Aero-engine

Abstract

The invention discloses an aero-engine which comprises a carburetor and an air inlet manifold, the carburetor is connected with the air inlet manifold through a connecting rubber pipe, and a heating assembly for heating the air inlet end of the air inlet manifold is arranged between the carburetor and the connecting rubber pipe. Working heat of the engine can be recycled and used for heating the oil-gas mixture, sufficient combustion of the oil-gas mixture in the air cylinder is guaranteed, and the output power can be improved while normal output of the engine is guaranteed.

Description

Technical Field

[0001] The invention relates to an engine, in particular to an aviation engine capable of improving output power. Background Art

[0002] As a power output device, the engine is widely used in all walks of life. During the operation of the engine, the carburetor needs to mix a certain proportion of fuel and air, and then the oil-gas mixture is sent into the cylinder for combustion. The generated gas pushes the piston to do work, and converts the linear motion into rotational motion through the connecting rod and crankshaft, thereby outputting mechanical energy. For aircraft engines, due to the low temperature at high altitudes, the ambient temperature of aircraft engines is low, and when aircraft engines are started at low temperatures, there is a problem of low output power.

[0003] In order to solve the problem of low output power of aircraft engines when starting at low temperatures, Chinese patent document CN210599212U discloses a new carburetor heating device for piston engines, including copper tube one, copper tube two and a hollow metal heat-conducting shell; the coolant of the engine's cooling and heat dissipation system enters the hollow metal heat-conducting shell through copper tube one, heating the carburetor branch pipe, so that the carburetor branch pipe is basically maintained at the engine cylinder head temperature of about 40 degrees to 50 degrees, so that the atomization effect is better and the power output is smoother and more stable, thereby ensuring the normal and efficient operation of the engine in a high-altitude and low-temperature environment.

[0004] Another Chinese patent document CN211343171U discloses a heavy oil engine air filter assembly and an aircraft engine, including an air filter body and a heating device, the heating device is directly or indirectly used to heat the air passing through the air filter; the air filter assembly is provided with a heating device, which can well preheat the fuel and combustion air at startup, has a simple structure and is easy to operate, so that the heavy oil can be more fully atomized and mixed, ensuring that the heavy oil engine is smoothly started in a low temperature environment and good combustion is formed, thereby achieving energy saving, environmental protection and low cost after the heavy oil is used in the engine.

[0005] In the above-mentioned patent documents, the normal starting of the engine in a low temperature environment can be ensured by heating the carburetor branch pipe or heating the air filter, but the actual output power still needs to be improved. Summary of the invention

[0006] In order to solve the technical problem in the prior art that the output power of an engine needs to be improved under a low temperature environment, the present invention provides an aircraft engine, comprising a carburetor and an intake manifold, wherein the carburetor and the intake manifold are connected by a connecting hose, wherein a heating component for heating the intake end of the intake manifold is provided between the carburetor and the connecting hose.

[0007] In the prior art, although the heating method can ensure that the engine starts normally in a low temperature environment, there is still a problem of low output power. After analyzing the reasons for the low output power, it is found that in the prior art, although the fuel and air temperatures in the carburetor are appropriate and the carburetor atomization effect is good after refueling the carburetor branch pipe or air filter, the temperature of the oil-gas mixture will drop from the time it comes out of the carburetor to the time it enters the intake manifold due to the influence of the ambient temperature, resulting in incomplete combustion in the cylinder, a decrease in the crankshaft speed, and large fluctuations in the crankshaft speed, which ultimately leads to a decrease in the engine output power.

[0008] In this solution, a heating component is provided between the carburetor and the connecting hose. After the heating component is used to heat the intake end of the intake manifold, the oil-gas mixture will be heated when passing through the intake manifold. The heated oil-gas mixture will then be distributed through the intake manifold and enter the respective cylinders for combustion. The heated oil-gas mixture can burn more fully in the cylinder, thereby ensuring the normal output of the engine and improving the output power.

[0009] Preferably, the heating assembly includes a heater and a heating tube, the heating tube is provided with a heating portion for heating the heater, and the heater is connected to a connecting hose. In this solution, the heater is heated by the provided heating tube, and after the heater is heated, the oil-gas mixture passing through the heater is also heated, and the heated oil-gas mixture enters the intake manifold through the connecting hose, which can ensure that the oil-gas mixture is fully burned in the cylinder, and the structure is simple.

[0010] Preferably, an intake passage connected to the intake manifold is provided in the heater, and the heating unit heats the intake passage. In this solution, the oil-gas mixture passing through the intake passage can be directly heated by using the heating unit to heat the intake passage, which can reduce the heat loss during the heating process, ensure the heating effect of the oil-gas mixture, and further ensure the full combustion of the oil-gas mixture in the cylinder, and the structure is simple.

