CN212615078U

CN212615078U - Air inlet system of aircraft engine and pressure stabilizing box thereof

Info

Publication number: CN212615078U
Application number: CN202021323043.0U
Authority: CN
Inventors: 周丹; 唐中; 韩龙章
Original assignee: Chongqing Zongshen Aircraft Engine Manufacturing Co ltd
Current assignee: Chongqing Zongshen Aviation Engine Manufacturing Co.,Ltd.
Priority date: 2020-07-08
Filing date: 2020-07-08
Publication date: 2021-02-26
Anticipated expiration: 2030-07-08

Abstract

The utility model discloses an aeroengine air intake system and surge tank thereof, wherein the surge tank includes surge tank body, its characterized in that: the middle part of pressure stabilizing box body is provided with the air inlet, the both ends of pressure stabilizing box body are divided and are established gas outlet A and gas outlet B. By adopting the pressure stabilizing box and the air inlet system in the embodiment, the area of the air inlet system can be reduced, the weight is reduced, and the airflow can be stabilized.

Description

Air inlet system of aircraft engine and pressure stabilizing box thereof

Technical Field

The utility model relates to a surge tank especially relates to an aeroengine air intake system's of four jar horizontal opposition surge tank.

Background

In the existing four-cylinder engine, each cylinder block is generally connected with an air source. Such an arrangement is suitable for the automotive industry with large layout space.

Aeroengine, especially unmanned aerial vehicle, the overall arrangement space is little, and requires the lightweight. And the air intake system is a core component for ensuring the high efficiency and stable air intake of the engine. One key index for evaluating the air intake effect of the engine is the consistency of airflow provided by an air intake system to each cylinder of the engine (air intake uniformity). At present, an air inlet system of an aeroengine hardly ensures that the engine keeps stable uniformity under different throttle working conditions.

Chinese patent CN204691937U discloses an oil-gas supply system for a four-cylinder internal combustion engine, and specifically discloses: the carburetor comprises a carburetor A, a carburetor B, an intake manifold A and an intake manifold B, wherein the carburetor A is connected with the intake manifold A, the carburetor B is connected with the intake manifold B, and a balance pipe communicated with the intake manifold A and the intake manifold B is arranged between the intake manifold A and the intake manifold B. The balance pipe is adopted in the patent to balance the problem of oil supply balance of the four cylinders.

However, the left two cylinders in the above patent use one air source, and the right two cylinders use the other air source, so that the requirement of light weight of the aircraft engine cannot be met, and too much space is required in spatial layout.

SUMMERY OF THE UTILITY MODEL

An object of the utility model is to provide a surge tank can provide a lightweight, the little and stable aero-engine air intake system of admitting air of occupation space for aero-engine.

In order to achieve the above object, the present invention is realized as follows: the utility model provides an aeroengine air intake system's surge tank, includes surge tank body, its characterized in that: the middle part of pressure stabilizing box body is provided with the air inlet, the both ends of pressure stabilizing box body are divided and are established gas outlet A and gas outlet B. By adopting the patent and the same pressure stabilizing box, air sources can be simultaneously provided for the air inlet manifold A and the air inlet manifold B of the engine, the occupation of an air inlet system can be reduced, and the weight of the air inlet system is reduced. In addition, the middle of the air inlet system is used for air inlet through a single air source, air outlet is formed in the two ends of the air inlet system, air flow can be promoted to be uniformly distributed to the air outlets on the two sides, and air inlet stability is improved.

Preferably, an air outlet pipe A is arranged at the air outlet A, and an air outlet pipe B is arranged at the air outlet B.

In order to further improve the flow speed stability of the outlet section of the pressure stabilizing box, a uniform filter screen is arranged in the air outlet pipe A and/or the air outlet pipe B.

In order to further improve the flow speed stability of the outlet section of the pressure stabilizing box, the uniform filter screen is provided with filter holes, the uniform filter screen is arranged in the air outlet pipe A or the air outlet pipe B, and the direction of the filter holes is consistent with the axial direction of the air outlet pipe A or the air outlet pipe B.

Optionally, the uniform filter screens are fixedly arranged in the air outlet pipe A and the air outlet pipe B, or the uniform filter screens are separately arranged in the air outlet pipe A and the air outlet pipe B.

Preferably, the uniform filter screen is provided with an outer cylinder wall, a plurality of filter holes which are parallel to each other are uniformly distributed in the outer cylinder wall, the direction of the filter holes is along the axial direction of the outer cylinder wall, and the uniform filter screen is welded and installed in the air inlet pipe A and the air inlet pipe B.

Further, the axial length of the uniform filter screen can be 20-45 mm. If the axial length of the uniform filter screen is too short, the flow guiding and stabilizing effects are poor, and if the axial length of the uniform filter screen is too long, the wind resistance is too large. Preferably, the axial length of the uniform filter screen is 30 mm.

