Thermophotovoltaic power generation system for hypersonic flight vehicle and hypersonic flight vehicle

Abstract

The invention relates to the field of aircrafts, and discloses a thermophotovoltaic power generation system for a hypersonic flight vehicle and the hypersonic flight vehicle, the thermophotovoltaic power generation system for the hypersonic flight vehicle comprises an engine and a thermophotovoltaic assembly, the engine comprises a first channel arranged in the side wall of a combustion chamber and used for conveying fuel; the thermophotovoltaic assembly converts heat energy in the combustion cavity into electric energy, is opposite to the first channel and is used for exchanging heat with the first channel. The thermal photovoltaic assembly is arranged in the combustion cavity, absorbs heat generated by combustion and converts the heat into electric energy, thermal protection of the combustion chamber is achieved, sufficient electric quantity can be provided for the aircraft, and the power utilization requirement of the aircraft is met. And the thermophotovoltaic module is cooled through the fuel flowing in the first channel in the side wall, so that the thermoelectric conversion performance of the thermophotovoltaic module is improved.

Description

Technical Field

[0001] The present application belongs to the field of aircraft, and in particular, relates to a thermal photovoltaic power generation system for a hypersonic aircraft and a hypersonic aircraft. Background Art

[0002] Hypersonic aircraft refers to winged or wingless aircraft such as missiles and artillery shells that fly at speeds exceeding five times the speed of sound.

[0003] With the development of technology, the aircraft power supply system supplies power to a large number of electronic equipment and mechanical equipment, and the demand for electrical energy is increasing. However, the size and weight requirements of the aircraft are strict. How to improve the thermal protection and power supply of the aircraft is an urgent problem that needs to be solved. Summary of the invention

[0004] The embodiments of the present application provide a thermal photovoltaic power generation system for a hypersonic aircraft and a hypersonic aircraft, which can improve the power supply and thermal protection of the aircraft.

[0005] In a first aspect, an embodiment of the present application provides a thermophotovoltaic power generation system for a hypersonic aircraft, comprising: an engine and a thermophotovoltaic module, the engine comprising an air inlet and a combustion chamber connected along its own axis, the combustion chamber comprising a side wall, a combustion chamber formed by the side wall, and a first channel arranged inside the side wall for transporting fuel, the first channel being connected to the combustion chamber; the thermophotovoltaic module is disposed in the combustion chamber, for converting heat energy generated by combustion of fuel in the combustion chamber into electrical energy, the thermophotovoltaic module is stacked with the side wall in a thickness direction and opposite to the first channel, for exchanging heat with the first channel.

[0006] In some embodiments of the present application, a plurality of the first passages are arranged at intervals along the circumference of the combustion chamber and are extended along the axial direction of the engine.

[0007] In some embodiments of the present application, the first channel includes a feed end and a discharge end, the feed end and the discharge end are both arranged close to the air inlet duct, and the discharge end is connected to the combustion chamber.

[0008] In some embodiments of the present application, the thermophotovoltaic components are laid on the side wall along the circumference of the combustion chamber to form a closed power generation layer.

[0009] In some embodiments of the present application, along the axial direction of the engine, the thermophotovoltaic component extends from the connection between the combustion chamber and the intake duct to a side away from the intake duct, and the length of the thermophotovoltaic component is less than or equal to the length of the combustion chamber.

[0010] In some embodiments of the present application, along the axial direction of the engine, the thermophotovoltaic module includes a first radiation section and a second radiation section. The second radiation section is located on the side of the first radiation section facing away from the intake passage. The peak wavelength that the first radiation section can absorb is greater than the peak wavelength that the second radiation section can absorb.

[0011] In some embodiments of the present application, the thermophotovoltaic module includes a photovoltaic cell, a filter, and a radiator stacked along the thickness direction of the side wall. The filter is disposed between the photovoltaic cell and the radiator.

[0012] In some embodiments of the present application, the material of the photovoltaic cell in the first radiation section includes indium arsenide, and the material of the photovoltaic cell in the second radiation section includes gallium antimonide.

[0013] In some embodiments of the present application, the combustion chamber further includes a reflux mechanism and a fuel storage device. The fuel storage device is communicated with the feed end, and the reflux mechanism is communicated between the discharge end and the fuel storage device for controlling the fuel flow rate into the combustion chamber.

[0014] In some embodiments of the present application, the reflux mechanism includes a second passage, a first control valve, and a nozzle. The first control valve is connected to the second passage, the first passage, and the nozzle. The second passage is communicated with the discharge end, the nozzle is communicated with the combustion chamber, and the first control valve is used to control the fuel flow rate of the nozzle.

[0015] In some embodiments of the present application, a first temperature detection component is further included. The first temperature detection component is used to detect a first temperature value of the thermophotovoltaic module, and is configured to increase the fuel flow rate in the first passage and turn on the reflux mechanism when the first temperature value is greater than a first preset value.

[0016] In some embodiments of the present application, the side wall includes an inner wall and an outer wall along the thickness direction. The first passage is disposed between the inner wall and the outer wall. The inner wall encloses to form a combustion chamber, and the inner wall includes a silicon carbide material.

[0017] In a second aspect, an embodiment of the present application further provides a hypersonic aircraft, including the thermophotovoltaic power generation system for a hypersonic aircraft in the first aspect above.