[0011] Preferably, the heating part extends into the heater and surrounds the intake passage and then extends out of the heater. This solution can increase the contact area between the heating part and the heater, has a better heating effect on the oil-gas mixture, further ensures the full combustion of the oil-gas mixture in the cylinder, and has a simple structure.

[0012] Preferably, the heating pipe further comprises a connection part connected to the heating medium supply system, and the connection part is detachably connected to the heating part. The detachable connection in this solution facilitates the replacement of the heating pipe and the connection part.

[0013] Preferably, a clamping piece is sleeved at the connection between the connecting part and the heating part. The provision of the clamping piece in this solution can achieve a tight and sealed connection between the connecting part and the heating part, thereby avoiding the loss of the medium in the heating part.

[0014] Preferably, a cooling system is also included, and the connecting part is connected to the return water pipeline of the cooling system. Since a large amount of heat is generated during the operation of the aircraft engine, and the cooling system is a necessary mechanism that can dissipate the high heat generated when the engine is working in time, the temperature of the flowing medium in the return water pipeline of the cooling system is relatively high. In this solution, after the connecting part is connected to the return water pipeline of the cooling system, the high-temperature flowing medium in the return water pipeline is used as the heating medium in the heating pipe, that is, the heat recovered by the cooling system in the process of cooling the engine is used as energy to heat the oil-gas mixture, realizing the reuse of the heat of the aircraft engine. On the one hand, it can reduce the waste of heat of the aircraft engine, and on the other hand, it can also save the additional heating device of the oil-gas mixture, which can reduce the cost of the heating component.

[0015] Preferably, the heater is connected to the carburetor via a fastener. In this solution, the arrangement of the fastener can ensure a secure connection between the heater and the carburetor.

[0016] Preferably, a connection end is provided at one end of the heater facing the carburetor, a connection hole is provided on the connection end, and the fastener is connected to the connection hole. In this solution, the connection hole on the connection end is provided to cooperate with the fastener to realize the fastening connection between the heater and the carburetor, and the structure is simple.

[0017] Preferably, sealing rings are provided on both sides of the heater. In this solution, the provision of the sealing rings can achieve a sealed connection between the heater and the carburetor and the connecting hose, and the structure is simple.

[0018] The present invention has the following beneficial effects:

[0019] 1. The present invention can recover the working heat of the engine and use the working heat to heat the oil-gas mixture, thereby ensuring the full combustion of the oil-gas mixture in the cylinder, and can improve the output power while ensuring the normal output of the engine. BRIEF DESCRIPTION OF THE DRAWINGS

[0020] Figure 1 A schematic diagram of an aircraft engine embodiment of the present invention;

[0021] Figure 2 for Figure 1 The right side schematic diagram of

[0022] Figure 3 for Figure 1 A top view of

[0023] Figure 4 for Figure 1 The structural diagram of the heating tube;

[0024] Figure 5 It is a schematic diagram of the local structure of an aircraft engine;

[0025] Figure 6 for Figure 5 Top view of the . DETAILED DESCRIPTION

[0026] The following is further described in detail through specific implementation methods:

[0027] 1. Definition

[0028] Intake manifold: refers to the intake pipe from the carburetor to the cylinder head intake duct. Its function is to distribute the air and fuel mixture from the carburetor or throttle body to the intake duct of each cylinder.

[0029] 2. The reference numerals in the drawings of the specification include: water inlet 1, air intake duct 11, heater 2, heating connecting pipe 3, water outlet 4, connecting part 5, heating part 6, carburetor 7, intake manifold 8, sealing ring 9, connecting end 10.

[0030] The embodiment is basically as shown in the attached Figure 1-Figure 6 As shown: an aircraft engine, including a carburetor 7, an intake manifold 8 and a cooling system, the carburetor 7 is connected to the intake manifold 8 through a connecting hose, and a heating component for heating the intake end of the intake manifold 8 is arranged between the carburetor 7 and the connecting hose. The cooling system includes a return water pipeline for the flow of a medium.

[0031] Specifically, the heating assembly includes a heater 2 and a heating tube. The heating tube is provided with a heating portion 6 for heating the heater 2 and a connecting portion 5 connected to a heating medium supply system. A clamp is provided at the connection between the connecting portion 5 and the heating portion 6 to achieve a detachable connection between the connecting portion 5 and the heating portion 6. The heater 2 is connected to a connecting hose. In this embodiment, the connecting portion 5 is covered with a jacket and connected by a clamp. The heating medium supply system is provided by a cooling system, so the connecting portion 5 is connected to a return water pipeline of the cooling system, and the cooling medium in the cooling system that absorbs the heat energy of the aircraft engine is used as the heating medium in the connecting portion 5.

