CN217681984U - Low-power-level aviation piston engine - Google Patents
Low-power-level aviation piston engine Download PDFInfo
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- CN217681984U CN217681984U CN202221787950.XU CN202221787950U CN217681984U CN 217681984 U CN217681984 U CN 217681984U CN 202221787950 U CN202221787950 U CN 202221787950U CN 217681984 U CN217681984 U CN 217681984U
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Abstract
The utility model provides a small power level aviation piston engine, including engine cartridge receiver casing, the cartridge receiver casing is curved surface transition structure, is provided with the crankshaft slot on it and is used for installing the bent axle, installs gear drive's starter motor, gear drive's alternator and two gear drive's magnetors in the cartridge receiver casing, the bent axle is connected with the starter motor gear through the bent axle tooth, be fixed with four cranks on the bent axle, install the connecting rod on each crank, the one end of each connecting rod keeping away from the bent axle is installed the piston, piston one end stretches into engine cylinder; the casing is also provided with a camshaft groove for installing a camshaft, the camshaft controls the opening and closing of the valve through a hydraulic tappet, a mandril and a rocker arm, and the piston engine has compact structure, high power-weight ratio and good reliability and can supply oil for all moving surfaces for lubrication.
Description
Technical Field
The utility model relates to the technical field of engines, especially, relate to an aviation heavy oil piston engine.
Background
The piston aeroengine is a reciprocating internal combustion engine for providing flight power for aircrafts (airplanes, helicopters, air boats and the like), the currently used compression ignition type heavy oil aeroengine is basically a four-stroke engine, compared with gasoline, heavy oil has the characteristics of large viscosity and high flash point, the transportation and storage are safe and reliable, and the piston aeroengine is universal for oil plants in military fields such as aviation, shipborne and the like, and can simplify and guarantee. However, heavy oil has high viscosity and poor flow property, atomization and evaporation effects are poor at low temperature, and the requirement of light weight of an aero-engine is considered, so that the cooling of the four-stroke engine is mostly carried out by air cooling, and the complex design of an internal cavity of the engine is reduced. The proper power and power-weight ratio is important, two-stroke piston engines mostly adopt a carburetor oil supply mode, and the reliable atomization and reasonable combustion of heavy oil are difficult to guarantee by directly adopting the existing carburetor. Therefore, the two-stroke engine adopts crankcase air intake, lubricating oil is mixed into fuel oil to lubricate and exchange the engine, the structures of scavenging, lubricating, cooling and the like are complex, the power-weight ratio is high, but the two-stroke engine is only limited to a low-power gasoline aircraft engine.
SUMMERY OF THE UTILITY MODEL
The to-be-solved technical problem of the utility model is to overcome the not enough of prior art, provide a compact structure, the power-weight ratio is high, the good reliability, can be for the lubricated piston engine of all motion face fuel feeding.
In order to solve the technical problem, the utility model discloses a following technical scheme: a low-power-grade aviation piston engine comprises an engine case shell, a piston, a cylinder barrel and a cylinder head, wherein the case shell is of a curved surface transition structure, a crankshaft groove is formed in the case shell and used for mounting a crankshaft, a gear-driven starting motor, a gear-driven alternating-current generator and two gear-driven magnetors are mounted in the case shell, the crankshaft is connected with a starting motor gear through a crankshaft tooth, four cranks are fixed on the crankshaft, a connecting rod is mounted on each crank, a piston is mounted at one end, away from the crankshaft, of each connecting rod, the piston, the cylinder barrel and the cylinder head jointly form a combustion chamber of the engine, one end of each piston extends into an engine cylinder, and the engine cylinder is provided with four air cooling cylinders which are horizontally arranged in an opposite mode; the casing body is further provided with a camshaft groove for installing a camshaft, the camshaft is connected with a hydraulic tappet, one end of the hydraulic tappet is connected with a push rod, the push rod is connected with a rocker arm, the rocker arm is connected with an air valve, and the camshaft controls the air valve to open and close through the hydraulic tappet, the push rod and the rocker arm.
A crankshaft groove oil outlet is also formed in the crankshaft groove, and hydraulic pressure in the oil way enters the joint of the crankshaft and the casing from the crankshaft groove oil outlet; and a camshaft groove oil outlet is formed in the camshaft groove, and hydraulic pressure in an oil path enters the joint of the camshaft and the casing from the camshaft groove oil outlet.
A hydraulic tappet hole is formed in the casing body and used for installing a hydraulic tappet, a hydraulic tappet oil outlet hole is formed in the hydraulic tappet hole, and hydraulic pressure in an oil path enters the joint of the hydraulic tappet and the casing body from the hydraulic tappet oil outlet hole; the crankshaft groove is characterized in that a cylinder hole is formed in the lower side of the axis of the crankshaft groove and used for installing a cylinder, a hydraulic tappet hole and a camshaft groove are formed in the upper side of the axis of the crankshaft groove, and the crankshaft groove, the camshaft groove and the hydraulic tappet hole are connected in a curved surface transition mode.
