A waste heat thermoelectric power generation system and method for an aviation piston engine

Abstract

The application provides a waste heat thermoelectric power generation system and method of an aviation piston engine. The system comprises: a cylinder sleeve, one end of the cylinder sleeve is provided with a cylinder cover, a first thermoelectric element is arranged on the outer wall of the cylinder sleeve, a first heat exchange fin is arranged on the outer wall of the first thermoelectric element, a flow straightener is arranged outside the first heat exchange fin, a combustion chamber and a piston sliding along the inner wall of the cylinder sleeve are arranged in the cylinder sleeve; an exhaust pipe connected with the exhaust port of the cylinder sleeve, 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 element is arranged between the outer wall of the exhaust pipe and the third heat exchange fin; and an electric energy storage device connected with the first thermoelectric element and the second thermoelectric element. The application is beneficial to improving the utilization efficiency of the waste heat of the aviation piston engine.

Description

Technical Field

[0001] This invention relates to the field of engine technology, and also to a waste heat thermoelectric power generation system and method for an aircraft piston engine. Background Technology

[0002] A piston engine is a device that generates power through the combustion of fuel within a cylinder, with the cylinder's charge expanding. During operation, the high-temperature air-fuel mixture pushes the piston towards top dead center, transferring some heat to the cylinder walls. Simultaneously, during exhaust, the high-temperature exhaust gases, containing a significant amount of heat, are directly released into the atmosphere. Traditional piston engines employ either air or water cooling to maintain the cylinder walls within a specific temperature range. Air cooling involves directly mounting heat sinks on the cylinder block, allowing heat to dissipate through direct contact with the air, with some heat also radiating away. Water cooling uses coolant channels within the cylinder block; the flowing coolant absorbs heat and further exchanges it with the air through a radiator. Both methods result in significant heat loss into the environment, hindering energy conservation, emission reduction, and efficient use of fuel energy. Summary of the Invention

[0003] The technical problem to be solved by the present invention is to provide a waste heat thermoelectric power generation system and method for aircraft piston engines, so as to improve the utilization efficiency of waste heat from aircraft piston engines.

[0004] To solve the above-mentioned technical problems, the technical solution of the present invention is as follows:

[0005] A first aspect of the present invention provides a waste heat thermoelectric power generation system for an aircraft piston engine, comprising:

[0006] A cylinder liner, one end of which is fitted with a cylinder head, a first thermoelectric unit is provided on the outer wall of the cylinder liner, a first heat exchange fin is installed on the outer wall of the first thermoelectric unit, a shroud is provided outside the first heat exchange fin, and a combustion chamber and a piston that slides along the inner wall of the cylinder liner are provided inside the cylinder liner.

[0007] An exhaust pipe connected to the cylinder liner exhaust port has a second heat exchange fin on its inner wall and a third heat exchange fin on its outer wall. A second thermoelectric unit is provided between the outer wall of the exhaust pipe and the third heat exchange fin.

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

[0009] In this configuration, the air-fuel mixture in the combustion chamber is combusted into a high-pressure mixture when the piston reaches top dead center. Driven by this high-pressure mixture, the piston moves towards bottom dead center, and the resulting heat is transferred from the high-pressure mixture to the cylinder liner and cylinder head, raising their temperatures. Air enters through the shroud, cooling the first heat exchange fins. The hot side of the first thermoelectric generator contacts the cylinder liner and cylinder head, while the cold side contacts the first heat exchange fins. The temperature difference between the hot and cold sides of the first thermoelectric generator generates an electromotive force, which outputs electrical energy to the energy storage device.

[0010] The exhaust gas generated by combustion inside the cylinder liner passes through the exhaust pipe; the exhaust gas and the second heat exchange fins transfer heat to the exhaust pipe; the hot side of the second thermoelectric cell contacts the exhaust pipe, and the cold side contacts the third heat exchange fins; the hot and cold sides of the second thermoelectric cell form a temperature difference to generate an electromotive force, which outputs electrical energy to the energy storage device.

[0011] Optionally, the system further includes a controller electrically connected to the fairing;

[0012] The controller adjusts the opening of the fairing based on the real-time temperature of the cylinder liner outer wall.

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

[0014] The temperature sensor collects the real-time temperature of the cylinder liner outer wall and sends it to the controller, which then adjusts the opening of the fairing according to the temperature of the cylinder liner outer wall and the target temperature.

