Horizontal aviation piston engine

Abstract

The invention relates to the technical field of aero-engines, and provides a horizontal aero-piston engine which comprises an engine main body structure, a speed reducing mechanism, a lubricating mechanism, a cooling mechanism and a gas path mechanism. The engine main body structure is connected with the speed reducing mechanism which is used for being connected with a propeller. The lubricating mechanism and the engine main body structure form a circulation loop; the cooling mechanism is connected with the engine main body structure and used for cooling the engine main body structure; the gas path mechanism is connected with the engine main body structure and used for introducing gas into the engine main body structure and discharging waste gas. According to the horizontal type aviation piston engine, a conventional in-line piston engine applied to an automobile is transformed into the horizontal type piston engine, so that the horizontal type piston engine can output a proper rotating speed for the propeller, and meanwhile it is guaranteed that the height of the center of an output shaft of the propeller is suitable for the layout of the aviation engine; the horizontal piston engine can be used as an aero-engine, and the manufacturing cost of the aero-engine is reduced.

Description

Technical Field

[0001] The invention relates to the technical field of aviation engines, and in particular to a horizontal aviation piston engine. Background Art

[0002] Existing aviation piston engines generally adopt a horizontally opposed layout. Although this design performs well in some performance indicators, it also has some significant technical challenges and market limitations. Specifically, these engines are relatively complex in technical implementation, resulting in limited mass production capacity and high costs. This high technical difficulty and high cost limit their application in a wider market.

[0003] With the rapid development of the low-altitude economy, the demand for aviation piston engines is growing. The low-altitude economy covers the manufacturing and operation of aircraft such as drones and electric vertical take-off and landing vehicles (eVTOL), as well as logistics, agriculture, tourism, urban management and other fields. The development of this market urgently requires an aviation piston engine that is both highly reliable and low-cost to promote the rapid development of the low-altitude economy. Summary of the invention

[0004] The invention provides a horizontal aviation piston engine, which is used to solve the defects of the aviation piston engines with horizontally opposed layout in the prior art, such as high technical difficulty and high production cost.

[0005] The present invention provides a horizontal aviation piston engine, comprising: an engine main structure, a speed reduction mechanism, a lubricating mechanism, a cooling mechanism and an air path mechanism; the engine main structure is connected to the speed reduction mechanism, and the speed reduction mechanism is used to be connected to a propeller; the lubricating mechanism and the engine main structure form a circulation loop to lubricate the engine main structure; the cooling mechanism is connected to the engine main structure, and the cooling mechanism is used to cool the engine main structure; the air path mechanism is connected to the engine main structure, and the air path mechanism is used to introduce gas into the engine main structure and discharge exhaust gas after combustion.

[0006] According to a horizontal aviation piston engine provided by the present invention, the engine main structure includes a first housing and a lubricating oil pump, the lubricating oil pump is arranged in the first housing, and the lubricating oil pump is used to pump lubricating oil to other components of the engine main structure; the lubrication mechanism includes: a second housing and a first pipeline, the second housing is arranged below the first housing and is connected to the first housing, and the two ends of the first pipeline are respectively connected to the second housing and the lubricating oil pump.

[0007] According to a horizontal aviation piston engine provided by the present invention, the cooling mechanism and the engine main structure are configured to form a first cooling cycle loop and a second cooling cycle loop; wherein, when the temperature in the engine main structure is less than a first preset value, the first cooling cycle loop operates, and when the temperature in the engine main structure is greater than or equal to the first preset value, the second cooling cycle loop operates.

[0008] According to a horizontal aviation piston engine provided by the present invention, the engine main structure has a water inlet and a water outlet; the first cooling circulation loop includes a thermostat, a second pipeline and a pump connected in sequence, the thermostat is connected to the water outlet, and the pump is connected to the water inlet; when the first cooling circulation loop is running, the cooling medium flows through the thermostat, and the thermostat is in a closed state.

[0009] According to a horizontal aviation piston engine provided by the present invention, the second cooling circulation loop includes the thermostat, the third pipeline, the radiator, the fourth pipeline and the pump connected in sequence; when the second cooling circulation loop is running, the thermostat is in an open state.

