Fuel injection air pump for aero-engine

Abstract

The utility model discloses a fuel injection air pump for an aero-engine, which comprises an air pump body with a piston cavity, one end of the air pump body is connected with an air pump cover for covering one end of the piston cavity, and the air pump body and the air pump cover are provided with a cooling water channel surrounding the piston cavity. And the cooling water channel is provided with a water inlet and a water outlet. According to the scheme, the problem that carbon deposition is likely to happen to the air pump cover of the fuel injection air pump in the prior art is solved.

Description

Technical Field

[0001] The utility model relates to a fuel system of an aircraft engine, in particular to a fuel injection air pump used for the aircraft engine. Background Art

[0002] A fuel injection air pump is a device that assists fuel injection into the engine by generating compressed gas. The fuel injection air pump includes an air pump body, an air pump cover, a piston, a connecting rod, a crankshaft, and a pressure relief valve. A piston chamber that cooperates with the piston is provided in the air pump body. The air pump cover is connected to the air pump body and closes one end of the piston chamber. The connecting rod connects the piston to the crankshaft, and the piston is driven to reciprocate through the rotation of the crankshaft. The pressure relief valve is installed on the air pump cover. When the fuel injection air pump is working, the reciprocating motion of the piston and the compressed gas will generate a lot of heat, thereby increasing the temperature of the air pump body and the air pump cover. The fuel injection air pump moves at high speed in the air with the aircraft engine, so the fuel injection air pump is cooled by guiding the airflow to blow on the surface of the air pump body and the air pump cover.

[0003] Chinese patent document CN111535924A discloses a spark-ignition two-stroke aviation heavy oil piston engine, including an air pump, a cooling water inlet hole is provided on the air pump and connected to a cooling water inlet channel, and a cooling water outlet hole is provided on the air pump and connected to a cooling water outlet channel. Although the prior art discloses that the air pump can be water-cooled, it does not disclose the specific arrangement form of the cooling water channel of the air pump.

[0004] Although the above prior art provides a water-cooled air pump, the prior art air pump is designed with the same air intake and exhaust directions. In actual use, it is found that carbon deposits are easily formed at the pressure relief valve inside the air pump cover, the top of the piston, etc., resulting in abnormal fluctuations in air pressure, which affects the normal use of the air pump. Utility Model Content

[0005] The utility model aims to provide a fuel injection air pump for an aircraft engine, so as to solve the problem that carbon deposition is easy to occur on the air pump cover of the fuel injection air pump in the prior art.

[0006] In order to achieve the above-mentioned purpose, the basic scheme of the utility model provides a fuel injection air pump for an aircraft engine, including an air pump body with a piston cavity, one end of the air pump body is connected to an air pump cover covering one end of the piston cavity, the air pump body and the air pump cover are provided with a cooling water channel surrounding the piston cavity, and the cooling water channel is provided with a water inlet and a water outlet.

[0007] The beneficial effect of this basic solution is that by adopting such an arrangement, the cooling water can cool both the air pump body and the air pump cover, thereby avoiding the carbon deposition problem caused by the air pump cover being too hot, which is beneficial to the normal use of the fuel injection air pump.

[0008] Preferably, the cooling water channel comprises a pump body water channel arranged on the air pump body and a pump cover water channel arranged on the air pump cover, and the pump body water channel and the pump cover water channel are interconnected. Such an arrangement facilitates the orderly flow of cooling water, thereby further improving the cooling effect.

[0009] Preferably, the pump body water channel is in an unclosed ring shape arranged along the circumference of the piston cavity, the water inlet is arranged at one end of the pump body water channel, and the other end of the pump body water channel is connected to the pump cover water channel. Such an arrangement is conducive to further improving the cooling effect of the fuel injection air pump.

[0010] Preferably, the pump cover water channel includes a plurality of side water channels arranged along the side of the air pump cover and a plurality of end water channels arranged along the end of the pump cover, and all the side water channels and the end water channels are connected to form a reciprocating zigzag channel. Such an arrangement is conducive to further improving the cooling effect of the fuel injection air pump.

[0011] Preferably, the water outlet is arranged at the end surface of the air pump cover. Such an arrangement is helpful to further improve the cooling effect of the fuel injection air pump.

[0012] The utility model has the following beneficial effects:

[0013] The adoption of this solution avoids the problem of internal carbon deposition on the air pump cover of the fuel injection air pump due to excessive temperature, is conducive to ensuring the stability of air pressure, and prolongs the service life of the fuel injection air pump. BRIEF DESCRIPTION OF THE DRAWINGS

[0014] Figure 1 It is a schematic diagram of an embodiment of a fuel injection air pump for an aircraft engine of the utility model;

[0015] Figure 2 for Figure 1 The main view;

[0016] Figure 3 for Figure 2 Middle AA section view;

[0017] Figure 4 for Figure 2 Middle BB section view;

[0018] Figure 5 for Figure 2 A top view of

[0019] Figure 6 for Figure 5 Middle CC section view. DETAILED DESCRIPTION

[0020] The following is further described in detail through specific implementation methods:

[0021] The reference numerals in the drawings of the specification include: air pump cover 1, air pump body 2, water outlet 3, water inlet 4, pump body water channel 5, end surface water channel 6, side water channel 7, diversion hole 8, piston chamber 9.