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

[0016] Optionally, both the air inlet and the air outlet are provided with guide vanes.

[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] The controller controls the opening degree of the air flow regulating mechanism based on the real-time temperature and target temperature of the cylinder liner outer wall.

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

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

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

[0022] A second aspect of the present invention provides a method for generating electricity from the waste heat of an aircraft piston engine, comprising:

[0023] The air-fuel mixture in the combustion chamber is burned into a high-pressure mixture when the piston reaches top dead center;

[0024] The piston moves to its 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 and the cylinder head, causing the temperature of the cylinder liner and the cylinder head to rise.

[0025] Air enters through the shroud and cools the first heat exchange fins;

[0026] The hot side of the first thermoelectric unit is in contact with the cylinder liner and the cylinder head, and the cold side is in contact with the first heat exchange fins.

[0027] The hot and cold surfaces of the first thermoelectric cell generate an electromotive force by creating a temperature difference, which outputs electrical energy to the energy storage device.

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

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

[0030] The hot side of the second thermoelectric unit is in contact with the exhaust pipe, and the cold side is in contact with the third heat exchange fins;

[0031] The hot and cold surfaces of the second thermoelectric cell generate an electromotive force by creating a temperature difference, which outputs electrical energy to the energy storage device.

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

[0033] The above-described solution of the present invention converts the heat dissipated from the cylinder block and the heat in the exhaust of an aircraft 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 aircraft in low-temperature environments at high altitudes to ensure a large temperature difference, which is beneficial to improving the efficiency of thermoelectric power generation. Attached Figure Description

[0034] Figure 1 This is a schematic diagram of the waste heat thermoelectric power generation system of an aircraft piston engine in an embodiment of the present invention;

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

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

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

[0038] Figure 5 This is a top view of the exhaust pipe of an aircraft piston engine in an embodiment of the present invention;

[0039] Figure 6 This is a flowchart of the waste heat thermoelectric power generation method of an aircraft piston engine in an embodiment of the present invention;

[0040] Figure 7 This is a flowchart of a specific embodiment of the waste heat thermoelectric power generation method for an aircraft piston engine according to the present invention.

[0041] Explanation of reference numerals in the attached drawings: 11-Cylinder liner, 111-Temperature sensor, 12-Cylinder head, 13-First thermoelectric unit, 14-First heat exchange fin, 15-Screen, 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 unit, 3-Electric energy storage device, 4-Controller. Detailed Implementation

[0042] Exemplary embodiments of the invention will now be described in more detail with reference to the accompanying drawings. While exemplary embodiments of the invention are shown in the drawings, it should be understood that the invention can be implemented in various forms and should not be limited to the embodiments set forth herein. Rather, these embodiments are provided to enable a more thorough understanding of the invention and to fully convey the scope of the invention to those skilled in the art.

[0043] like Figures 1 to 5 As shown, an embodiment of the present invention proposes a waste heat thermoelectric power generation system for an aircraft piston engine, comprising:

[0044] A cylinder liner 11 is provided with a cylinder head 12 installed at one end of the cylinder liner 11. A first thermoelectric unit 13 is provided on the outer wall of the cylinder liner 11. A first heat exchange fin 14 is installed on the outer wall of the first thermoelectric unit 13. A shroud 15 is provided outside the first heat exchange fin 14. A combustion chamber 16 and a piston 17 that slides along the inner wall of the cylinder liner 11 are provided inside the cylinder liner 11.

[0045] An exhaust pipe 21 is connected to the exhaust port of the cylinder liner 11. The inner wall of the exhaust pipe 21 is provided with a second heat exchange fin 22, the outer wall of the exhaust pipe 21 is provided with a third heat exchange fin 23, and a second thermoelectric unit 24 is provided between the outer wall of the exhaust pipe 21 and the third heat exchange fin 23.

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

[0047] In this process, the air-fuel mixture in the combustion chamber 16 is burned into a high-pressure mixture when the piston 16 reaches top dead center. Driven by the high-pressure mixture, the piston 16 moves to bottom dead center, and the heat generated is transferred from the high-pressure mixture to the cylinder liner 11 and the cylinder head 12, raising their temperatures. Air enters from the shroud 15, cooling the first heat exchange fins 14. The hot surface of the first thermoelectric generator 13 contacts the cylinder liner 11 and the cylinder head 12, while the cold surface contacts the first heat exchange fins 14. The temperature difference between the hot and cold surfaces of the first thermoelectric generator 13 generates an electromotive force, which outputs electrical energy to the energy storage device 3.

