阅读说明：本技术 一种旋流进气埋入式进气道及其工作方式，以及飞行器 (Swirl air inlet embedded type air inlet channel, working mode thereof and aircraft ) 是由 万丽颖 王天绥 肖毅 任志文 赵胜海 安平 陈尊敬 赵政衡 王春利 万志明 戴佳 于 2019-12-05 设计创作，主要内容包括：本发明实施例公开了一种旋流进气埋入式进气道及其工作方式,以及飞行器,包括：设置于弹体腹部的埋入式进气道,以及设置于弹体腹部、且位于进气道前端位置的旋流流动控制装置；其中,旋流流动控制装置,用于改变气流流动方向、气流流体结构以及气流能量分布,使得气流进入进气道之前形成能量分布均匀的旋流式气流流体。本发明实施例解决了现有用于减少低能量附面层对进气道性能影响的方式,由于无法完全解决由于低能量附面层在进气道前导流面形成的分离包,而影响埋入式进气道的性能。(The embodiment of the invention discloses a swirl air inlet embedded type air inlet channel and a working mode thereof, and an aircraft, wherein the swirl air inlet embedded type air inlet channel comprises: the device comprises an embedded air inlet channel arranged at the belly of the projectile body and a rotational flow control device arranged at the belly of the projectile body and positioned at the front end of the air inlet channel; the rotational flow control device is used for changing the flow direction of the airflow, the structure of the airflow fluid and the energy distribution of the airflow, so that the rotational flow type airflow fluid with uniform energy distribution is formed before the airflow enters the air inlet channel. The embodiment of the invention solves the problem that the performance of the embedded air inlet is influenced because a separation packet formed by the low-energy boundary layer on the front flow guide surface of the air inlet cannot be completely solved in the conventional mode for reducing the influence of the low-energy boundary layer on the performance of the air inlet.)

1. A swirl flow inlet submerged inlet duct, comprising: the device comprises an embedded air inlet channel arranged at the belly of the projectile body and a rotational flow control device arranged at the belly of the projectile body and positioned at the front end of the air inlet channel;

the rotational flow control device is used for changing the flow direction of the airflow, the structure of the airflow fluid and the energy distribution of the airflow, so that the rotational flow type airflow fluid with uniform energy distribution is formed before the airflow enters the air inlet channel.

2. The swirl inlet submerged entry channel of claim 1, wherein the submerged entry channel comprises an inlet, an inlet internal channel, and an inlet outlet;

and the airflow fluid entering the channel in the air inlet from the air inlet is cyclone airflow fluid with uniform energy distribution after the cyclone flow control device performs cyclone treatment.

3. The swirl inlet submerged inlet according to claim 2, wherein the swirl flow control device is located at a position where a low energy flow boundary layer is formed at the belly of the projectile.

4. The swirl inlet submerged intake duct of claim 3, wherein the swirl flow control device is located at a distance of between 500 and 700 meters from the intake port.

5. The buried swirl inlet of any of claims 1-4 where the swirl flow control device is a swirl generator.

6. The submerged swirl inlet according to any of claims 1-4,

the negative pressure that the engine produced is less than far away to the even spiral-flow type air current fluidic influence of energy distribution in the passageway in the intake duct the negative pressure that the engine produced has the air current fluidic influence of low energy flow boundary layer in the passageway in the intake duct.

7. The buried swirl inlet of claim 6 wherein the swirling air flow fluid entering the channel in the inlet with a uniform internal energy distribution does not form a separation pocket at the leading flow surface of the inlet under the force of the negative pressure of the engine.

8. A working method of the swirl intake embedded type air inlet is characterized in that the working method is implemented by adopting the swirl intake embedded type air inlet according to any one of claims 1 to 7, and the working method comprises the following steps:

carrying out rotational flow treatment on the low-energy flow boundary layer through a rotational flow control device which is arranged at the belly of the projectile body and is positioned at the front end of the air inlet;

the rotational flow treatment on the low-energy flow boundary layer changes the airflow flowing direction, the airflow fluid structure and the airflow energy distribution, so that the rotational flow type airflow fluid with uniform energy distribution is formed before the airflow enters the air inlet channel.