The engine case shell is divided into a left case body and a right case body.
The left box body and the right box body are symmetrically arranged to form four horizontally-opposite cylinder holes, and four horizontally-opposite air cooling cylinders are arranged.
The cylinder comprises a cylinder head, a cylinder barrel, a connecting flange, a guide inner wall and a cylinder stabilizing wall, wherein the cylinder barrel is provided with radiating fins at the periphery, the upper part of the cylinder barrel is provided with connecting threads, the lower part of the cylinder barrel is provided with the connecting flange, the inner diameter of the upper part of the cylinder barrel is smaller than that of the lower part of the cylinder barrel, the guide inner wall is used for limiting the movement of a piston, and the cylinder stabilizing wall is used for stabilizing the movement of the cylinder head.
The cooling fin is wound around the cylinder head and is of a fin structure, an air inlet and an air outlet are arranged above the cooling fin, the air inlet is connected with an air inlet pipe of an engine, and the air outlet is connected with an exhaust pipe of the engine; the upper part of the cylinder head is provided with a group of valve holes which are respectively communicated with an air inlet and an air outlet; the upper portion of the cylinder head main body is further provided with a rocker arm support, a connecting flange is further arranged around the rocker arm support, and a group of ejector rod holes are formed in the connecting flange.
The utility model discloses piston engine provides initial power for the bent axle through starter motor, drives the camshaft rotation through the gear after the bent axle is rotatory, and the camshaft controls the valve through hydraulic tappet, ejector pin, rocking arm and opens and shuts. Meanwhile, the crankshaft drives the piston to reciprocate in the cylinder through the connecting rod. The cylinder then powers the piston through an intake stroke, a compression stroke, a power stroke, and an exhaust stroke. The engine has the compression ratio of 8.5 and the piston displacement of 3.29L, and has the advantages of compact structure, reduced installation size of the engine and high power-weight ratio. In order to reduce the friction force when the moving parts such as the crankshaft, the camshaft and the rocker arm are matched with other parts as much as possible, the engine is provided with a hydraulic pump and is matched with a corresponding oil circuit to supply oil for lubricating all moving surfaces.
Drawings
FIG. 1 is a schematic view of the structure of a low power grade aviation piston engine of the present invention;
FIG. 2 is a schematic structural view of the crankshaft connecting rod mechanism of the present invention;
fig. 3 is a schematic structural view of the left and right casings of the aviation piston engine (symmetrical structure on the left and right sides);
FIG. 4 is a schematic view of the piston structure of the present invention;
FIG. 5 is a schematic view of the cylinder structure of the present invention;
fig. 6 is a schematic view of the cylinder head structure of the present invention;
FIG. 7 is a view of the structure of the hydraulic tappet assembly of the present invention;
FIG. 8 is a view of the motor assembly structure of the present invention;
FIG. 9 is a distribution diagram of the cylinder of the present invention;
fig. 10 is a cross-sectional view of the cylinder head of the present invention;
in the figure: the engine comprises an engine case shell-1, a piston-2, a cylinder barrel-3, a cylinder head-4, a crank groove-5, a crank shaft-6, a starting motor gear-7, an alternator gear-8, a magneto gear-9, a crank-10, a connecting rod-11, a camshaft groove-12, a camshaft-13, a hydraulic tappet-14, a mandril-15, a rocker arm-16, a valve-17, a crank groove oil outlet-18, a camshaft groove oil outlet-19, a hydraulic tappet hole-20, a cylinder hole-21, a cylinder barrel cylindrical body-22, a radiating fin-23, a connecting thread-24, a connecting flange-25, a cylinder head main body-26, an air inlet-27, an air outlet-28, a valve hole-29 and an engine-30.
Detailed Description
In order to facilitate understanding of the present invention, the present invention will be described more fully hereinafter with reference to the accompanying drawings. Preferred embodiments of the present invention are shown in the drawings. The invention may, however, be embodied in many different forms and should not be construed as limited to the embodiments set forth herein. Rather, these embodiments are provided so that this disclosure will be thorough and complete.