[0018] The thermophotovoltaic power generation system for a hypersonic vehicle and the hypersonic vehicle according to the embodiments of the present application place the thermophotovoltaic module in the combustion chamber, absorb the heat generated by combustion and convert it into electric energy, providing sufficient power for the vehicle to meet its power consumption requirements. And the fuel flowing in the first channel in the side wall cools the thermophotovoltaic module, provides thermal protection for the combustion chamber, and improves the thermoelectric conversion performance of the thermophotovoltaic module. BRIEF DESCRIPTION OF THE DRAWINGS

[0019] In order to more clearly illustrate the technical solutions of the embodiments of the present application, the following will briefly introduce the drawings required to be used in the embodiments of the present application. For those of ordinary skill in the art, other drawings can also be obtained based on these drawings without creative efforts.

[0020] Figure 1 Structural schematic diagram of an aircraft provided by some embodiments of the present application;

[0021] Figure 2 Structural schematic diagram of the thermophotovoltaic power generation system provided by some embodiments of the present application;

[0022] Figure 3 For Figure 2 Cross-sectional view taken along the A-A direction in

[0023] Figure 4 Schematic diagram of the reflux mechanism of the thermophotovoltaic power generation system provided by the embodiments of the present application.

[0024] Description of the reference numerals in the drawings:

[0025] 10, engine; 11, intake duct; 12, combustion chamber; 13, tail nozzle; 14, center cone structure; 20, fuselage; 30, wing; X, first direction; Y, second direction;

[0026] 100, thermophotovoltaic module; 110, first radiation section; 120, second radiation section; 101, photovoltaic cell; 102, filter; 103, radiator;

[0027] 200, side wall; 201, inner wall; 202, outer wall; 210, combustion chamber; 220, first channel; 221, feed end; 222, discharge end;

[0028] 300, fuel storage device; 301, storage tank; 302, pump; 303, second control valve; 310, reflux mechanism; 311, second channel; 312, first control valve; 313, nozzle. DETAILED DESCRIPTION OF THE EMBODIMENTS

[0029] The embodiments of the technical solution of the present application will be described in detail below in conjunction with the accompanying drawings. The following embodiments are only used to more clearly illustrate the technical solution of the present application, so they are only examples and cannot be used to limit the protection scope of the present application.

[0030] Unless otherwise defined, all technical and scientific terms used herein have the same meaning as commonly understood by those of ordinary skill in the technical field to which this application belongs; the terms used herein are only for the purpose of describing specific embodiments and are not intended to limit this application; the terms "including" and "having" and any variations thereof in the specification and claims of this application and the above drawings are intended to cover non-exclusive inclusion.

[0031] In the description of the embodiments of this application, technical terms such as "first" and "second" are only used to distinguish different objects and cannot be understood as indicating or implying relative importance or implicitly indicating the quantity, specific order or primary-secondary relationship of the indicated technical features. In the description of the embodiments of this application, the meaning of "a plurality" is more than two, unless otherwise specifically defined.

[0032] Referring to "embodiments" herein means that the specific features, structures or characteristics described in connection with the embodiments can be included in at least one embodiment of this application. The phrase appears in various places in the specification does not necessarily refer to the same embodiment, nor is it an independent or alternative embodiment mutually exclusive with other embodiments. Those skilled in the art explicitly and implicitly understand that the embodiments described herein can be combined with other embodiments.

[0033] In the description of the embodiments of this application, the term "and / or" is only a description of the association relationship of associated objects, indicating that there can be three relationships. For example, A and / or B can represent: A exists alone, A and B exist simultaneously, and B exists alone. In addition, the character " / " in this article generally represents an "or" relationship between the associated objects before and after.

[0034] In the description of the embodiments of this application, the term "a plurality" refers to more than two (including two). Similarly, "a plurality of groups" refers to more than two groups (including two groups), and "a plurality of pieces" refers to more than two pieces (including two pieces).

[0035] In the description of the embodiments of this application, technical terms such as "center", "longitudinal", "transverse"

[0036] "length", "width", "thickness", "upper", "lower", "front", "rear", "left", "right"

[0037] "vertical", "horizontal", "top", "bottom", "inner", "outer", "clockwise", "counterclockwise"

[0038] The orientation or positional relationship indicated by "axial", "radial", "circumferential", etc. is based on the orientation or positional relationship shown in the drawings. It is only for the convenience of describing the embodiments of the present application and simplifying the description, rather than indicating or implying that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation. Therefore, it should not be construed as a limitation to the embodiments of the present application.

[0039] In the description of the embodiments of the present application, unless otherwise clearly specified and limited, technical terms such as "installation", "connection", "connection", "fixation", etc. should be understood in a broad sense. For example, it can be a fixed connection, a detachable connection, or integrated; it can also be a mechanical connection or an electrical connection; it can be directly connected, or indirectly connected through an intermediate medium, and can be the communication inside two elements or the interaction relationship between two elements. For those of ordinary skill in the art, the specific meanings of the above terms in the embodiments of the present application can be understood according to specific circumstances.

[0040] Thermophotovoltaic (TPV) power generation technology uses the thermal radiation energy generated by a high-temperature heat source and directly converts it into electrical energy through a photovoltaic cell. Specifically, the photon energy in the high-temperature heat source radiation excites the semiconductor material to generate electron-hole pairs. Under the action of the built-in electric field of the semiconductor pn junction, the electrons and holes are separated and collected to generate current output.