9. An aircraft, characterized in that it comprises: a missile and a swirl inlet submerged inlet channel as claimed in any one of claims 1 to 6;

the swirl air inlet embedded type air inlet channel is arranged at the belly of the projectile body and is formed with a region with a low-energy flow boundary layer.

Technical Field

The present application relates to, but is not limited to, aircraft inlet technology, and more particularly to a swirl flow inlet embedded inlet and operating method thereof, and an aircraft.

Background

In order to meet the requirements of low flight resistance, high stealth performance and multi-platform mounting of an aeroweapon, an embedded air inlet channel with small external size, low resistance and high stealth is widely used by the aeroweapon.

The performance of the air inlet channel, which is an important component of an aircraft propulsion system, will directly affect operational performance, while the performance of the buried air inlet channel is greatly affected by a low-energy inflow boundary layer, and particularly in a low-flow state, the low-energy inflow boundary layer sucked by the air inlet channel forms a large separation on a front flow guide surface under the influence of a counter pressure gradient (i.e., negative pressure generated by an engine), and the total pressure recovery coefficient and the circumferential distortion index of the air inlet channel are sharply reduced.

However, the above methods for reducing the influence of the low energy boundary layer on the performance of the air intake duct can only change the flow direction of the low energy boundary layer or discharge part of the low energy boundary layer out of the air intake duct, and the problem of the separation packet formed by the low energy boundary layer cannot be completely solved.

Disclosure of Invention

In order to solve the technical problem, embodiments of the present invention provide a swirl intake embedded intake duct, a working method thereof, and an aircraft, so as to solve the problem that in the existing method for reducing the influence of a low energy boundary layer on the performance of an intake duct, the influence on the performance of an embedded intake duct due to a separation packet formed by the low energy boundary layer on a front flow guide surface of the intake duct cannot be completely solved.

The embodiment of the invention provides a swirl air inlet embedded type air inlet, which comprises: the device comprises an embedded air inlet channel arranged at the belly of the projectile body and a rotational flow control device arranged at the belly of the projectile body and positioned at the front end of the air inlet channel;

the rotational flow control device is used for changing the flow direction of the airflow, the structure of the airflow fluid and the energy distribution of the airflow, so that the rotational flow type airflow fluid with uniform energy distribution is formed before the airflow enters the air inlet channel.

Optionally, in the swirl intake buried intake duct described above, the buried intake duct includes an intake port, an intake duct inner passage, and an intake duct outlet;

and the airflow fluid entering the channel in the air inlet from the air inlet is cyclone airflow fluid with uniform energy distribution after the cyclone flow control device performs cyclone treatment.

Optionally, in the swirl inflow embedded air inlet described above, the swirl flow control device is disposed at a position where a low-energy flow boundary layer is formed on the abdomen of the projectile body.

Optionally, in the swirl-inlet submerged inlet described above, the distance between the swirl flow control device and the inlet is between 500 m and 700 m.

Alternatively, in a swirl-inlet submerged inlet as described above,

the rotational flow control device is a vortex generator.

Alternatively, in a swirl-inlet submerged inlet as described above,

the negative pressure that the engine produced is less than far away to the even spiral-flow type air current fluidic influence of energy distribution in the passageway in the intake duct the negative pressure that the engine produced has the air current fluidic influence of low energy flow boundary layer in the passageway in the intake duct.

Optionally, in the swirl intake embedded intake duct as described above, the swirl airflow entering the passage in the intake duct and having a uniform internal energy distribution does not form a separation packet on the front flow surface of the intake duct under the action of the negative pressure of the engine.

The embodiment of the invention also provides a working method of the swirl air inlet embedded type air inlet, which is implemented by adopting any one of the swirl air inlet embedded type air inlets, and comprises the following steps:

carrying out rotational flow treatment on the low-energy flow boundary layer through a rotational flow control device which is arranged at the belly of the projectile body and is positioned at the front end of the air inlet;

the rotational flow treatment on the low-energy flow boundary layer changes the airflow flowing direction, the airflow fluid structure and the airflow energy distribution, so that the rotational flow type airflow fluid with uniform energy distribution is formed before the airflow enters the air inlet channel.

