阅读说明：本技术 一种进气道辅助进气装置及具有其的飞机 (Air inlet channel auxiliary air inlet device and airplane with same ) 是由 刘方良 孙智孝 王霄 朱宇 孙超 于 2019-09-23 设计创作，主要内容包括：本申请属于飞机发动机进气道辅助进气设计技术领域,具体涉及一种进气道辅助进气装置,包括：辅助进气活门,设置在飞机发动机进气道底部开设的辅助进气口中,该辅助进气口连通飞机起落架舱；辅助进气活门由飞机发动机进气道与飞机起落架舱内的压差驱动,当飞机发动机进气道内的压力小于飞机起落架舱内的压力时,辅助进气活门打开；当飞机发动机进气道内的压力大于飞机起落架舱内的压力时,辅助进气活门关闭。此外,还涉及一种具有上述进气道辅助进气装置的飞机,该飞机的辅助进气口位于飞机发动机进气道的前段。(The application belongs to the technical field of aircraft engine intake duct auxiliary air intake design, concretely relates to intake duct auxiliary air intake device, include: the auxiliary air inlet valve is arranged in an auxiliary air inlet formed at the bottom of an air inlet passage of an aircraft engine, and the auxiliary air inlet is communicated with an aircraft landing gear cabin; the auxiliary air inlet valve is driven by the pressure difference between an air inlet passage of the aircraft engine and the cabin of the aircraft landing gear, and is opened when the pressure in the air inlet passage of the aircraft engine is smaller than the pressure in the cabin of the aircraft landing gear; and when the pressure in the air inlet passage of the aircraft engine is greater than the pressure in the landing gear cabin of the aircraft, the auxiliary air inlet valve is closed. In addition, the aircraft with the air inlet auxiliary air inlet device is also related, and an auxiliary air inlet of the aircraft is positioned at the front section of an air inlet of an engine of the aircraft.)

1. an intake port auxiliary intake device, comprising:

the auxiliary air inlet valve (1) is arranged in an auxiliary air inlet formed at the bottom of an aircraft engine air inlet (2), and the auxiliary air inlet is communicated with an aircraft landing gear cabin (3);

The auxiliary air inlet valve (1) is driven by the pressure difference between the air inlet channel (2) of the aircraft engine and the landing gear cabin (3),

when the pressure in the aircraft engine air inlet channel (2) is smaller than the pressure in the aircraft landing gear cabin (3), the auxiliary air inlet valve (1) is opened;

and when the pressure in the aircraft engine air inlet channel (2) is greater than the pressure in the aircraft landing gear cabin (3), the auxiliary air inlet valve (1) is closed.

2. The port auxiliary intake apparatus according to claim 1,

Further comprising:

an auxiliary air inlet duct (4) having an inlet located in the landing gear bay (3) of the aircraft and an outlet communicating with the auxiliary air inlet; the auxiliary air inlet valve (1) is arranged in an inlet of the auxiliary air inlet channel (4).

3. The port auxiliary intake apparatus according to claim 2,

The auxiliary air inlet valve (1) is of an inward opening type.

4. The port auxiliary intake apparatus according to claim 2,

The auxiliary air inlet channel (4) and a forward included angle between the air inlet channels (2) of the aircraft engine are larger than a backward included angle.

5. the port auxiliary intake apparatus according to claim 4,

the forward included angle between the auxiliary air inlet channel (4) and the aircraft engine air inlet channel (2) is 50 degrees;

The auxiliary air inlet channel (4) and a backward included angle between the air inlet channels (2) of the aircraft engine are 30 degrees.

6. the port auxiliary intake apparatus according to claim 2,

The inlet area of the auxiliary air inlet channel (4) is 0.1-0.3 of the throat area of the aircraft engine air inlet channel (2).

7. The port auxiliary intake apparatus according to claim 6,

The slenderness ratio of the inlet of the auxiliary air inlet channel (4) is 2-4.

8. The port auxiliary intake apparatus according to claim 2,

The auxiliary air inlet valve (1) is hinged with the wall surface of the inlet of the auxiliary air inlet channel (4);

the intake apparatus is assisted to intake duct still includes:

And the stop block (5) is arranged at the inlet of the auxiliary air inlet channel (4), and the auxiliary air inlet valve (1) is abutted against the stop block (5) when closed.

