CN112177773B

CN112177773B - Aviation piston engine

Info

Publication number: CN112177773B
Application number: CN202011055522.3A
Authority: CN
Inventors: 何清华; 潘钟键; 邹湘伏; 杨斌; 刘厚根
Original assignee: Sunward Intelligent Equipment Co Ltd
Current assignee: Sunward Intelligent Equipment Co Ltd
Priority date: 2020-09-29
Filing date: 2020-09-29
Publication date: 2021-08-06
Anticipated expiration: 2040-09-29
Also published as: CN112177773A

Abstract

The invention discloses an aviation piston engine which comprises an engine shell, a crank connecting rod mechanism, a mechanical supercharger, a turbocharger, a belt transmission mechanism, a fuel pump, a generator and a starting motor. The crank-connecting rod mechanism comprises a crankshaft which is horizontally arranged, two cranks are fixed on the crankshaft, two opposite connecting rods are arranged on each crank, and a piston is arranged at one end, far away from the crankshaft, of each connecting rod. The engine shell comprises a box body and four cylinder bodies, wherein the box body is mounted with the crankshaft in a shaft-embracing mode, the four cylinder bodies are mounted on the box body and communicated with the box body, and the four pistons are arranged in the corresponding cylinder bodies in a sliding mode. The engine has compact structure, reduced installation size and high power-weight ratio. A mechanical supercharger and a turbocharger are connected in series, so that scavenging can be performed at high and low speeds, and redundancy is realized.

Description

Aviation piston engine

Technical Field

The invention relates to the technical field of engines, in particular to an aviation heavy oil piston engine.

Background

The prior aviation piston engine mainly uses aviation gasoline, the prior compression ignition type aviation heavy oil piston engine is basically four-stroke, a gas distribution phase mechanism is adopted, the total weight of the engine is increased, the components and parts are complex to form, a crankshaft rotates for two circles to do work once, and the power-weight ratio is lower; in addition, the cooling of the four-stroke engine adopts more air cooling so as to reduce the complex design of an internal cavity of the engine. The traditional two-stroke engine adopts crankcase air intake, lubricating oil is mixed into fuel oil to moisten and exchange the engine, the structures of scavenging, lubricating, cooling and the like are complex, the power-weight ratio is higher, but the two-stroke engine is only limited to a low-power gasoline aero-engine, and the two-stroke structural form is not suitable for a high-power aero heavy oil engine which has higher requirements on air intake pressure and a lubricating mode and needs supercharging. Therefore, the current four-stroke engine and two-stroke engine are not suitable for being used as aviation kerosene piston engines.

Disclosure of Invention

The invention aims to overcome the defects of the prior art and provide the aviation heavy oil piston engine which is compact in structure, high in power-weight ratio, good in reliability and low in operation cost.

In order to solve the technical problems, the invention adopts the following technical scheme:

an aviation piston engine comprises an engine shell, a crank connecting rod mechanism, a mechanical supercharger, a turbocharger, a belt transmission mechanism, a fuel pump, a generator and a starting motor;

the crank connecting rod mechanism comprises a crankshaft which is horizontally arranged, two cranks are fixed on the crankshaft, each crank comprises a crankshaft neck parallel to the crankshaft and two crank arms connected between the crankshaft and the crankshaft necks, and the two crank arms are respectively arranged at two ends of the crankshaft necks; the axial center lines of the two crank journals are respectively arranged on two sides of the axial center plane of the crank, and the axial center lines of the crank and the two crank journals are on the same plane; two connecting rods are rotatably arranged on each crankshaft neck, the extending directions of the two connecting rods on each crankshaft neck are opposite, the four connecting rods are sequentially arranged along the axial direction of the crankshaft, and one end, far away from the crankshaft, of each connecting rod is provided with a piston;

the engine shell comprises a box body mounted with the crankshaft in a shaft-hung manner and four cylinder bodies which are mounted on the box body and communicated with the box body, the four cylinder bodies are horizontally arranged, the four cylinder bodies correspond to four connecting rods one by one, and the pistons are slidably arranged in the corresponding cylinder bodies; the cylinder body is provided with a first air scanning port and an air exhaust port;

the mechanical supercharger is arranged at the upper end of the box body, the turbocharger is arranged on one side of the box body along the axial direction of the crankshaft, and the generator and the starting motor are both arranged at one end of the box body far away from the turbocharger;

the first air sweeping ports of the four cylinder bodies are communicated with the air outlet end of the mechanical supercharger through an air inlet manifold, the air outlet end of the turbocharger is communicated with the air inlet end of the mechanical supercharger through a hose, and the air exhaust ports of the four cylinder bodies are communicated with the air inlet end of the turbocharger through hoses;

