CN104908972A - Splicing units of noise reduction flow guide wall for aircraft ground test - Google Patents
Splicing units of noise reduction flow guide wall for aircraft ground test Download PDFInfo
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- CN104908972A CN104908972A CN201510332483.XA CN201510332483A CN104908972A CN 104908972 A CN104908972 A CN 104908972A CN 201510332483 A CN201510332483 A CN 201510332483A CN 104908972 A CN104908972 A CN 104908972A
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Abstract
The invention discloses splicing units of a noise reduction flow guide wall for an aircraft ground test. The splicing units are transversely spliced to form the wall, and windward sides of the splicing units are in arc shapes capable of guiding the air flow into air in an inclining manner; the splicing units comprise a stainless steel micro-hole plate, a sound absorption material plate and a galvanized steel plate in sequence from the windward sides to leeward sides; the flow guide wall is fastened on the ground foundation, and a multi-way sound absorption structure is adopted in the windward sides to reduce the noise; the arc-shaped windward sides can guide the jetted airflow into the air, and therefore the noise and the wind speed are reduced to ensure safety of objects, vehicles and persons of the outer side of the flow guide wall and normal work; any safety hidden troubles are eliminated, noise pollution treatment is reinforced, residents in an airport and periphery are benefited, and the green airport is built.
Description
Technical field
The present invention relates to air equipment field, especially a kind of when the test run of aircraft floor high thrust for reducing the concatenation unit of the training wall of test run noise.
Background technology
The high temperature and high speed waste gas that aero-engine is discharged in high thrust test run situation threatens the safety of ground staff, vehicle.The noise that driving engine produces, up to 130 to 145 decibels, causes severe jamming to neighbouring resident and staff.For this reason, generally have employed water conservancy diversion and silencing unit abroad.
The sound barrier also energy water conservancy diversion up to 12 meters is built on Los Angeles,U.S airport; The baffle of Japan's Narita Airport construction up to 10 meters and the noise protection facility of multiple exhausting silencer combination; German designs in 2000 and be installed as jet deflector and sound barrier combination noise protection facility.
Review domestic, the construction of noise-reducing device is just at the early-stage.Trace it to its cause: one is low to the attention degree of water conservancy diversion noise reduction; Two is that noise-reducing device is many is monopolized by foreign technology, equipment manufacturing cost surprising (up to 4000-5000 ten thousand Renminbi), and domestic most unit is difficult to burden.Along with China's expanding economy, the impact of neighbouring personnel during aircraft test run and environment is more and more paid attention to, but proprietary technology level does not pass a test, though there are all theory visions, reliability and noise reduction are all difficult to meet the growing market demand in actual applications.So far market there is not yet the aircraft test run noise reduction training wall of a domestic independent development.
Summary of the invention
For the air-flow that in prior art, aero-engine produces when ground run near the problem that threatens of personnel and object, the object of this invention is to provide a kind of concatenation unit of aircraft floor test run noise reduction training wall, this concatenation unit adopts multiple tracks sound absorption structure to reduce wind and makes an uproar, with the noise that abundant absorption band width is different, the windward side of arc can be spliced by several concatenation units, the air-flow come by engine spray leads in the air instantaneously, from the object reduced outside noise and wind speed two aspect guarantee training wall and the safety of personnel.
For achieving the above object, technical scheme of the present invention is as follows:
A kind of concatenation unit of aircraft floor test run noise reduction training wall, by the horizontally-spliced one-tenth body of wall of several concatenation units, the windward side of this concatenation unit is in air-flow being tilted upward the aerial arc of guiding, and concatenation unit is followed successively by corrosion-resistant steel microwell plate, sound-absorbing panel, insulation board and panel, cavity layer and back shrouding from windward side to lee face.
Further, described corrosion-resistant steel microwell plate laminates up and down at the join domain of adjacent two described concatenation units.
Further, the bottom of concatenation unit is fixed in ground base by chemical anchor bolts.
Further, described concatenation unit is fixed on by crab-bolt and is positioned on the sub-truss of its lee face.
Further, described corrosion-resistant steel microwell plate is densely covered with the hole that diameter is 0.8-1.0mm, percentage of perforation is 9%-10%.
Further, described sound-absorbing panel is rubber and plastic boards, and its thickness is 20mm; Described insulation board and panel is rubber and plastic boards, and its thickness is 40mm.
Further, described cavity layer is that 40mm is thick, and its inside is provided with latticed skeleton.
Further, described back shrouding is zincing steel sheet.
