Aviation kerosene self-preheating type rotor engine cooling structure

Abstract

The aviation kerosene self-preheating type rotor engine cooling structure comprises a rear end cover, an air cylinder body and a front end cover, the rear end cover and the front end cover are arranged on the two sides of the air cylinder body respectively, the air cylinder body is provided with an air cylinder body, a cooling oil channel is formed in an interlayer of the inner wall of the air cylinder body, and the cooling oil channel is arranged in a hot arc area of the air cylinder body. The hot arc area of the cylinder block body is in an arc shape, an oil inlet and an oil outlet are formed in the two ends of the cooling oil channel respectively, the oil inlet is communicated with a fuel tank through a first oil pipe, and the oil outlet is communicated with a fuel pump through a second oil pipe. Serious quality problems of sealing failure, cylinder score and the like caused by overhigh thermal load and large temperature difference between a hot arc region and a cold arc region of the air-cooled rotor engine are effectively solved, and the service life of the air-cooled rotor engine is prolonged.

Description

Technical Field

[0001] The invention belongs to the technical field of rotary engines, and in particular relates to an aviation kerosene self-preheating type rotary engine cooling structure. Background Art

[0002] The rotary engine has the advantages of simple structure, light weight, small size and high power. It is an ideal power source for aircraft such as drones and cruise missiles. However, due to the high heat generated by air-cooled rotary engines, high combustion chamber temperature, and large temperature difference between the cold arc zone and the hot arc zone, serious faults such as cylinder pulling, sealing spring failure, and sealing system failure will occur, which greatly reduces the service life and safety of air-cooled rotary engines. Although water-cooled rotary engines can solve the heat load problem, they require additional parts such as water pumps, water tanks, cooling water, etc., which greatly increases the weight of the entire machine and is not suitable for use on aircraft such as drones and cruise missiles. At the same time, domestic rotary engine fuels are all gasoline or ethanol, and there is also a problem of poor fuel safety. Summary of the invention

[0003] In order to solve the problems in the prior art, the present invention proposes a cooling structure for an aviation kerosene self-preheating rotary engine.

[0004] The purpose of the present invention and the technical problem to be solved are achieved by adopting the following technical scheme. According to the cooling structure of an aviation kerosene self-preheating rotary engine proposed by the present invention, the cooling structure includes a rear end cover, a cylinder block and a front end cover. The rear end cover and the front end cover are respectively arranged on both sides of the cylinder block. The cylinder block has a cylinder body. A cooling oil channel is arranged in the inner wall interlayer of the cylinder body. The cooling oil channel is arranged in the hot arc zone of the cylinder body. The hot arc zone of the cylinder body is in an arc shape. An oil inlet and an oil outlet are respectively arranged at both ends of the cooling oil channel. The oil inlet is connected to the fuel tank through a first oil pipe, and the oil outlet is connected to the engine intake system through a second oil pipe. A fuel pump is arranged on one of the first oil pipe and the second oil pipe.

[0005] According to the above technical scheme, the normal temperature aviation kerosene in the fuel tank is continuously replenished to the hot arc zone of the cylinder body, and this cycle is continuously continued. The aviation kerosene is used to take away the heat from the hot arc zone of the engine, and the aviation kerosene is preheated at the same time, thereby solving the problems of high temperature in the hot arc zone of the rotary engine and large temperature difference between the hot arc zone and the cold arc zone. At the same time, the aviation kerosene is preheated, which effectively improves the atomization effect of the aviation kerosene, so that the rotary engine can fully ignite the aviation kerosene.

[0006] Furthermore, a plurality of fins for heat dissipation are provided on the outer wall of the hot arc zone of the cylinder body, the fins are distributed in a circle, and the length of the fins gradually increases from the air inlet to the exhaust port, and a plurality of heat dissipation fins are provided on the outer walls of the rear end cover and the front end cover at intervals, and the number of fins and the spacing distance of the fins correspond to the heat dissipation fins.

