Waste heat thermoelectric power generation system and method of aviation piston engine

Abstract

The invention provides a waste heat thermoelectric power generation system and method of an aviation piston engine. The system comprises a cylinder sleeve, a cylinder cover is installed at one end of the cylinder sleeve, a first thermoelectric monomer is arranged on the outer wall of the cylinder sleeve, a first heat exchange fin is installed on the outer wall of the first thermoelectric monomer, a fairing is arranged outside the first heat exchange fin, and a second thermoelectric monomer is installed on the outer wall of the first thermoelectric monomer. A combustion chamber and a piston sliding along the inner wall of the cylinder sleeve are arranged in the cylinder sleeve; the exhaust pipe is connected with the cylinder sleeve exhaust port, a second heat exchange fin is arranged on the inner wall of the exhaust pipe, a third heat exchange fin is arranged on the outer wall of the exhaust pipe, and a second thermoelectric monomer is arranged between the outer wall of the exhaust pipe and the third heat exchange fin; the electric energy storage device is connected with the first thermoelectric monomer and the second thermoelectric monomer; the waste heat utilization efficiency of the aviation piston engine can be improved.

Description

Technical Field

[0001] The present invention relates to the technical field of engines, and also to a waste heat temperature difference power generation system and method of an aviation piston engine. Background Art

[0002] A piston engine is a device that performs work by burning fuel in the cylinder and expanding the charge in the cylinder. When the piston engine is working, the high-temperature mixture in the cylinder will transfer some heat to the cylinder wall while pushing the piston to the top dead center. At the same time, during the exhaust process, the high-temperature exhaust gas also contains a large amount of heat energy, which is directly discharged into the atmosphere. In traditional piston engines, air cooling or water cooling solutions are introduced to keep the cylinder wall within a certain temperature range. The air cooling solution is to directly arrange heat sinks on the cylinder body, and the heat is dissipated through direct contact with the air through the heat sink, and some heat is also directly radiated. The water cooling solution is to arrange a coolant flow channel inside the cylinder body, and the coolant will absorb heat during the flow process, and further exchange the heat to the air through the radiator. Both solutions will cause heat to be directly dissipated into the environment, resulting in a large amount of ineffective heat loss, which is not conducive to energy conservation and emission reduction and the efficient use of energy in fuel. Summary of the invention

[0003] The technical problem to be solved by the present invention is to provide a waste heat temperature difference power generation system and method for an aviation piston engine, so as to improve the utilization efficiency of the waste heat of the aviation piston engine.

[0004] In order to solve the above technical problems, the technical solution of the present invention is as follows:

[0005] The first aspect of the present invention provides a waste heat temperature difference power generation system for an aviation piston engine, comprising:

[0006] A cylinder sleeve, one end of which is provided with a cylinder head, an outer wall of which is provided with a first thermoelectric cell, an outer wall of which is provided with a first heat exchange fin, a fairing is provided outside the first heat exchange fin, a combustion chamber is provided inside the cylinder sleeve and a piston sliding along the inner wall of the cylinder sleeve;

[0007] An exhaust pipe connected to the cylinder liner exhaust port, wherein a second heat exchange fin is disposed on the inner wall of the exhaust pipe, a third heat exchange fin is disposed on the outer wall of the exhaust pipe, and a second thermoelectric unit is disposed between the outer wall of the exhaust pipe and the third heat exchange fin;

[0008] An electric energy storage device connected to the first thermoelectric monomer and the second thermoelectric monomer;

[0009] Wherein, the mixed gas in the combustion chamber is burned into a high-pressure mixed gas when the piston moves to the top dead center; the piston moves toward the bottom dead center under the push of the high-pressure mixed gas, and the heat generated is transferred from the high-pressure mixed gas to the cylinder liner and the cylinder head, so that the temperature of the cylinder liner and the cylinder head increases; air enters from the fairing to cool the first heat exchange fin; the hot surface of the first thermoelectric cell contacts the cylinder liner and the cylinder head, and the cold surface contacts the first heat exchange fin; the hot surface and the cold surface of the first thermoelectric cell form a temperature difference to generate an electromotive force, and output electric energy to the electric energy storage device;

[0010] Among them, the exhaust gas generated by combustion in the cylinder liner passes through the exhaust pipe; the exhaust gas and the second heat exchange fin transfer heat to the exhaust pipe; the hot surface of the second thermoelectric cell contacts the exhaust pipe, and the cold surface contacts the third heat exchange fin; the hot surface and the cold surface of the second thermoelectric cell form a temperature difference to generate an electromotive force, and output electric energy to the electric energy storage device.

