CN211343091U

CN211343091U - Aviation piston internal combustion engine

Info

Publication number: CN211343091U
Application number: CN201922433612.0U
Authority: CN
Inventors: 皮礼平; 吴玉平; 黄友; 钟贤; 刘宇航
Original assignee: Chongqing Zongshen Aircraft Engine Manufacturing Co ltd
Current assignee: Chongqing Zongshen Aviation Engine Manufacturing Co.,Ltd.
Priority date: 2019-12-30
Filing date: 2019-12-30
Publication date: 2020-08-25
Anticipated expiration: 2029-12-30

Abstract

The utility model discloses an aviation piston internal-combustion engine, including many sets of cylinder heads and cylinder body and cooling system, its characterized in that: the cooling system comprises a plurality of cooling water channels which are connected in parallel, each cooling water channel comprises a cylinder body water jacket and a cylinder head water jacket, each cylinder body water channel comprises a water inlet, a water outlet of each cylinder body water jacket is connected with a water inlet of the cylinder head water jacket matched with the cylinder body water jacket, and each cylinder head water channel is provided with a water outlet. Adopt the utility model discloses a high-power aviation piston internal-combustion engine can improve the reliability of engine.

Description

Aviation piston internal combustion engine

Technical Field

The utility model relates to an aeroengine field especially relates to an aeropiston engine.

Background

At present, an aviation piston internal combustion engine generally adopts an engine with a plurality of cylinder bodies. In contrast, the cooling method of the cylinder head and cylinder block of the conventional multi-cylinder engine generally includes: air-cooled cylinder body and water-cooled cylinder head. The plurality of cylinder bodies are used for radiating in a series mode, namely the plurality of cylinder bodies are only provided with one cooling water inlet, and cooling water flows into the cylinder body cooling water channel through the inlet and then flows out of one cooling water outlet after flowing through all the cylinder bodies.

The existing cooling mode of the aircraft engine has the following defects: 1. the cooling air is required to be introduced separately to cool the cylinder head, and the burden of an aircraft engine, particularly an engine of an unmanned aerial vehicle aircraft, is increased. 2. The cooling effect of each cylinder is not uniform. 3. The cooling modes and heat exchange coefficients of the cylinder body and the cylinder head are different, so that the temperature difference between the cylinder body and the cylinder head is large, the difference of thermal expansion coefficients is large, and the reliability of an engine is insufficient.

In addition, the existing engine oil cooler is a pipe-belt type oil cooler, and lubricating oil in the oil cooler is cooled by blowing external air through a heat dissipation belt. When the environment temperature is too low in high altitude, the lubricating oil temperature is also low, and the lubricating oil flow is reduced, resulting in poor lubrication of the engine.

SUMMERY OF THE UTILITY MODEL

An object of the utility model is to provide a good and even aviation piston internal-combustion engine of cooling effect.

In order to achieve the above object, the present invention is realized as follows: an aviation piston internal combustion engine comprises a plurality of sets of cylinder heads, cylinder bodies and cooling systems, and is characterized in that: the cooling system comprises a plurality of cooling water channels which are connected in parallel, each cooling water channel comprises a cylinder body water jacket and a cylinder head water jacket, each cylinder body water channel comprises a water inlet, a water outlet of each cylinder body water jacket is connected with a water inlet of the cylinder head water jacket matched with the cylinder body water jacket, and each cylinder head water channel is provided with a water outlet. By adopting the arrangement mode, the water-cooling mode can be adopted for the cylinder head and the cylinder body of the engine at the same time, and each set of cylinder head and cylinder body is cooled in a parallel connection mode. Therefore, the temperature of the cylinder head and the cylinder body can be ensured to be equivalent, and the expansion coefficient is equivalent; and the cooling effect of each set of cylinder head cylinder body is uniform, and the reliability of the engine is improved.

For further improving the lubricated effect of engine, the utility model discloses an internal-combustion engine includes the oil cooler, the oil cooler is including the oil cooler body that has oil pocket and water cavity, be provided with the coolant chamber on the oil cooler body, the coolant chamber includes and separates into intake chamber and play hydroecium by foraminiferous baffle, be provided with the inlet opening with cylinder head water jacket delivery port one-to-one on the intake chamber, each cylinder head water jacket's delivery port passes through the pipe connection with the inlet opening of intake chamber respectively, be provided with the apopore on the play hydroecium, just intake chamber and play hydroecium respectively with the water cavity of oil cooler body communicates with each other.