[0041] Among them, the operating temperature range of the photovoltaic cell is usually between -40°C and 85°C, and the standard operating temperature is 25°C. At this temperature, the output power of the photovoltaic cell reaches its rated value. When the thermophotovoltaic module is installed in the engine and the heat of the engine combustion chamber is converted into electrical energy, due to the limited cold source of the aircraft, it is difficult for the photovoltaic cell to be cooled to the standard operating temperature, and the conversion performance will decline.

[0042] In view of this, the embodiments of the present application provide a thermophotovoltaic power generation system for a hypersonic aircraft, which sets a thermophotovoltaic module to absorb the thermal energy of combustion and convert it into electrical energy to increase the power supply of the hypersonic aircraft, and sets the thermophotovoltaic module on the side wall opposite to the first channel, so as to cool the thermophotovoltaic module through low-temperature fuel, providing thermal protection for the combustion chamber, so that the thermophotovoltaic module operates within the operating temperature range and improves the thermoelectric conversion performance of the thermophotovoltaic module.

[0043] Figure 1 Schematic diagram of the structure of a hypersonic aircraft provided by some embodiments of the present application; Figure 2 Schematic diagram of the structure of a thermophotovoltaic power generation system provided by some embodiments of the present application.

[0044] Such as Figure 1 and Figure 2As shown in the figure, some embodiments of the present application provide a thermophotovoltaic power generation system for a hypersonic vehicle, including an engine 10 and a thermophotovoltaic module 100. The engine 10 includes an air inlet 11 and a combustion chamber 12 that are communicatively connected along its own axial direction. The combustion chamber 12 includes a side wall 200, a combustion cavity 210 formed by enclosing the side wall 200, and a first channel 220 disposed inside the side wall 200 for delivering fuel. The first channel 220 is communicatively connected with the combustion cavity 210. The thermophotovoltaic module 100 is placed in the combustion cavity 210 and is configured to convert the thermal energy generated by the combustion of fuel in the combustion cavity 210 into electrical energy. The thermophotovoltaic module 100 is stacked with the side wall 200 in the thickness direction and is opposite to the first channel 220 for heat exchange with the first channel 220.

[0045] The engine 10 includes an air inlet 11 and a combustion chamber 12 along the first direction X. The air inlet 11 is communicatively connected with the combustion chamber 12, and the gas entering from the air inlet 11 flows into the combustion chamber 12 for ignition and / or combustion support.

[0046] The air inlet 11 is capable of capturing the externally flowing high-speed air and providing a sufficient amount of air for the combustion chamber 12. Exemplarily, the air inlet 11 can decelerate and pressurize the high-speed air flow. In one example, the air inlet 11 can also adjust the air flow rate entering the engine 10.

[0047] In one example, the air inlet 11 includes a center cone structure 14. When the air flow passes through the center cone structure 14, an oblique shock wave will be generated around it. After the air flow passes through the oblique shock wave, the speed decreases and the pressure increases, thereby achieving deceleration and pressurization.

[0048] The fuel and air in the combustion chamber 12 are mixed and burned. Exemplarily, an igniter can be provided in the combustion chamber 12 to ignite the fuel or the fuel can auto-ignite after colliding with the air.

[0049] The combustion chamber 12 includes a side wall 200, and the side wall 200 has a certain thickness. Exemplarily, the side wall 200 can be a solid wall or a hollow wall. Wherein, the thickness direction is the second direction Y.

[0050] Exemplarily, along the first direction X, the thickness of the side wall 200 can be equal everywhere or unequal.

[0051] A first channel 220 is provided inside the side wall 200, and the first channel 220 is used for delivering fuel. Exemplarily, the fuel in the fuel storage device 300 is delivered into the combustion cavity 210. Wherein, the combustion storage device is disposed in the fuselage 20.

[0052] Exemplarily, the first channel 220 can be a pipe or a hole structure. Exemplarily, the cross-sectional shape of the first channel 220 can be circular, rectangular, triangular, etc.

[0053] Exemplarily, the first channel 220 may be arranged to extend in one direction or multiple directions. In one example, the first channel 220 is spirally disposed within the outer wall 202 around the axis of the engine 10.

[0054] Exemplarily, the first channel 220 includes one or more.

[0055] Exemplarily, the fuel may be hydrocarbon fuel, liquid hydrogen fuel, boron-based fuel, etc. Exemplarily, the fuel has a relatively high cold energy. In one example, the fuel is liquid hydrogen fuel between -250 °C and -252 °C. In another example, the fuel is hydrocarbon fuel between -40 °C and 20 °C.

[0056] The side wall 200 encloses to form a combustion chamber 210, and the combustion chamber 210 communicates with the intake passage 11. Gas is sent into the combustion chamber 210 through the intake passage 11, and the first channel 220 transports the fuel into the combustion chamber 210. Exemplarily, self-ignition occurs in the combustion chamber 210 by the collision of the fuel with the high-speed and high-pressure gas, thereby generating a propulsion force for the aircraft.

[0057] The thermophotovoltaic component 100 is disposed in the combustion chamber 12, absorbs the heat generated by combustion in the combustion chamber 210, and converts the heat of combustion into electrical energy. Exemplarily, the thermophotovoltaic component 100 is connected to a storage battery, and the generated electrical energy is stored in the storage battery to supply power to other electrical devices of the aircraft.