[0011] Optionally, the system further comprises a controller, wherein the controller is electrically connected to the fairing;

[0012] Wherein, the controller adjusts the opening of the fairing according to the real-time temperature of the outer wall of the cylinder liner.

[0013] Optionally, a temperature sensor is installed on the outer wall of the cylinder sleeve, and the temperature sensor is electrically connected to the controller;

[0014] The temperature sensor sends the collected real-time temperature of the outer wall of the cylinder liner to the controller, so that the controller adjusts the opening of the fairing according to the temperature of the outer wall of the cylinder liner and the target temperature.

[0015] Optionally, the fairing is provided with an air inlet and an air outlet, and the air inlet and the air outlet are arranged opposite to each other.

[0016] Optionally, guide plates are provided in both the air inlet and the air outlet.

[0017] Optionally, an air flow regulating mechanism is provided in the air outlet, and the air flow regulating mechanism is electrically connected to the controller;

[0018] Wherein, the controller controls the opening of the air flow regulating mechanism according to the received real-time temperature and target temperature of the outer wall of the cylinder liner.

[0019] Optionally, the air flow regulating mechanism is an air flow valve.

[0020] Optionally, a plurality of second heat exchange fins are provided on the inner wall of the exhaust pipe, and the plurality of second heat exchange fins are evenly spaced and arranged on the inner wall of the exhaust pipe.

[0021] Optionally, a plurality of third heat exchange fins are provided on the outer wall of the exhaust pipe, and the plurality of third heat exchange fins are evenly spaced and arranged on the outer wall of the exhaust pipe.

[0022] The second aspect of the present invention provides a method for generating electricity using waste heat temperature difference of an aviation piston engine, comprising:

[0023] The mixed gas in the combustion chamber is burned into a high-pressure mixed gas when the piston runs to the top dead center;

[0024] The piston moves toward the bottom dead center under the push of the high-pressure mixed gas, and the heat generated is transferred from the high-pressure mixed gas to the cylinder liner and the cylinder head, so that the temperature of the cylinder liner and the cylinder head increases;

[0025] Air enters from the fairing to cool the first heat exchange fin;

[0026] The hot surface of the first thermoelectric cell is in contact with the cylinder sleeve and the cylinder head, and the cold surface is in contact with the first heat exchange fin;

[0027] The hot surface and the cold surface of the first thermoelectric cell form a temperature difference to generate an electromotive force, and output electric energy to the electric energy storage device;

[0028] The exhaust gas generated by combustion in the cylinder liner passes through the exhaust pipe;

[0029] The exhaust gas and the second heat exchange fin transfer heat to the exhaust pipe;

[0030] The hot surface of the second thermoelectric cell is in contact with the exhaust pipe, and the cold surface is in contact with the third heat exchange fin;

[0031] The hot surface and the cold surface of the second thermoelectric cell form a temperature difference to generate an electromotive force, and output electric energy to the electric energy storage device.

[0032] The above solution of the present invention includes at least the following beneficial effects:

[0033] The above scheme of the present invention converts the heat emitted by the cylinder and the heat in the exhaust gas of the aviation piston engine into electrical energy, effectively improving the energy utilization efficiency of the system. It fully utilizes the advantage of efficient heat exchange generated by the high-speed movement of the aircraft in a low-temperature environment at high altitude to ensure a large temperature difference, which is conducive to improving the efficiency of temperature difference power generation. BRIEF DESCRIPTION OF THE DRAWINGS

[0034] Figure 1 Schematic diagram of the structure of the waste heat temperature difference power generation system of the aviation piston engine in the embodiment of the present invention;

[0035] Figure 2is a front view of an aviation piston engine cylinder body in an embodiment of the present invention;

[0036] Figure 3 is a top view of a cylinder body of an aviation piston engine in an embodiment of the present invention;

[0037] Figure 4 is a front view of an exhaust pipe of an aviation piston engine in an embodiment of the present invention;

[0038] Figure 5 is a top view of an exhaust pipe of an aviation piston engine according to an embodiment of the present invention;

[0039] Figure 6 It is a flow chart of the method for power generation by temperature difference of waste heat of an aviation piston engine in an embodiment of the present invention;

[0040] Figure 7 It is a flow chart of a specific embodiment of the method for power generation by temperature difference of waste heat of an aviation piston engine in an embodiment of the present invention.