Furthermore, the top of the cooling water chamber is also provided with an air collecting chamber, an air hole is arranged between the air collecting chamber and the cooling water chamber, and the air collecting chamber is provided with a vent valve.

Preferably, each cylinder head water jacket is provided with a pipeline connected with a temperature sensor.

Preferably, the cylinder head and the cylinder body are four sets.

To further provide the horsepower of an aircraft engine, the cylinder block has a bore diameter of 86 mm.

Has the advantages that:

1. the utility model discloses an internal-combustion engine cylinder bore diameter increases to 86mm, increases the engine performance to 145 horsepower.

2. The utility model discloses adopt water-cooling mode to the cylinder head and the cylinder body of internal-combustion engine simultaneously to each set of cylinder head cylinder body adopts parallel mode to cool off. The temperature of the cylinder head and the cylinder body can be ensured to be equivalent, and the expansion coefficient is equivalent; and the cooling effect of each set of cylinder head cylinder body is uniform, and the reliability of the internal combustion engine is improved. Reduce the wind scooper device.

3. The utility model discloses a lubricating oil temperature adopts the coolant liquid cooling control by the internal-combustion engine cylinder head outflow, and on the internal-combustion engine was installed to the integration, install top (4 cylinder head delivery port departments), carry out the heat exchange through coolant liquid temperature and lubricating oil, control the lubricating oil temperature, the problem of lubricating oil supercooling in the slow, high altitude that the lubricating oil temperature rises when solving the start-up.

4. Just the utility model discloses an internal-combustion engine can match high performance booster, turbocharging controller. Is more suitable for larger and heavier aircrafts.

Drawings

FIG. 1 is a front view of an internal combustion engine in an embodiment;

FIG. 2 is a structural view of a cylinder head and a cylinder body in the embodiment;

FIG. 3 is an isometric view of the cylinder head water jacket and cylinder block water channel of the embodiment;

FIG. 4 is a front view of a head water jacket and a block water jacket in the embodiment;

FIG. 5 is an isometric view of an oil cooler of the embodiment;

FIG. 6 is a front sectional view of an oil cooler in the embodiment.

Detailed Description

The following detailed description of the embodiments of the present invention will be made with reference to the accompanying drawings, but the present invention is not limited to these embodiments, and any modifications or replacements within the basic spirit of the embodiments still fall within the scope of the present invention claimed in the claims.

Example (b): as shown in fig. 1-6, the present embodiment provides an internal combustion engine for an aircraft, and in particular, a high power internal combustion engine suitable for use in large, heavy aircraft.

The internal combustion engine in this embodiment adopts four sets of cylinder head cylinder bodies, and cylinder head 2 and cylinder body 1 in this embodiment all adopt water-cooling's cooling system, cooling system includes many parallelly connected cooling water course, specifically: each cooling water channel comprises a cylinder body water jacket 10 and a cylinder head water jacket 20, each cylinder body water channel 10 comprises a water inlet A11, a water outlet A12 of each cylinder body water jacket is connected with a water inlet B21 of the cylinder head water jacket 20 matched with the cylinder body water jacket, and each cylinder head water channel is provided with a water outlet B22. And each cylinder head water jacket is provided with a pipeline 3 connected with a temperature sensor.

In addition, the internal-combustion engine of this embodiment still includes oil cooler 4, oil cooler is including the oil cooler body 41 that has oil pocket and water cavity, be provided with the cooling water room 42 on the oil cooler body, the cooling water room includes and is separated into intake chamber 44 and play hydroecium 45 by foraminiferous baffle 43, be provided with four inlet openings 46 with cylinder head water jacket delivery port one-to-one on the intake chamber, the delivery port of each cylinder head water jacket passes through inlet channel 47 with the inlet opening of intake chamber respectively and is connected, be provided with the apopore on the play hydroecium, the apopore is connected with outlet channel 48. And the water inlet chamber and the water outlet chamber are respectively communicated with the water cavity of the oil cooler body. The oil chamber of the oil cooler body is connected with an oil inlet pipeline 51 and an oil outlet pipeline 52 respectively.