As shown in fig. 1-8, a low-power grade aviation piston engine includes an engine casing 1, a piston 2, a cylinder barrel 3, and a cylinder head 4, where the casing is of a curved transition structure, and is provided with a crankshaft slot 5 for mounting a crankshaft 6, a gear-driven starter motor, a gear-driven alternator, and two gear-driven magnetors (shown in the figure as a starter motor gear 7, an alternator gear 8, and a magnetor gear 9) are mounted in the casing, the crankshaft is connected with the starter motor gear through a crankshaft tooth, four cranks 10 are fixed on the crankshaft 6, a connecting rod 11 is mounted on each crank, one end of each connecting rod, which is far away from the crankshaft, is provided with the piston 2, the piston, the cylinder barrel, and the cylinder head jointly form a combustion chamber of the engine, one end of the piston extends into an engine cylinder, and the engine cylinder has four air-cooled cylinders arranged in a horizontal opposition; the casing body is further provided with a camshaft groove 12 for mounting a camshaft 13, the camshaft 13 is connected with a hydraulic tappet 14, one end of the hydraulic tappet 14 is connected with a mandril 15, the mandril 15 is connected with a rocker arm 16, the rocker arm is connected with a valve 17, and the camshaft controls the valve to open and close through the hydraulic tappet, the mandril and the rocker arm.
A crankshaft groove oil outlet 18 is also formed in the crankshaft groove 5, and hydraulic pressure in an oil way enters the joint of the crankshaft and the casing body from the crankshaft groove oil outlet; and a camshaft groove oil outlet 19 is formed in the camshaft groove 12, and hydraulic pressure in an oil path enters the joint of the camshaft and the casing from the camshaft groove oil outlet.
A hydraulic tappet hole 20 is formed in the casing body and used for mounting a hydraulic tappet, a hydraulic tappet oil outlet hole is formed in the hydraulic tappet hole, and hydraulic pressure in an oil path enters the joint of the hydraulic tappet and the casing body from the hydraulic tappet oil outlet hole; the crankshaft groove is characterized in that a cylinder hole 21 is further formed in the lower side of the axis of the crankshaft groove and used for installing a cylinder, a hydraulic tappet hole and a camshaft groove are formed in the upper side of the axis of the crankshaft groove, and the crankshaft groove, the camshaft groove and the hydraulic tappet hole are connected in a curved surface transition mode.
The engine case shell is divided into a left case body and a right case body, through the design of connection of oil holes and oil paths in a crankshaft groove, a camshaft groove and a hydraulic tappet hole, lubrication and cooling are provided for parts at all moving positions in an engine, and the connection among the crankshaft groove, the camshaft groove and the hydraulic tappet hole forms a base through curved surface transition connection, so that the base is provided for all the parts of the engine, the design structure is simplified, and the weight of the case is reduced.
The left box body and the right box body are symmetrically arranged to form four horizontally-opposite cylinder holes, and four horizontally-opposite air cooling cylinders are arranged.
The cylinder head comprises a cylindrical body 22 of the cylinder barrel, and is characterized in that heat radiating fins 23 are arranged around the cylindrical body 22 of the cylinder barrel, connecting threads 24 are arranged on the upper portion of the cylindrical body of the cylinder barrel, a connecting flange 25 is arranged on the lower portion of the cylindrical body of the cylinder barrel, the inner diameter of the upper portion of the cylindrical body of the cylinder barrel is smaller than that of the lower portion of the cylindrical body of the cylinder barrel, the cylinder head further comprises a guide inner wall and a cylinder stabilizing wall, the guide inner wall is used for limiting the movement of a piston, and the cylinder stabilizing wall is used for stabilizing the movement of a cylinder head.
As shown in fig. 10, cooling fins are wound around the cylinder head main body 26, the cooling fins are of a fin structure, an air inlet 27 and an air outlet 28 are arranged above the cooling fins, the air inlet is connected with an engine air inlet pipe, and the air outlet is connected with an engine exhaust pipe; the upper part of the cylinder head main body is provided with a group of valve holes 29 which are respectively communicated with an air inlet and an exhaust port; the hydraulic tappet is characterized in that a rocker arm support (a connecting rocker arm 16) is further arranged on the upper portion of the cylinder head main body, a connecting flange is further arranged around the rocker arm support, a group of ejector rod holes are formed in the connecting flange, when the engine works, the hydraulic tappet forms a rigid structure, a transmission chain gap caused by abrasion can be eliminated in real time, information of a camshaft is transmitted, the hydraulic tappet engine does not work, and the hydraulic tappet is in an elastic state at the moment (without lubricating oil pressure).
The camshaft is connected with the crankshaft through a gear to obtain power, and the strokes of the four cylinders are sequentially controlled.
As shown in fig. 9, the engine 30 has four horizontally opposed air-cooled cylinders, two on the left side and two on the right side. During the intake stroke, aviation fuel and air are drawn into the cylinder and after the gasoline and air mixture is ignited, the expanding gases cause the piston to move inward in a power stroke, eventually performing an exhaust stroke.