[0058] Exemplarily, the thermophotovoltaic component 100 is stacked and installed on the side wall 200 and may be in contact with the side wall 200, thereby improving the heat exchange efficiency between the thermophotovoltaic component 100 and the side wall 200. In another example, the thermophotovoltaic component 100 may also be spaced from the side wall 200.

[0059] Exemplarily, the thermophotovoltaic component 100 has a shape such as a sheet, a ring, a strip, a block, etc. that is convenient for absorbing heat. The thermophotovoltaic component 100 may be one or more.

[0060] The thermophotovoltaic component 100 and the side wall 200 are stacked in the second direction Y. Exemplarily, the thermophotovoltaic component 100 is an annular power generation layer that is open along the circumference of the combustion chamber 210, or an annular power generation layer that is closed along the circumference of the combustion chamber 210.

[0061] The thermophotovoltaic component 100 and the first channel 220 at least partially overlap in the thickness direction of the side wall 200. In one example, in the thickness direction of the side wall 200, the projection of the first channel 220 on the thermophotovoltaic component 100 is placed within the thermophotovoltaic component 100.

[0062] When the fuel with cold energy flows through the first channel 220, it exchanges heat with the thermophotovoltaic module 100, cools the thermophotovoltaic module 100 whose temperature has risen due to fuel combustion, maintains the thermophotovoltaic module 100 within the operating temperature range, and improves the conversion efficiency.

[0063] The thermophotovoltaic module 100 is placed in the combustion chamber 210 to absorb the heat generated by combustion and convert it into electrical energy, providing sufficient power for the aircraft to meet its power consumption requirements. Moreover, the fuel flowing in the first channel 220 within the side wall 200 cools the thermophotovoltaic module 100, improving the service life and thermoelectric conversion efficiency of the thermophotovoltaic module 100.

[0064] In an embodiment of the present application, the engine 10 further includes a tail nozzle 13. Along the axial direction of the engine 10, the tail nozzle 13 is placed on the side of the combustion chamber 12 facing away from the air inlet 11, and the tail nozzle 13 is communicated with the combustion chamber 12. When the high-temperature and high-pressure gas in the combustion chamber 12 sprays backward from the tail nozzle 13 at a high speed, it will generate a forward reaction force on the aircraft, thereby pushing the aircraft forward.

[0065] Exemplarily, the tail nozzle 13 includes a converging section and a diverging section. The converging section has a contracting trend compared with the combustion chamber 12, and the diverging section has an expanding trend compared with the converging section. Along the axial direction of the engine 10, the converging section is placed between the combustion chamber 12 and the diverging section. In the converging section, the gas flow velocity gradually increases, and the pressure and temperature decrease somewhat; in the diverging section, the gas further expands and accelerates, and finally sprays out from the tail pipe outlet at an extremely high speed.

[0066] In one example, the tail nozzle 13 includes a de Laval nozzle.

[0067] Figure 3 For Figure 2 the cross-sectional view along the A-A direction in

[0068] As Figure 2 and Figure 3 shown, in some embodiments of the present application, a plurality of first channels 220 are arranged at intervals along the circumferential direction of the combustion chamber 210 and extend along the axial direction of the engine 10.

[0069] Exemplarily, the plurality of first channels 220 can be arranged at equal intervals or at unequal intervals.

[0070] In one example, the cross-section of the side wall 200 is rectangular, and a plurality of first channels 220 are uniformly distributed on the four sides of the side wall 200.

[0071] Each first channel 220 extends along the first direction X. Exemplarily, along the first direction X, the length of the first channel 220 can be less than or equal to the length of the combustion chamber 12 along the first direction X.

[0072] Exemplarily, a plurality of first channels 220 may communicate with each other, partially communicate with each other, or be independent of each other. Exemplarily, a plurality of first channels 220 may be supplied with fuel simultaneously or partially supplied with fuel.

[0073] Exemplarily, along the first direction X, the length of the first channel 220 is greater than the length of the thermophotovoltaic module 100.

[0074] By arranging a plurality of first channels 220 circumferentially around the combustion chamber 210, the side wall 200 can be better cooled, thereby improving the cooling of the thermophotovoltaic module 100. The first channel 220 extending axially can facilitate the arrangement of the first channel 220 within the side wall 200 and uniformly provide cooling along the axial direction.

[0075] Continuing to refer to Figure 2 and Figure 3 , in an alternative embodiment of the present application, the first channel 220 includes a feed end 221 and a discharge end 222. Both the feed end 221 and the discharge end 222 are close to the intake passage 11, and the discharge end 222 communicates with the combustion chamber 210.

[0076] When combustion occurs in the combustion chamber 12, the combustion temperature on the side close to the intake passage 11 is lower than the combustion temperature on the side far from the intake passage 11.

[0077] The cooling capacity of the first channel 220 continuously decreases from the feed end 221 to the discharge end 222. By arranging the feed end 221 on the side close to the intake passage 11, the side wall 200 can be better cooled, improving the service life of the side wall 200.

[0078] That is to say, the temperature of the part of the thermophotovoltaic module 100 placed far from the intake passage 11 is higher than the temperature of the part close to the intake passage 11. In order to maintain the optimal operating temperature range of the thermophotovoltaic module 100, the feed end 221 is corresponding to the part of the thermophotovoltaic module 100 with a lower heating temperature, improving the cooling effect of the thermophotovoltaic module 100.