the fuel pump is arranged between the box body and the turbocharger, an input shaft of the fuel pump is in transmission connection with the crankshaft, and the four cylinder bodies are communicated with the fuel pump through fuel pipes;

the belt transmission mechanism comprises a first belt wheel fixed on an input shaft of the mechanical supercharger, a second belt wheel fixed on an input shaft of the generator, a third belt wheel in transmission connection with the crankshaft, and a belt running around the first belt wheel, the second belt wheel and the third belt wheel;

the third belt pulley is arranged on one side, far away from the turbocharger, of the box body, a flywheel is fixed at one end, far away from the box body, of the third belt pulley, the starting motor is provided with a telescopic gear shaft, and the gear shaft can be in meshing transmission with the flywheel when extending out.

The mechanical supercharger and the third belt wheel are accelerated through a certain transmission ratio, so that the mechanical supercharger has certain supercharging scavenging capacity when the engine is at a low speed, and compressed air is conveyed to a scavenging port of a cylinder body through an air inlet manifold. When the engine reaches a certain rotating speed, the air compressed by the turbocharger is large enough to directly open the bypass valve inside the mechanical supercharger, at the moment, the mechanical supercharger idles, the supercharging effect is not generated, and the engine is completely provided with air inlet pressure by the turbocharger. Meanwhile, when the engine flies in the air and the turbocharger is damaged, the mechanical supercharger can still maintain certain power to enable the aircraft to return. Therefore, the mechanical supercharger and the turbocharger are connected in series, scavenging can be carried out at high and low speeds, redundancy backup is carried out, the mechanical supercharger is driven by the engine, reliability is good, the mechanical supercharger can still normally work when the turbocharger fails, installation is convenient, and regular maintenance can be carried out.

The two-stroke aviation heavy oil piston engine has the advantages of compact structure and high power-weight ratio, and specifically comprises the following components:

1) each cylinder body is directly communicated with the mechanical supercharger through an air inlet manifold, the cylinder body is provided with a scavenging hole, and the piston reciprocates to scavenge air, so that a gas distribution phase structure is not needed.

2) The belt transmission mechanism is adopted, the mechanical supercharger, the generator and the cooling water pump can be driven to operate through the rotation of the crankshaft, and the engine can be started to work through the meshing transmission of the flywheel added at one end of the belt pulley and the starting motor; the crankshaft is used for outputting power to drive a fuel pump assembly to work, and the fuel pump assembly is arranged at the other end of the engine; therefore, the components can be compactly arranged, the power-weight ratio is improved, and the reliability is high.

3) The double-crank structure is adopted, and two connecting rods are arranged on each crank, so that the length of the crank shaft is shorter, the weight is lighter, and the four cylinder bodies are horizontally arranged in an opposite mode, so that the size of the engine is greatly reduced, and the power-weight ratio is effectively improved.

Thus, the piston engine of the present invention can be adapted to most aircraft and applications with high power-to-weight ratio requirements, as long as the power match is sufficient. It is also possible to replace the existing supercharger with a smaller scavenge pump, the power-to-weight ratio of the engine will be higher and the size more compact. And the engine uses aviation kerosene as fuel, so that the economy is good, and the running cost is low.

As a further improvement of the above technical solution:

a cooling water pump is further mounted at one end, far away from the turbocharger, of the box body, the cooling water pump is located above the generator, a fourth belt wheel is mounted on an input shaft of the cooling water pump, and the outer circumference of the fourth belt wheel is abutted to the belt and applies radial thrust to the belt; and cooling channels are arranged at the two ends of the cylinder body in the axial direction and are communicated with a cooling water pump in a circulating manner through pipelines.

When the water pump is installed, the belt wheel compresses the belt, and the belt can be driven to operate by the belt, so that the structure is compact, and the operation is reliable. The whole engine is cooled by water, the cooling efficiency is higher than that of the conventional air cooling, and the cylinder body and the cylinder head are provided with cooling liquid inlet channels so that the cooling liquid can reach quickly.

And one end of the crankshaft, which is close to the third belt wheel, is provided with a propeller mounting flange, so that hydraulic oil is allowed to be used for driving the propeller pitch. The propeller mounting flange is arranged on the outer side of the flywheel.

An accessory box is mounted on the end face, close to one end of the turbocharger, of the box body, a driving gear and two driven gears which are in meshed transmission with the driving gear are arranged in the accessory box, the driving gear is in transmission connection with a crankshaft, the fuel pump is fixed on the wall face, back to the box body, of the accessory box, and an input shaft of the fuel pump is in key connection with the crankshaft; the low-pressure fuel pump is in transmission connection with one driven gear, and the oil pump is in transmission connection with the other driven gear.