[0041] Explanation of the reference numerals: 11-cylinder liner, 111-temperature sensor, 12-cylinder head, 13-first thermoelectric cell, 14-first heat exchange fin, 15-fairing, 151-air inlet, 152-air outlet, 1521-air flow regulating mechanism, 16-combustion chamber, 17-piston, 18-throttle valve, 19-piston connecting rod, 21-exhaust pipe, 22-second heat exchange fin, 23-third heat exchange fin, 24-second thermoelectric cell, 3-electric energy storage device, 4-controller. DETAILED DESCRIPTION

[0042] The exemplary embodiments of the present invention will be described in more detail below with reference to the accompanying drawings. Although the exemplary embodiments of the present invention are shown in the accompanying drawings, it should be understood that the present invention can be implemented in various forms and should not be limited by the embodiments set forth herein. On the contrary, these embodiments are provided in order to enable a more thorough understanding of the present invention and to enable the scope of the present invention to be fully communicated to those skilled in the art.

[0043] like Figures 1 to 5 As shown, an embodiment of the present invention provides a waste heat temperature difference power generation system of an aviation piston engine, comprising:

[0044] A cylinder sleeve 11, a cylinder head 12 is installed at one end of the cylinder sleeve 11, a first thermoelectric cell 13 is installed on the outer wall of the cylinder sleeve 11, a first heat exchange fin 14 is installed on the outer wall of the first thermoelectric cell 13, a fairing 15 is provided outside the first heat exchange fin 14, a combustion chamber 16 and a piston 17 sliding along the inner wall of the cylinder sleeve 11 are provided in the cylinder sleeve 11;

[0045] An exhaust pipe 21 connected to the exhaust port of the cylinder sleeve 11, a second heat exchange fin 22 is provided on the inner wall of the exhaust pipe 21, a third heat exchange fin 23 is provided on the outer wall of the exhaust pipe 21, and a second thermoelectric monomer 24 is provided between the outer wall of the exhaust pipe 21 and the third heat exchange fin 23;

[0046] An electric energy storage device 3 connected to the first thermoelectric monomer 13 and the second thermoelectric monomer 24;

[0047] The mixture in the combustion chamber 16 is burned into a high-pressure mixture when the piston 16 moves to the top dead center; the piston 16 moves toward the bottom dead center under the push of the high-pressure mixture, and the heat generated is transferred from the high-pressure mixture to the cylinder liner 11 and the cylinder head 12, so that the temperature of the cylinder liner 11 and the cylinder head 12 increases; air enters from the fairing 15 to cool the first heat exchange fin 14; the hot surface of the first thermoelectric cell 13 contacts the cylinder liner 11 and the cylinder head 12, and the cold surface contacts the first heat exchange fin 14; the hot surface and the cold surface of the first thermoelectric cell 13 form a temperature difference to generate an electromotive force, and output electric energy to the electric energy storage device 3;

[0048] Among them, the exhaust gas generated by combustion in the cylinder liner 11 passes through the exhaust pipe 21; the exhaust gas and the second heat exchange fins 22 transfer heat to the exhaust pipe 21; the hot surface of the second thermoelectric cell 24 contacts the exhaust pipe 21, and the cold surface contacts the third heat exchange fins 23; the hot surface and the cold surface of the second thermoelectric cell 24 form a temperature difference to generate an electromotive force, and output electric energy to the electric energy storage device 3.

[0049] The waste heat temperature difference power generation system of the aviation piston engine of the embodiment of the present invention converts the heat emitted by the cylinder and the heat in the exhaust gas of the aviation piston engine into electrical energy, effectively improving the energy utilization efficiency of the system. It makes full use of the advantage of efficient heat exchange generated by the high-speed movement of the aircraft in a low-temperature environment at high altitude to ensure a large temperature difference, which is conducive to improving the efficiency of temperature difference power generation.

[0050] The embodiment of the present invention arranges the thermoelectric cells on the cylinder body and the exhaust pipe, utilizes the heat transferred to the cylinder wall from the combustion in the cylinder and the heat in the exhaust gas to heat the hot surface, utilizes the cold air in the high altitude environment to cool the cold surface, ensures the temperature difference and stable heat flux density between the hot surface and the cold surface, and cooperates with the thermoelectric cells to realize waste heat recovery of the aviation piston engine, converts part of the heat into electrical energy, realizes efficient utilization of energy, and improves the endurance of the aircraft.

[0051] Semiconductor temperature difference uses the Seebeck effect to convert thermal energy into electrical energy. In actual use, the p-type thermoelectric element and the n-type thermoelectric element are connected at the hot end with a metal conductor, and their cold ends are connected to the cold end electrode, thus forming a thermoelectric cell. The resistance input at the open circuit end of the thermoelectric cell is an external load. When there is a temperature difference between the hot and cold surfaces of the thermoelectric cell, current will flow through the circuit, directly converting thermal energy into electrical energy.