The utility model discloses piston engine provides initial power for the bent axle through starter motor, drives the camshaft rotation through the gear after the bent axle is rotatory, and the valve is controlled through hydraulic tappet, ejector pin, rocking arm to the camshaft and opens and shuts. Meanwhile, the crankshaft drives the piston to reciprocate in the cylinder through the connecting rod. The cylinder then powers the piston through an intake stroke, a compression stroke, a power stroke, and an exhaust stroke. The engine has the compression ratio of 8.5 and the piston displacement of 3.29L, and has the advantages of compact structure, reduced installation size of the engine and high power-weight ratio. In order to reduce the friction force when the moving parts such as the crankshaft, the camshaft and the rocker arm are matched with other parts as much as possible, the engine is provided with a hydraulic pump and is matched with a corresponding oil circuit to supply oil for lubricating all moving surfaces.
Claims (7)
1. A low-power-level aviation piston engine comprises an engine casing, a piston, a cylinder barrel and a cylinder head, and is characterized in that the casing is of a curved surface transition structure, a crankshaft groove is formed in the casing and used for mounting a crankshaft, a gear-driven starting motor, a gear-driven alternating-current generator and two gear-driven magnetors are mounted in the casing, the crankshaft is connected with a starting motor gear through a crankshaft tooth, four cranks are fixed on the crankshaft, a connecting rod is mounted on each crank, one end, far away from the crankshaft, of each connecting rod is provided with the piston, the cylinder barrel and the cylinder head jointly form a combustion chamber of the engine, one end of the piston extends into an engine cylinder, and the engine cylinder is provided with four air-cooled cylinders which are horizontally arranged in an opposite mode; the casing is characterized in that the casing body is further provided with a camshaft groove for mounting a camshaft, the camshaft is connected with a hydraulic tappet, one end of the hydraulic tappet is connected with a push rod, the push rod is connected with a rocker arm, the rocker arm is connected with a valve, and the camshaft controls the valve to open and close through the hydraulic tappet, the push rod and the rocker arm.
2. The small power class aviation piston engine of claim 1, wherein said crankshaft slot is further provided with a crankshaft slot oil outlet, and the hydraulic pressure in the oil path enters the connection between the crankshaft and the casing from the crankshaft slot oil outlet; and a camshaft groove oil outlet is formed in the camshaft groove, and hydraulic pressure in an oil path enters the joint of the camshaft and the casing from the camshaft groove oil outlet.
3. The low-power grade aviation piston engine according to claim 1, wherein a hydraulic tappet hole is further formed in the casing body for mounting a hydraulic tappet, a hydraulic tappet oil outlet hole is further formed in the hydraulic tappet hole, and hydraulic pressure in an oil path enters a joint of the hydraulic tappet and the casing body from the hydraulic tappet oil outlet hole; the crankshaft groove is characterized in that a cylinder hole is further formed in the lower side of the axis of the crankshaft groove and used for installing a cylinder, a hydraulic tappet hole and a camshaft groove are formed in the upper side of the axis of the crankshaft groove, and the crankshaft groove, the camshaft groove and the hydraulic tappet hole are connected in a curved surface transition mode.
4. A low power grade aviation piston engine in accordance with claim 1, wherein said engine case housing is divided into a left case and a right case.
5. A low power class aviation piston engine in accordance with claim 4, wherein said left and right pockets are symmetrically mounted to define four horizontally opposed cylinder bores and four horizontally opposed air cooled cylinders are mounted.
6. The small power class aviation piston engine as claimed in claim 1, wherein the cylinder barrel is provided with fins around it, the upper part of the cylinder barrel is provided with connecting threads, the lower part of the cylinder barrel is provided with a connecting flange, the inner diameter of the upper part of the cylinder barrel is smaller than that of the lower part, the engine further comprises a guiding inner wall and a cylinder stabilizing wall, the guiding inner wall is used for limiting the movement of the piston, and the cylinder stabilizing wall is used for stabilizing the movement of the cylinder head.
7. The small power grade aviation piston engine as claimed in claim 1, wherein a heat sink is wound around the cylinder head, the heat sink is of a fin structure, an air inlet and an air outlet are arranged above the heat sink, the air inlet is connected with an engine air inlet pipe, and the air outlet is connected with an engine air outlet pipe; the upper part of the cylinder head is provided with a group of valve holes which are respectively communicated with an air inlet and an air outlet; the upper portion of the cylinder head is further provided with a rocker arm support, a connecting flange is further arranged around the rocker arm support, and a group of ejector rod holes are formed in the connecting flange.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202221787950.XU CN217681984U (en) | 2022-07-12 | 2022-07-12 | Low-power-level aviation piston engine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202221787950.XU CN217681984U (en) | 2022-07-12 | 2022-07-12 | Low-power-level aviation piston engine |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN217681984U true CN217681984U (en) | 2022-10-28 |
Family
ID=83715173
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202221787950.XU Active CN217681984U (en) | 2022-07-12 | 2022-07-12 | Low-power-level aviation piston engine |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN217681984U (en) |
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2022
- 2022-07-12 CN CN202221787950.XU patent/CN217681984U/en active Active
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