According to the invention, the crankshaft is used for driving the driving gear to rotate so as to drive the driven gear to rotate, and the two ends of the driven gear are provided with the connecting ports, so that different engine accessories are ensured to be installed, and the applicability is further improved.

The low-pressure fuel pump and the oil pump are both driven by the crankshaft, and the reliability is high. The low pressure fuel pump draws fuel and supplies the fuel to the high pressure fuel pump.

The wall surface of the accessory box, which faces away from the box body, is provided with two accessory interfaces for driving and connecting the driven gears and external equipment, and the two accessory interfaces correspond to the two driven gears one by one.

And a lubricating channel is formed in the crank connecting rod mechanism and is circularly communicated with the oil pump through a pipeline, so that a dry pressure lubricating system is formed. An independent lubricating oil channel is arranged in the engine body, so that oil cooling is performed on key parts of the engine and the piston, and a cooling system is used for redundancy backup.

And oil ducts are formed in the crankshaft, the crank, the connecting rod and the piston pin for connecting the piston and the connecting rod, and the oil ducts in the crankshaft, the crank, the connecting rod and the piston pin are communicated to form the lubricating oil duct.

The oil injection device is characterized in that an oil injection nozzle for cooling the piston is installed on the inner wall of the box body and is communicated with the fuel pump through a pipeline, and the number of the oil injection nozzles is four, and the four oil injection nozzles correspond to the four pistons one to one.

And an oil nozzle is arranged in the engine body, so that oil injection cooling is performed on the piston when the engine runs, and the service life of the piston is prolonged. The nozzle is fixed on the engine oil pipeline, so that enough engine oil can enter the oil nozzle when the engine works.

The crank shaft is fixedly connected with balancing weights in one-to-one correspondence with the crank arms, and the crank arms and the corresponding balancing weights are respectively arranged at two ends of the crank shaft in the radial direction.

The generator is removably mounted to the engine housing by a generator mounting bracket assembly, the generator being rotatable relative to the engine housing to tension the belt.

Compared with the prior art, the invention has the advantages that:

1. the aviation piston engine has the advantages of compact structure, reduced installation size and high power-weight ratio. As long as the power matching is enough, the method can be suitable for most aircrafts and occasions with high power-to-weight ratio requirements.

2. The aviation piston engine provided by the invention is self-provided with water cooling and lubrication, and the service life of the engine is prolonged by the independent lubricating system and cooling system, and the aviation piston engine is reliable in operation and has low requirements on environment.

3. The aviation piston engine adopts the series connection of the mechanical supercharger and the turbocharger, can scavenge air at high and low speeds, and simultaneously performs redundancy backup. And the mechanical supercharger is driven by the engine, so that the reliability is good, the turbocharger can still normally work when the turbocharger fails, the installation is convenient, and the regular maintenance is only needed.

4. The aviation piston engine uses aviation kerosene as fuel, and has good economical efficiency and low operation cost.

Drawings

Fig. 1 is a schematic perspective view of an aviation piston engine according to the embodiment.

Fig. 2 is a schematic perspective view of another perspective view of the aviation piston engine of the embodiment.

Fig. 3 is a schematic perspective view of the aviation piston engine of the embodiment (the accessory case and the fuel pump are omitted).

Fig. 4 is a schematic perspective view of another perspective view of the aviation piston engine of the present embodiment (with the accessory case and fuel pump omitted).

Fig. 5 is a schematic perspective view of the engine housing.

Fig. 6 is a schematic perspective view of an engine housing (omitting a supercharger mount).

Fig. 7 is a perspective view of an engine housing (omitting a supercharger mounting seat) from another perspective.

Fig. 8 is a perspective view of the engine half shell.

Fig. 9 is a perspective view of another perspective of the engine half shell.

Fig. 10 is a schematic structural view of the crank link mechanism.

Fig. 11 is a schematic diagram of the assembled engine half-shell and crank-link mechanism.

Fig. 12 is a perspective view of the accessory case.

FIG. 13 is a perspective view of an alternate view of the accessory case.