[0022] The embodiment is basically as shown in the attached Figures 1 to 6 As shown: A fuel injection air pump for an aircraft engine, comprising an air pump body 2 having a piston cavity 9, one end of the air pump body 2 is connected to an air pump cover 1 for covering one end of the piston cavity 9. In this embodiment, the air pump cover 1 is connected to the air pump body 2 by bolts, and a sealing ring is arranged between the air pump cover 1 and the air pump body 2 to prevent gas and liquid leakage. A cooling water channel surrounding the piston cavity 9 is arranged on the air pump body 2 and the air pump cover 1, and the cooling water channel is provided with a water inlet 4 and a water outlet 3, so that cooling water enters the cooling water channel from the water inlet 4 and then flows out from the water outlet 3, so that the cooling water takes away the heat of the air pump cover 1 and the air pump body 2 when flowing through the cooling water channel.

[0023] In this embodiment, the cooling water channel includes a pump body water channel 5 provided on the air pump body 2 and a pump cover water channel provided on the air pump cover 1, and the pump body water channel 5 and the pump cover water channel are connected to each other. Specifically, the pump body water channel 5 is in the shape of an unclosed ring arranged along the circumference of the piston cavity 9, the water inlet 4 is arranged at one end of the pump body water channel 5, and the other end of the pump body water channel 5 is connected to the pump cover water channel, so that the cooling water flows into the pump body water channel from one end and flows out from the other end to the pump cover water channel. Specifically, a guide hole 8 for connecting the pump body water channel 5 and the pump cover water channel is provided on the air pump body 2. When the cooling water flows in the pump body water channel 5, it will basically flow around the piston cavity 9 in one circle, so that the surrounding of the air pump body 2 can be cooled.

[0024] In this embodiment, the pump cover water channel includes a plurality of side water channels 7 arranged along the side of the air pump cover 1 and a plurality of end water channels 6 arranged along the end of the pump cover. All side water channels 7 and end water channels 6 are connected to form a reciprocating zigzag channel, so that the cooling water flows back and forth in the pump cover water channel and passes through the side and end of the entire air pump cover 1. In this embodiment, there are three side water channels 7, which are distributed circumferentially along the side of the air pump cover 1, and there are two end water channels 6, which connect the three side water channels 7 in sequence to form a reciprocating zigzag channel. In this embodiment, the water outlet 3 is arranged at the end face of the air pump cover 1.

[0025] The specific implementation process is as follows:

[0026] The water inlet 4 and the water outlet 3 are connected to the external cooling water circulation system. When the aircraft engine is working, the cooling water continuously flows through the cooling water channel at the air pump body 2 and the air pump cover 1 to take away the heat (the path shown by the arrow in the figure is the flow path of the cooling water), thereby realizing continuous cooling of the fuel injection air pump. The adoption of this solution effectively avoids the problem of lubricating oil failure due to excessive temperature of the fuel injection air pump, thereby avoiding the problem of a large amount of carbon deposits in the fuel injection air pump and abnormal wear between the moving parts, which affects the performance and life.

[0027] The above is only an embodiment of the utility model, and the common knowledge such as the known specific structure and characteristics in the scheme is not described in detail here. It should be pointed out that for those skilled in the art, several deformations and improvements can be made without departing from the structure of the utility model, which should also be regarded as the protection scope of the utility model, and these will not affect the effect of the implementation of the utility model and the practicality of the patent.

Claims

1. A fuel injection air pump for an aircraft engine, comprising an air pump body having a piston chamber, one end of the air pump body being connected to an air pump cover for covering one end of the piston chamber, characterized in that: The air pump body and the air pump cover are provided with a cooling water channel surrounding the piston cavity, and the cooling water channel is provided with a water inlet and a water outlet.

2. A fuel injection air pump for an aircraft engine according to claim 1, characterized in that: The cooling water channel comprises a pump body water channel arranged on the air pump body and a pump cover water channel arranged on the air pump cover, and the pump body water channel and the pump cover water channel are communicated with each other.

3. A fuel injection air pump for an aircraft engine according to claim 2, characterized in that: The pump body water channel is in the shape of an unclosed ring arranged along the circumference of the piston cavity, the water inlet is arranged at one end of the pump body water channel, and the other end of the pump body water channel is communicated with the pump cover water channel.

4. A fuel injection air pump for an aircraft engine according to claim 3, characterized in that: The pump cover water channel comprises a plurality of side water channels arranged along the side of the air pump cover and a plurality of end surface water channels arranged along the end of the pump cover. All the side water channels and the end surface water channels are connected to form a reciprocating zigzag channel.

5. A fuel injection air pump for an aircraft engine according to claim 4, characterized in that: The water outlet is arranged at the end surface of the air pump cover.

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