[0048] 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 unit 24 contacts the exhaust pipe 21, and the cold surface contacts the third heat exchange fins 23; the hot and cold surfaces of the second thermoelectric unit 24 form a temperature difference to generate an electromotive force, which outputs electrical energy to the energy storage device 3.

[0049] The waste heat thermoelectric power generation system for an aircraft piston engine, as described in this invention, converts the heat dissipated from the cylinder block and the heat in the exhaust of the aircraft piston engine into electrical energy, effectively improving the system's energy utilization efficiency. It fully utilizes the advantage of efficient heat exchange generated by the aircraft's high-speed movement in the low-temperature environment at high altitudes to ensure a large temperature difference, which is beneficial for improving the thermoelectric power generation efficiency.

[0050] In this embodiment of the invention, thermoelectric generators are arranged on the cylinder block and exhaust pipe. The heat transferred from combustion in the cylinder to the cylinder wall and the heat in the exhaust are used to heat the hot surface, while the cold air in the high-altitude environment is used to cool the cold surface. This ensures a stable temperature difference and heat flux density between the hot and cold surfaces. In conjunction with the thermoelectric generators, waste heat recovery from the aircraft piston engine is achieved, converting some of the heat into electrical energy, thus realizing efficient energy utilization and improving the endurance of the aircraft.

[0051] Semiconductor thermoelectric generators utilize the Seebeck effect to convert heat energy into electrical energy. In practical applications, p-type and n-type thermoelectric elements are connected at their hot ends with a metal conductor, and their cold ends are connected to a cold-end electrode, thus forming a single thermoelectric unit. The resistance at the open-circuit terminal of the thermoelectric unit serves as the external load. When a temperature difference exists between the hot and cold sides of the thermoelectric unit, current flows through the circuit, directly converting heat energy into electrical energy.

[0052] This invention utilizes the fact that during the operation of an aircraft piston engine, the cylinder block and exhaust pipe temperatures are significantly higher than the ambient temperature. This heat can be used to heat the hot surface of a thermoelectric unit. Part of this heat is absorbed as Poldier heat, and the other part is transferred to the cold end through heat conduction. During flight, as altitude increases, the air temperature decreases, and the aircraft piston engine moves at high speed relative to the air, creating favorable conditions 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 includes a controller 4, which 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 wirelessly connected to the controller. The controller controls the opening of the fairing's air outlet (the size of the air outlet opening) to adjust the air volume, ensuring that the final cooling rate of the cylinder block matches the engine operating conditions. This avoids unsuitable cooling rates that could lead to excessively low or high cylinder block temperatures, affecting the engine's stable and efficient operation.

[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 liner 11, and the temperature sensor 111 is electrically connected to the controller 4.

[0057] The temperature sensor 111 sends the 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 provides the data basis for controlling the shroud outlet.

[0059] like Figure 3 As shown, in an optional embodiment of the present invention, the shroud 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 through the air inlet of the fairing, cools the first heat exchange fins, and flows out through the air outlet, ensuring that the first heat exchange fins are at a low temperature.

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

[0062] Specifically, deflectors are installed in both the air inlet and outlet to optimize airflow and improve 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 degree of the air flow regulating mechanism 1521 based on the real-time temperature and target temperature of the outer wall of the cylinder liner 11.

[0065] Specifically, the airflow regulation 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 remains in the shroud for cooling the first heat exchange fins; the smaller the opening, the less air is discharged, and the more air remains in the shroud for cooling the first heat exchange fins, resulting in a lower temperature for the first heat exchange fins. By adjusting the opening of the air outlet using the airflow regulation mechanism, the airflow through the shroud is changed, thereby achieving precise control over the cylinder block's heat dissipation rate.

[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 that can execute the controller's opening commands, improving the accuracy of air outlet opening control. The air flow valve also includes a sensor that can accurately measure and adjust the airflow at the outlet, providing the controller with airflow data.