[0007] According to the above technical scheme, it is beneficial to increase the cooling wind speed, further reduce the temperature difference of the entire hot arc zone and the temperature difference between the hot arc zone and the cold arc zone, and effectively solve the serious quality problems of the air-cooled rotary engine caused by excessively high temperature in the hot arc zone and excessive temperature difference between the hot arc zone and the cold arc zone, such as cylinder pulling, failure of the sealing spring due to excessive temperature, and failure of the sealing system due to deformation due to temperature difference. Thereby, the reliability and life of the rotary engine are effectively improved while ensuring the small size and low weight of the whole machine.

[0008] Furthermore, an oil inlet joint is provided at the oil inlet, an oil outlet joint is provided at the oil outlet, threads are provided at the ends of the oil inlet and the oil outlet, and the oil inlet joint and the oil outlet joint are respectively connected to the oil inlet and the oil outlet through threads.

[0009] In summary, the rotary engine cylinder body structure proposed in the present invention can effectively solve the problems of excessive thermal load and large temperature difference between the hot arc zone and the cold arc zone of the air-cooled rotary engine, thereby effectively solving the serious quality problems of the air-cooled rotary engine such as sealing failure and cylinder pulling caused by excessive thermal load and large temperature difference between the hot arc zone and the cold arc zone, and prolonging the service life of the air-cooled rotary engine. At the same time, it can preheat the aviation kerosene, improve the atomization effect of the aviation kerosene, and make the aviation kerosene burn more fully.

[0010] The above description is only an overview of the technical solution of the present invention. In order to more clearly understand the technical means of the present invention, it can be implemented according to the contents of the specification. In order to make the above and other purposes, features and advantages of the present invention more obvious and easy to understand, the following preferred embodiments are specifically cited and described in detail with reference to the accompanying drawings. BRIEF DESCRIPTION OF THE DRAWINGS

[0011] Figure 1 The present invention is a schematic structural diagram of a rotary engine using an aviation kerosene self-preheating rotary engine cooling structure of the present invention.

[0012] Figure 2 It is a front view of the cylinder body in the present invention.

[0013] Figure 3 yes Figure 2 Left side view.

[0014] Figure 4 yes Figure 2 sectional view of . DETAILED DESCRIPTION

[0015] The technical solution of the present invention is further described below in conjunction with the accompanying drawings and preferred embodiments.

[0016] An embodiment of a cooling structure of an aviation kerosene self-preheating rotary engine: See also Figures 1 to 4A rotary engine adopting an aviation kerosene self-preheating rotary engine cooling structure of the present invention comprises a rear end cover 1, a cylinder block 2 and a front end cover 3, wherein the rear end cover 1 and the front end cover 3 are respectively arranged on both sides of the cylinder block 2, the cylinder block 2 comprises a cylinder body 201, a cooling oil passage 203 is arranged in an inner wall interlayer (between the inner wall and the outer wall of the cylinder block 2), the cooling oil passage 203 is arranged in a hot arc zone of the cylinder body 201, the hot arc zone of the cylinder body 201 is in an arc shape, an oil inlet 204 and an oil outlet 205 are respectively arranged at both ends of the cooling oil passage 203, threads are arranged at the ends of the oil inlet 204 and the oil outlet 205, an oil inlet joint 5 and an oil outlet joint 4 are respectively connected to the oil inlet 204 and the oil outlet 205 through threads, that is, the oil inlet joint 5 is connected to the fuel tank through a first oil pipe, and the oil outlet joint 4 is connected to the fuel pump through a second oil pipe; When working, the fuel pump pumps the aviation fuel preheated by the hot arc zone of the cylinder block 2 into the engine intake system, and the normal temperature aviation kerosene in the fuel tank continuously replenishes the hot arc zone of the cylinder block 2, and this cycle continues. The aviation kerosene is used to take away the heat from the hot arc zone of the engine and preheat the aviation kerosene at the same time, thereby solving the problems of high temperature in the hot arc zone of the rotary engine and large temperature difference between the hot arc zone and the cold arc zone. At the same time, the aviation kerosene is preheated, which effectively improves the atomization effect of the aviation kerosene, so that the rotary engine can fully ignite the aviation kerosene.

[0017] In other embodiments of the present invention, the fuel tank may be connected to the fuel pump through a first oil pipe, the fuel pump is connected to the oil inlet connector 5 through the first oil pipe, and the oil outlet connector 4 is connected to the engine intake system through a second oil pipe.