[0010] According to a horizontal aviation piston engine provided by the present invention, the cooling mechanism also includes an expansion water tank; the fourth pipeline has: a first opening, a second opening, a third opening and a fourth opening, the first opening is connected to the radiator, the second opening is connected to the pump, the third opening is connected to the expansion water tank, the fourth opening is provided with a cover body, and the cover body is provided with a pressure valve; when the pressure in the fourth pipeline is greater than a second preset value, the pressure valve opens, and the cooling medium in the fourth pipeline enters the expansion water tank; when the pressure in the fourth pipeline is less than the second preset value, the pressure valve closes, and the cooling medium in the expansion water tank flows back to the fourth pipeline.

[0011] A horizontal aviation piston engine provided according to the present invention also includes a connecting mechanism, wherein the engine main structure includes a rotating shaft, and the two ends of the rotating shaft are respectively connected to the reduction mechanism and the connecting mechanism; the connecting mechanism includes: a generator rotor, a first belt, a first pulley and a second pulley; the generator rotor is provided with a multi-groove pulley, and the multi-groove pulley is transmission-connected to the first pulley and the second pulley through the first belt; wherein the first pulley is used to connect to the drive pre-rotation mechanism, and the second pulley is used to connect to the pump.

[0012] According to a horizontal aviation piston engine provided by the present invention, the air path mechanism includes an intake assembly and an exhaust assembly; the intake assembly includes: a filter, a throttle and an intake manifold connected in sequence, and the intake manifold is connected to the main structure of the engine; the exhaust assembly includes: an exhaust manifold, a first exhaust pipe, an exhaust muffler and a second exhaust pipe connected in sequence, and the exhaust manifold is connected to the main structure of the engine.

[0013] According to a horizontal aviation piston engine provided by the present invention, the reduction mechanism comprises a ring gear, a shock absorber and a reducer connected in sequence; the ring gear is connected to the rotating shaft, and the reducer is used to be connected to the propeller.

[0014] A horizontal aviation piston engine provided according to the present invention also includes an electronic control mechanism, which includes multiple pairs of electronic control components; each pair of the electronic control components includes: a temperature and pressure sensor, a speed sensor and an electronic control unit, the temperature and pressure sensor is arranged on the intake manifold, the speed sensor is arranged on the rotating shaft, the temperature and pressure sensor, the speed sensor and the electronic control unit are electrically connected; wherein the ring gear is configured as one of the speed sensors.

[0015] The horizontal aviation piston engine provided by the present invention transforms a conventional in-line piston engine used in automobiles into a horizontal piston engine. By transforming the arrangement of a speed reduction mechanism, a lubrication mechanism, a cooling mechanism and an air path mechanism, the horizontal piston engine can output a suitable rotation speed for a propeller, and at the same time ensures that the height of the center of the propeller output shaft is suitable for the layout of the aviation engine, so that the horizontal piston engine can be used as an aviation engine, thereby reducing the manufacturing cost of the aviation engine and contributing to the rapid development of the low-altitude economy. BRIEF DESCRIPTION OF THE DRAWINGS

[0016] In order to more clearly illustrate the technical solutions in the present invention or the prior art, the following briefly introduces the drawings required for use in the embodiments or the description of the prior art. Obviously, the drawings described below are some embodiments of the present invention. For ordinary technicians in this field, other drawings can be obtained based on these drawings without paying creative work.

[0017] Figure 1 This is one of the structural schematic diagrams of the horizontal aviation piston engine provided by the present invention.

[0018] Figure 2 yes Figure 1 A local enlarged view of point A shown in FIG.

[0019] Figure 3 This is the second structural schematic diagram of the horizontal aviation piston engine provided by the present invention.

[0020] Figure 4 yes Figure 3 A partial enlarged view of point B is shown in FIG.

[0021] Figure 5 This is the third structural schematic diagram of the horizontal aviation piston engine provided by the present invention.

[0022] Figure 6 This is the fourth structural schematic diagram of the horizontal aviation piston engine provided by the present invention.