An embodiment of the present invention further provides an aircraft, including: a missile and a swirl flow inlet submerged inlet channel as described in any one of the above;

the swirl air inlet embedded type air inlet channel is arranged at the belly of the projectile body and is formed with a region with a low-energy flow boundary layer.

According to the swirl air inlet embedded type air inlet channel and the working mode thereof and the aircraft provided by the embodiment of the invention, the swirl flow control device is arranged at the belly of the projectile body and the front end position of the air inlet channel, so that airflow fluid containing a low-energy flow boundary layer is converted into swirl airflow fluid with uniform energy distribution, the energy distribution of the airflow entering a channel in the air inlet channel is uniform, the total energy is improved, the influence of backpressure gradient on the airflow in the channel in the air inlet channel is small, the recovery coefficient of the air inlet channel under medium and small flow can be greatly improved, the energy uniformity of an outlet of the air inlet channel is greatly improved, and the circumferential distortion index of the outlet of the air.

Drawings

The accompanying drawings are included to provide a further understanding of the invention and are incorporated in and constitute a part of this specification, illustrate embodiments of the invention and together with the example serve to explain the principles of the invention and not to limit the invention.

Fig. 1 is a schematic structural diagram of a swirl intake embedded intake duct according to an embodiment of the present invention;

FIG. 2 is a schematic fluid flow diagram of a gas stream formed without the use of a cyclonic flow control device in an embodiment of the invention;

FIG. 3 is a schematic representation of the flow stream created using a cyclonic flow control apparatus in an embodiment of the invention;

FIG. 4 is a schematic illustration of the flow stream formed without the use of a cyclonic flow control device in an embodiment of the invention;

FIG. 5 is a schematic diagram of the flow stream formed using the cyclonic flow control apparatus of an embodiment of the present invention.

Detailed Description

In order to make the objects, technical solutions and advantages of the present invention more apparent, embodiments of the present invention will be described in detail below with reference to the accompanying drawings. It should be noted that the embodiments and features of the embodiments in the present application may be arbitrarily combined with each other without conflict.

The technical solution provided by the present invention is explained in detail by several specific examples below. The following specific embodiments of the present invention may be combined, and the same or similar concepts or processes may not be described in detail in some embodiments.

Fig. 1 is a schematic structural diagram of a swirl intake embedded intake duct according to an embodiment of the present invention. The swirl intake embedded intake duct provided by the embodiment may include: the device comprises an embedded air inlet channel 4 arranged at the belly of the projectile body and a rotational flow control device 2 arranged at the belly of the projectile body and positioned at the front end of the air inlet channel 4;

the rotational flow control device 2 in the embodiment of the invention is used for changing the flow direction, the flow structure and the energy distribution of the air flow, so that the rotational flow type air flow with uniform energy distribution is formed before the air flow enters the air inlet.

The embodiment of the invention provides a swirl air inlet embedded type air inlet and an aircraft using the same, aiming at the problems that the current embedded type air inlet is influenced by low energy flow of a boundary layer and the performance of the air inlet in a medium and small flow state is poor. The swirling flow control device 2 according to the embodiment of the present invention may be, for example, a vortex generator.

According to the swirl air inlet embedded type air inlet provided by the embodiment of the invention, the swirl flow control device 2 is arranged at a certain position of the front end of the air inlet 4 at the belly of the projectile body 1, so that the flow direction, the flow structure and the energy distribution of the air flow can be changed under the action of the swirl flow control device 2, and the swirl air flow with uniform energy distribution is formed before the air flow enters the air inlet.

Fig. 2 is a schematic view of an airflow formed by a swirling flow control device in an embodiment of the present invention, and fig. 3 is a schematic view of an airflow formed by a swirling flow control device in an embodiment of the present invention.

Referring to fig. 1 to 3, the embedded air inlet 4 includes an air inlet 3, an inner channel of the air inlet 4 and an air inlet outlet 5, an air flow passes through the projectile body 1 to form a low energy adhesion surface layer with a certain thickness, the air flow direction and the fluid structure are changed by the swirl flow control device 2, and a swirl fluid with uniform energy distribution is formed after a certain distance development, enters the inner channel of the embedded air inlet 4 through the embedded air inlet 3, and flows out through the embedded air inlet outlet 5 after flowing sufficiently in the embedded air inlet 4, namely, enters the engine air inlet.

