CN112623197B - Shunt device for cavity noise control and noise control method - Google Patents
Shunt device for cavity noise control and noise control method Download PDFInfo
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- CN112623197B CN112623197B CN202011612744.0A CN202011612744A CN112623197B CN 112623197 B CN112623197 B CN 112623197B CN 202011612744 A CN202011612744 A CN 202011612744A CN 112623197 B CN112623197 B CN 112623197B
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- dividing device
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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
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- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Physics & Mathematics (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Fluid Mechanics (AREA)
- Acoustics & Sound (AREA)
- Multimedia (AREA)
- Air-Flow Control Members (AREA)
- Current-Collector Devices For Electrically Propelled Vehicles (AREA)
Abstract
The invention provides a shunt 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 the front part of the cavity, namely at a proper position behind the front edge, so as to force the separated air flow at the front edge of the cavity to generate further separated flow: a part of the air flow deflects upwards, so that the impact on the rear wall of the cavity is reduced; the other part of the air flow deflects downwards to enter the cavity, so that disturbance waves fed back from the rear wall are weakened; meanwhile, disturbance is generated on the form of the flow field in the cavity, and the occurrence of self-oscillation is avoided. The cavity noise control flow dividing device designed by the invention has simple structural form and is easy to process; the cavity noise control method is effective, and can remarkably reduce cavity noise.
Description
Technical Field
The invention belongs to the field of aircraft noise control, and relates to a cavity noise control flow dividing device.
Background
The cavity structures are common structures of aircraft such as landing gear cabins, slat/wing-flap cabins, equipment cabins, and missile cabins. During the take-off and landing of the aircraft and during the flight, when the door is opened, the cavity is exposed to the air flow, and the incoming flow shear layer in the front of the cavity interacts with the air flow inside the cavity, which may generate self-oscillation and strong noise. On one hand, strong noise can influence the environment around an airport, so that noise pollution is caused; on the other hand, intense cavity noise can lead to damage to the internal structure of the cavity, equipment failure or misoperation, and in severe cases, the flight safety can be compromised.
The current common cavity noise control device is to install turbulence devices such as a sloping plate device, a flat plate device, a sawtooth device, a cylindrical device, a perforated plate device and the like at the front edge of the cavity. These devices have a suppression effect on the cavity noise, but they have a close relationship with the incoming flow velocity.
Disclosure of Invention
The invention aims to: a shunt device and a noise control method for cavity noise control are provided, which are used for reducing the noise in the cavity.
The invention arranges a flow dividing device at the front part of the cavity, namely at a proper position behind the front edge, so as to force the separated air flow at the front edge of the cavity to generate further separated flow: a part of the air flow deflects upwards, so that the impact on the rear wall of the cavity is reduced; the other part of the air flow deflects downwards to enter the cavity, so that disturbance waves fed back from the rear wall are weakened; meanwhile, disturbance is generated on the form of the flow field in the cavity, and the occurrence of self-oscillation is avoided. The cavity noise control flow dividing device designed by the invention has simple structural form and is easy to process; the cavity noise control method is effective, and can remarkably reduce cavity noise.
The technical scheme of the invention is as follows: in one aspect, a cavity noise controlled shunt device is provided, comprising a cavity 1 and a shunt device 2; the cavity 1 is of a cavity structure with one side open; the flow dividing device 2 is arranged at the front part of the opening side of the cavity 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 shunt device 2 is greater than the maximum thickness t.
Further, the centre line of the shunt device 2 coincides with the plane of the cavity opening.
Further, the distance s between the rear end surface of the flow dividing device 2, which is far away from the airflow incoming direction, and the front edge of the cavity is larger than the maximum thickness t of the flow dividing device 2;
the maximum thickness t is 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 shunt device 2 to the length L of the cavity is not more than 1%.
Further, the ratio of the maximum height h of the shunt device 2 to the height D of the cavity is not more than 10%.
Further, the width of the shunt 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 comprising:
the flow dividing device 2 is arranged at the front part of the opening side of the cavity 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 shunt device 2 is greater than the maximum thickness t;
by adjusting any one or more of the maximum thickness t, the maximum height h, the wedge angle, the distance s of the shunt device 2, the noise inside the cavity is reduced.
The technical effects are as follows: according to the cavity noise generation mechanism, the flow regulation is carried out on the separated air flow at the front edge of the cavity, so that the form of the flow field in the cavity is changed, meanwhile, the flow in the cavity is disturbed, and the occurrence of self-oscillation is avoided. 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 diagram of a cavity splitting assembly;
fig. 2 is a schematic structural view of a wedge-shaped shunt device.