[0023] Reference numerals: 1. Engine main structure; 11. First housing; 12. Rotating shaft; 13. Water outlet; 21. Ring gear; 22. Shock absorber; 23. Input shaft; 24. Output shaft; 25. Second belt; 26. Propeller; 31. Second housing; 32. First pipeline; 33. Heat sink; 4. Cooling mechanism; 41. Thermostat; 42. Second pipeline; 43. Third pipeline; 44. Fourth pipeline; 45. Pump; 46. Cover; 441. First opening; 442 , second opening; 443, third opening; 444, fourth opening; 51, filter; 52, throttle; 53, intake manifold; 54, exhaust manifold; 55, first exhaust pipe; 56, exhaust muffler; 57, second exhaust pipe; 6, temperature and pressure sensor; 71, end cover; 72, suspension mounting point; 81, generator rotor; 82, first belt; 83, first pulley; 84, second pulley; 85, tensioner; 9, drive pre-rotation mechanism. DETAILED DESCRIPTION

[0024] In order to make the purpose, technical solution and advantages of the present invention clearer, the technical solution of the present invention will be clearly and completely described below in conjunction with the drawings of the present invention. Obviously, the described embodiments are part of the embodiments of the present invention, not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of the present invention.

[0025] Combine the following Figure 1-Figure 6 A horizontal aviation piston engine according to the invention is described.

[0026] like Figure 1As shown, in an embodiment of the present invention, a horizontal aviation piston engine includes: an engine main structure 1, a speed reduction mechanism, a lubricating mechanism, a cooling mechanism 4 and a gas path mechanism. The engine main structure 1 is connected to the speed reduction mechanism to reduce the speed of the engine main structure 1 output, and the speed reduction mechanism is connected to the propeller 26 so that the propeller 26 has a suitable speed. The lubricating mechanism and the engine main structure 1 form a circulation loop, and the lubricating oil in the lubricating mechanism enters the engine main structure 1 to lubricate the various components in the engine main structure 1, and then enters the lubricating mechanism again so that the lubricating oil is circulated. The cooling mechanism 4 is connected to the engine main structure 1, and the cooling mechanism 4 is used to cool the engine main structure 1 to reduce the temperature of the engine main structure 1 and ensure the normal operation of the engine. The gas path mechanism is connected to the engine main structure 1, and the gas path mechanism is used to pass gas into the engine main structure 1, and the gas participates in combustion in the engine main structure 1, and the exhaust gas generated by the combustion is discharged by the gas path mechanism.

[0027] The horizontal aviation piston engine provided in the embodiment of the present invention transforms a conventional in-line piston engine used in automobiles into a horizontal piston engine. By transforming the arrangement of the reduction mechanism, the lubrication mechanism, the cooling mechanism and the gas path mechanism, the horizontal piston engine can output a suitable rotation speed for the propeller, while ensuring that the height of the center of the propeller output shaft is suitable for the layout of the aviation engine, so that the horizontal piston engine can be used as an aviation engine, reducing the manufacturing cost of the aviation engine and contributing to the rapid development of the low-altitude economy.

[0028] like Figure 1 As shown, in an embodiment of the present invention, the engine main structure 1 includes a first housing 11 and a lubricating oil pump. The lubricating oil pump is arranged in the first housing 11, and the lubricating oil pump is used to pump lubricating oil to other components of the engine main structure 1. The lubricating mechanism includes: a second housing 31 and a first pipeline 32, and the second housing 31 is arranged below the first housing 11 and is connected to the first housing 11. The lubricating oil enters the second housing 31 from the first housing 11 for collection, and then is transported to the lubricating oil pump by the first pipeline 32, and is transported to various parts of the engine main structure 1 by the lubricating oil pump for lubrication, and then flows back to the first housing 11. Such a circulation flow realizes the continuous lubrication of various components in the engine main structure 1.

[0029] The second housing 31 is disposed at the bottom of the first housing 11 to facilitate the collection of lubricating oil. Furthermore, a heat sink 33 is disposed on the side of the first housing 11 to cool the lubricating oil in the first housing 11.

[0030] In the embodiment of the present invention, the cooling mechanism 4 and the engine main structure 1 are configured to form a first cooling cycle and a second cooling cycle, wherein the first cooling cycle operates when the temperature in the engine main structure 1 is less than a first preset value, and the second cooling cycle operates when the temperature in the engine main structure 1 is greater than or equal to the first preset value. That is, when the temperature in the engine main structure 1 is low, the first cooling cycle operates, and when the temperature in the engine main structure 1 is high, the second cooling cycle operates.