Illustration of the drawings: 1. an engine housing; 11. a box body; 111. a partition plate; 1111. a first through hole; 112. a generator mounting base; 113. starting a motor mounting seat; 114. a cooling water pump mounting base; 115. an accessory case interface; 1151. a groove; 1152. a second through hole; 1153. a third through hole; 116. installing an interface; 117. a supercharger mounting seat; 118. a chamber; 119. a half box body; 12. a cylinder body; 13. an intake manifold; 14. an oil jet; 15. a positioning part; 151. a fourth via hole; 152. and a ring groove. 2. A crank link mechanism; 21. a crankshaft; 211. mounting a propeller flange; 212. spline connecting holes; 213. an oil passage hole; 22. a crankshaft neck; 23. a crank arm; 24. a connecting rod; 25. a piston; 26. a balancing weight; 27. an end cap; 3. a mechanical supercharger; 4. a turbocharger; 5. a belt drive mechanism; 51. a first pulley; 52. a second pulley; 53. a third belt pulley; 54. a belt; 55. a flywheel; 6. a fuel pump; 7. a generator; 8. starting the motor; 81. a gear shaft; 9. a cooling water pump; 91. a fourth pulley; 10. an accessory case; 101. a driving gear; 102. a driven gear; 103. a fifth through hole; 104. a sixth through hole; 105. an accessory interface.

Detailed Description

The invention is further described below with reference to specific preferred embodiments, without thereby limiting the scope of protection of the invention.

Example 1:

as shown in fig. 1 to 4, the aviation piston engine of the embodiment includes an engine housing 1, a crank link mechanism 2, a supercharger 3, a turbocharger 4, a belt transmission mechanism 5, a fuel pump 6, a generator 7, a starter motor 8, a cooling water pump 9, and an accessory case 10.

As shown in fig. 10, the crank link mechanism 2 includes a crankshaft 21 disposed horizontally, two cranks are fixed to the crankshaft 21, the cranks include a crank journal 22 parallel to the crankshaft 21, and two crank arms 23 connected between the crankshaft 21 and the crank journal 22, the two crank arms 23 being provided at both ends of the crank journal 22; the crank shaft 21 is fixedly connected with balancing weights 26 corresponding to the crank arms 23 one by one, and the crank arms 23 and the corresponding balancing weights 26 are respectively arranged at two ends of the crank shaft 21 in the radial direction. The axial center lines of the two crank journals 22 are respectively arranged on two sides of the axial center plane of the crank shaft 21, and the axial center lines of the crank shaft 21 and the two crank journals 22 are on the same plane; two connecting rods 24 are rotatably mounted on each crank journal 22, the two connecting rods 24 on each crank journal 22 extend in opposite directions, four connecting rods 24 are sequentially arranged along the axial direction of the crankshaft 21, and a piston 25 is mounted at one end of each connecting rod 24 away from the crankshaft 21.

The crankshaft 21 is a double-crank crankshaft, four cylinders share two cranks, each crankshaft neck is provided with 2 connecting rods 24, and the connecting rods 24 are fixed on the cranks through end covers 27 and bolts. A weight 26 is attached to the crankshaft 21 to balance the crankshaft 21 rotating at a high speed. The small end of the connecting rod connects the piston 25 and the connecting rod 24 together by a piston pin. The crankshaft 21 is provided with an oil passage hole 213, which ensures that the oil passages between the crankshaft bearing bush and the connecting rod bearing bush are mutually connected, and can convey lubricating oil to the parts needing lubrication. The crankshaft 21 is provided with a splined connection hole 212 at one end to drive a camshaft in the fuel pump assembly and a propeller connection flange 211 directly provided at the other end. The crankshaft 21 and the crank are empty in the middle, and the weight can be reduced to the maximum extent without affecting the strength.

As shown in fig. 5 to 9 and 11, the engine case 1 includes a case 11 mounted around a crankshaft 21, and four cylinders 12 mounted on the case 11. The box body 11 is assembled by two half box bodies 119 which are respectively arranged on two sides of the axial center line of the crankshaft through a plurality of bolts, and sealing leakage between the machine bodies on two sides is avoided.

Be equipped with baffle 111 in the box 11, set up the first through-hole 1111 that can supply the bent axle to pass on the baffle 111, baffle 111 divide into two cavities 118 with two crank one-to-one of bent axle 21 with the box 11 inner chamber, cavity 118 is used for holding corresponding crank, four cylinder body 12 divide into two sets ofly, every group includes that two branches locate the cylinder body 12 of bent axle axial central plane both sides, cylinder body 12 and the cavity 118 intercommunication that corresponds, cylinder body 12 horizontal arrangement, the axial direction of cylinder body 12 is perpendicular with the axial direction of bent axle, first scanning gas mouth has been seted up on the cylinder body 12, exhaust port and fuel inlet, first scanning gas mouth is seted up in the upper end of cylinder body 12, the exhaust port is seted up in the lower extreme of cylinder body 12 and is opposed along the radial direction of cylinder body 12 with first scanning gas mouth, the exhaust port directly is connected with exhaust hose 41. The four cylinder bodies 12 correspond to four connecting rods 24 one by one, the connecting rods 24 extend into the corresponding cylinder bodies 12, and the pistons 25 are slidably arranged in the corresponding cylinder bodies 12.