[0079] Exemplarily, the first channel 220 is U-shaped. Fuel enters the first channel 220 from the feed end 221, flows from the side close to the intake passage 11 towards the direction of the tail nozzle 13, then flows back from the side close to the tail nozzle 13 towards the intake passage 11, and flows into the combustion chamber 210 from the discharge end 222 for combustion. The cooling capacity of the fuel at the feed end 221 is the largest, which can effectively and efficiently cool the thermophotovoltaic module 100. Since the temperature on the side of the combustion chamber 12 close to the tail nozzle 13 is relatively high, the fuel is heated and thus flows into the combustion chamber 210 more easily for combustion.

[0080] Among them, the first channel 220 includes a first extension section, a second extension section, and a connection section. The first extension section and the second extension section are connected by the connection section, and both the first extension section and the second extension section extend along the first direction X.

[0081] In one example, the first extension section and the second extension section are stacked along the thickness direction of the side wall 200. The first extension section is disposed between the second extension section and the thermophotovoltaic module 100. The first extension section is connected to the feed end 221, and a heat insulation layer can be provided between the first extension section and the second extension section.

[0082] In another example, the first extension section and the second extension section are arranged side by side around the circumference of the combustion chamber 210.

[0083] Continue to refer to Figure 3 As shown, in another embodiment of the present application, the thermophotovoltaic module 100 is laid on the side wall 200 to form a closed power generation layer along the circumference of the combustion chamber 210.

[0084] The attachment of the thermophotovoltaic module 100 to the side wall 200 can improve the heat exchange efficiency between the thermophotovoltaic module 100 and the first channel 220. Exemplarily, the thermophotovoltaic module 100 is installed and cooperated with the side wall 200 without a gap by means of bonding, clamping, bolt fastening, etc.

[0085] In one example, the side wall 200 includes an inner wall 201 and an outer wall 202 along the second direction Y. The inner wall 201 encloses to form the combustion chamber 12. The thermophotovoltaic module 100 is disposed in contact with the inner wall 201.

[0086] The thermophotovoltaic module 100 forms a closed power generation layer along the circumference of the combustion chamber 210, which can absorb the heat in the combustion chamber 210 in all directions, increase the absorption area of the thermophotovoltaic module 100 in the combustion chamber 210, thereby improving the thermoelectric conversion efficiency and power generation.

[0087] Furthermore, in one embodiment of the present application, the side wall 200 includes an inner wall 201 and an outer wall 202 along the thickness direction. The first channel 220 is disposed between the inner wall 201 and the outer wall 202. The inner wall 201 encloses to form the combustion chamber 210, and the inner wall 201 includes a silicon carbide material.

[0088] Silicon carbide has a relatively high melting point and can withstand the extremely high temperature inside the combustion chamber 12. It can still maintain stable physical and chemical properties in a high-temperature environment, is not prone to deformation, melting or decomposition, and ensures the structural integrity of the combustion chamber 12 under high-temperature working conditions. Silicon carbide has a relatively high thermal conductivity and can quickly transfer the heat absorbed by the wall surface of the combustion chamber 12, making the temperature distribution of the inner wall 201 more uniform, avoiding local overheating, which is beneficial to improving the overall thermal management efficiency of the combustion chamber 12 and ensuring the stability of the temperature field in the combustion chamber 12. And the silicon carbide material is lighter in weight, which is beneficial to reducing the weight of the aircraft.

[0089] In another embodiment of the present application, the first channel 220 can be manufactured using a lighter titanium alloy, thereby greatly reducing the weight of the aircraft.

[0090] Continue to refer Figure 2 In some optional embodiments of the present application, along the axial direction of the engine 10, the thermophotovoltaic component 100 extends from the connection between the combustion chamber 12 and the intake duct 11 to the side away from the intake duct 11, and the length of the thermophotovoltaic component 100 is less than or equal to the length of the combustion chamber 12.

[0091] After the fuel is burned, the temperature in the combustion chamber 12 increases. Along the first direction X, the temperature in the combustion chamber 12 increases continuously from the air inlet 11 to the direction away from the air inlet 11. The thermophotovoltaic module 100 forms a low temperature zone close to the air inlet 11 and a high temperature zone away from the air inlet 11. Since the heat-resistant temperature of the thermophotovoltaic module 100 is limited, in order to increase the service life of the thermophotovoltaic module 100 and improve the power generation efficiency, the thermophotovoltaic module 100 should be placed away from the excessively high temperature position in the high temperature zone.

[0092] Specifically, the thermophotovoltaic assembly 100 is laid from the beginning of the combustion chamber 12 close to the air inlet 11 to the end away from the air inlet 11, so as to fully utilize the heat of the low temperature area and part of the high temperature area of ​​the combustion chamber 12.

[0093] Exemplarily, along the first direction X, the length of the thermophotovoltaic assembly 100 is less than or equal to four fifths of the length of the combustion chamber 12 . In one example, the length of the thermophotovoltaic assembly 100 is equal to one half or two thirds of the length of the combustion chamber 12 .

[0094] In other embodiments of the present application, the thermophotovoltaic assembly 100 is placed in the middle of the combustion chamber 12 along the first direction X, thereby improving the heat conversion efficiency of the thermophotovoltaic assembly 100 .