[0052] The embodiment of the present invention utilizes that when the aviation piston engine is working, the temperature of the cylinder and the exhaust pipe is significantly higher than the ambient temperature, and the heat can be used to heat the hot surface of the thermoelectric monomer. Part of the heat is absorbed as Portier heat, and the other part is transferred to the cold end through heat conduction. During the flight, as the altitude increases, the air temperature becomes lower and lower, and the aviation piston engine moves at a high speed relative to the air, which creates a powerful condition for significantly reducing the temperature of the cold end and increasing the temperature difference with the hot end.

[0053] like Figure 1 As shown, in an optional embodiment of the present invention, the system further comprises a controller 4, and the controller 4 is electrically connected to the fairing 15;

[0054] The controller 4 adjusts the opening of the fairing 15 according to the real-time temperature of the outer wall of the cylinder liner 11 .

[0055] Specifically, the fairing is connected to the controller by radio, and the controller controls the opening of the fairing air outlet (the size of the air outlet opening) to adjust the air volume, ensuring that the final heat dissipation speed of the cylinder matches the engine operating conditions, avoiding inappropriate heat dissipation rate causing the cylinder temperature to be too low or too high, affecting the stable and efficient operation of the engine.

[0056] like Figures 1 to 3 As shown, in an optional embodiment of the present invention, a temperature sensor 111 is installed on the outer wall of the cylinder sleeve 11, and the temperature sensor 111 is electrically connected to the controller 4;

[0057] The temperature sensor 111 sends the collected real-time temperature of the outer wall of the cylinder liner 11 to the controller 4 , so that the controller 4 adjusts the opening of the fairing 15 according to the temperature of the outer wall of the cylinder liner 11 and the target temperature.

[0058] Specifically, a temperature sensor is used to collect the real-time temperature of the cylinder liner, which is used to detect the cylinder temperature and to form a data basis for controlling the air outlet of the fairing.

[0059] like Figure 3 As shown, in an optional embodiment of the present invention, the fairing 15 is provided with an air inlet 151 and an air outlet 152, and the air inlet 151 and the air outlet 152 are arranged opposite to each other.

[0060] Specifically, air enters from the air inlet of the fairing, cools the first heat exchange fins, and flows out from the air outlet, ensuring that the first heat exchange fins are at a relatively low temperature.

[0061] In an optional embodiment of the present invention, guide plates are provided in both the air inlet 151 and the air outlet 152 .

[0062] Specifically, guide plates are provided in both the air inlet and the air outlet to optimize the air flow path and improve the heat exchange efficiency.

[0063] like Figure 1 and Figure 3 As shown, in an optional embodiment of the present invention, an air flow regulating mechanism 1521 is provided in the air outlet 152, and the air flow regulating mechanism 1521 is electrically connected to the controller 4;

[0064] The controller 4 controls the opening of the air flow regulating mechanism 1521 according to the received real-time temperature and target temperature of the outer wall of the cylinder sleeve 11 .

[0065] Specifically, the air flow regulating mechanism is mainly used to adjust the opening of the air outlet. The larger the opening, the more air is discharged, and the less air is left in the fairing for cooling the first heat exchange fins; the smaller the opening, the less air is discharged, and the more air is left in the fairing for cooling the first heat exchange fins, and the lower the temperature of the first heat exchange fins. By setting the air flow regulating mechanism to adjust the opening of the air outlet, the air flow through the fairing is changed, thereby achieving precise control of the heat dissipation speed of the cylinder.

[0066] In an optional embodiment of the present invention, the air flow regulating mechanism 1521 is an air flow valve.

[0067] Specifically, the air flow valve is equipped with an intelligent control module, which can execute the opening instruction of the controller to improve the accuracy of the opening control of the air outlet. The air flow valve is also equipped with a sensor, which can accurately measure and adjust the air flow of the air outlet and provide the controller with the air flow data of the air outlet.

[0068] like Figure 2 As shown, a plurality of first heat exchange fins 14 are installed on the outer wall of the first thermoelectric cell 13 , and the plurality of first heat exchange fins 14 are evenly spaced and arranged on the outer wall of the first thermoelectric cell 13 .

[0069] Specifically, the first heat exchange fins are used to ensure that the cold surface of the first thermoelectric cell is at a lower temperature, forming a temperature difference with the hot surface of the first thermoelectric cell, thereby generating electrical energy. A plurality of first heat exchange fins may be arranged along the circumference of the first thermoelectric cell.

[0070] like Figure 4 and Figure 5 As shown, in an optional embodiment of the present invention, a plurality of second heat exchange fins 22 are provided on the inner wall of the exhaust pipe 21 , and the plurality of second heat exchange fins 22 are evenly spaced and arranged on the inner wall of the exhaust pipe 21 .