Two oil nozzles 14 for cooling the piston are mounted on the inner wall of the chamber 118, and the two oil nozzles 14 are respectively provided on the two case halves 119. The number of the oil nozzles 14 is four, and the four oil nozzles 14 correspond to the four pistons 25 one by one. The oil jet 14 is fixed to the oil line to ensure that sufficient oil enters the oil jet 14 when the engine is operating.

The middle part of the end face of one end of the box body 11, on which the belt transmission mechanism 5 is mounted, extends outwards to form the positioning part 15, the positioning part 15 is provided with a fourth through hole 151 for the crankshaft to penetrate through, and the inner wall of the fourth through hole 151 is provided with a ring groove 152 for positioning the crankshaft.

The turbocharger 4, the fuel pump 6, and the accessory case 10 are provided on one side of the case 11 in the axial direction of the crankshaft 21, and the belt transmission mechanism 5, the generator 7, the starter motor 8, and the cooling water pump 9 are provided on the other side of the case 11 in the axial direction of the crankshaft 21.

A supercharger mounting seat 117 having an inner cavity is provided at the upper end of the casing 11, and the supercharger 3 is mounted to the upper end of the casing 11 via the supercharger mounting seat 117. An installation flange 121 for installing the intake manifold 13 is arranged at the upper part of the cylinder body 12, and a second scavenging port communicated with the first scavenging port is formed in the installation flange 121. The inner cavity of the supercharger mounting seat 117 communicates with the scavenging port of the cylinder block 12 through the intake manifold 13.

The turbocharger 4 is connected to one side of the housing 11 in the axial direction of the crankshaft 21 by a bracket.

The first scavenging ports of the four cylinders 12 are communicated with the air outlet end of the mechanical supercharger 3 through an air inlet manifold 13, the air outlet end of the turbocharger 4 is communicated with the air inlet end of the mechanical supercharger 3 through an air inlet hose 31, and the exhaust ports of the four cylinders 12 are communicated with the air inlet end of the turbocharger 4 through an exhaust hose 41.

A generator mounting base 112 and a starter motor mounting base 113 are provided on a lower portion of an end surface of one end (an end opposite to the turbocharger 4) of the case 11 in the axial direction of the crankshaft, and the starter motor mounting base 113 is provided below the generator mounting base 112. A cooling water pump mounting seat 114 is arranged on the upper part of the end surface of the box body 11 on which the generator mounting seat 112 is mounted. The other end face of the box body 11 is provided with a mounting interface 116 at the upper part for mounting the engine body on the aircraft, and is connected with the engine mounting rack through a shock absorption pad.

The generator 7 is detachably connected to the case 11 via a generator mount 112, and the generator 7 is rotatable relative to the engine case 1 to tension the belt 54. The starting motor 8 is detachably connected with the box body 11 through a starting motor mounting seat 113. The cooling water pump 9 is detachably connected to the tank 11 through a cooling water pump mount 114.

The belt transmission mechanism 5 includes a first pulley 51 fixed to the input shaft of the supercharger 3, a second pulley 52 fixed to the input shaft of the generator 7, a third pulley 53 drivingly connected to the crankshaft 21, and a belt 54 running around the first pulley 51, the second pulley 52, and the third pulley 53.

The third belt wheel 53 is arranged at one end of the crankshaft 21, a flywheel 55 is fixed at one end of the third belt wheel 53, the starting motor 8 is provided with a telescopic gear shaft 81, and the gear shaft 81 can be meshed with the flywheel 55 for transmission when extending.

The cooling water pump 9 is positioned above the generator 7, a fourth belt pulley 91 is arranged on an input shaft of the cooling water pump 9, the outer circumference of the fourth belt pulley 91 is abutted with the belt 54 and applies radial thrust to the belt 54; both ends of the cylinder body 12 in the axial direction are provided with cooling channels which are communicated with the cooling water pump 9 in a circulating way through pipelines.

In this embodiment, a propeller mounting flange 211 is disposed at one end of the crankshaft 21 close to the third pulley 53, and the propeller mounting flange 211 is disposed at an outer side of the flywheel 55.

An accessory box interface 115 is arranged on the end face of the other end of the box body 11 in the axial direction of the crankshaft, and the accessory box 10 is detachably connected with the box body 11 through the accessory box interface 115. As shown in fig. 12 and 13, a driving gear 101 and two driven gears 102, both of which are in mesh transmission with the driving gear 101, are provided in the attachment box 10, and one end of the attachment box 10 facing the casing 11 is opened to expose the driving gear 101 and the driven gears 102. The end surface of the box body 11 for mounting the accessory box is recessed towards the inside of the box body 11 to form a groove 1151 matched with the inner cavity of the accessory box, and the groove is used for mounting and sealing the accessory box 10. The cavity wall of the accessory box 10 and the groove wall of the groove 1151 enclose a working space for the driving gear 101 and the driven gear 102.