[0031] like Figure 3 and Figure 4 As shown, in an embodiment of the present invention, the engine main structure 1 has a water inlet and a water outlet 13. The first cooling circulation loop includes a thermostat 41, a second pipeline 42 and a pump 45 connected in sequence, the thermostat 41 is connected to the water outlet 13, and the pump 45 is connected to the water inlet.

[0032] Specifically, when the temperature in the engine main structure 1 is low, the cooling medium enters the thermostat 41, the second pipeline 42, and the pump 45 from the water outlet 13, and enters the engine main structure 1 from the water inlet of the engine main structure 1 for circulation cooling. In this embodiment, the cooling medium flows through the thermostat 41, but the thermostat 41 is in a closed state.

[0033] like Figure 1 and Figure 2 As shown, the second cooling circulation loop includes a thermostat 41, a third pipeline 43, a radiator, a fourth pipeline 44 and a pump 45 connected in sequence. When the temperature in the engine main structure 1 is high, the cooling medium enters the thermostat 41, the third pipeline 43, the radiator, the fourth pipeline 44, and the pump 45 from the water outlet 13, and enters the engine main structure 1 from the water inlet of the engine main structure 1 to cool the engine main structure 1. In this embodiment, the thermostat 41 is in an open state, and the thermostat 41 automatically adjusts the flow of the cooling medium entering the radiator by sensing the temperature of the cooling medium, thereby adjusting the heat dissipation capacity of the cooling mechanism 4, which not only helps the piston engine to maintain the optimal operating temperature, but also improves fuel economy and reduces emissions.

[0034] like Figure 2 As shown, in the embodiment of the present invention, the cooling mechanism 4 further includes an expansion water tank. The fourth pipeline 44 has a first opening 441, a second opening 442, a third opening 443 and a fourth opening 444, wherein the first opening 441 is connected to the radiator, the second opening 442 is connected to the pump 45, the third opening 443 is connected to the expansion water tank, and the fourth opening 444 is provided with a cover 46, and the cover 46 is provided with a pressure valve.

[0035] After passing through the radiator, the cooling medium enters the fourth pipeline 44 through the first opening 441. When the pressure in the fourth pipeline 44 is greater than the second preset value, that is, when the pressure of the cooling medium in the fourth pipeline 44 reaches the opening pressure of the cover 46, the pressure valve opens, and the cooling medium enters the expansion tank through the third opening 443. When the temperature of the cooling medium drops and the pressure decreases, the fourth pipeline 44 forms a vacuum, and the cooling medium is sucked back from the expansion tank to the fourth pipeline 44, and enters the pump 45 through the second opening 442.

[0036] like Figure 1 As shown, the speed reduction mechanism includes a ring gear 21, a shock absorber 22 and a speed reducer connected in sequence. The main engine structure 1 has a rotating shaft 12, which is connected to the ring gear 21, driving the ring gear 21 to rotate, and then driving the shock absorber to rotate. The shock absorber is connected to the input shaft 23 of the speed reducer, and the input shaft 23 of the speed reducer is connected to the output shaft 24 through a second belt 25. The output shaft 24 is used to connect with the propeller 26, so that the speed of the piston engine is input to the propeller 26 after being decelerated by the speed reducer, so that the speed of the piston engine matches the speed of the propeller 26.

[0037] Furthermore, the reducer is installed on the outside of the engine main structure 1 through a bracket, and the reducer is provided with a refueling port, a liquid level observation port and an oil drain port to perform refueling, liquid level observation and oil draining on the reducer.

[0038] like Figure 5 As shown, in an embodiment of the present invention, the air circuit mechanism includes an intake assembly and an exhaust assembly. The intake assembly includes a filter 51, a throttle 52 and an intake manifold 53 connected, and the intake manifold 53 is connected to the engine main structure 1. The exhaust assembly includes an exhaust manifold 54, a first exhaust pipe 55, an exhaust muffler 56 and a second exhaust pipe 57 connected in sequence, and the exhaust manifold 54 is connected to the engine main structure 1.