[0071] Specifically, the second heat exchange fin is used to transfer heat to the exhaust pipe, so that the exhaust pipe is at a higher temperature state, thereby increasing the temperature of the hot surface of the second thermoelectric cell.

[0072] like Figure 4 As shown, in an optional embodiment of the present invention, a plurality of third heat exchange fins 23 are provided on the outer wall of the exhaust pipe 21 , and the plurality of third heat exchange fins 23 are evenly spaced and arranged on the outer wall of the exhaust pipe 21 .

[0073] Specifically, the third heat exchange fin is in contact with the cold surface of the second thermoelectric cell. When the aircraft is in flight, the third heat exchange fin and the air in the environment will have a large relative speed, and the heat in the third heat exchange fin can quickly enter the air. In this case, there will be a large temperature difference between the hot end and the cold end of the second thermoelectric cell, which can generate an electromotive force and output electrical energy to the outside. Here, the shape and arrangement of the third heat exchange fin 23 can be set according to the specific situation to increase the contact area and heat exchange efficiency with the high-speed moving air.

[0074] like Figures 1 to 5 As shown, a specific embodiment of the waste heat temperature difference power generation system of the aviation piston engine of the embodiment of the present invention includes:

[0075] The power generation system mainly includes a cylinder temperature difference power generation device. The schematic diagram of the cylinder temperature difference power generation device is as follows: Figure 2 and Figure 3 As shown, the first thermoelectric monomer 13 is arranged outside the cylinder liner 11. The shape of the first thermoelectric monomer 13 is not limited and it forms a circle around the outer wall of the cylinder liner 11; the first heat exchange fin 14 is arranged outside the first thermoelectric monomer 13, and the first heat exchange fin 14 is wrapped by the fairing 15 of the cylinder body. The function of the fairing 15 is to rectify the air flow outside the cylinder liner 11 to promote uniform and effective heat exchange; the fairing 15 includes an air flow regulating mechanism 1521 at the air inlet 151 and the air outlet 152. In addition, there are other mechanisms or components to ensure the normal operation of the engine, such as the throttle 18 (it can also be a spark plug, etc.). At the same time, a temperature sensor 111 is installed on the outer wall of the cylinder liner 11, and its value is used to detect the temperature of the cylinder liner 11 and serve as a control reference for the air flow regulating mechanism 1521.

[0076] During the operation of the aviation piston engine, the mixed gas in the cylinder burns when the piston 17 moves to the top dead center, and the high-pressure mixed gas in the cylinder pushes the piston 17 to move to the bottom dead center. In this process, part of the heat will be transferred from the mixed gas to the cylinder liner 11 and the cylinder head 12, so that the temperature of the cylinder liner 11 and the cylinder head 12 increases; at the same time, air enters from the air inlet 151 of the fairing 15, cools the first heat exchange fin 14, and flows out from the air flow regulating mechanism 1521 at the air outlet 152, ensuring that the first heat exchange fin 14 is at a lower temperature. The hot surface of the first thermoelectric monomer 13 contacts the cylinder liner 11 and the cylinder head 12, and the cold surface contacts the first heat exchange fin 14. In this case, the cold surface and the hot surface of the first thermoelectric monomer 13 will form a large temperature difference, and the combustion in the cylinder will continue to transfer heat to the cylinder liner 11 and the cylinder head 12, and the heat source is stable. In this case, the cylinder body thermoelectric power generation system generates electromotive force, which can output electric energy to the outside, and can transmit the electric energy to the electric energy storage device 3 for storage and utilization.

[0077] In addition, for the cylinder block temperature difference power generation device, air enters from the air inlet 151 of the fairing 15, cools the first heat exchange fin 14, and flows out from the air flow regulating mechanism 1521. This process will take away part of the heat of the cylinder head 12; part of the heat will also be consumed in the process of the cylinder block temperature difference power generation device outputting electrical energy. When the heat of the mixture burned in the combustion chamber 16 transferred to the cylinder liner 11 and the cylinder head 12 is not enough to maintain the energy output from the first heat exchange fin 14 and the cylinder block temperature difference power generation device, the temperature of the cylinder liner 11 will be too low. Conversely, it will cause the temperature of the cylinder liner 11 to be too high. During the operation of the aviation piston engine, the cylinder liner 11 needs to be maintained within a certain temperature range. Therefore, it is necessary to change the heat dissipation rate by controlling the air circulation at the air flow regulating mechanism 1521 to ensure that the cylinder liner 11 is at an appropriate temperature. The specific control method can be as follows Figure 6 Schematic diagram shown.