The bottom wall of the groove 1151 is provided with a second through hole 1152 matched with the crankshaft and a third through hole 1153 matched with the output shaft of the driven gear in the accessory box. The bottom wall of the inner cavity of the accessory box 10 is provided with a fifth through hole 103 matched with the crankshaft 21 and a sixth through hole 104 matched with the output shaft of the driven gear.

The driving gear 101 is in transmission connection with the crankshaft 21, the fuel pump 6 is fixed on the wall surface of the accessory box 10, which is back to the box body 11, an input shaft of the fuel pump 6 is fixedly connected with the crankshaft 21 through a spline, and the crankshaft 21 drives the fuel pump assembly to operate. The fuel inlets of the four cylinders 12 are each in communication with the fuel pump 6 via a fuel line. The box body 11 is provided with a low-pressure fuel pump and an oil pump, the low-pressure fuel pump is in transmission connection with one end of one driven gear 102, the output shaft of which extends into the box body 11, and the oil pump is in transmission connection with one end of the other driven gear 102, the output shaft of which extends into the box body 11.

The wall surface of the accessory box 10 facing away from the box body 11 is provided with two accessory interfaces 105 for the driven gear 102 to be in transmission connection with external equipment, and the two accessory interfaces are in one-to-one correspondence with the two driven gears 102.

The driving gear 101 rotates together with the crankshaft 21, and simultaneously drives the two driven gears 102 to rotate, thereby outputting power to the accessories. And the accessory interface 105 can be connected with an external component to output power to the accessory. One of the attachment interfaces 105 may be used as a pitch actuator interface and may be equipped with a hydraulic pitch controller. And the other one is used as a spare interface, the mounting size is designed according to the common interface of the parts, when no accessory is required to be mounted, the interface can be sealed by a cover plate and can be opened when required. The output ends driven by the two driven gears 102 are connected through a flat key to transmit power.

Oil passages are formed in the crankshaft 21, the crank, the connecting rod 24 and piston pins connecting the pistons 25 and the connecting rod 24, and the oil passages in the crankshaft 21, the crank, the connecting rod 24 and piston pins are communicated to form lubricating oil passages. The lubricating channel is circularly communicated with the oil pump through a pipeline.

Referring to fig. 1, under the action of the battery, the starting motor 8, the motor gear shaft extends out to mesh with the flywheel 55, the flywheel 55 is driven to rotate, the crankshaft 21 is driven to rotate, the connecting rod 24 on the crankshaft 21 pushes the piston 25 to reciprocate, the gas compression in the cylinder block 12 is overcome, until the temperature of the compressed air in the cylinder reaches the ignition and burning of the fuel, the starting motor 8 gear shaft retracts, and the starting motor 8 is disengaged from the flywheel 55.

When the crankshaft 21 rotates, the third belt wheel 53 is rotated, and the belt 54 on the third belt wheel 53 drives the supercharger 3, the generator 7, and the cooling water pump 9 to start rotating. The mechanical supercharger 3 is positioned above the engine and is connected with the turbocharger 4 in series, and the middle of the mechanical supercharger is connected with the turbocharger by a rubber hose. During the installation, can demolish rubber hose, increase the intercooler and cool off the air after the compression. The mechanical supercharger 3 and the third belt wheel 53 are accelerated through a certain transmission ratio, so that the mechanical supercharger 3 has certain supercharging scavenging capacity at the low speed of the engine, and compressed air is conveyed to a scavenging port of a cylinder body through the air inlet manifold 13. When the engine reaches a certain rotating speed, the air pressure compressed by the turbocharger 4 is large enough, a bypass valve in the mechanical supercharger 3 is directly opened, the mechanical supercharger 3 idles at the moment, the supercharging effect is not generated, and the engine is completely provided with air inlet pressure by the turbocharger 4. Meanwhile, when the engine flies in the air and the turbocharger 4 is damaged, the mechanical supercharger 3 can still maintain certain power to enable the aircraft to return.

The generator 7 is driven by the belt 54 to work, a certain transmission ratio exists between the third belt wheel 53 and the belt wheel of the generator 7, and the generator 7 starts to generate power continuously from the rotation of the crankshaft 21, so that the normal operation of equipment on the aircraft is ensured. The mounting bracket of the generator 7 is adjustable to tension the belt 54 at the appropriate time.