[0095] Continue to refer Figure 2 In some embodiments of the present application, along the axial direction of the engine 10, the thermophotovoltaic assembly 100 includes a first radiation section 110 and a second radiation section 120, the second radiation section 120 is located on the side of the first radiation section 110 facing away from the air inlet duct 11, and the peak wavelength that can be absorbed by the first radiation section 110 is greater than the peak wavelength that can be absorbed by the second radiation section 120.

[0096] The first radiation section 110 is close to or placed in a relatively low temperature area of ​​the combustion chamber 12, and the second radiation end is placed in a relatively high temperature area of ​​the combustion chamber 12. The wavelength of the relatively high temperature area is short, and the wavelength of the relatively low temperature area is long.

[0097] In order to improve the thermoelectric conversion efficiency, the thermophotovoltaic module 100 is segmented along the first direction X. For the region with a higher temperature, the second radiation segment 120 with a shorter absorption wavelength is provided, and for the region with a lower temperature, the first radiation segment 110 with a longer absorption wavelength is provided.

[0098] Exemplarily, the peak absorption wavelength of the first radiation segment 110 is 1.2 times, 1.5 times, 2 times, etc. of the peak absorption wavelength that the second radiation segment 120 can absorb. In one example, the peak absorption wavelength that the first radiation segment 110 can absorb is 700 nm, and the peak absorption wavelength of the second radiation segment 120 is 840 nm.

[0099] Continue to refer to Figure 3 , in some embodiments of the present application, the thermophotovoltaic module 100 includes a photovoltaic cell 101, a filter 102, and a radiator 103 that are stacked along the thickness direction of the side wall 200, and the filter 102 is disposed between the photovoltaic cell 101 and the radiator 103.

[0100] That is to say, the photovoltaic cell 101, the filter 102, and the radiator 103 are sequentially arranged along the second direction Y.

[0101] Exemplarily, the radiator 103 first obtains heat from the combustion of the fuel in the combustion chamber 210. After absorbing heat, the radiator 103 is heated to the working temperature, for example, the working temperature is in the range of 1000 - 2000 °C. The radiator 103 at the working temperature will convert the absorbed thermal energy into thermal radiation energy and emit it outward in the form of photons.

[0102] The filter 102 is located between the radiator 103 and the photovoltaic cell 101 and screens the photons emitted by the radiator 103. The filter 102 will intercept the photons with energy less than the bandgap width of the photovoltaic cell 101 and reflect these photons back to the radiator 103 so that they can be reused. In addition to reflecting low-energy photons, the filter 102 can also reflect high-energy photons with shorter wavelengths back to the radiator 103 to avoid causing an excess electrical load on the photovoltaic cell 101, thereby achieving optical matching between the radiator 103 and the photovoltaic cell 101, improving the utilization efficiency of thermal energy, being able to reduce the working temperature of the photovoltaic cell 101, and contributing to improving the stability and service life of the photovoltaic cell 101.

[0103] The suitable photons filtered by the filter 102 irradiate the surface of the photovoltaic cell 101. The semiconductor material in the photovoltaic cell 101 absorbs these photons, and the energy of the photons is transferred to the electrons in the semiconductor. When the photon energy is greater than the bandgap energy of the semiconductor, electrons will transition from the valence band to the conduction band, thereby generating electron-hole pairs in the semiconductor and increasing the concentrations of free electrons and holes in the semiconductor material. Under the action of the internal electric field of the photovoltaic cell 101, the electron-hole pairs are separated. The electrons are attracted to the positive electrode of the cell, while the holes are attracted to the negative electrode of the cell, thus forming an electric current. The formed current passes through the external circuit connected to the photovoltaic cell 101, which can provide power for various electrical devices of the aircraft and complete the output and utilization of electrical energy.

[0104] Exemplarily, there is a first spacing between the radiator 103 and the filter 102, and a second spacing between the filter 102 and the photovoltaic cell 101. The first spacing is greater than the second spacing, which can effectively reduce the temperatures of the filter 102 and the photovoltaic cell 101 and improve the stability and service life of the photovoltaic cell 101.

[0105] In some embodiments of the present application, the material of the photovoltaic cell 101 in the first radiation section 110 includes indium arsenide, and the material of the photovoltaic cell 101 in the second radiation section 120 includes gallium antimonide.

[0106] The bandgap width of indium arsenide (InAs) is about 0.35 eV; the bandgap width of gallium antimonide (GaSb) is 0.725 eV (300K). The photovoltaic cell 101 of indium arsenide has a good response to infrared light, especially in the infrared region with a longer wavelength; the spectral response range of the photovoltaic cell 101 of gallium antimonide is mainly in the near-infrared region.

[0107] Therefore, by correspondingly setting the photovoltaic cells 101 with different materials in the first radiation section 110 and the second radiation section 120 at different temperatures, the conversion efficiency of the photovoltaic cell 101 can be improved.

[0108] In another embodiment of the present application, the radiator 103 includes a silicon carbide material, which improves the thermal conductivity and high-temperature resistance characteristics.

[0109] As Figure 2 shown, in some embodiments of the present application, the thermophotovoltaic power generation system further includes a fuel storage device 300 for storing fuel. The fuel storage device 300 can be arranged on the engine 10 or the fuselage 20 of the aircraft.

[0110] Exemplarily, the fuel storage device 300 includes a storage tank 301, a pump 302, and a second control valve 303. The storage tank 301 is connected to the pump 302 through a pipeline, and the outlet of the pump 302 is connected to the first channel 220 through the second control valve 303. The second control valve 303 can control the output flow rate of the fuel.

