CN108019295B - Turbulent flow noise reduction device for aircraft engine - Google Patents
Turbulent flow noise reduction device for aircraft engine Download PDFInfo
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- CN108019295B CN108019295B CN201711350041.3A CN201711350041A CN108019295B CN 108019295 B CN108019295 B CN 108019295B CN 201711350041 A CN201711350041 A CN 201711350041A CN 108019295 B CN108019295 B CN 108019295B
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- culvert
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- convergence
- convergence section
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K1/00—Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto
- F02K1/44—Nozzles having means, e.g. a shield, reducing sound radiation in a specified direction
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- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Exhaust Silencers (AREA)
Abstract
The invention provides a turbulence noise reduction device of an aeroengine, which comprises an inner culvert cylinder, a cone sleeved in an inner cavity of the inner culvert cylinder, a plurality of turbulence bodies arranged on the wall of the same half part of the inner culvert cylinder, and an outer culvert cylinder sleeved outside the inner culvert cylinder through connection with the turbulence bodies; the inner culvert cylinder body consists of a first convergence section, a straight section and a second convergence section, wherein the straight section and the second convergence section are respectively butted with two ends of the first convergence section; the disturbing fluid is a plate-shaped member, two ends of the disturbing fluid are respectively butted and arranged at the butt joint position between the two convergence sections and the end part of one end of the outer culvert cylinder, and the other end of the outer culvert cylinder is far away from the second convergence section; the cone is coaxially sleeved on one side of the second convergence section of the inner culvert cylinder body. The turbulent flow noise reduction device provided by the invention can cause deviation of high-speed air flow of the culvert caused by direction deviation of air flow of the culvert and the culvert, change the propagation path of jet flow noise, enable the jet flow noise to radiate upwards, weaken radiation downwards, and further enhance the noise reduction effect.
Description
Technical Field
The invention belongs to the field of structural design of an aircraft engine, particularly relates to the field of an aircraft engine spray pipe, and particularly relates to a turbulence and noise reduction device of the aircraft engine.
Background
Strict airworthiness regulations of aircraft noise are formulated and promulgated by international civil aviation organization and various national civil aviation organizations, and engine jet noise is one of the main noise sources of the aircraft. Therefore, it is necessary to develop a preliminary study of jet flow noise reduction for a turbofan engine with a large bypass ratio. The existing noise reduction scheme surrounds the content high-speed airflow through the outer content low-speed airflow and plays a role in shielding the noise generated by the content high-speed airflow, so that the jet flow noise of an engine is reduced, but the noise reduction scheme has the following defects: although the outer culvert low-speed airflow has a shielding effect on the inner culvert high-speed airflow, the shielding effect is poor and the noise reduction effect is weak due to the symmetric reflection of noise generated by the inner culvert high-speed airflow.
Disclosure of Invention
The invention aims to provide a turbulence and noise reduction device for an aeroengine, which overcomes or alleviates at least one of the defects in the prior art.
The purpose of the invention is realized by the following technical scheme: a turbulence noise reduction device for an aircraft engine comprises an inner culvert cylinder, a cone sleeved in an inner cavity of the inner culvert cylinder, a plurality of turbulence bodies arranged on the wall of the same half part of the inner culvert cylinder, and an outer culvert cylinder sleeved outside the inner culvert cylinder through connection with the turbulence bodies; the inner culvert cylinder body is composed of a first convergence section, a straight section and a second convergence section, wherein the straight section and the second convergence section are respectively in butt joint with two ends of the first convergence section; the disturbing fluid is a plate-shaped member, two ends of the disturbing fluid are respectively butted and arranged at the butt joint position between the two convergence sections and the end part of one end of the outer culvert cylinder, and the other end of the outer culvert cylinder is far away from the second convergence section; the cone is coaxially sleeved on one side of the second convergence section of the inner culvert cylinder body.
Preferably, the turbulent flow bodies are arranged in three groups.
Preferably, a gap of 30mm to 50mm is left between the turbulent fluid and the end part of one end of the outer culvert cylinder connected with the turbulent fluid.
The turbulent flow noise reduction device for the aircraft engine has the advantages that the device can cause deviation of inner culvert high-speed airflow due to direction deviation of inner culvert airflow and outer culvert airflow, changes a propagation path of jet flow noise, enables the jet flow noise to be mainly radiated upwards, weakens radiation downwards, and accordingly enhances the noise reduction effect.
Drawings
FIG. 1 is a schematic structural diagram of a turbulence and noise reduction device of an aircraft engine according to the present invention;
FIG. 2 is a schematic view of the operation principle of the turbulence and noise reduction device of the aero-engine of the present invention.
Reference numerals:
1-outer culvert cylinder, 2-inner culvert cylinder, 3-turbulent flow and 4-cone.
Detailed Description
In order to make the implementation objects, technical solutions and advantages of the present invention clearer, the technical solutions in the embodiments of the present invention will be described in more detail below with reference to the accompanying drawings in the embodiments of the present invention. In the drawings, the same or similar reference numerals denote the same or similar elements or elements having the same or similar functions throughout. The described embodiments are only some, but not all embodiments of the invention. The embodiments described below with reference to the drawings are illustrative and intended to be illustrative of the invention and are not to be construed as limiting the invention. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.
The turbulent flow noise reduction device of the aero-engine of the present invention will be further described in detail with reference to the accompanying drawings.
