CN112623197A - Shunting device for cavity noise control and noise control method - Google Patents
Shunting device for cavity noise control and noise control method Download PDFInfo
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- CN112623197A CN112623197A CN202011612744.0A CN202011612744A CN112623197A CN 112623197 A CN112623197 A CN 112623197A CN 202011612744 A CN202011612744 A CN 202011612744A CN 112623197 A CN112623197 A CN 112623197A
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- cavity
- flow
- flow dividing
- noise control
- noise
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C23/00—Influencing air flow over aircraft surfaces, not otherwise provided for
- B64C23/005—Influencing air flow over aircraft surfaces, not otherwise provided for by other means not covered by groups B64C23/02 - B64C23/08, e.g. by electric charges, magnetic panels, piezoelectric elements, static charges or ultrasounds
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- G—PHYSICS
- G10—MUSICAL INSTRUMENTS; ACOUSTICS
- G10K—SOUND-PRODUCING DEVICES; METHODS OR DEVICES FOR PROTECTING AGAINST, OR FOR DAMPING, NOISE OR OTHER ACOUSTIC WAVES IN GENERAL; ACOUSTICS NOT OTHERWISE PROVIDED FOR
- G10K11/00—Methods or devices for transmitting, conducting or directing sound in general; Methods or devices for protecting against, or for damping, noise or other acoustic waves in general
- G10K11/16—Methods or devices for protecting against, or for damping, noise or other acoustic waves in general
- G10K11/161—Methods or devices for protecting against, or for damping, noise or other acoustic waves in general in systems with fluid flow
Abstract
The invention provides a shunting device for cavity noise control and a noise control method, which are used for reducing the noise in a cavity. The invention arranges a flow dividing device at a proper position in the front of the cavity, namely behind the front edge, and forces the separated airflow at the front edge of the cavity to generate further separated flow: a part of the airflow deflects upwards to reduce the impact on the rear wall of the cavity; the other part of the airflow deflects downwards to enter the cavity, so that disturbance waves fed back from the rear wall are weakened; meanwhile, disturbance is generated on the flow field form in the cavity, and the self-oscillation is avoided. The shunting device for controlling the cavity noise has a simple structural form and is easy to process; the used cavity noise control method is effective, and the cavity noise can be obviously reduced.
Description
Technical Field
The invention belongs to the field of airplane noise control, and relates to a shunting device for cavity noise control.
Background
Cavity structures are common structures of aircraft, such as landing gear bays, slat/flap bays, equipment bays, and magazine bays. During the taking off and landing process and the flying process of the airplane, when the cabin door is opened, the cavity is exposed to airflow, the incoming flow shear layer in the front of the cavity interacts with the airflow in the cavity, and self-oscillation is possibly generated to generate strong noise. On one hand, strong noise can affect the environment around an airport, causing noise pollution; on the other hand, strong cavity noise can lead to structural damage inside the cavity, equipment malfunction or malfunction, and in severe cases, flight safety can be compromised.
The current common cavity noise control device is to install a spoiler device, such as a swash plate device, a flat plate device, a sawtooth device, a cylindrical device, a perforated plate device, etc., at the front edge of the cavity. These devices have a cavity noise suppression effect, but these devices are closely related to the incoming flow velocity.
Disclosure of Invention
The purpose of the invention is as follows: a shunt device for cavity noise control and a noise control method are provided, which are used for reducing the noise inside a cavity.
The invention arranges a flow dividing device at a proper position in the front of the cavity, namely behind the front edge, and forces the separated airflow at the front edge of the cavity to generate further separated flow: a part of the airflow deflects upwards to reduce the impact on the rear wall of the cavity; the other part of the airflow deflects downwards to enter the cavity, so that disturbance waves fed back from the rear wall are weakened; meanwhile, disturbance is generated on the flow field form in the cavity, and the self-oscillation is avoided. The shunting device for controlling the cavity noise has a simple structural form and is easy to process; the used cavity noise control method is effective, and the cavity noise can be obviously reduced.
The technical scheme of the invention is as follows: in one aspect, a shunt device for cavity noise control is provided, which comprises a cavity 1 and a shunt device 2; the cavity 1 is a cavity structure with an opening at one side; the flow divider 2 is arranged in front of the cavity opening side and behind the front edge;
the flow dividing device 2 is of a wedge-shaped structure or a plate-shaped structure; the maximum height h of the flow dividing means 2 is greater than the maximum thickness t.
Further, the centre line of the flow dividing device 2 coincides with the plane of the cavity opening.
Further, the distance s from the rear end surface of the flow dividing device 2 far away from the airflow incoming direction to the front edge of the cavity is greater than the maximum thickness t of the flow dividing device 2;
the maximum thickness t refers to the maximum distance between the front end face and the rear end face of the flow dividing device 2.
Further, the ratio of the distance s to the length L of the cavity is not more than 5%.
Further, the ratio of the maximum thickness t of the flow dividing device 2 to the length L of the cavity is not more than 1%.