[0078] During the operation of the aviation piston engine, the exhaust gas generated by the combustion in the cylinder will be discharged through the exhaust pipe 21. The exhaust gas temperature is relatively high, and a large amount of heat will be transferred to the exhaust pipe 21. At the same time, the second heat exchange fin 22 is arranged inside the exhaust pipe 21 to further transfer heat to the exhaust pipe 21, which will make the exhaust pipe 21 at a relatively high temperature. The second thermoelectric monomer 24 is arranged outside the exhaust pipe 21. The shape of the second thermoelectric monomer 24 is not limited, and it forms a circle around the outer wall of the exhaust pipe 21. The hot surface of the second thermoelectric monomer 24 contacts the outside of the exhaust pipe 21, and the cold surface contacts the third heat exchange fin 23 outside the exhaust pipe 21. When the aircraft is in flight, the third heat exchange fin 23 outside the exhaust pipe 21 will have a large relative speed with the ambient air, and the heat in the third heat exchange fin 23 can quickly enter the air. In this case, there will be a large temperature difference between the hot end and the cold end of the second thermoelectric monomer 24, which can generate electromotive force, output electric energy to the outside, and can be transmitted to the electric energy storage device 3 for storage and utilization.

[0079] The structure of the engine in this embodiment may also include other components that can complete the engine function, such as a piston connecting rod 19.

[0080] An embodiment of the present invention proposes a waste heat temperature difference power generation system for an aviation piston engine, which can convert the heat emitted by the cylinder and the heat in the exhaust gas in the aviation piston engine into electrical energy, effectively improving the energy utilization efficiency of the system; and the utilization of heat only involves the recovery of waste heat, which will not affect the working performance of the original aviation piston engine; the cold surface of the thermoelectric monomer fully utilizes the advantage of efficient heat exchange caused by the high-speed movement of the aircraft in a low-temperature environment at high altitudes to ensure a large temperature difference, which is beneficial to improving the efficiency of temperature difference power generation; the cylinder fairing and the air flow control mechanism ensure that the cylinder temperature is evenly distributed, and the cylinder can be kept in a suitable temperature range during the operation of the aviation piston engine, which is beneficial to improving the performance of the engine.

[0081] like Figure 6 As shown, an embodiment of the present invention provides a method for power generation by temperature difference of waste heat of an aviation piston engine, which adopts the power generation system by temperature difference of waste heat of an aviation piston engine as described in any one of the above embodiments, and comprises the following steps:

[0082] Step 601, the mixed gas in the combustion chamber 16 is burned into a high-pressure mixed gas when the piston 16 runs to the top dead center;

[0083] Step 602, the piston 16 moves toward the bottom dead center under the push of the high-pressure mixed gas, and the heat generated is transferred from the high-pressure mixed gas to the cylinder liner 11 and the cylinder head 12, so that the temperature of the cylinder liner 11 and the cylinder head 12 increases;

[0084] Step 603, air enters from the fairing 15 to cool the first heat exchange fins 14;

[0085] Step 604 , the hot surface of the first thermoelectric cell 13 contacts the cylinder sleeve 11 and the cylinder head 12 , and the cold surface contacts the first heat exchange fin 14 ;

[0086] Step 605 , a temperature difference is formed between the hot surface and the cold surface of the first thermoelectric cell 13 to generate an electromotive force, and output electric energy to the electric energy storage device 3 ;

[0087] Step 606, the exhaust gas generated by the combustion in the cylinder liner 11 passes through the exhaust pipe 21;

[0088] Step 607, the exhaust gas and the second heat exchange fins 22 transfer heat to the exhaust pipe 21;

[0089] Step 608 , the hot surface of the second thermoelectric cell 24 contacts the exhaust pipe 21 , and the cold surface contacts the third heat exchange fin 23 ;

[0090] Step 609 : The hot surface and the cold surface of the second thermoelectric cell 24 form a temperature difference to generate an electromotive force, and output electric energy to the electric energy storage device 3 .

[0091] The waste heat temperature difference power generation method of the aviation piston engine of the embodiment of the present invention converts the heat emitted by the cylinder and the heat in the exhaust gas of the aviation piston engine into electrical energy, effectively improving the energy utilization efficiency of the system. It fully utilizes the advantage of efficient heat exchange generated by the high-speed movement of the aircraft in a low-temperature environment at high altitude to ensure a large temperature difference, which is conducive to improving the efficiency of temperature difference power generation.

[0092] In an optional embodiment of the present invention, the method further comprises:

[0093] In step 6010, the temperature sensor 111 sends the collected real-time temperature of the outer wall of the cylinder liner 11 to the controller 4, so that the controller 4 adjusts the opening of the fairing 15 according to the temperature of the outer wall of the cylinder liner 11 and the target temperature.