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

[0069] Specifically, the function of the first heat exchange fins is to ensure that the cold surface of the first thermoelectric unit has a low temperature, creating a temperature difference with the hot surface of the first thermoelectric unit, thereby generating electrical energy. Multiple first heat exchange fins can be arranged along the circumference of the first thermoelectric unit.

[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 on the inner wall of the exhaust pipe 21.

[0071] Specifically, the second heat exchange fins are used to transfer heat to the exhaust pipe, so that the exhaust pipe is at a higher temperature, thereby increasing the temperature of the second thermoelectric unit's hot surface.

[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 on the outer wall of the exhaust pipe 21.

[0073] Specifically, the third heat exchange fin contacts the cold side of the second thermoelectric unit. During aircraft flight, the third heat exchange fin experiences a significant relative velocity with the ambient air, allowing heat from the fin to rapidly dissipate into the air. In this situation, a large temperature difference exists between the hot and cold ends of the second thermoelectric unit, generating an electromotive force and outputting electrical energy. The shape and arrangement of the third heat exchange fin 23 can be customized to improve the contact area with the high-speed airflow and enhance heat exchange efficiency.

[0074] like Figures 1 to 5 As shown, a specific embodiment of the waste heat thermoelectric power generation system for an aircraft piston engine according to an embodiment of the present invention includes:

[0075] The power generation system mainly includes a cylinder block thermoelectric generator. A schematic diagram of the cylinder block thermoelectric generator is shown below. Figure 2 and Figure 3 As shown, a first thermoelectric element 13 is arranged on the outer side of the cylinder liner 11. The shape of the first thermoelectric element 13 is not limited, and it is arranged in a circle around the outer wall of the cylinder liner 11. A first heat exchange fin 14 is arranged on the outer side of the first thermoelectric element 13. The first heat exchange fin 14 is wrapped by a cylinder block shroud 15. The function of the shroud 15 is to rectify the airflow outside the cylinder liner 11 and promote uniform and effective heat exchange. The shroud 15 includes an airflow 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 valve 18 (or spark plugs, etc.). At the same time, a temperature sensor 111 is installed on the outer wall of the cylinder liner 11. Its value is used to detect the temperature of the cylinder liner 11 and serves as a control reference for the airflow regulating mechanism 1521.

[0076] During the operation of an aero-piston engine, the air-fuel mixture in the cylinder burns when the piston 17 reaches near top dead center. The high-pressure mixture in the cylinder pushes the piston 17 towards bottom dead center. During this process, some heat is transferred from the mixture to the cylinder liner 11 and cylinder head 12, raising their temperatures. Simultaneously, air enters from the air inlet 151 of the cowl 15, cooling the first heat exchange fins 14, and exits from the airflow regulating mechanism 1521 at the air outlet 152, ensuring the first heat exchange fins 14 remain at a low temperature. The hot side of the first thermoelectric generator 13 contacts the cylinder liner 11 and cylinder head 12, while the cold side contacts the first heat exchange fins 14. Under these conditions, a significant temperature difference is formed between the hot and cold sides of the first thermoelectric generator 13, and the combustion in the cylinder continuously conducts heat to the cylinder liner 11 and cylinder head 12, ensuring a stable heat source. In this situation, the cylinder block thermoelectric power generation system generates an electromotive force, which can output electrical energy, which can be transmitted to the energy storage device 3 for storage and utilization.

[0077] Additionally, for the cylinder block thermoelectric generator, air enters from the air inlet 151 of the shroud 15, cools the first heat exchange fins 14, and flows out from the airflow regulating mechanism 1521. This process carries away some heat from the cylinder head 12; the cylinder block thermoelectric generator also consumes some heat during its power output. When the heat transferred from the combustion mixture in the combustion chamber 16 to the cylinder liner 11 and cylinder head 12 is insufficient to sustain the energy output from the first heat exchange fins 14 and the cylinder block thermoelectric generator, the cylinder liner 11 temperature will be too low. Conversely, it will lead to the cylinder liner 11 temperature being too high. During the operation of the aero-piston engine, the cylinder liner 11 needs to be maintained within a certain temperature range. Therefore, it is necessary to control the airflow at the airflow regulating mechanism 1521 to change the heat dissipation rate and ensure that the cylinder liner 11 is at a suitable temperature. Specific control methods can be as follows: Figure 6 The diagram shown is shown in the image.