The cooling water pump 9 is driven by means of a belt 54, which is pressed during installation. The belt wheel on the cooling water pump 9 and the third belt wheel 53 have a certain transmission ratio, once the crankshaft 5 rotates, the cooling water pump 9 starts to work, the cooling liquid in the external water tank is continuously pumped into the engine, and the cooling liquid is discharged after circulation.

In the aviation piston engine of the embodiment, 4 air inlet manifolds are arranged on the base of the mechanical supercharger, and air flowing through the mechanical supercharger is conveyed to the scavenging port on the cylinder body. The cylinder bodies are horizontally arranged oppositely, and have no gas distribution phase structure, and the cylinder bodies are provided with scavenging holes, and the pistons are used for reciprocating operation to scavenge gas. The mechanical supercharger and the turbocharger are connected in series, the engine is matched with the mechanical supercharger and the turbocharger, the mechanical supercharger is directly driven by the engine at a low-speed section and is scavenged by supercharged gas, and the mechanical supercharger is driven by gas compressed by the turbocharger at a high-speed section. The redundant design ensures flight safety.

A crank link mechanism: a double-crank structure is used, two connecting rods are arranged on each crank, and the cranks have 3 supporting points. The same oil channel is arranged between the crank and the connecting rod, and the front end of the crank is provided with a propeller flange connecting surface which allows hydraulic oil to be used for driving the propeller pitch.

An accessory box: the crankshaft is used for driving the driving gear to rotate, so that the driven gear is driven to rotate, and connecting ports are formed in the two ends of the driven gear, so that different engine accessories are installed.

A fuel system: the fuel pump assembly is arranged at one end of an engine and is directly connected by a crankshaft spline. The fuel pump assembly is provided with a low-pressure oil pump and a high-pressure oil pump, and the low-pressure oil pump sucks fuel oil and then supplies the fuel oil to the high-pressure oil pump.

A cooling system: the whole engine is water-cooled, an independent lubricating oil channel is arranged in the engine body, and a cooling system is redundant and backup. The engine drives the water pump through belt transmission to cool the cylinder body and the cylinder head, and the cylinder body and the cylinder head are both provided with cooling liquid inlet channels so as to facilitate the rapid arrival of the cooling liquid. The engine body is internally provided with an independent lubricating oil channel, on one hand, the lubricating oil channel is conveyed to the interior of the crankshaft through pressure, and further, the lubricating oil channel is conveyed to the piston pin through the oil channel in the connecting rod, so that the key parts of the engine and the piston are subjected to oil cooling. Wherein, the oil nozzle is arranged in the engine body to forcibly cool the interior of the piston.

The above description is only for the preferred embodiment of the present application and should not be taken as limiting the present application in any way, and although the present application has been disclosed in the preferred embodiment, it is not intended to limit the present application, and those skilled in the art should understand that they can make various changes and modifications within the technical scope of the present application without departing from the scope of the present application, and therefore all the changes and modifications can be made within the technical scope of the present application.

Claims

1. An aviation piston engine is characterized by comprising an engine shell (1), a crank connecting rod mechanism (2), a mechanical supercharger (3), a turbocharger (4), a belt transmission mechanism (5), a fuel pump (6), a generator (7) and a starting motor (8);

the crank connecting rod mechanism (2) comprises a crankshaft (21) which is horizontally arranged, two cranks are fixed on the crankshaft (21), each crank comprises a crankshaft journal (22) which is parallel to the crankshaft (21), and two crank arms (23) which are connected between the crankshaft (21) and the crankshaft journals (22), and the two crank arms (23) are respectively arranged at two ends of the crankshaft journals (22); the axial center lines of the two crank journals (22) are respectively arranged on two sides of the axial center plane of the crank shaft (21), and the axial center lines of the crank shaft (21) and the two crank journals (22) are on the same plane; each crank neck (22) is rotatably provided with two connecting rods (24), the extending directions of the two connecting rods (24) on each crank neck (22) are opposite, the four connecting rods (24) are sequentially arranged along the axial direction of the crankshaft (21), and one end, far away from the crankshaft (21), of each connecting rod (24) is provided with a piston (25);

the engine shell (1) comprises a box body (11) which is mounted with a crankshaft (21) in a shaft-embracing mode, and four cylinder bodies (12) which are mounted on the box body (11) and communicated with the box body (11), wherein the four cylinder bodies (12) are all horizontally arranged, the four cylinder bodies (12) correspond to four connecting rods (24) one by one, and pistons (25) are slidably arranged in the corresponding cylinder bodies (12); the cylinder body (12) is provided with a first air sweeping port and an air exhaust port;

