CN211174417U

CN211174417U - Self-heating type air inlet manifold of aircraft engine

Info

Publication number: CN211174417U
Application number: CN201922398231.3U
Authority: CN
Inventors: 罗刚; 杨鹏程; 韩龙章; 刘政灿
Original assignee: Chongqing Zongshen Aircraft Engine Manufacturing Co ltd
Current assignee: Chongqing Zongshen Aviation Engine Manufacturing Co.,Ltd.
Priority date: 2019-12-27
Filing date: 2019-12-27
Publication date: 2020-08-04
Anticipated expiration: 2029-12-27

Abstract

The utility model discloses an aeroengine self-heating type air intake manifold, including air intake manifold, air intake manifold's the position department of being connected with the carburetor is climbing pipeline, its characterized in that: and a hot water pipeline is arranged on the outer wall of the climbing pipeline of the intake manifold, one end of the hot water pipeline is connected with the water outlet of the cylinder head water channel, and the other end of the hot water pipeline is connected with the expansion kettle. Adopt the utility model discloses an air intake manifold can improve the fuel thermal efficiency of engine.

Description

Self-heating type air inlet manifold of aircraft engine

Technical Field

The utility model relates to an air intake manifold of engine especially relates to an air intake manifold that can self-heat for aeroengine.

Background

For a carbureted or throttle body gasoline injected engine, the intake manifold refers to the intake conduit after the carburettor or throttle body and before the cylinder head intake port. Its function is to distribute the mixture of air and fuel oil from carburetor or throttle body to the intake channel of each cylinder.

A intake manifold and carburetor hookup location for on the aeroengine because of having the climbing design, combustible mixture behind the carburetor appears climbing here and hits the wall, and the fuel condenses, and liquid fuel is wrapped up by the high velocity gas flow and is carried and get into the combustion chamber for the great and air-mixed inhomogeneous of fuel particle in the combustion chamber, finally leads to the burning insufficient, discharges not good, and the thermal efficiency is low.

SUMMERY OF THE UTILITY MODEL

An object of the utility model is to provide a burn abundant, the emission is good, and the thermal efficiency is high is used for self-heating type air intake manifold on the aeroengine.

In order to achieve the above object, the present invention is realized as follows: the self-heating type air inlet manifold for the aircraft engine comprises an air inlet manifold, wherein a climbing pipeline is arranged at the position, connected with a carburetor, of the air inlet manifold, a hot water pipeline is arranged on the outer wall of the climbing pipeline of the air inlet manifold, one end of the hot water pipeline is connected with a water channel outlet of an engine cylinder head, and the other end of the hot water pipeline is connected with an expansion kettle.

In order to further improve the heat efficiency, the outer wall of the climbing pipeline is used as a partial hot water cavity wall of the hot water pipeline.

Preferably, a socket is arranged at one end of the hot water pipeline, a port is arranged at a water outlet of the water channel of the cylinder head, the socket is inserted into the port for connection, and an O-shaped sealing ring is further arranged between the socket and the port.

Preferably, the other end of the hot water pipeline is connected with the expansion kettle through a hose, and the hose is respectively connected with the port of the hot water pipeline and the port of the expansion kettle through anchor ears.

In order to further improve the thermal efficiency, the hot water pipeline is divided into an inlet pipeline connected with a water outlet of the cylinder head water channel and an outlet pipeline connected with the expansion kettle, a water cavity is formed between the inlet pipeline and the outlet pipeline, and the water cavity partially wraps the outer wall of the climbing pipeline.

To further increase the thermal efficiency, the cross-section of the water chamber is larger than the cross-sections of the inlet and outlet pipes.

In order to further improve the thermal efficiency, the water cavity takes part of the outer wall of the climbing pipeline as a cavity wall.

Has the advantages that:

the utility model discloses a through carrying out design optimization to air intake manifold, utilize cylinder head delivery port hot water to heat manifold climbing position, increase this position and ambient temperature, can increase fuel evaporation and reduce the fuel and condense, further reduce fuel atomization particle diameter.

Additionally, the utility model discloses an intake manifold still has following advantage:

1. the mixed gas in the air inlet manifold is heated, so that the fuel oil volatilization effect of the aircraft engine in a low-temperature environment is improved, and the air inlet is more uniform; 2. the carburetor connected with the air inlet pipe is heated, so that the phenomenon that the carburetor of the aircraft engine freezes in the high-altitude low-temperature environment is improved; 3. the fuel oil and the air are mixed more fully and are combusted more uniformly, the emission is improved, the heat efficiency is improved, and the carbon deposition is reduced; 4. and a part of useless heat is recovered by utilizing the heat of the cooling water, so that the utilization efficiency of the energy of the engine is improved.