9. the port auxiliary intake apparatus according to claim 8,

The auxiliary air inlet valve (1) is hinged to the wall surface of the inlet of the auxiliary air inlet channel (4) through a hinge shaft (6).

10. An aircraft, characterized in that it has an inlet auxiliary air inlet device according to any one of claims 1-9, and that the auxiliary air inlet is situated in the front section of the aircraft engine inlet (2).

Technical Field

The application belongs to the technical field of auxiliary air inlet design of aircraft engine air inlet channels, and particularly relates to an auxiliary air inlet device of an air inlet channel and an aircraft with the same.

Background

the auxiliary inlet valve is arranged on the aircraft engine air inlet channel, so that auxiliary air inlet to the engine air inlet channel is opened when the aircraft takes off, the total pressure recovery coefficient of the air inlet channel is improved, the engine installation thrust can be further improved, and the take-off running distance of the aircraft can be shortened.

the auxiliary air inlet valve arranged on the current airplane has the following defects:

1) The aircraft is arranged outside the aircraft, the aerodynamic appearance of the aircraft is damaged, and the stealth performance of the aircraft is influenced;

2) The opening and closing of the airplane are controlled by the driving mechanism, the operation and the control are complex, the opening and the closing of the airplane cannot be ensured to be timely, in addition, the driving mechanism increases the weight burden of the airplane and aggravates the shortage of precious space resources on the airplane;

3) And the improvement of the total pressure recovery coefficient of the air inlet passage of the engine is difficult to guarantee.

the present application is made in view of the above-mentioned drawbacks of the prior art.

disclosure of Invention

the present application is directed to an auxiliary inlet device for an inlet duct and an aircraft having the same, which overcome or alleviate at least one of the disadvantages of the prior art.

The technical scheme of the application is as follows:

one aspect provides a port assist intake apparatus, including:

The auxiliary air inlet valve is arranged in an auxiliary air inlet formed at the bottom of an air inlet passage of an aircraft engine, and the auxiliary air inlet is communicated with an aircraft landing gear cabin;

The auxiliary air inlet valve is driven by the pressure difference between an air inlet of an aircraft engine and the cabin of the aircraft landing gear,

When the pressure in the air inlet channel of the aircraft engine is smaller than the pressure in the landing gear cabin of the aircraft, the auxiliary air inlet valve is opened;

and when the pressure in the air inlet passage of the aircraft engine is greater than the pressure in the landing gear cabin of the aircraft, the auxiliary air inlet valve is closed.

according to at least one embodiment of the present application, further comprising:

the inlet of the auxiliary air inlet channel is positioned in the landing gear cabin of the airplane, and the outlet of the auxiliary air inlet channel is communicated with the auxiliary air inlet; the auxiliary intake valve is disposed in an inlet of the auxiliary intake duct.

According to at least one embodiment of the present application, the auxiliary intake shutter is inwardly open.

According to at least one embodiment of the present application, a forward angle between the auxiliary inlet and the aircraft engine inlet is greater than a rearward angle.

According to at least one embodiment of the present application, the forward angle between the auxiliary inlet duct and the aircraft engine inlet duct is 50 °;

The backward included angle between the auxiliary air inlet channel and the air inlet channel of the aircraft engine is 30 degrees.

according to at least one embodiment of the application, the inlet area of the auxiliary inlet is 0.1-0.3 of the throat area of the aircraft engine inlet.

According to at least one embodiment of the present application, the inlet of the auxiliary inlet has a slenderness ratio of 2-4.

According to at least one embodiment of the application, the auxiliary air inlet valve is hinged with the wall surface of the inlet of the auxiliary air inlet channel through a hinge shaft;

the intake passage auxiliary intake device further includes:

and the stop block is arranged at the inlet of the auxiliary air inlet channel and is abutted against the stop block when the auxiliary air inlet valve is closed.

in another aspect, an aircraft is provided, which has any one of the above-mentioned auxiliary air intake devices for an air intake duct, and the auxiliary air intake is located at a front section of an air intake duct of an engine of the aircraft.

drawings

FIG. 1 is a schematic structural diagram of an auxiliary intake device of an intake port according to an embodiment of the present disclosure;

Fig. 2 is a schematic view of an auxiliary intake valve provided in an embodiment of the present application when opened;

fig. 3 is a schematic view of the auxiliary intake valve provided in the embodiment of the present application when it is closed;

wherein:

1-auxiliary air intake valve; 2-aircraft engine inlet; 3-aircraft landing gear bay; 4-auxiliary air inlet channel; 5-a stop block; 6-articulated shaft.