The embodiment also provides an air intake system of an aircraft engine, which comprises the pressure stabilizing box, wherein an air outlet A of the pressure stabilizing box body is connected with a carburetor A, the carburetor A is connected with an air intake manifold A, an air outlet B of the pressure stabilizing box body is connected with a carburetor B, the carburetor B is connected with the air intake manifold B, the air intake manifold A is Y-shaped, the air intake manifold A is provided with an inlet connected with the carburetor A and two air intake pipes respectively connected with a cylinder body, the air intake manifold B is Y-shaped, and the air intake manifold B is provided with an inlet connected with the carburetor B and two air intake pipes respectively connected with the cylinder body.

Has the advantages that:

the utility model discloses an aeroengine's surge tank mainly is applied to the aeroengine of four jar horizontal opposition. One pressure stabilizing box and one air source are adopted, and air is supplied to 4 cylinder bodies simultaneously. And through the mode that middle air inlet, both ends were given vent to anger to and through setting up the even filter screen in the surge tank, can promote the air current evenly and smoothly be distributed to air intake manifold in, further enter into among the cylinder body.

Additionally, the utility model provides an equal filtration pore that sets up on the equal filter screen, the direction in equal filtration pore is parallel respectively with outlet duct A and outlet duct B. Therefore, the vortex formed by the airflow at the end part of the pressure stabilizer due to the change of the direction can be avoided, the airflow is guided through the filter equalizing hole and is divided into parallel small beams, and the airflow can stably and uniformly enter the carburetor from the pressure stabilizer box.

Drawings

FIG. 1 is an isometric view of a surge tank in an embodiment;

FIG. 2 is a front view of a surge tank in an embodiment;

FIG. 3 is a right side view of a surge tank in an embodiment;

FIG. 4 is a top view of a surge tank 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. 1-4, the present embodiment provides a surge tank for use in an air intake system of an aircraft engine, but may also be used in engines in other fields, such as an automobile engine, a tricycle engine, etc.

In addition, the surge tank and the air intake system provided in the embodiment are mainly applied to four-cylinder horizontally-opposed aircraft engines. The air intake system in the embodiment comprises a pressure stabilizing box, a carburetor A, a carburetor B, an air intake manifold A and an air intake manifold B. Since the intake system in the present embodiment is applied to a four-cylinder engine, intake manifold a and intake manifold B in the present embodiment are both Y-shaped intake manifolds. The Y-shaped intake manifold is an intake manifold with one air inlet and two air outlets. Specifically, the intake manifold has a total section, one end of the total section is an air inlet, the other end of the total section is respectively connected with two subsections, and the end parts of the subsections are air outlets. The sections are air inlet pipes of the engine and are respectively connected with a cylinder body of the engine.

In this embodiment only one surge tank is used. The pressure stabilizing box in the embodiment is provided with a pressure stabilizing box body 1, an air inlet is formed in the middle of the pressure stabilizing box body, and an air outlet A and an air outlet B are formed in two ends of the pressure stabilizing box body respectively. The air outlet A is connected with the carburetor A, and the carburetor A is connected with the air inlet end of the air inlet manifold A. The air outlet B is connected with the carburetor B, and the carburetor B is connected with the air inlet end of the air inlet manifold B. And the air inlet of the pressure stabilizing box is connected with an air source. The air flow enters from the middle part of the pressure stabilizing box, and flows out from the two ends and respectively enters into the carburetor A and the carburetor B.

In another embodiment of the present embodiment, an air inlet pipe 11 is disposed at the air inlet, and a negative pressure nozzle mounting seat 12 is disposed on an upper end wall of the air inlet pipe. An air outlet pipe A13 is arranged at the air outlet A, the carburetor A is connected with the air outlet pipe A, an air outlet pipe B14 is arranged at the air outlet B, and the carburetor B is connected with the air outlet pipe B. And the air outlet pipe A and the air outlet pipe B are both provided with a uniform filter screen 2. Of course, it is also possible to choose to provide it only on one side and not on the other. In this embodiment, both the outlet tube a and the outlet tube B are provided.

Because the pressure stabilizing box in the embodiment adopts the mode of air inlet in the middle and air outlet at two ends, the direction of the airflow can be changed at the two ends, and the vortex can be formed again to influence the stability of the airflow.

Therefore, in the embodiment, the uniform filter screens are arranged in the air outlet pipe A and the air outlet pipe B of the surge tank, and the uniform filter screens are used for preventing the airflow from generating vortex and generating direction disorder at the position and guiding the direction of the airflow so that the airflow can stably flow into the carburetor at a flow speed.

Specifically, the uniform filter screen in this embodiment is provided with a plurality of uniform filter holes which are axially consistent with the air outlet pipe a and the air outlet pipe B. The filter holes can be formed by welding a plurality of metal plates transversely, longitudinally, obliquely and the like in a staggered manner, and can also be integrally formed in manufacturing. And the cross-sectional shape of the filtration equalizing holes can be selected from, but not limited to, a circle, a triangle, a quadrangle, a polygon, a special shape, a honeycomb shape and the like. In this embodiment, a honeycomb shape is used.