[0078] During the operation of an aircraft piston engine, the exhaust gas produced by combustion in the cylinder is discharged through the exhaust pipe 21. The exhaust gas is at a high temperature, and a large amount of heat is transferred to the exhaust pipe 21. Simultaneously, a second heat exchange fin 22 arranged inside the exhaust pipe 21 further transfers heat to the exhaust pipe 21, keeping it at a high temperature. A second thermoelectric element 24 is arranged outside the exhaust pipe 21. The shape of the second thermoelectric element 24 is not limited, and it forms a ring around the outer wall of the exhaust pipe 21. The hot side of the second thermoelectric element 24 contacts the outer side of the exhaust pipe 21, and the cold side contacts the third heat exchange fin 23 on the outer side of the exhaust pipe 21. During aircraft flight, the third heat exchange fin 23 on the outer side of the exhaust pipe 21 has a large relative velocity with the ambient air, allowing heat from the third heat exchange fin 23 to quickly enter the air. Under these conditions, a large temperature difference exists between the hot and cold ends of the second thermoelectric element 24, generating an electromotive force and outputting electrical energy, which can be transmitted to the energy storage device 3 for storage and utilization.

[0079] The engine structure in this embodiment may also include other components that can perform engine functions, such as piston connecting rod 19.

[0080] The embodiments of this invention propose a waste heat thermoelectric power generation system for an aircraft piston engine. This system converts the heat dissipated from the cylinder block and the heat in the exhaust of the aircraft piston engine into electrical energy, effectively improving the system's energy utilization efficiency. Furthermore, the utilization of heat only involves the recovery of waste heat and does not affect the original operating performance of the aircraft piston engine. The cold surface of the thermoelectric unit fully utilizes the advantage of efficient heat exchange generated by the aircraft's high-speed movement in the low-temperature environment at high altitudes to ensure a large temperature difference, which is beneficial to improving the thermoelectric power generation efficiency. The cylinder block cowling and airflow control mechanism ensure uniform cylinder block temperature distribution and keep the cylinder block within a suitable temperature range during the operation of the aircraft piston engine, which is beneficial to improving engine performance.

[0081] like Figure 6 As shown, an embodiment of the present invention proposes a waste heat thermoelectric power generation method for an aircraft piston engine, employing a waste heat thermoelectric power generation system for an aircraft piston engine as described in any of the above embodiments, comprising the following steps:

[0082] Step 601: The mixture in the combustion chamber 16 is burned into a high-pressure mixture when the piston 16 reaches top dead center;

[0083] Step 602: The piston 16 moves to 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, causing the temperature of the cylinder liner 11 and the cylinder head 12 to rise.

[0084] Step 603: Air enters from the shroud 15 to cool the first heat exchange fins 14;

[0085] Step 604: The hot side of the first thermoelectric unit 13 contacts the cylinder liner 11 and the cylinder head 12, and the cold side contacts the first heat exchange fin 14.

[0086] Step 605: The hot and cold surfaces of the first thermoelectric cell 13 form a temperature difference to generate an electromotive force, which outputs electrical energy to the energy storage device 3.

[0087] Step 606: The exhaust gas generated by combustion inside 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 side of the second thermoelectric unit 24 contacts the exhaust pipe 21, and the cold side contacts the third heat exchange fin 23.

[0090] In step 609, the hot and cold surfaces of the second thermoelectric cell 24 form a temperature difference, generating an electromotive force, which outputs electrical energy to the energy storage device 3.

[0091] The waste heat thermoelectric power generation method for aircraft piston engines of this invention converts the heat dissipated from the cylinder block and the heat in the exhaust of the aircraft 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 aircraft in low-temperature environments at high altitudes to ensure a large temperature difference, which is beneficial to improving the thermoelectric power generation efficiency.

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

[0093] In step 6010, the temperature sensor 111 sends the 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 degree of the air flow regulating mechanism 1521 based on the real-time temperature and target temperature of the outer wall of the cylinder liner 11.