[0039] Specifically, after being filtered by the filter 51, the gas enters the engine main structure 1 through the throttle 52 and the intake manifold 53 to participate in combustion. The exhaust gas generated by the combustion is discharged into the atmosphere through the exhaust manifold 54, the first exhaust pipe 55, the exhaust muffler 56, and the second exhaust pipe 57.

[0040] like Figure 5 As shown, in an embodiment of the present invention, the suspension bracket is integrated with the end cover 71 of the engine timing chain, and is provided with four through holes, each of which forms a suspension mounting point 72, and a vibration-damping pad is provided inside each suspension mounting point 72 for mounting a vibration absorber.

[0041] like Figure 6As shown, in an embodiment of the present invention, the horizontal aviation piston engine also includes a connecting mechanism, one end of the rotating shaft 12 is connected to the gear ring 21 of the reduction mechanism, and the other end is connected to the connecting mechanism. The connecting mechanism includes: a generator rotor 81, a first belt 82, a first pulley 83 and a second pulley 84. The generator rotor 81 is provided with a multi-groove pulley, and the multi-groove pulley is connected to the first pulley 83 and the second pulley 84 through the first belt 82 to drive the first pulley 83 and the second pulley 84 to rotate. Further, the first pulley 83 is used to connect with the driving pre-rotation mechanism 9 to drive the driving pre-rotation mechanism 9 to rotate. The second pulley 84 is used to connect with the pump 45 to drive the pump 45 to rotate.

[0042] Further, in an embodiment of the present invention, the horizontal aviation piston engine further includes an electronic control mechanism, which includes multiple pairs of electronic control components. Each pair of electronic control components includes: a temperature and pressure sensor 6, a speed sensor and an electronic control unit. The temperature and pressure sensor 6 is arranged on the intake manifold 53, the speed sensor is arranged on the rotating shaft 12, and the temperature and pressure sensor 6 and the speed sensor are both electrically connected to the electronic control unit.

[0043] Specifically, in this embodiment, the number of electronic control components is multiple pairs, that is, after one electronic control component fails, other electronic control components can still work normally, so as to ensure the reliability of the piston engine and realize redundant design.

[0044] Furthermore, the electronic control unit receives information input from the temperature and pressure sensors and the speed sensor, performs calculations, processing and judgment, and then outputs instructions to control various functions of the piston engine, thereby achieving fast, accurate and automatic control.

[0045] Optionally, in an embodiment of the present invention, the number of the electronic control components is two. A rotation speed sensor is disposed on the rotating shaft 12 of the engine main structure 1 , and the other rotation speed sensor is replaced by the ring gear 21 .

[0046] The horizontal aviation piston engine provided by the embodiment of the present invention solves the problem that the rotation speed of a conventional engine does not match the rotation speed of a propeller when the conventional engine is used as an aviation engine; solves the lubrication problem when an in-line engine is converted into a horizontal engine; solves the cooling problem of the horizontal engine; at the same time, an air path mechanism suitable for aviation engines is designed to achieve a redundant design of an electronic control system; a suspension structure and a connecting mechanism suitable for aviation engines are designed, so that a conventional in-line engine that can only be used in automobiles can be converted into a horizontal structure so that it can be used in aircraft, thereby reducing the manufacturing cost of the aviation engine, and the converted horizontal aviation piston engine has high reliability and long service life.

[0047] Finally, it should be noted that the above embodiments are only used to illustrate the technical solutions of the present invention, rather than to limit it. Although the present invention has been described in detail with reference to the aforementioned embodiments, those skilled in the art should understand that they can still modify the technical solutions described in the aforementioned embodiments, or make equivalent replacements for some of the technical features therein. However, these modifications or replacements do not deviate the essence of the corresponding technical solutions from the spirit and scope of the technical solutions of the embodiments of the present invention.

Claims

1. A horizontal aviation piston engine, characterized in that: include: Engine main structure, speed reduction mechanism, lubrication mechanism, cooling mechanism and gas path mechanism; The engine main body structure is connected to the speed reduction mechanism, and the speed reduction mechanism is used to connect to the propeller; The lubrication mechanism and the main engine structure form a circulation loop to lubricate the main engine structure; The cooling mechanism is connected to the main structure of the engine, and the cooling mechanism is used to cool the main structure of the engine; The gas path mechanism is connected to the main structure of the engine, and is used to introduce gas into the main structure of the engine and discharge exhaust gas after combustion.