[0111] Exemplarily, the second control valve 303 may be one valve or multiple valves. In one example, the second control valve 303 includes a stop valve.

[0112] Figure 4 Schematic diagram of the reflux mechanism 310 of the thermophotovoltaic power generation system provided by the embodiments of the present application.

[0113] As Figure 4 shown, in some embodiments of the present application, the combustion chamber 12 further includes a reflux mechanism 310 and a fuel storage device 300. The fuel storage device 300 is communicated with the feed end, and the reflux mechanism 310 is communicated between the discharge end 222 and the fuel storage device 300, and is used to control the fuel flow rate into the combustion chamber 12.

[0114] The fuel is not only used for combustion in the combustion chamber 12 but also for cooling the thermophotovoltaic module 100. Therefore, the fuel flow rate in the first channel 220 has an important influence on the cooling effect of the thermophotovoltaic module 100.

[0115] The reflux mechanism 310 performs reflux heat exchange on a part of the fuel in the first channel 220.

[0116] Exemplarily, the reflux mechanism 310 may be disposed inside the side wall 200 or inside the fuselage 20.

[0117] Exemplarily, the reflux mechanism 310 may connect the feed end 221 and the discharge end 222 of the first channel 220, or the reflux mechanism 310 is connected between the discharge end 222 and the fuel storage device 300.

[0118] Exemplarily, the reflux mechanism 310 may include one or more.

[0119] In order to increase the fuel flow rate in the first channel 220 and ensure a certain fuel flow rate for combustion in the combustion chamber 12, the excess fuel in the first channel 220 is recycled through the reflux mechanism 310 to improve the cooling effect on the thermophotovoltaic module 100 and the side wall 200.

[0120] Further, in some embodiments of the present application, the reflux mechanism 310 includes a second channel 311, a first control valve 312, and a nozzle 313. The first control valve 312 is connected to the second channel 311, the first channel 220, and the nozzle 313. The second channel 311 is communicated with the discharge end 222, the nozzle 313 is communicated with the combustion chamber 210, and the first control valve 312 is used to control the fuel flow rate of the nozzle 313.

[0121] Exemplarily, the first control valve 312 may be an electronically controlled or hydraulically controlled proportional valve. The flow rates in the nozzle 313 and the second channel 311 are controlled by controlling the spool ratio.

[0122] Exemplarily, the second channel 311 includes an inlet and an outlet. The inlet is connected to the first control valve 312, and the outlet is connected to the discharge end 222 or to the fuel storage device 300.

[0123] In one example, in order to improve the cooling effect of the first channel 220 on the thermophotovoltaic module 100, the fuel flow rate in the first channel 220 is increased. The first control valve 312 is controlled to make the output flow rate of the control nozzle 313 a preset flow rate, and the excess flow rate flows back from the second channel 311 to the fuel storage device 300, thereby increasing the flow rate of the first channel 220 and improving the heat exchange efficiency with the thermophotovoltaic module 100.

[0124] In one example, the nozzles 313 are uniformly spaced along the circumferential direction of the combustion chamber 210.

[0125] When the combustion condition is controlled within a preset range by the first control valve 312, the cooling capacity of the first channel 220 is increased, and further the heat exchange efficiency with the thermophotovoltaic module 100 is improved.

[0126] In addition, in other embodiments of the present application, the second channel 311 is disposed within the side wall 200 and is disposed opposite to the thermophotovoltaic module 100.

[0127] In one example, along the first direction X, the second channel 311 is disposed parallel to and communicated with the first channel 220. Exemplarily, the first channel 220 may also be disposed at an angle to the first channel 220.

[0128] In another example, along the circumferential direction of the combustion chamber 12, the first channel 220 and the second channel 311 are alternately disposed.

[0129] The second channel 311 is disposed within the side wall 200 to make full use of the cooling capacity of the fuel in the second channel 311 and improve the heat exchange efficiency with the thermophotovoltaic module 100.

[0130] In addition, in some alternative embodiments of the present application, the thermophotovoltaic power generation system for a hypersonic vehicle further includes a first temperature detection member (not shown in the figure). The first temperature detection member is configured to detect a first temperature value of the thermophotovoltaic module 100, and is configured to increase the fuel flow rate in the first channel 220 and activate the reflux mechanism 310 when the first temperature value is greater than a first preset value.

[0131] Exemplarily, the first preset value may be the tolerance temperature of the photovoltaic cell 101. In one example, the first preset value is 500K.

[0132] Exemplarily, by increasing the opening degree of the second control valve 303, the fuel flow rate in the first channel 220 is increased.

[0133] Exemplarily, by opening the first control valve 312, the reflux mechanism 310 is thus opened. In one example, when the first control valve 312 is closed, the fuel in the first channel 220 completely flows into the combustion chamber 210 for combustion.

[0134] Exemplarily, the first temperature detection component is electrically connected to the first control valve 312 and the second control valve 303 through a controller.

[0135] The flow rate in the first channel 220 is controlled by the first temperature detection component, thereby improving the cooling effect on the thermophotovoltaic module 100, ensuring the safe use of the thermophotovoltaic module 100 and extending its service life.