[0096] like Figure 7 As shown, a specific embodiment of the waste heat thermoelectric power generation method for an aircraft piston engine according to an embodiment of the present invention includes:

[0097] When controller 4 receives task planning instruction 701 (i.e., target temperature, range 150 to 160°), it estimates the target temperature of cylinder liner 11 702 and performs control mode determination 708 based on the input command value or current status. When entering manual control mode 703, control instructions are directly applied to airflow regulating mechanism 1521, and the status of airflow regulating mechanism is determined 704 in conjunction with status parameters 709. When entering closed-loop control 707, the program automatically determines the status of airflow regulating mechanism 1521 706 based on the current status parameters 709, and then applies control instructions to airflow regulating mechanism. Then, the working mode correction process 705 is entered, the cylinder block target temperature is re-estimated 702, and the next control cycle is entered 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 needs to adjust the opening of the airflow regulation mechanism 1521 to increase / decrease the opening of the air outlet in order to regulate the airflow through the shroud 15 and achieve 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, and ensure the stable operation of the engine and the thermal power generation efficiency.

[0099] It should be noted that this device corresponds to the method described above, and all implementations in the method embodiments described above are applicable to the embodiments of this device and can achieve the same technical effect. Further details are omitted in this embodiment.

[0100] It should be noted that in the apparatus and method of the present invention, the components or steps can obviously be decomposed and / or recombined. These decompositions and / or recombinations should be considered equivalent solutions of the present invention. Furthermore, the steps for performing the above series of processes can naturally be performed in the order described and in chronological order, but are not necessarily required to be performed in chronological order. Some steps can be performed in parallel, overlapping, or independently of each other.

[0101] It should be noted that in the above embodiments, the terms "comprising," "including," or any other variations thereof are intended to cover non-exclusive inclusion, such that a process, method, article, or apparatus that comprises a list of elements includes not only those elements but also other elements not expressly listed, or elements inherent to such a process, method, article, or apparatus. Without further limitations, an element defined by the phrase "comprising one..." does not exclude the presence of other identical elements in the process, method, article, or apparatus that includes that element. Furthermore, it should be noted that the scope of the methods and apparatuses in the embodiments described above is not limited to performing functions in the order shown or discussed, but may also include performing functions substantially simultaneously or in the reverse order, depending on the functions involved. For example, the described methods may be performed in a different order than described, and various steps may be added, omitted, or combined. Additionally, features described with reference to certain examples may be combined in other examples.

[0102] The above description represents the preferred embodiments of the present invention. It should be noted that those skilled in the art can make various improvements and modifications without departing from the principles of the present invention, and these improvements and modifications should also be considered within the scope of protection of the present invention.