The oil cooler body in this embodiment is a continuous arrangement of a layer of oil cavities 55 and a layer of water cavities 56 at intervals, wherein the oil cavities are communicated with each other, and the water cavities are communicated with each other. For example, the oil cooler body disclosed in chinese patent CN208950661U described in the background of the present invention can be used.

In another embodiment of this embodiment, a gas collection chamber 53 is further disposed at the top of the cooling water chamber, a gas hole is disposed between the gas collection chamber and the cooling water chamber, and a vent valve 54 is disposed at the top of the gas collection chamber. The uncapping pressure of the vent valve is 1.3 bar. The gas collection chamber is equivalent to an expansion pot, and the vent valve is equivalent to an expansion pot cover. The surplus gas in the cooling water can be discharged.

In another embodiment of the present embodiment, the cylinder diameter of the cylinder in the present embodiment is 86 mm.

With the internal combustion engine of the present embodiment, the cylinder bore diameter was increased to 86mm, increasing the engine performance to 145 horsepower. The horsepower and the displacement are improved, so that the internal combustion engine of the embodiment can be matched with a high-performance supercharger and a turbocharging controller. Is more suitable for larger and heavier aircrafts.

In addition, the cylinder head and the cylinder body of the embodiment both adopt a water cooling mode, and each set of cylinder head and cylinder body adopts a parallel connection mode for cooling. The temperature of the cylinder head and the cylinder body can be ensured to be equivalent, and the expansion coefficient is equivalent; and the cooling effect of each set of cylinder head cylinder body is uniform, and the reliability of the engine is improved. Reduce the wind scooper device.

The lubricating oil temperature of this embodiment adopts the coolant cooling control that flows out by the engine cylinder head, and the integration is installed on the engine, installs top (4 cylinder head delivery port departments), carries out the heat exchange through coolant temperature and lubricating oil, controls the lubricating oil temperature, solves the slow, the supercooling problem of lubricating oil in the high altitude of lubricating oil temperature rise when starting. Air is mixed in the cooling liquid, the cooling effect of the engine can be influenced, and redundant air can flow to the overflow bottle through the vent hole through the air collection chamber and the vent valve in the embodiment so as to be communicated to the atmosphere; when the internal combustion engine stops, the pressure in the gas collection chamber is reduced along with the reduction of the temperature of the cooling liquid, when the gas in the gas collection chamber is lower than the environmental pressure, the water replenishing valve of the expansion pot cover is opened, and the cooling liquid in the overflow bottle is replenished to the cooling system through the water replenishing valve.

Claims

1. An aviation piston internal combustion engine comprises a plurality of sets of cylinder heads, cylinder bodies and cooling systems, and is characterized in that: the cooling system comprises a plurality of cooling water channels which are connected in parallel, each cooling water channel comprises a cylinder body water jacket and a cylinder head water jacket, each cylinder body water channel comprises a water inlet, a water outlet of each cylinder body water jacket is connected with a water inlet of the cylinder head water jacket matched with the cylinder body water jacket, and each cylinder head water channel is provided with a water outlet.

2. An aviation piston internal combustion engine as in claim 1 wherein: the oil cooler comprises an oil cooler body with an oil cavity and a water cavity, wherein a cooling water chamber is arranged on the oil cooler body, the cooling water chamber comprises a water inlet chamber and a water outlet chamber which are separated by a partition plate with holes, water inlet holes in one-to-one correspondence with water outlets of cylinder head water jackets are formed in the water inlet chamber, the water outlets of each cylinder head water jacket are connected with the water inlet holes of the water inlet chamber through pipelines respectively, water outlet holes are formed in the water outlet chamber, and the water inlet chamber and the water outlet chamber are communicated with the water cavity of the oil cooler body respectively.

3. An aviation piston internal combustion engine as in claim 2 wherein: the top of the cooling water chamber is also provided with an air collecting chamber, an air hole is arranged between the air collecting chamber and the cooling water chamber, and the air collecting chamber is provided with a vent valve.

4. An aviation piston internal combustion engine as in claim 1, 2 or 3 wherein: each cylinder head water jacket is respectively connected with a temperature sensor.

5. An aviation piston internal combustion engine as in claim 4 wherein: the cylinder head and the cylinder body are four sets.

6. An aviation piston internal combustion engine as in claim 5 wherein: the cylinder diameter of the cylinder body is 86 mm.