[0136] Wherein, in some embodiments of the present application, the thermophotovoltaic power generation system for a hypersonic vehicle further includes a second temperature detection component (not shown in the figure), and the second temperature detection component is used to detect the second temperature value of the first channel 220, and is configured to increase the flow rate of the fuel in the first channel 220 and open the reflux mechanism 310 when the second temperature value is greater than a second preset value.

[0137] Exemplarily, the second preset value may be the tolerance temperature of the side wall 200. In one example, the second preset value is 1100K.

[0138] Exemplarily, the second temperature detection component is electrically connected to the first control valve 312 and the second control valve 303 through a controller.

[0139] The temperature of the side wall 200 without the thermophotovoltaic module 100 can be monitored, thereby ensuring the safety of the engine 10 and extending the service life of the engine 10.

[0140] Some embodiments of the present application further provide a hypersonic vehicle, including the thermophotovoltaic power generation system for a hypersonic vehicle in the above embodiments.

[0141] The above are only the specific embodiments of the present application. Those skilled in the art can clearly understand that for the convenience and brevity of description, the specific working processes of the systems, modules, and units described above can refer to the corresponding processes in the foregoing method embodiments, and will not be repeated here. It should be understood that the protection scope of the present application is not limited thereto. Any person skilled in the art can easily think of various equivalent modifications or substitutions within the technical scope disclosed in the present application, and these modifications or substitutions should all be covered within the protection scope of the present application.

Claims

1. A thermophotovoltaic power generation system for a hypersonic vehicle, characterized in that: include: The engine comprises an intake passage and a combustion chamber which are connected and arranged along the axial direction thereof, wherein the combustion chamber comprises a side wall, a combustion chamber formed by the side wall, and a first channel arranged inside the side wall for conveying fuel, wherein the first channel is connected to the combustion chamber; A thermophotovoltaic assembly is disposed in the combustion chamber and is used to convert heat energy generated by the combustion of fuel in the combustion chamber into electrical energy. The thermophotovoltaic assembly is stacked with the side wall in the thickness direction and is opposite to the first channel and is used to exchange heat with the first channel.

2. The thermophotovoltaic power generation system for a hypersonic vehicle according to claim 1, characterized in that: A plurality of the first passages are arranged at intervals along the circumferential direction of the combustion chamber and extend along the axial direction of the engine.

3. The thermophotovoltaic power generation system for a hypersonic vehicle according to claim 2, characterized in that: The first channel includes a feed end and a discharge end, wherein the feed end and the discharge end are both arranged close to the air inlet passage, and the discharge end is communicated with the combustion chamber.

4. The thermophotovoltaic power generation system for a hypersonic vehicle according to claim 1, characterized in that: The thermal photovoltaic components are laid on the side walls along the circumference of the combustion chamber to form a closed power generation layer.

5. The thermophotovoltaic power generation system for a hypersonic vehicle according to claim 4, characterized in that: Along the axial direction of the engine, the thermophotovoltaic assembly is extended from the connection between the combustion chamber and the air intake duct to a side away from the air intake duct, and the length of the thermophotovoltaic assembly is less than or equal to the length of the combustion chamber.

6. The thermophotovoltaic power generation system for a hypersonic vehicle according to claim 1, characterized in that: Along the axial direction of the engine, the thermophotovoltaic assembly includes a first radiation section and a second radiation section, the second radiation section is located on the side of the first radiation section facing away from the air inlet duct, and the peak wavelength absorbable by the first radiation section is greater than the peak wavelength absorbable by the second radiation section.

7. The thermophotovoltaic power generation system for a hypersonic vehicle according to claim 6, characterized in that: The thermophotovoltaic assembly includes a photovoltaic cell, a filter and a radiator which are stacked along the thickness direction of the side wall, and the filter is placed between the photovoltaic cell and the radiator.

8. The thermophotovoltaic power generation system for a hypersonic vehicle according to claim 7, characterized in that: The material of the photovoltaic cell in the first radiation section includes indium arsenide, and the material of the photovoltaic cell in the second radiation section includes gallium antimonide.

9. The thermophotovoltaic power generation system for a hypersonic vehicle according to claim 3, characterized in that: The combustion chamber further comprises a reflux mechanism and a fuel storage device, wherein the fuel storage device is connected to the feed end, and the reflux mechanism is connected to the discharge end and the fuel storage device, and is used to control the fuel flow rate entering the combustion chamber.

10. The thermophotovoltaic power generation system for a hypersonic vehicle according to claim 9, characterized in that: The reflux mechanism includes a second channel, a first control valve and a nozzle, the first control valve is connected to the second channel, the first channel and the nozzle, the second channel is connected to the discharge end, the nozzle is connected to the combustion chamber, and the first control valve is used to control the fuel flow of the nozzle.

11. The thermophotovoltaic power generation system for a hypersonic vehicle according to claim 10, characterized in that: It also includes a first temperature detection component, which is used to detect a first temperature value of the thermal photovoltaic component and is configured to increase the flow rate of the fuel in the first channel and open the reflux mechanism when the first temperature value is greater than a first preset value.

12. The thermophotovoltaic power generation system for a hypersonic vehicle according to claim 1, characterized in that: The side wall includes an inner wall and an outer wall along the thickness direction, the first channel is arranged between the inner wall and the outer wall, the inner wall surrounds and forms a combustion chamber, and the inner wall includes silicon carbide material.

13. A hypersonic aircraft, characterized in that: A thermophotovoltaic power generation system for a hypersonic aircraft comprising any one of claims 1 to 12.

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