Further, the ratio of the maximum height h of the flow dividing device 2 to the height D of the cavity is not more than 10%.
Further, the width of the flow dividing device 2 corresponds to the width of the cavity 1.
In another aspect, there is provided a cavity noise control method using the shunt device as described above, the method including:
the flow divider 2 is arranged in front of the cavity opening side and behind the front edge;
the flow dividing device 2 is of a wedge-shaped structure or a plate-shaped structure; the maximum height h of the flow dividing device 2 is larger than the maximum thickness t;
the noise inside the cavity is reduced by adjusting any one or more of the maximum thickness t, the maximum height h, the wedge angle and the distance s of the flow dividing device 2.
The technical effects are as follows: according to the generation mechanism of cavity noise, the invention changes the flow field form in the cavity by adjusting the flow of the separated air flow at the front edge of the cavity, and meanwhile generates disturbance to the flow in the cavity, thereby avoiding the occurrence of self-oscillation. Analysis shows that the surface noise of the wall plate in different areas of the cavity is reduced by 7.3dB on average.
Drawings
FIG. 1 is a schematic structural view of a cavity shunting device;
fig. 2 is a schematic structural diagram of the wedge-shaped shunt device.
Detailed Description
Fig. 1 is a schematic structural diagram of a cavity shunt device, and in combination with fig. 1, in this embodiment, a shunt device for cavity noise control is provided, which includes a cavity 1 and a shunt device 2; the cavity 1 is a cavity structure with an opening at one side; the flow dividing device 2 is arranged in front of the cavity opening side and behind the front edge. The flow dividing device 2 is of a wedge-shaped structure or a plate-shaped structure; the maximum height h of the flow dividing means 2 is greater than the maximum thickness t.
The present embodiment forces the separation flow at the front edge of the cavity to generate a further separation flow by arranging the flow dividing device 2 in front of the cavity opening side and behind the front edge: a part of the airflow deflects upwards to reduce the impact on the rear wall of the cavity; the other part of the airflow deflects downwards to enter the cavity, so that disturbance waves fed back from the rear wall are weakened; meanwhile, disturbance is generated on the flow field form in the cavity, and the self-oscillation is avoided.
In this embodiment, the center line of the flow divider 2 coincides with the plane of the cavity opening, so that the flow divider is easy to install, and the maximum flow division is realized.
In addition, the distance s from the rear end surface of the flow dividing device 2 far away from the airflow incoming direction to the front edge of the cavity is larger than the maximum thickness t of the flow dividing device 2; the maximum thickness t refers to the maximum distance between the front end face and the rear end face of the flow dividing device 2. When s is 0 or s is smaller than the thickness of the flow divider 2, the flow divider 2 of the present invention will be the same as the conventional flow divider at the leading edge of the cavity 1.
In this embodiment, it is obtained through Computational Fluid Dynamics (CFD), computational aeroacoustics (CAA) or wind tunnel test methods that when the flow dividing device 2 satisfies one or more of the following conditions, the noise reduction can be significantly achieved, and the specific conditions are:
the ratio of the distance s to the length L of the cavity is not more than 5%; the ratio of the maximum thickness t of the flow dividing device 2 to the length L of the cavity is not more than 1%; the ratio of the maximum height h of the flow dividing device 2 to the height D of the cavity is not more than 10 percent; the width of the flow dividing device 2 corresponds to the width of the cavity 1.
Fig. 2 is a schematic structural diagram of a wedge-shaped flow divider, and when the flow divider 2 is of a wedge-shaped structure, the values of the windward angles α and β of the flow divider 2 are as follows: alpha is more than or equal to 0 degree and less than or equal to 90 degrees, beta is more than or equal to 0 degree and less than or equal to 90 degrees.
In this embodiment, a method for controlling cavity noise is provided by using the shunt device, where the method includes: the flow divider 2 is arranged in front of the cavity opening side and behind the front edge; the flow dividing device 2 is of a wedge-shaped structure or a plate-shaped structure; the maximum height h of the flow dividing device 2 is larger than the maximum thickness t; by adjusting any one or more of the maximum thickness t, the maximum height h, the wedge angle and the distance s of the flow dividing device 2, the separation degree of the incoming flow of the front edge can be further adjusted to reduce the noise inside the cavity.
The shunting device for controlling the cavity noise has a simple structural form and is easy to process; the used cavity noise control method is effective, and the cavity noise can be obviously reduced.
Claims (8)
1. The shunt device for cavity noise control is characterized by comprising a cavity (1) and a shunt device (2); the cavity (1) is of a cavity structure with an opening at one side; the flow dividing device (2) is arranged at the front part of the cavity opening side and behind the front edge;
the flow dividing device (2) is of a wedge-shaped structure or a plate-shaped structure; the maximum height h of the flow dividing device (2) is larger than the maximum thickness t.
2. A shunt device according to claim 1, characterized in that the centre line of the shunt device (2) coincides with the plane of the cavity opening.