In addition, the uniform filter screen in the embodiment may be integrally arranged with the air outlet pipe a and the air outlet pipe B during manufacturing, the uniform filter screen may be welded in the air outlet pipe a and the air outlet pipe B, or the uniform filter screen may be detachably mounted in the air outlet pipe a and the air outlet pipe B.

In this embodiment, the uniform filtering net 2 has an outer cylinder wall 21, a plurality of uniform filtering holes 22 are uniformly arranged in the outer cylinder wall, the plurality of uniform filtering holes are uniformly arranged along a circumference, and the direction of the filtering holes is along the axial direction of the outer cylinder wall. In this embodiment, the air outlet pipe a and the air outlet pipe B are respectively provided with a welding spot (hole), and when the uniform filter screen is installed at the air outlet pipe a and the air outlet pipe B, the air outlet pipe a and the air outlet pipe B are respectively welded with the uniform filter screen at the welding spot by adopting a welding mode. And then, before installing the carburetor, the uniform filter screens are respectively installed in the air outlet pipe A and the air outlet pipe B.

The uniform filter screen in the embodiment has a certain length in the axial direction, for example, 20-45mm may be selected, and the selection is not limited to 20mm, 25mm, 30mm, 35mm, 40mm or 45 mm. And of course, the length of the air outlet pipe A and the air outlet pipe B can be set according to the specific length. However, the axial length of the uniform filter screen is designed to be too short, which may result in poor flow guiding effect, and the axial length of the uniform filter screen is designed to be 30mm in this embodiment, which may result in large wind resistance.

Because the pressure stabilizing box in the embodiment is adopted, the direction of the uniform filtering holes on the uniform filtering net is consistent with the axial direction of the air outlet pipe A and the air outlet pipe B. In this way, the formation of vortices in the gas flow at the stabiliser end due to changes in direction can be avoided. The air flow is guided through the filter holes and is divided into parallel small beams through the filter holes which are parallel to each other and have a certain length, so that the air flow can stably and uniformly enter the carburetor through the pressure stabilizing box.

The air intake system of the aircraft engine of the embodiment is mainly applied to four-cylinder horizontally-opposed aircraft engines. One pressure stabilizing box and one air source are adopted, and air is supplied to 4 cylinder bodies simultaneously. And through the pressure stabilizing box that the middle part was admitted air, both ends were given vent to anger to and through setting up the equal filter screen in pressure stabilizing box, can promote the air current evenly and steadily be distributed to four intake pipes in, further enter into among the cylinder body.

Claims

1. The utility model provides an aeroengine air intake system's surge tank, includes surge tank body, its characterized in that: the middle part of pressure stabilizing box body is provided with the air inlet, the both ends of pressure stabilizing box body are divided and are established gas outlet A and gas outlet B.

2. A surge tank according to claim 1, wherein: an air outlet pipe A is arranged at the air outlet A, and an air outlet pipe B is arranged at the air outlet B.

3. A surge tank according to claim 2, wherein: and a uniform filter screen is arranged in the air outlet pipe A and/or the air outlet pipe B.

4. A surge tank according to claim 3, wherein: the equal filter screen is provided with filter holes, the equal filter screen is installed in the air outlet pipe A or the air outlet pipe B, and the direction of the filter holes is consistent with the axial direction of the air outlet pipe A or the air outlet pipe B.

5. A surge tank according to claim 4, wherein: the equal filter screens are fixedly arranged in the air outlet pipe A and the air outlet pipe B, or the equal filter screens are separately arranged in the air outlet pipe A and the air outlet pipe B.

6. A surge tank according to claim 5, wherein: the uniform filter screen is provided with an outer cylinder wall, a plurality of filter holes which are parallel to each other are uniformly distributed in the outer cylinder wall, the direction of the filter holes is along the axial direction of the outer cylinder wall, and the uniform filter screen is respectively welded with the air inlet pipe A and the air inlet pipe B.

7. A surge tank according to claim 3, 4, 5 or 6, wherein: the axial length of the uniform filter screen is 20-45 mm.

8. A surge tank according to claim 7, wherein: the axial length of the filter screen is 30 mm.

9. An aircraft engine air intake system comprising the surge tank defined in claim 1, 2, 3, 4, 5, 6, 7 or 8, wherein: the air outlet A of the pressure stabilizing box body is connected with a carburetor A, the carburetor A is connected with an air inlet manifold A, the air outlet B of the pressure stabilizing box body is connected with a carburetor B, the carburetor B is connected with an air inlet manifold B, the air inlet manifold A is Y-shaped, the air inlet manifold A is provided with an inlet connected with the carburetor A and two air inlet pipes respectively connected with a cylinder body, the air inlet manifold B is Y-shaped, and the air inlet manifold B is provided with an inlet connected with the carburetor B and two air inlet pipes respectively connected with the cylinder body.