electricity for the system (s) of edge (142, 144) at least partially from the heat (112, 115) received from the heat source (110); a thermoelectric generator (130) arranged to receive residual heat (122) from the thermionic generator (120); the thermoelectric generator (130) being adapted to generate electricity for one or more edge systems (142, 144) at least partially from residual heat (122) received from the thermionic generator (120).
    [16" id="c-fr-0016]
    The aircraft (50) of claim 15, wherein the thermoelectric generator (130) comprises a silicon carbide metal oxide-semiconductor field effect transistor thermoelectric generator (130).
    [17" id="c-fr-0017]
    Aircraft (50) according to claim 15, wherein the heat source (110) comprises sampling air or exhaust gas from a propulsion engine associated with the aircraft (50).
    [18" id="c-fr-0018]
    Aircraft (50) according to claim 15, wherein the heat source (110) comprises solar heat.
    [19" id="c-fr-0019]
    The aircraft (50) of claim 15 wherein the on-board system (s) comprises / comprise an engine control system (142) or an ice protection system (144).
    [20" id="c-fr-0020]
    20. Aircraft (50) according to claim 15, the aircraft (50) being an unmanned aerial vehicle.
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    优先权:
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    US14/927,841|2015-10-30|
    US14/927,841|US10291156B2|2015-10-30|2015-10-30|Combined hybrid thermionic and thermoelectric generator|
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