Claims

1. A thermoelectric generator system for a piston aeroengine, characterised in that, The application relates to a cylinder sleeve, a cylinder cover, a first thermoelectric element, a first heat exchange fin, a rectifier cover, a combustion chamber, a piston, an exhaust pipe, a second thermoelectric element, an electric energy storage device, a controller, a temperature sensor, an air inlet, an air outlet, a guide plate, an air flow adjusting mechanism, an air flow valve, a plurality of second heat exchange fins and a plurality of third heat exchange fins. The application relates to a cylinder sleeve, a cylinder cover, a first thermoelectric element, a first heat exchange fin, a rectifier cover, a combustion chamber, a piston, an exhaust pipe, a second thermoelectric element, an electric energy storage device, a controller, a temperature sensor, an air inlet, an air outlet, a guide plate, an air flow adjusting mechanism, an air flow valve, a plurality of second heat exchange fins and a plurality of third heat exchange fins. The application relates to a cylinder sleeve, a cylinder cover, a first thermoelectric element, a first heat exchange fin, a rectifier cover, a combustion chamber, a piston, an exhaust pipe, a second thermoelectric element, an electric energy storage device, a controller, a temperature sensor, an air inlet, an air outlet, a guide plate, an air flow adjusting mechanism, an air flow valve, a plurality of second heat exchange fins and a plurality of third heat exchange fins. The application relates to a cylinder sleeve, a cylinder cover, a first thermoelectric element, a first heat exchange fin, a rectifier cover, a combustion chamber, a piston, an exhaust pipe, a second thermoelectric element, an electric energy storage device, a controller, a temperature sensor, an air inlet, an air outlet, a guide plate, an air flow adjusting mechanism, an air flow valve, a plurality of second heat exchange fins and a plurality of third heat exchange fins. The application relates to a cylinder sleeve, a cylinder cover, a first thermoelectric element, a first heat exchange fin, a rectifier cover, a combustion chamber, a piston, an exhaust pipe, a second thermoelectric element, an electric energy storage device, a controller, a temperature sensor, an air inlet, an air outlet, a guide plate, an air flow adjusting mechanism, an air flow valve, a plurality of second heat exchange fins and a plurality of third heat exchange fins. The application relates to a cylinder sleeve, a cylinder cover, a first thermoelectric element, a first heat exchange fin, a rectifier cover, a combustion chamber, a piston, an exhaust pipe, a second thermoelectric element, an electric energy storage device, a controller, a temperature sensor, an air inlet, an air outlet, a guide plate, an air flow adjusting mechanism, an air flow valve, a plurality of second heat exchange fins and a plurality of third heat exchange fins. The application relates to a cylinder sleeve, a cylinder cover, a first thermoelectric element, a first heat exchange fin, a rectifier cover, a combustion chamber, a piston, an exhaust pipe, a second thermoelectric element, an electric energy storage device, a controller, a temperature sensor, an air inlet, an air outlet, a guide plate, an air flow adjusting mechanism, an air flow valve, a plurality of second heat exchange fins and a plurality of third heat exchange fins. The application relates to a cylinder sleeve, a cylinder cover, a first thermoelectric element, a first heat exchange fin, a rectifier cover, a combustion chamber, a piston, an exhaust pipe, a second thermoelectric element, an electric energy storage device, a controller, a temperature sensor, an air inlet, an air outlet, a guide plate, an air flow adjusting mechanism, an air flow valve, a plurality of second heat exchange fins and a plurality of third heat exchange fins. The application relates to a cylinder sleeve, a cylinder cover, a first thermoelectric element, a first heat exchange fin, a rectifier cover, a combustion chamber, a piston, an exhaust pipe, a second thermoelectric element, an electric energy storage device, a controller, a temperature sensor, an air inlet, an air outlet, a guide plate, an air flow adjusting mechanism, an air flow valve, a plurality of second heat exchange fins and a plurality of third heat exchange fins. The application relates to a cylinder sleeve, a cylinder cover, a first thermoelectric element, a first heat exchange fin, a rectifier cover, a combustion chamber, a piston, an exhaust pipe, a second thermoelectric element, an electric energy storage device, a controller, a temperature sensor, an air inlet, an air outlet, a guide plate, an air flow adjusting mechanism, an air flow valve, a plurality of second heat exchange fins and a plurality of third heat exchange fins.

2. The aviation piston engine waste heat thermoelectric power generation system of claim 1, wherein, The application relates to a cylinder sleeve, a cylinder cover, a first thermoelectric element, a first heat exchange fin, a rectifier cover, a combustion chamber, a piston, an exhaust pipe, a second thermoelectric element, an electric energy storage device, a controller, a temperature sensor, an air inlet, an air outlet, a guide plate, an air flow adjusting mechanism, an air flow valve, a plurality of second heat exchange fins and a plurality of third heat exchange fins.

3. The aviation piston engine waste heat thermoelectric power generation system of claim 2, wherein, The application relates to a cylinder sleeve, a cylinder cover, a first thermoelectric element, a first heat exchange fin, a rectifier cover, a combustion chamber, a piston, an exhaust pipe, a second thermoelectric element, an electric energy storage device, a controller, a temperature sensor, an air inlet, an air outlet, a guide plate, an air flow adjusting mechanism, an air flow valve, a plurality of second heat exchange fins and a plurality of third heat exchange fins.

4. The aviation piston engine waste heat thermoelectric power generation system of claim 2, wherein, The application relates to a cylinder sleeve, a cylinder cover, a first thermoelectric element, a first heat exchange fin, a rectifier cover, a combustion chamber, a piston, an exhaust pipe, a second thermoelectric element, an electric energy storage device, a controller, a temperature sensor, an air inlet, an air outlet, a guide plate, an air flow adjusting mechanism, an air flow valve, a plurality of second heat exchange fins and a plurality of third heat exchange fins. The application relates to a cylinder sleeve, a cylinder cover, a first thermoelectric element, a first heat exchange fin, a rectifier cover, a combustion chamber, a piston, an exhaust pipe, a second thermoelectric element, an electric energy storage device, a controller, a temperature sensor, an air inlet, an air outlet, a guide plate, an air flow adjusting mechanism, an air flow valve, a plurality of second heat exchange fins and a plurality of third heat exchange fins.