Detailed Description
Fig. 1 is a schematic structural diagram of a cavity shunt device, and in combination with fig. 1, the present embodiment provides a shunt device controlled by cavity noise, which includes a cavity 1 and a shunt device 2; the cavity 1 is of a cavity structure with one side open; the shunt device 2 is arranged in front of the open side of the cavity, 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 shunt device 2 is greater than the maximum thickness t.
By arranging the flow dividing means 2 in front of the open side of the cavity and behind the leading edge, the separated air flow at the leading edge of the cavity is forced to create a further separated flow: a part of the air flow deflects upwards, so that the impact on the rear wall of the cavity is reduced; the other part of the air flow deflects downwards to enter the cavity, so that disturbance waves fed back from the rear wall are weakened; meanwhile, disturbance is generated on the form of the flow field in the cavity, and the occurrence of self-oscillation is avoided.
In this embodiment, the center line of the shunt device 2 coincides with the plane of the cavity opening, so that the installation of the shunt device is easy, and the maximum shunt is realized.
In addition, the distance s between the rear end surface of the flow dividing device 2, which is far away from the airflow incoming direction, and the front edge of the cavity is larger than the maximum thickness t of the flow dividing device 2; the maximum thickness t is 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 less than the thickness of the shunt device 2, the shunt device 2 of the present invention will be identical to the prior art cavity 1 leading edge spoiler.
In this embodiment, by Computational Fluid Dynamics (CFD), computational aero-acoustic (CAA) or wind tunnel test methods, it is obtained that when the shunt device 2 satisfies one or more of the following conditions, the following 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 shunt device 2 to the length L of the cavity is not more than 1%; the ratio of the maximum height h of the shunt device 2 to the height D of the cavity is not more than 10%; the width of the shunt device 2 corresponds to the width of the cavity 1.
Fig. 2 is a schematic structural diagram of a wedge-shaped splitting device, and when the splitting device 2 has a wedge-shaped structure, the values of angles of attack α and β of the splitting device 2 are as follows: alpha is more than or equal to 0 degree and less than or equal to 90 degrees, and beta is more than or equal to 0 degree and less than or equal to 90 degrees.
In this embodiment, with the shunt device as described above, there is provided a cavity noise control method, the method including: the flow dividing device 2 is arranged at the front part of the opening side of the cavity 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 shunt device 2 is greater than the maximum thickness t; by adjusting any one or more of the maximum thickness t, the maximum height h, the wedge angle, the distance s of the shunt device 2, the degree of separation of the incoming flow at the leading edge can be further adjusted to reduce noise inside the cavity.
The cavity noise control flow dividing device designed by the invention has simple structural form and is easy to process; the cavity noise control method is effective, and can remarkably reduce cavity noise.
Claims (5)
1. A cavity noise control shunt device, which is characterized by comprising a cavity (1) and a shunt device (2); the cavity (1) is of a cavity structure with one side open; the flow dividing device (2) is arranged at the front part of the opening side of the cavity 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 ratio of the maximum thickness t of the shunt 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%;
the central line of the shunt device (2) coincides with the plane of the cavity opening; the flow dividing device (2) enables the gas flow to generate separation flow: a part of the air flow deflects upwards, so that the impact on the rear wall of the cavity is reduced; the other part of the air flow deflects downwards to enter the cavity, so that disturbance waves fed back from the rear wall are weakened; meanwhile, disturbance is generated on the form of the flow field in the cavity, and the occurrence of self-oscillation is avoided.
2. A flow dividing device according to claim 1, characterized in that the distance s of the rear end surface of the flow dividing device (2) facing away from the direction of incoming flow of the air flow from the front edge of the cavity is greater than the maximum thickness t of the flow dividing device (2);
the maximum thickness t is the maximum distance between the front end face and the rear end face of the flow dividing device (2).
3. The shunt device according to claim 2, wherein the ratio of the distance s to the length L of the cavity is not more than 5%.
4. A shunt device according to claim 2, characterised in that the width of the shunt device (2) corresponds to the width of the cavity (1).
5. A cavity noise control method using the shunt device according to any one of claims 1 to 4, characterized in that the method comprises:
the flow dividing device (2) is arranged at the front part of the opening side of the cavity 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 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 noise inside the cavity is reduced.
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| 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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| Publication Number | Publication Date |
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| CN112623197A CN112623197A (en) | 2021-04-09 |
| CN112623197B true CN112623197B (en) | 2023-08-04 |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| CN114735203B (en) * | 2022-06-13 | 2022-09-23 | 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 |
Citations (6)
| 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 |
| 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 |
Family Cites Families (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US9746010B2 (en) * | 2014-04-09 | 2017-08-29 | University Of Florida Research Foundation, Incorporated | Noise control of cavity flows using active and/or passive receptive channels |
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- 2020-12-29 CN CN202011612744.0A patent/CN112623197B/en active Active
Patent Citations (6)
| 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 |
| 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 |
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| CN112623197A (en) | 2021-04-09 |
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