As shown in fig. 1 and 2, the turbulence noise reduction device for the aircraft engine is used for reducing jet flow noise of an engine nozzle and comprises a containing cylinder 2, a cone 4 sleeved in an inner cavity of the containing cylinder 2, a plurality of turbulence bodies 3 arranged on the same half cylinder wall of the containing cylinder 2, and a containing cylinder 1 sleeved outside the containing cylinder 2 through being connected with the turbulence bodies 3. The method specifically comprises the following steps:
the inner culvert cylinder 2 is composed of a first convergence section, a straight section and a second convergence section, wherein the straight section and the second convergence section are respectively in butt joint with two ends of the first convergence section, and the butt joint between the first convergence section and the second convergence section is arranged at one side of the outer culvert cylinder 1 in a deviation manner. The disturbing fluid 3 is a plate-shaped member, two ends of the disturbing fluid are respectively butted at the butt joint between the two convergence sections and one end part (namely, the outlet A) of the outer culvert cylinder 1, wherein three groups of disturbing fluid 3 are selected and arranged, the three groups of disturbing fluid are uniformly distributed on the upper half area of the outer wall surface of the outer culvert cylinder 1, the disturbing fluid 3 is selected to leave a gap of 30 mm-50 mm from the end part of one end of the outer culvert cylinder 1 connected with the disturbing fluid, and the other end of the outer culvert cylinder 1 is far away from the second convergence section for arrangement. And the cone 4 is coaxially sleeved on one side of the second convergent section of the inner culvert cylinder 2.
The working principle of the turbulence and noise reduction device for an aircraft engine according to the present invention is briefly described below with reference to fig. 1 and 2.
The outer culvert airflow C has a local low-pressure area after passing through the turbulent flow body 3, the direction of the airflow at the outlet A of the outer culvert cylinder body 1 is changed, and the airflow upwards deflects by a certain angle relative to the inner culvert airflow B. The deviation of the directions of the connotative air flow B and the connotative air flow C causes deviation of connotative high-speed air flow, changes the propagation path of jet flow noise, enables the jet flow noise to be mainly radiated upwards, weakens the radiation downwards, and further enhances the noise reduction effect.
The above description is only for the specific embodiment of the present invention, but the scope of the present invention is not limited thereto, and any changes or substitutions that can be easily conceived by those skilled in the art within the technical scope of the present invention are included in the scope of the present invention. Therefore, the protection scope of the present invention shall be subject to the protection scope of the appended claims.
Claims (3)
1. A turbulence noise reduction device of an aircraft engine is characterized by comprising a containing cylinder body (2), a cone (4) sleeved in an inner cavity of the containing cylinder body (2), a plurality of turbulence bodies (3) arranged on the same half cylinder wall of the containing cylinder body (2), and an outer containing cylinder body (1) sleeved outside the containing cylinder body (2) through being connected with the turbulence bodies (3); the inner culvert cylinder (2) is composed of a first convergence section, a straight section and a second convergence section, wherein the straight section and the second convergence section are respectively in butt joint with two ends of the first convergence section, and the butt joint between the first convergence section and the second convergence section is arranged towards one side of the outer culvert cylinder (1); the disturbing fluid (3) is a plate-shaped member, two ends of the disturbing fluid are respectively arranged at the butt joint between the two convergence sections and the end part of one end of the external culvert cylinder (1) in a butt joint mode, and the other end of the external culvert cylinder (1) is far away from the second convergence section; the cone (4) is coaxially sleeved on one side of the second convergent section of the inner culvert cylinder body (2).
2. Aeroengine flow-disturbing noise-reducing device according to claim 1, wherein said flow-disturbing bodies (3) are provided in three groups.
3. The aeroengine flow-disturbing noise-reducing device of claim 1, wherein a gap of 30mm to 50mm is left between the turbulent flow body (3) and the end of one end of the culvert cylinder (1) connected with the turbulent flow body.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201711350041.3A CN108019295B (en) | 2017-12-15 | 2017-12-15 | Turbulent flow noise reduction device for aircraft engine |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201711350041.3A CN108019295B (en) | 2017-12-15 | 2017-12-15 | Turbulent flow noise reduction device for aircraft engine |
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| Publication Number | Publication Date |
|---|---|
| CN108019295A CN108019295A (en) | 2018-05-11 |
| CN108019295B true CN108019295B (en) | 2021-03-30 |
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Families Citing this family (2)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN114878175B (en) * | 2022-04-15 | 2024-02-23 | 中国航发沈阳发动机研究所 | Outer culvert area synchronous regulating mechanism of inner culvert and outer culvert split-flow exhaust system |
| CN115030837B (en) * | 2022-08-10 | 2022-11-08 | 中国空气动力研究与发展中心低速空气动力研究所 | Spout noise reduction device |
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US7870722B2 (en) * | 2006-12-06 | 2011-01-18 | The Boeing Company | Systems and methods for passively directing aircraft engine nozzle flows |
| FR2921700A1 (en) * | 2007-09-28 | 2009-04-03 | Snecma Sa | HOUSING FOR A TURBOMACHINE TUBE WITH PATTERNS WITH JET NOISE REDUCTION |
| FR2969122B1 (en) * | 2010-12-20 | 2012-12-28 | Aircelle Sa | INTERNAL STRUCTURE FOR A NACELLE FOR A DOUBLE TURBOREACTOR FLOW OF AN AIRCRAFT |
| FR2975135B1 (en) * | 2011-05-12 | 2016-07-22 | Snecma | REVERSE CONE OF MICROJETS TURNOVER TURNOVER |
| CN103133180B (en) * | 2011-11-25 | 2015-06-10 | 中航商用航空发动机有限责任公司 | Low jet flow noise spray pipe and turbofan engine including the same |
| CN104405530B (en) * | 2014-10-16 | 2016-03-02 | 南京航空航天大学 | Separately gas-discharging type turbofan engine exhausting and denoising system |
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| CN108019295A (en) | 2018-05-11 |
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