[0094] In an optional embodiment of the present invention, step 6010 specifically includes:

[0095] The controller 4 controls the opening of the air flow regulating mechanism 1521 according to the received real-time temperature and target temperature of the outer wall of the cylinder sleeve 11 .

[0096] like Figure 7 As shown, a specific embodiment of the method for power generation by temperature difference of waste heat of an aviation piston engine of an embodiment of the present invention includes:

[0097] When the controller 4 receives the task planning instruction 701 (i.e., the target temperature, ranging from 150 to 160°), it will estimate the target temperature of the cylinder sleeve 11 702, and make a control mode judgment 708 based on the incoming command value or the current state. When entering the manual control 703 mode, the control instruction is directly applied to the air flow regulating mechanism 1521, and the state of the air flow regulating mechanism is judged 704 in combination with the state parameter 709; when entering the closed-loop control 707, the program will automatically judge the state of the air flow regulating mechanism 1521 706 based on the current state parameter 709, and then apply the control instruction to the air flow regulating mechanism. Then enter the working mode correction 705 process, re-estimate the cylinder target temperature 702, and enter the next control cycle again.

[0098] When the controller 4 determines that the real-time temperature of the outer wall of the cylinder liner 11 collected by the temperature sensor 111 is not within the target temperature range, it is necessary to adjust the opening of the air flow regulating mechanism 1521, increase / decrease the opening of the air outlet, so as to adjust the air flow through the fairing 15, and realize precise control of the heat dissipation speed of the cylinder liner 11; control the temperature of the cylinder liner 11 so that the real-time temperature of the outer wall of the cylinder liner 11 is within the target temperature range, thereby ensuring the stable operation of the engine and the temperature difference power generation efficiency.

[0099] It should be noted that the device is a device corresponding to the above method, and all implementations in the above method embodiment are applicable to the embodiment of the device and can achieve the same technical effect. This embodiment will not be repeated.

[0100] It should be noted that in the apparatus and method of the present invention, it is obvious that each component or each step can be decomposed and / or recombined. These decompositions and / or recombinations should be regarded as equivalent solutions of the present invention. In addition, the steps of performing the above series of processes can naturally be performed in chronological order according to the order of description, but do not necessarily need to be performed in chronological order. Some steps can be performed in parallel, crosswise or independently of each other.

[0101] It should be noted that, in the above-mentioned embodiments, the terms "include", "comprise" or any other variant thereof are intended to cover non-exclusive inclusion, so that the process, method, article or device including a series of elements includes not only those elements, but also includes other elements not explicitly listed, or also includes elements inherent to such process, method, article or device. In the absence of further restrictions, the elements defined by the sentence "include one..." do not exclude the existence of other identical elements in the process, method, article or device including the element. In addition, it should be pointed out that the scope of the methods and devices in the implementation of the above-mentioned embodiments is not limited to performing functions in the order shown or discussed, and may also include performing functions in a substantially simultaneous manner or in the opposite order according to the functions involved, for example, the described method may be performed in an order different from that described, and various steps may also be added, omitted, or combined. In addition, the features described with reference to certain examples may be combined in other examples.

[0102] The above is a preferred embodiment of the present invention. It should be pointed out that for ordinary technicians in this technical field, several improvements and modifications can be made without departing from the principles of the present invention. These improvements and modifications should also be regarded as the scope of protection of the present invention.

Claims

1. A waste heat temperature difference power generation system for an aviation piston engine, characterized in that: include: A cylinder sleeve (11), one end of the cylinder sleeve (11) being provided with a cylinder head (12), an outer wall of the cylinder sleeve (11) being provided with a first thermoelectric cell (13), an outer wall of the first thermoelectric cell (13) being provided with a first heat exchange fin (14), a fairing (15) being provided outside the first heat exchange fin (14), a combustion chamber (16) and a piston (17) sliding along the inner wall of the cylinder sleeve (11) being provided inside the cylinder sleeve (11); an exhaust pipe (21) connected to the exhaust port of the cylinder sleeve (11), a second heat exchange fin (22) being provided on the inner wall of the exhaust pipe (21), a third heat exchange fin (23) being provided on the outer wall of the exhaust pipe (21), and a second thermoelectric monomer (24) being provided between the outer wall of the exhaust pipe (21) and the third heat exchange fin (23); An electric energy storage device (3) connected to the first thermoelectric cell (13) and the second thermoelectric cell (24); The mixed gas in the combustion chamber (16) burns to form a high-pressure mixed gas when the piston (16) moves to the top dead center; the piston (16) moves toward the bottom dead center under the push of the high-pressure mixed gas, and the heat generated is transferred from the high-pressure mixed gas to the cylinder liner (11) and the cylinder head (12), so that the temperature of the cylinder liner (11) and the cylinder head (12) increases; air enters from the fairing (15) to cool the first heat exchange fin (14); the hot surface of the first thermoelectric cell (13) contacts the cylinder liner (11) and the cylinder head (12), and the cold surface contacts the first heat exchange fin (14); the hot surface and the cold surface of the first thermoelectric cell (13) form a temperature difference to generate an electromotive force, and output electric energy to the electric energy storage device (3); The exhaust gas generated by combustion in the cylinder sleeve (11) passes through the exhaust pipe (21); the exhaust gas and the second heat exchange fin (22) transfer heat to the exhaust pipe (21); the hot surface of the second thermoelectric cell (24) contacts the exhaust pipe (21), and the cold surface contacts the third heat exchange fin (23); the hot surface and the cold surface of the second thermoelectric cell (24) form a temperature difference to generate an electromotive force, and output electric energy to the electric energy storage device (3).