Drawings

FIG. 1 is a block diagram of an autothermal intake manifold of an embodiment;

fig. 2 is a sectional view of an autothermal intake manifold in an 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 and 2, the self-heating intake manifold for an aircraft engine according to the present embodiment includes an intake manifold 1, a climbing pipe 11 is disposed at a position of the intake manifold connected to a carburetor, a hot water pipe 2 is disposed on an outer wall of the climbing pipe of the intake manifold, one end of the hot water pipe is connected to a water outlet of a water channel of an engine cylinder head 3, and the other end of the hot water pipe is connected to an expansion kettle 4.

The hot water pipeline is divided into an inlet pipeline 21 connected with a water outlet of a water channel of the cylinder head and an outlet pipeline 22 connected with the expansion kettle, a water cavity 23 is formed between the inlet pipeline and the outlet pipeline, and the water cavity partially wraps the outer wall of the climbing pipeline.

In one embodiment of this embodiment, the water cavity 23 has a partial outer wall of the climbing pipe 1 as a cavity wall. Therefore, the climbing pipeline can be coated by the water cavity, and the hot water of the water channel of the cylinder head is used for heating the air inlet manifold. In this embodiment, the cross section of the water chamber is larger than the cross sections of the inlet pipe and the outlet pipe.

In another embodiment of the present invention, an end of the inlet pipe is provided with a socket 24, an outlet of the cylinder head waterway is provided with a port, the socket is inserted into the port for connection, and an O-ring 25 is further disposed between the socket and the port.

As another implementation manner in this embodiment, the outlet pipe is connected to the expansion tank through a hose 5, and the hose is connected to the port of the hot water pipe and the inlet end of the expansion tank through hoops 6.

This embodiment utilizes cylinder head delivery port hot water to heat manifold climbing position, increases this position and peripheral temperature, can increase the evaporation of fuel and reduce the fuel and condense, further reduces the fuel atomization particle diameter.

And the following effects are also achieved by heating the middle-aged mixed gas in the intake manifold: 1. the fuel oil volatilization effect of the aircraft engine in a low-temperature environment is improved, so that the air intake is more uniform; 2. the carburetor connected with the air inlet pipe is heated, so that the phenomenon that the carburetor of the aircraft engine freezes in the high-altitude low-temperature environment is improved; 3. the fuel oil and the air are mixed more fully and are combusted more uniformly, the emission is improved, the heat efficiency is improved, and the carbon deposition is reduced; 4. and a part of useless heat is recovered by utilizing the heat of the cooling water, so that the utilization efficiency of the energy of the engine is improved.

Claims

1. An aircraft engine self-heating type air inlet manifold comprises an air inlet manifold, a climbing pipeline is arranged at the position of the air inlet manifold, which is connected with a carburetor, and the self-heating type air inlet manifold is characterized in that: and a hot water pipeline is arranged on the outer wall of the climbing pipeline of the intake manifold, one end of the hot water pipeline is connected with the water outlet of the cylinder head water channel, and the other end of the hot water pipeline is connected with the expansion kettle.

2. An aircraft engine self-heating intake manifold according to claim 1, wherein: the hot water pipeline takes the outer wall of the climbing pipeline as the wall of a part of hot water cavity.

3. An aircraft engine self-heating intake manifold according to claim 2, wherein: the hot water pipeline is characterized in that a socket is arranged at one end of the hot water pipeline, a port is arranged at a water outlet of the water channel of the cylinder head, the socket is inserted into the port for connection, and an O-shaped sealing ring is further arranged between the socket and the port.

4. An aircraft engine self-heating intake manifold according to claim 3, wherein: the other end of the hot water pipeline is connected with the expansion kettle through a hose, and the hose is respectively connected with the port of the hot water pipeline and the port of the expansion kettle through anchor ears.

5. An aircraft engine self-heating intake manifold according to claim 1, 2, 3 or 4, wherein: the hot water pipeline is divided into an inlet pipeline connected with a water outlet of the cylinder head water channel and an outlet pipeline connected with the expansion kettle, a water cavity is formed between the inlet pipeline and the outlet pipeline, and the water cavity partially wraps the outer wall of the climbing pipeline.

6. An aircraft engine self-heating intake manifold according to claim 5, wherein: the cross section of the water cavity is larger than the cross sections of the inlet pipeline and the outlet pipeline.

7. An aircraft engine self-heating intake manifold according to claim 5, wherein: and the water cavity takes part of the outer wall of the climbing pipeline as a cavity wall.