2. The horizontal aviation piston engine according to claim 1, characterized in that: The engine main structure comprises a first housing and a lubricating oil pump, wherein the lubricating oil pump is arranged in the first housing and is used to pump lubricating oil to other components of the engine main structure; The lubrication mechanism includes: a second housing and a first pipeline. The second housing is arranged below the first housing and communicated with the first housing. Two ends of the first pipeline are respectively communicated with the second housing and the lubricating oil pump.

3. The horizontal aviation piston engine according to claim 1, characterized in that: The cooling mechanism and the engine main structure are configured to form a first cooling circulation loop and a second cooling circulation loop; When the temperature in the main structure of the engine is lower than a first preset value, the first cooling cycle operates; when the temperature in the main structure of the engine is higher than or equal to the first preset value, the second cooling cycle operates.

4. The horizontal aviation piston engine according to claim 3, characterized in that: The engine main structure has a water inlet and a water outlet; The first cooling circulation loop comprises a thermostat, a second pipeline and a pump connected in sequence, the thermostat is connected to the water outlet, and the pump is connected to the water inlet; When the first cooling circuit is in operation, the coolant flows through the thermostat, and the thermostat is in a closed state.

5. The horizontal aviation piston engine according to claim 4, characterized in that: The second cooling circulation loop includes the thermostat, the third pipeline, the radiator, the fourth pipeline and the pump connected in sequence; When the second cooling circuit is in operation, the thermostat is in an open state.

6. The horizontal aviation piston engine according to claim 5, characterized in that: The cooling mechanism also includes an expansion water tank; The fourth pipeline has: a first opening, a second opening, a third opening and a fourth opening, the first opening is connected to the radiator, the second opening is connected to the pump, the third opening is connected to the expansion tank, the fourth opening is provided with a cover body, and the cover body is provided with a pressure valve; When the pressure in the fourth pipeline is greater than a second preset value, the pressure valve opens, and the cooling medium in the fourth pipeline enters the expansion water tank; When the pressure in the fourth pipeline is less than the second preset value, the pressure valve is closed, and the cooling medium in the expansion water tank flows back to the fourth pipeline.

7. The horizontal aviation piston engine according to claim 4, characterized in that: It also includes a connecting mechanism, the main structure of the engine includes a rotating shaft, and both ends of the rotating shaft are respectively connected to the speed reduction mechanism and the connecting mechanism; The connecting mechanism comprises: a generator rotor, a first belt, a first pulley and a second pulley; the generator rotor is provided with a multi-groove pulley, and the multi-groove pulley is connected to the first pulley and the second pulley through the first belt; Wherein, the first pulley is used to be connected to the driving pre-rotation mechanism, and the second pulley is used to be connected to the pump.

8. The horizontal aviation piston engine according to claim 7, characterized in that: The gas circuit mechanism includes an air intake component and an exhaust component; The air intake assembly comprises: a filter, a throttle valve and an intake manifold connected in sequence, and the intake manifold is connected to the main structure of the engine; The exhaust assembly comprises: an exhaust manifold, a first exhaust pipe, an exhaust muffler and a second exhaust pipe which are connected in sequence, and the exhaust manifold is connected to the main structure of the engine.

9. The horizontal aviation piston engine according to claim 8, characterized in that: The speed reduction mechanism comprises a gear ring, a shock absorber and a speed reducer connected in sequence; The ring gear is connected to the rotating shaft, and the reducer is used to be connected to the propeller.

10. The horizontal aviation piston engine according to claim 9, characterized in that: Also included is an electric control mechanism, the electric control mechanism including a plurality of pairs of electric control components; Each pair of the electronic control components comprises: a temperature and pressure sensor, a speed sensor and an electronic control unit, wherein the temperature and pressure sensor is arranged on the intake manifold, the speed sensor is arranged on the rotating shaft, and the temperature and pressure sensor, the speed sensor and the electronic control unit are electrically connected; In this case, the ring gear is designed as one of the rotational speed sensors.

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