Detailed Description

the present application will be described in further detail with reference to the following drawings and examples. It is to be understood that the specific embodiments described herein are merely illustrative of the relevant application and are not limiting of the application. It should be noted that, for convenience of description, only the portions related to the present application are shown in the drawings.

It should be noted that the embodiments and features of the embodiments in the present application may be combined with each other without conflict. The present application will be described in detail below with reference to the embodiments with reference to the attached drawings.

It should be noted that in the description of the present application, the terms of direction or positional relationship indicated by the terms "center", "upper", "lower", "left", "right", "vertical", "horizontal", "inner", "outer", etc. are based on the directions or positional relationships shown in the drawings, which are merely for convenience of description, and do not indicate or imply that the device or element must have a specific orientation, be constructed and operated in a specific orientation, and thus, should not be construed as limiting the present application. Furthermore, the terms "first," "second," and "third" are used for descriptive purposes only and are not to be construed as indicating or implying relative importance.

Furthermore, it should be noted that, in the description of the present application, unless otherwise explicitly specified or limited, the terms "mounted," "connected," and "connected" are to be construed broadly, e.g., as being fixedly connected, detachably connected, or integrally connected; can be mechanically or electrically connected; they may be connected directly or indirectly through intervening media, or they may be interconnected between two elements. The specific meaning of the above terms in the present application can be understood by those skilled in the art as the case may be.

The present application is described in further detail below with reference to fig. 1 to 3.

one aspect provides a port assist intake apparatus, including:

The auxiliary air inlet valve 1 is arranged in an auxiliary air inlet formed at the bottom of an aircraft engine air inlet 2, and the auxiliary air inlet is communicated with an aircraft landing gear cabin 3;

The auxiliary air inlet valve 1 is driven by the pressure difference between an air inlet passage 2 of an aircraft engine and a landing gear cabin 3 of the aircraft,

When the pressure in the aircraft engine air inlet 2 is smaller than the pressure in the aircraft landing gear cabin 3, the auxiliary air inlet valve 1 is opened;

when the pressure in the aircraft engine inlet duct 2 is greater than the pressure in the aircraft landing gear bay 3, the auxiliary inlet flap 1 is closed.

For the air inlet auxiliary air inlet device disclosed in the above embodiment, as can be understood by those skilled in the art, when an aircraft takes off and lands, the landing gear bay door of the aircraft is opened, the air pressure in the landing gear bay 3 of the aircraft is consistent with the outside air pressure, the pressure in the air inlet channel 2 of the aircraft engine is smaller than the pressure in the landing gear bay 3 of the aircraft, the auxiliary air inlet valve 1 is opened, air is introduced into the air inlet channel 1 of the aircraft engine, and the total pressure recovery coefficient is improved; when the airplane flies, the cabin door of the landing gear is closed, the pressure in the air inlet channel 2 of the airplane engine is greater than the pressure in the landing gear cabin 3 of the airplane, and the auxiliary air inlet valve 1 is closed.

for the air inlet auxiliary air inlet device disclosed in the above embodiment, as can be further understood by those skilled in the art, the auxiliary air inlet valve 1 is hidden inside the landing gear bay 3 of the aircraft, and the aerodynamic shape of the surface of the aircraft is not damaged when the auxiliary air inlet valve 1 is opened and closed, so that the stealth performance of the aircraft can be effectively ensured.