[0018] See also Figure 1 and Figure 4 A plurality of fins 202 for heat dissipation are arranged on the outer wall of the cylinder body 201 in the hot arc zone. The fins 202 are circumferentially distributed along the outer wall of the cylinder body 201, and the length of the fins 202 gradually increases from the air inlet to the exhaust port. At the same time, a plurality of heat dissipation fins are also arranged on the outer walls of the rear end cover 1 and the front end cover 3 at intervals. The number of fins 202 and the interval between two adjacent fins correspond to the heat dissipation fins. When the rotary engine is working, the cooling wind speed can be increased to further reduce the temperature difference of the entire hot arc zone and the temperature difference between the hot arc zone and the cold arc zone, effectively solving serious quality problems of the air-cooled rotary engine caused by excessively high temperature in the hot arc zone and excessive temperature difference between the hot arc zone and the cold arc zone, such as cylinder pulling, failure of the sealing spring due to excessive temperature, and failure of the sealing system due to deformation due to temperature difference. Because this solution does not require the addition of additional coolant, water pump, radiator and other accessories, it effectively improves the reliability and life of the rotary engine while ensuring the small size and low weight of the entire machine.

[0019] The above is only a preferred embodiment of the present invention. Any technician familiar with the profession, without departing from the scope of the technical solution of the present invention, any simple modification, equivalent change and modification made to the above embodiment based on the technical essence of the present invention, still falls within the scope of the technical solution of the present invention.

Claims

1. A cooling structure for a self-preheating rotary engine using aviation kerosene, comprising a cylinder block (2), characterized in that: The cylinder block (2) comprises a cylinder body (201), a cooling oil passage (203) being arranged in an inner wall interlayer of the cylinder body (201), the cooling oil passage (203) being arranged in a hot arc zone of the cylinder body (201), an oil inlet (204) and an oil outlet (205) being arranged at both ends of the cooling oil passage (203), the oil inlet (204) being connected to a fuel tank via a first oil pipe, the oil outlet (205) being connected to an engine air intake system via a second oil pipe, and a fuel pump being arranged on one of the first oil pipe and the second oil pipe.

2. The cooling structure of the aviation kerosene self-preheating rotary engine according to claim 1, characterized in that: A plurality of fins (202) for heat dissipation are provided on the outer wall of the hot arc zone of the cylinder body (201); the fins (202) are distributed in a circumferential direction, and the length of the fins (202) gradually increases from the air inlet to the air outlet.

3. The cooling structure of the aviation kerosene self-preheating rotary engine according to claim 1, characterized in that: An oil inlet connector (5) is provided at the oil inlet (204), and an oil outlet connector (4) is provided at the oil outlet (205).

4. The cooling structure of the aviation kerosene self-preheating rotary engine according to claim 3 is characterized in that: The ends of the oil inlet (204) and the oil outlet (205) are provided with threads, and the oil inlet connector (5) and the oil outlet connector (4) are respectively connected to the oil inlet (204) and the oil outlet (205) through the threads.

5. The cooling structure of the aviation kerosene self-preheating rotary engine according to claim 1, characterized in that: The hot arc area of ​​the cylinder body (201) is in the shape of a circular arc.

6. The cooling structure of the aviation kerosene self-preheating rotary engine according to claim 1, characterized in that: The second oil pipe is provided with a fuel pump.

7. The cooling structure of the aviation kerosene self-preheating rotary engine according to claim 1, characterized in that: A rotary engine adopting a cooling structure comprises a cylinder body (2), a front end cover (3) arranged on both sides of the cylinder body (2), and a rear end cover (1).

8. The cooling structure of the aviation kerosene self-preheating rotary engine according to claim 7, characterized in that: A plurality of fins (202) for heat dissipation are arranged on the outer wall of the hot arc zone of the cylinder body (201), the fins (202) are distributed in a circumferential direction, and the length of the fins (202) gradually increases from the air inlet to the air outlet; a plurality of heat dissipation fins are arranged at intervals on the outer walls of the rear end cover (1) and the front end cover (3), and the number and interval distance of the fins (202) correspond to those of the heat dissipation fins.

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