[0032] The heater 2 is provided with an intake passage 11 connected to the intake manifold 8. The heating unit 6 extends into the heater 2 and surrounds the intake passage 11 and then extends out of the heater 2, so that the heating unit 6 can heat the intake passage 11. The heater 2 is connected to the carburetor 7 through a fastener. Specifically, the heater 2 is provided with a connecting end 10 at one end facing the carburetor 7. The connecting end 10 is provided with a connecting hole, and the fastener is connected to the connecting hole. Sealing rings 9 are provided on both sides of the heater 2, and the fasteners are bolts.

[0033] The specific implementation process is as follows: In this embodiment, the aircraft engine takes a four-cylinder engine as an example, and the corresponding intake manifold 8 has four connecting pipes. Two groups of heating components are provided, and the two groups of heating components are connected by a heating connecting pipe 3. The connecting part 5 of one group of heating components is provided with a water inlet 1, and the connecting part 5 of the other group of heating components is provided with a water outlet 4. The connecting parts 5 at both ends are connected with the return water pipeline of the cooling system. When the aircraft engine is working, the medium in the return water pipeline recovers the heat energy of the aircraft engine, and the temperature of the medium rises and flows into the heating pipe through the connecting part 5. The heated medium flows in the heating pipe, heats the intake duct 11 of the heater 2 in the process of passing through the heater 2, and then flows out of the heating pipe and returns to the return water pipeline. Since the temperature of the medium will drop in the process of heating the intake duct 11, the temperature of the medium returning to the return water pipeline is low, and the heat energy of the aircraft engine can continue to be recovered. After the temperature of the intake duct 11 is heated, the oil-gas mixture flowing out of the carburetor 7 is heated when passing through the intake duct 11, the oil-gas mixture is heated, and then distributed to the corresponding cylinders through the intake manifold 8 for full combustion, thereby ensuring the normal output of the aircraft engine. Moreover, since the oil-gas mixture is fully burned, the output power of the aircraft engine is also effectively improved.

[0034] The aircraft engine in this embodiment was tested, and an aircraft engine without a heating component installed was tested under the same test conditions. Then, the throttle opening degree and the actual engine speed were recorded. The recorded results are shown in Table 1.

[0035] Table 1

[0036]

[0037] It can be seen from the recorded results in the above table that the aircraft engine in this embodiment can effectively improve the output power.

[0038] The above is only an embodiment of the present invention. The common sense such as the known specific structure and characteristics in the scheme is not described in detail here. The ordinary technicians in the relevant field know all the common technical knowledge in the technical field of the invention before the application date or priority date, can obtain all the existing technologies in the field, and have the ability to apply the conventional experimental means before that date. The ordinary technicians in the relevant field can improve and implement this scheme in combination with their own abilities under the enlightenment given by this application. Some typical known structures or known methods should not become obstacles for ordinary technicians in the relevant field to implement this application. It should be pointed out that for those skilled in the art, without departing from the structure of the present invention, several deformations and improvements can be made, which should also be regarded as the protection scope of the present invention, which will not affect the effect of the implementation of the present invention and the practicality of the patent. The protection scope required by this application shall be based on the content of its claims, and the specific implementation methods and other records in the specification can be used to interpret the content of the claims.

Claims

1. An aircraft engine, comprising a carburetor and an intake manifold, wherein the carburetor and the intake manifold are connected via a connecting hose, characterized in that: A heating component for heating the air inlet end of the intake manifold is provided between the carburetor and the connecting rubber hose.

2. The aircraft engine according to claim 1, characterized in that: The heating assembly comprises a heater and a heating tube, the heating tube is provided with a heating portion for heating the heater, and the heater is connected to the connecting hose.

3. The aircraft engine according to claim 2, characterized in that: An intake passage communicating with the intake manifold is disposed in the heater, and the heating unit heats the intake passage.

4. The aircraft engine according to claim 3, characterized in that: The heating portion extends into the heater, is arranged around the air inlet passage, and then extends out of the heater.

5. The aircraft engine according to claim 4, characterized in that: The heating pipe also includes a connecting portion connected to a heating medium supply system, and the connecting portion is detachably connected to the heating portion.

6. The aircraft engine according to claim 5, characterized in that: A clamping piece is sleeved on the connection between the connecting part and the heating part.

7. The aircraft engine according to claim 6, characterized in that: A cooling system is also included, and the connecting portion is communicated with a water return pipeline of the cooling system.

8. The aircraft engine according to any one of claims 2 to 7, characterized in that: The heater is connected to the carburetor via a fastener.

9. The aircraft engine according to claim 8, characterized in that: The heater is provided with a connecting end at one end facing the carburetor, the connecting end is provided with a connecting hole, and the fastener is connected to the connecting hole.

10. The aircraft engine according to claim 9, characterized in that: Sealing rings are arranged on both sides of the heater.

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