5. The aviation piston engine waste heat thermoelectric power generation system of claim 4, wherein, The application relates to a cylinder sleeve, a cylinder cover, a first thermoelectric element, a first heat exchange fin, a rectifier cover, a combustion chamber, a piston, an exhaust pipe, a second thermoelectric element, an electric energy storage device, a controller, a temperature sensor, an air inlet, an air outlet, a guide plate, an air flow adjusting mechanism, an air flow valve, a plurality of second heat exchange fins and a plurality of third heat exchange fins.

6. The aviation piston engine waste heat thermoelectric power generation system of claim 1, wherein, The application relates to a cylinder sleeve, a cylinder cover, a first thermoelectric element, a first heat exchange fin, a rectifier cover, a combustion chamber, a piston, an exhaust pipe, a second thermoelectric element, an electric energy storage device, a controller, a temperature sensor, an air inlet, an air outlet, a guide plate, an air flow adjusting mechanism, an air flow valve, a plurality of second heat exchange fins and a plurality of third heat exchange fins.

7. The aviation piston engine waste heat thermoelectric power generation system of claim 1, wherein, The application relates to a cylinder sleeve, a cylinder cover, a first thermoelectric element, a first heat exchange fin, a rectifier cover, a combustion chamber, a piston, an exhaust pipe, a second thermoelectric element, an electric energy storage device, a controller, a temperature sensor, an air inlet, an air outlet, a guide plate, an air flow adjusting mechanism, an air flow valve, a plurality of second heat exchange fins and a plurality of third heat exchange fins.

8. A method of recovering waste heat from an aviation piston engine by using a system for recovering waste heat from an aviation piston engine according to any one of claims 1 to 7, characterized in that, The application relates to a cylinder sleeve, a cylinder cover, a first thermoelectric element, a first heat exchange fin, a rectifier cover, a combustion chamber, a piston, an exhaust pipe, a second thermoelectric element, an electric energy storage device, a controller, a temperature sensor, an air inlet, an air outlet, a guide plate, an air flow adjusting mechanism, an air flow valve, a plurality of second heat exchange fins and a plurality of third heat exchange fins. The application relates to a cylinder sleeve, a cylinder cover, a first thermoelectric element, a first heat exchange fin, a rectifier cover, a combustion chamber, a piston, an exhaust pipe, a second thermoelectric element, an electric energy storage device, a controller, a temperature sensor, an air inlet, an air outlet, a guide plate, an air flow adjusting mechanism, an air flow valve, a plurality of second heat exchange fins and a plurality of third heat exchange fins. The application relates to a cylinder sleeve, a cylinder cover, a first thermoelectric element, a first heat exchange fin, a rectifier cover, a combustion chamber, a piston, an exhaust pipe, a second thermoelectric element, an electric energy storage device, a controller, a temperature sensor, an air inlet, an air outlet, a guide plate, an air flow adjusting mechanism, an air flow valve, a plurality of second heat exchange fins and a plurality of third heat exchange fins. The application relates to a cylinder sleeve, a cylinder cover, a first thermoelectric element, a first heat exchange fin, a rectifier cover, a combustion chamber, a piston, an exhaust pipe, a second thermoelectric element, The piston moves to 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 is increased; Air enters from the fairing, cooling the first heat exchange fins; The hot side of the first thermoelectric element is in contact with the cylinder liner and the cylinder head, and the cold side is in contact with the first heat exchange fins; The hot side and the cold side of the first thermoelectric element form a temperature difference to generate an electromotive force, which outputs electric energy to an electric energy storage device; The exhaust gas generated by combustion in the cylinder liner passes through the exhaust pipe; The exhaust gas and the second heat exchange fins transfer heat to the exhaust pipe; The hot side of the second thermoelectric element is in contact with the exhaust pipe, and the cold side is in contact with the third heat exchange fins; The hot side and the cold side of the second thermoelectric element form a temperature difference to generate an electromotive force, which outputs electric energy to an electric energy storage device; The method further comprises: 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; the controller controls the opening of the air flow adjusting mechanism according to the received real-time temperature of the outer wall of the cylinder liner and the target temperature.

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