3. A flow divider device according to claim 1, characterized in that the distance s of the rear end surface of the flow divider device (2) facing away from the incoming flow direction of the air flow from the front edge of the cavity is greater than the maximum thickness t of the flow divider device (2);
the maximum thickness t refers to the maximum distance between the front end face and the rear end face of the flow dividing device (2).
4. A shunt device according to claim 3, wherein the ratio of the distance s to the length L of the cavity is no more than 5%.
5. A shunt device according to claim 3, wherein the ratio of the maximum thickness t of the shunt device (2) to the length L of the cavity is not more than 1%.
6. A shunt device according to claim 3, characterized in that the ratio of the maximum height h of the shunt device (2) to the height D of the cavity is not more than 10%.
7. A shunt device according to claim 3, wherein the width of the shunt device (2) corresponds to the width of the cavity (1).
8. A cavity noise control method using the flow dividing device of any one of claims 1 to 7, the method comprising:
arranging the flow dividing device (2) in front of the cavity opening side and behind the front edge;
the flow dividing device (2) adopts a wedge-shaped structure or a plate-shaped structure; the maximum height h of the flow dividing device (2) is greater than the maximum thickness t;
and the noise inside the cavity is reduced by adjusting any one or more of the maximum thickness t, the maximum height h, the wedge angle and the distance s of the flow dividing device (2).
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| Application Number | Priority Date | Filing Date | Title |
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| CN202011612744.0A CN112623197B (en) | 2020-12-29 | 2020-12-29 | Shunt device for cavity noise control and noise control method |
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| CN202011612744.0A CN112623197B (en) | 2020-12-29 | 2020-12-29 | Shunt device for cavity noise control and noise control method |
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| CN112623197A true CN112623197A (en) | 2021-04-09 |
| CN112623197B CN112623197B (en) | 2023-08-04 |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114735203A (en) * | 2022-06-13 | 2022-07-12 | 中国空气动力研究与发展中心高速空气动力研究所 | Noise suppression device for triangular prism-shaped aircraft weapons cabin |
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|---|---|---|---|---|
| US5340054A (en) * | 1991-02-20 | 1994-08-23 | The United States Of America As Represented By The Secretary Of The Navy | Suppressor of oscillations in airframe cavities |
| US5699981A (en) * | 1996-03-18 | 1997-12-23 | The United States Of America As Represented By The Secretary Of The Air Force | Aircraft cavity acoustic resonance suppression system |
| US6050527A (en) * | 1997-12-19 | 2000-04-18 | The Boeing Company | Flow control device to eliminate cavity resonance |
| EP1247735A2 (en) * | 2001-04-06 | 2002-10-09 | DLR Deutsches Zentrum für Luft- und Raumfahrt e.V. | Method to reduce vibrations in cavities and surface arrangement in a fluid flow |
| CN102862676A (en) * | 2012-09-29 | 2013-01-09 | 中国航天空气动力技术研究院 | Noise reduction method for weapon cabin of supersonic aircraft on basis of turbulent flow on front-edge surface |
| US20150292533A1 (en) * | 2014-04-09 | 2015-10-15 | University Of Florida Research Foundation | Noise control of cavity flows using active and/or passive receptive channels |
| CN111120461A (en) * | 2020-01-19 | 2020-05-08 | 中国人民解放军海军工程大学 | Underwater flow excitation cavity noise control device |
-
2020
- 2020-12-29 CN CN202011612744.0A patent/CN112623197B/en active Active
Patent Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5340054A (en) * | 1991-02-20 | 1994-08-23 | The United States Of America As Represented By The Secretary Of The Navy | Suppressor of oscillations in airframe cavities |
| US5699981A (en) * | 1996-03-18 | 1997-12-23 | The United States Of America As Represented By The Secretary Of The Air Force | Aircraft cavity acoustic resonance suppression system |
| US6050527A (en) * | 1997-12-19 | 2000-04-18 | The Boeing Company | Flow control device to eliminate cavity resonance |
| EP1247735A2 (en) * | 2001-04-06 | 2002-10-09 | DLR Deutsches Zentrum für Luft- und Raumfahrt e.V. | Method to reduce vibrations in cavities and surface arrangement in a fluid flow |
| CN102862676A (en) * | 2012-09-29 | 2013-01-09 | 中国航天空气动力技术研究院 | Noise reduction method for weapon cabin of supersonic aircraft on basis of turbulent flow on front-edge surface |
| US20150292533A1 (en) * | 2014-04-09 | 2015-10-15 | University Of Florida Research Foundation | Noise control of cavity flows using active and/or passive receptive channels |
| CN111120461A (en) * | 2020-01-19 | 2020-05-08 | 中国人民解放军海军工程大学 | Underwater flow excitation cavity noise control device |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114735203A (en) * | 2022-06-13 | 2022-07-12 | 中国空气动力研究与发展中心高速空气动力研究所 | Noise suppression device for triangular prism-shaped aircraft weapons cabin |
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| CN112623197B (en) | 2023-08-04 |
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