the mechanical supercharger (3) is arranged at the upper end of the box body (11), the turbocharger (4) is arranged on one side of the box body (11) along the axial direction of the crankshaft (21), and the generator (7) and the starting motor (8) are both arranged at one end, far away from the turbocharger (4), of the box body (11);

first air sweeping ports of the four cylinder bodies (12) are communicated with an air outlet end of the mechanical supercharger (3) through an air inlet manifold (13), an air outlet end of the turbocharger (4) is communicated with an air inlet end of the mechanical supercharger (3) through a hose, and air exhaust ports of the four cylinder bodies (12) are communicated with an air inlet end of the turbocharger (4) through a hose;

the fuel pump (6) is arranged between the box body (11) and the turbocharger (4), an input shaft of the fuel pump (6) is in transmission connection with the crankshaft (21), and the four cylinder bodies (12) are communicated with the fuel pump (6) through fuel pipes;

the belt transmission mechanism (5) comprises a first belt wheel (51) fixed on an input shaft of the mechanical supercharger (3), a second belt wheel (52) fixed on an input shaft of the generator (7), a third belt wheel (53) in transmission connection with the crankshaft (21), and a belt (54) running around the first belt wheel (51), the second belt wheel (52) and the third belt wheel (53);

the third belt wheel (53) is arranged on one side, far away from the turbocharger (4), of the box body (11), a flywheel (55) is fixed at one end, far away from the box body (11), of the third belt wheel (53), the starting motor (8) is provided with a telescopic gear shaft (81), and the gear shaft (81) can be meshed with the flywheel (55) for transmission when extending out.

2. The aviation piston engine according to claim 1, characterized in that a cooling water pump (9) is further mounted at one end of the box body (11) far away from the turbocharger (4), the cooling water pump (9) is positioned above the generator (7), a fourth belt wheel (91) is mounted on an input shaft of the cooling water pump (9), the outer circumference of the fourth belt wheel (91) is abutted with the belt (54) and applies radial thrust to the belt (54); and both ends of the cylinder body (12) in the axial direction are provided with cooling channels, and the cooling channels are circularly communicated with a cooling water pump (9) through pipelines.

3. The aviation piston engine of claim 1, wherein an end of the crankshaft (21) proximate to the third pulley (53) is provided with a propeller mounting flange (211), the propeller mounting flange (211) being provided outside the flywheel (55).

4. The aviation piston engine as recited in claim 1, characterized in that an accessory case (10) is mounted on the end face of the case (11) near one end of the turbocharger (4), a driving gear (101) and two driven gears (102) which are both in meshing transmission with the driving gear (101) are arranged in the accessory case (10), the driving gear (101) is in transmission connection with the crankshaft (21), the fuel pump (6) is fixed on the wall face of the accessory case (10) opposite to the case (11), and the input shaft of the fuel pump (6) is in key connection with the crankshaft (21); the low-pressure fuel pump and the oil pump are arranged in the box body (11), the low-pressure fuel pump is in transmission connection with one driven gear (102), and the oil pump is in transmission connection with the other driven gear (102).

5. The aviation piston engine according to claim 4, characterized in that the wall surface of the accessory box (10) facing away from the box body (11) is provided with two accessory interfaces for the transmission connection of the driven gear (102) and external equipment, and the two accessory interfaces correspond to the two driven gears (102) one by one.

6. The aviation piston engine as claimed in claim 4, wherein the crank-link mechanism (2) is provided with a lubrication channel, and the lubrication channel is in circulating communication with the oil pump through a pipeline.

7. The aviation piston engine according to claim 6, characterized in that oil passages are formed in the crankshaft (21), the crank, the connecting rod (24) and the piston pin connecting the piston (25) and the connecting rod (24), and the oil passages in the crankshaft (21), the crank, the connecting rod (24) and the piston pin are communicated to form the lubricating oil passage.

8. An aircraft piston engine according to any of claims 1 to 7, characterised in that the internal walls of the housing (11) are fitted with oil jets (14) for cooling the pistons (25), the oil jets (14) being provided in four, four jets (14) being in one-to-one correspondence with four pistons (25).

9. An aviation piston engine according to any one of claims 1 to 7, wherein the crankshaft (21) is fixedly connected with counterweights (26) corresponding to the crank arms (23) one by one, and the crank arms (23) and the corresponding counterweights (26) are respectively arranged at two ends of the crankshaft (21) in the radial direction.

10. An aircraft piston engine according to any of claims 1 to 7, characterised in that the generator (7) is detachably mounted to the engine housing (1) by means of a generator mounting bracket assembly, the generator (7) being rotatable relative to the engine housing (1) to tension the belt (54).