In some optional embodiments, further comprising:

an auxiliary air inlet 4, the inlet of which is positioned in the landing gear cabin 3 of the airplane, and the outlet of which is communicated with the auxiliary air inlet; the auxiliary air inlet valve 1 is arranged in the inlet of the auxiliary air inlet channel 4; the auxiliary air inlet valve 1 is of an inward opening type.

to the air inlet auxiliary air inlet device disclosed in the above embodiment, those skilled in the art can understand that the auxiliary air inlet valve 1 is designed to be inward-opening, which can avoid the interference between the auxiliary air inlet valve 1 and the equipment in the landing gear bay 3, in addition, the outlet of the auxiliary air inlet 4 is arranged to be communicated with the auxiliary air inlet, the auxiliary air inlet valve 1 is arranged in the inlet of the auxiliary air inlet 4, which can avoid the interference to the flow field in the auxiliary air inlet when the auxiliary air inlet valve 1 is opened, and it can be easily understood that the auxiliary air inlet 4 is located in the landing gear bay 3 and is communicated with the auxiliary air inlet arranged at the bottom of the air inlet 2 of the aircraft engine, which can be designed to have shorter length, so as to reduce the weight of the auxiliary air inlet.

in some alternative embodiments, the angle between the auxiliary inlet duct 4 and the aircraft engine inlet duct 2 is greater in the forward direction than in the rearward direction.

For the air intake duct auxiliary air intake device disclosed in the above embodiment, it can be understood by those skilled in the art that the auxiliary air intake duct 4 adopts a differential forward flow design, and the forward included angle between the auxiliary air intake duct 4 and the aircraft engine air intake duct 2 is larger than the backward included angle, so that the uniformity of air intake mixing can be improved, and the flow separation can be reduced.

in some alternative embodiments, the angle between the auxiliary inlet duct 4 and the aircraft engine inlet duct 2 is 50 °;

The rearward angle between the auxiliary inlet duct 4 and the aircraft engine inlet duct 2 is 30 °.

In some alternative embodiments, the inlet area of the auxiliary inlet 4 is 0.1 to 0.3 of the throat area of the aircraft engine inlet 2;

The inlet length-to-fineness ratio of the auxiliary air inlet channel 4 is 2-4.

for the intake port auxiliary intake device disclosed in the above embodiment, it can be understood by those skilled in the art that the length-to-fineness ratio of the inlet of the auxiliary intake port 4 is designed to be 2-4, that is, the inlet of the auxiliary intake port 4 is designed to be slit-shaped and has a larger length-to-fineness ratio, so that under the condition that the areas of the inlets of the auxiliary intake ports 4 are the same, a larger intake efficiency and a larger mixing uniformity can be obtained, thereby improving the total pressure recovery coefficient and reducing the distortion.

in some alternative embodiments, the auxiliary intake valve 1 is hinged with the wall surface of the inlet of the auxiliary intake duct 4 through a hinge shaft 6;

the intake passage auxiliary intake device further includes:

And the stop block 5 is arranged at the inlet of the auxiliary air inlet channel 4 and is abutted against the stop block 5 when the auxiliary air inlet valve 1 is closed.

For the auxiliary air intake device of the air intake duct disclosed in the above embodiment, it can be understood by those skilled in the art that the stopper 5 has a limiting effect on the auxiliary air intake valve 1 when the auxiliary air intake valve 1 is closed, so as to ensure the closing effect of the auxiliary air intake valve 1 at the inlet of the auxiliary air intake duct 4.

Another aspect provides an aircraft having any one of the above-mentioned auxiliary inlet devices, wherein the auxiliary inlet is located at the front section of the aircraft engine inlet 2.

In order to achieve a good stealth effect of the current aircraft, an inlet lip edge of an engine inlet channel of the current aircraft is usually designed to be extremely thin and swept backwards, so that when the aircraft takes off, large-area separated flow appears near the inlet of the engine inlet channel of the aircraft, and the throat is easy to block; in addition, the bent inner pipeline is designed to shield an engine inlet, flow separation is further aggravated, total pressure recovery is reduced, and engine installation thrust is reduced.

the aircraft that this application embodiment discloses, it sets up the anterior segment at aircraft engine intake duct 2 with supplementary air inlet, can improve total pressure recovery for the low energy separation flow injection energy near the import, has guaranteed the intensive mixing, reduces the distortion.

So far, the technical solutions of the present application have been described in connection with the preferred embodiments shown in the drawings, but it is easily understood by those skilled in the art that the scope of the present application is obviously not limited to these specific embodiments. Equivalent changes or substitutions of related technical features can be made by those skilled in the art without departing from the principle of the present application, and the technical scheme after the changes or substitutions will fall into the protection scope of the present application.