2. The waste heat temperature difference power generation system of the aviation piston engine according to claim 1, characterized in that: It also includes a controller (4), wherein the controller (4) is electrically connected to the fairing (15); The controller (4) adjusts the opening of the fairing (15) according to the real-time temperature of the outer wall of the cylinder liner (11).

3. The waste heat temperature difference power generation system of the aviation piston engine according to claim 2, characterized in that: A temperature sensor (111) is installed on the outer wall of the cylinder sleeve (11), and the temperature sensor (111) is electrically connected to the controller (4); The temperature sensor (111) sends the collected real-time temperature of the outer wall of the cylinder liner (11) to the controller (4), so that the controller (4) adjusts the opening of the fairing (15) according to the temperature of the outer wall of the cylinder liner (11) and the target temperature.

4. The waste heat temperature difference power generation system of an aviation piston engine according to claim 2, characterized in that: The fairing (15) is provided with an air inlet (151) and an air outlet (152), and the air inlet (151) and the air outlet (152) are arranged opposite to each other.

5. The waste heat temperature difference power generation system of the aviation piston engine according to claim 4, characterized in that: The air inlet (151) and the air outlet (152) are both provided with guide plates.

6. The waste heat temperature difference power generation system of the aviation piston engine according to claim 4, characterized in that: An air flow regulating mechanism (1521) is provided in the air outlet (152), and the air flow regulating mechanism (1521) is electrically connected to the controller (4); The controller (4) controls the opening of the air flow regulating mechanism (1521) according to the received real-time temperature and target temperature of the outer wall of the cylinder liner (11).

7. The waste heat temperature difference power generation system of the aviation piston engine according to claim 6, characterized in that: The air flow regulating mechanism (1521) is an air flow valve.

8. The waste heat temperature difference power generation system of an aviation piston engine according to claim 1, characterized in that: A plurality of second heat exchange fins (22) are provided on the inner wall of the exhaust pipe (21); the plurality of second heat exchange fins (22) are evenly spaced and arranged on the inner wall of the exhaust pipe (21).

9. The waste heat temperature difference power generation system of an aviation piston engine according to claim 1, characterized in that: A plurality of third heat exchange fins (23) are provided on the outer wall of the exhaust pipe (21); the plurality of third heat exchange fins (23) are evenly spaced and arranged on the outer wall of the exhaust pipe (21).

10. A method for powering electricity using waste heat and temperature difference of an aviation piston engine, using the waste heat and temperature difference power generation system of an aviation piston engine as claimed in any one of claims 1 to 9, characterized in that: include: The mixed gas in the combustion chamber (16) burns to form a high-pressure mixed gas when the piston (16) reaches the top dead center; The piston (16) moves toward the bottom dead center under the push of the high-pressure mixed gas, and the heat generated is transferred from the high-pressure mixed gas to the cylinder liner (11) and the cylinder head (12), so that the temperature of the cylinder liner (11) and the cylinder head (12) increases; Air enters from the fairing (15) to cool the first heat exchange fins (14); The hot surface of the first thermoelectric cell (13) is in contact with the cylinder sleeve (11) and the cylinder head (12), and the cold surface is in contact with the first heat exchange fin (14); The hot surface and the cold surface of the first thermoelectric cell (13) form a temperature difference to generate an electromotive force, and output electric energy to the electric energy storage device (3); Exhaust gas generated by combustion in the cylinder liner (11) passes through the exhaust pipe (21); The exhaust gas and the second heat exchange fins (22) transfer heat to the exhaust pipe (21); The hot surface of the second thermoelectric cell (24) is in contact with the exhaust pipe (21), and the cold surface is in contact with the third heat exchange fin (23); The hot surface and the cold surface of the second thermoelectric cell (24) form a temperature difference to generate an electromotive force, and output electric energy to the electric energy storage device (3).

Images