In the embodiment of the present invention, the swirling flow control device 2 may be disposed at a position where a low-energy flow boundary layer is formed at the belly of the projectile body 1, for example, the distance between the swirling flow control device 2 and the air inlet 3 may be 500 m to 700 m.

It should be noted that fig. 1 to fig. 3 are illustrated by taking a mode that the belly of the projectile is above as an example, fig. 4 is a schematic diagram of an airflow formed by a rotational flow control device in an embodiment which is not adopted in the present invention, and fig. 5 is a schematic diagram of an airflow formed by a rotational flow control device in an embodiment which is adopted in the present invention.

As shown in fig. 2 and 4, since the negative pressure generated by the engine forms a backpressure gradient, in the case of not using the swirl flow control device in the embodiment of the present invention, the low-energy flow boundary layer forms a large separation packet on the front flow surface of the inlet channel under the influence of the backpressure gradient.

As shown in fig. 3 and 5, although the negative pressure generated by the engine forms a backpressure gradient, in the case of using the swirling flow control device in the embodiment of the present invention, since the air flow entering the passage in the air intake duct 4 from the air intake 3 is a swirling air flow having uniform energy distribution after being subjected to swirling treatment by the swirling flow control device 2, even under the action of the negative pressure of the engine, a separation pocket is not formed on the front guide surface of the air intake duct.

As can be seen from fig. 4 and 5, the influence of the negative pressure generated by the engine on the swirling airflow with uniform energy distribution in the channel in the air inlet channel is much smaller than the influence of the negative pressure generated by the engine on the airflow with low energy flow boundary layer in the channel in the air inlet channel.

According to the swirl air inlet embedded type air inlet provided by the embodiment of the invention, the swirl flow control device is arranged at the belly of the projectile body and positioned at the front end of the air inlet, and airflow fluid containing a low-energy flow boundary layer is converted into swirl airflow fluid with uniform energy distribution, so that the energy distribution of the airflow entering a channel in the air inlet is uniform, the total energy is improved, the influence of adverse pressure gradient on the airflow in the channel in the air inlet is small, the coefficient of recovery of the air inlet under medium and small flow can be greatly improved, the energy uniformity of an outlet of the air inlet is greatly improved, and the circumferential distortion index of the outlet of the air inlet is reduced.

Based on the fixed-geometry wide-speed-range supersonic inlet provided by the embodiment of the invention, the embodiment of the invention also provides a working method of the swirl air inlet embedded type inlet, which comprises the following steps:

carrying out rotational flow treatment on the low-energy flow boundary layer through a rotational flow control device which is arranged at the belly of the projectile body and is positioned at the front end of the air inlet;

the rotational flow treatment of the low-energy flow boundary layer changes the flow direction of the air flow, the structure of the air flow fluid and the energy distribution of the air flow, so that the rotational flow type air flow fluid with uniform energy distribution is formed before the air flow enters the air inlet channel.

The working method of the fixed swirl intake embedded air inlet provided by the embodiment of the invention is the working method executed by the swirl intake embedded air inlet in each embodiment of the invention, and has the same technical effect as the swirl intake embedded air inlet.

Based on the embedded swirl intake duct provided by the embodiment of the invention, the embodiment of the invention also provides an aircraft, for example, a missile, and the aircraft can comprise: a missile, a swirl intake submerged inlet as provided in any embodiment of the invention;

referring to fig. 1 to 5, the swirl inlet buried type air inlet is disposed at the belly of a projectile body and is formed with a region of a low-energy flow boundary layer.

The embodiment of the invention is suitable for the embedded air inlet which utilizes the vortex generator to generate the swirl air inlet and the aircraft using the device.

Although the embodiments of the present invention have been described above, the above description is only for the convenience of understanding the present invention, and is not intended to limit the present invention. It will be understood by those skilled in the art that various changes in form and details may be made therein without departing from the spirit and scope of the invention as defined by the appended claims.