The beneficial effect of aircraft floor high thrust test run noise reduction training wall of the present invention is: be 1. that the air-flow that aero-engine can eject by arc leads in the air instantaneously in the windward side of wind break wall, reduces the wind speed of wind break wall lee face side; 2. corrosion-resistant steel microwell plate, sound absorber flitch and zincing steel sheet three layers of sound absorption structure are set in windward side to absorb noise; 3. the lee face of wind break wall is provided with sub-truss, fixes wind break wall by the chemical anchor bolts of bottom and sub-truss, enable wind break wall bear the wind-force of 12 grades of effects; 4. the wind break wall of modularity is convenient to produce, transport and assembling, all adopting the anchor bolts such as chemical anchor bolts or corrosion-resistant steel self lock nut, promoting Joint strenght when assembling wind break wall and sub-truss; 5. low, the high financial profit of productive costs, the site use fees of aircraft test run in surface facility be 6000-16000 unit/time, and cost of the present invention is 200-300 ten thousand yuan, expectation can in 1.5-2 cost-recovering.
Accompanying drawing explanation
Fig. 1 is the structural representation of the concatenation unit of aircraft floor test run noise reduction training wall of the present invention;
Fig. 2 is the schematic diagram that concatenation unit of the present invention is arranged on sub-truss;
Fig. 3 is the schematic diagram of the lee face of training wall of the present invention;
Fig. 4 is one of training wall using state schematic diagram of the present invention;
Fig. 5 is training wall using state schematic diagram two of the present invention.
Detailed description of the invention
Below in conjunction with accompanying drawing, describe the specific embodiment of the present invention in detail.
As Fig. 1, Fig. 2, Fig. 3, shown in Fig. 4, for the specific embodiment of aircraft floor test run noise reduction training wall of the present invention, the concatenation unit of noise reduction training wall of aircraft floor high thrust test run in the present embodiment, by the horizontally-spliced one-tenth body of wall 2 of several concatenation units 1, the windward side of this concatenation unit 1 is in air-flow being tilted upward the aerial arc of guiding, concatenation unit 1 is followed successively by corrosion-resistant steel microwell plate 17 from windward side to lee face, sound-absorbing panel 18, insulation board and panel 15, cavity layer 16 and back shrouding 19, wherein, the corrosion-resistant steel microwell plate 17 of thickness t=1.0-1.2mm is densely covered with the hole that aperture is 0.8-1.0mm, be preferably 1.0mm, percentage of perforation is 9%-10%, sound-absorbing panel 18 is rubber and plastic boards, and its thickness is 20mm, insulation board and panel 15 is rubber and plastic boards, and its thickness is 40mm, cavity layer 16 is that 40mm is thick, and its inside is provided with latticed skeleton 22, back shrouding 19 is the zincing steel sheet of thickness t=1.0mm.Corrosion-resistant steel microwell plate 17 laminates up and down at the join domain of adjacent two concatenation units 1.The bottom of concatenation unit 1 is fixed in ground base 13 by chemical anchor bolts.Concatenation unit 1 is fixed on by crab-bolt and is positioned on the sub-truss 3 of its lee face.
Multiple concatenation unit 1 is had to be spliced into body of wall 2, body of wall 2 and sub-truss 3 form noise reduction training wall, body of wall 2 camber, wherein the side of body of wall 2 indent is windward side, the air-flow that aircraft sprays directly blows this side, and by windward side, air-flow is tilted upward guiding in the air, the side of body of wall 2 evagination is lee face, sub-truss 3 is fixed on this lee face, and the bottom of body of wall 2 and sub-truss 3 is all fixedly connected in ground base 13 by chemical anchor bolts.
Sub-truss 3 comprises arc skeleton 5, column 8, tie-beam and Curved beam 7,9, arc skeleton 5 is arranged along its length and is covered on the lee face of concatenation unit 1 junction, and be anchored fixing with body of wall 2, column 8 and arc skeleton 5 one_to_one corresponding, the upper end anchor connection of column 8 at arc skeleton 5 near body of wall 2 top place, chemical anchor bolts 14 anchor connection is passed through in ground base 13 in the lower end of column 8, two Curved beams 7,9 connect waist and the top of every root post 8 respectively, and form connecting joint with column 8 at waist.At connecting joint place, attaching parts 9 is set, arc skeleton 5 is provided with attaching parts 4,6, tie-beam 10 two ends are anchor connection attaching parts 4 and attaching parts 9 respectively, tie-beam 11 two ends are anchor connection attaching parts 9 and attaching parts 6 respectively, tie-beam 12 two ends are anchor connection attaching parts 6 and column 8 lower end respectively, forms multiple triangular framing unit with this between arc skeleton 5 and column 8.
Noise reduction training wall of the present invention can meet following all kinds of aircraft floor test run: from current maximum expanded letter machine A380 to expanded letter machine B747, A340, B777, B787, A330; Middle body machine B767, B757; Narrow body machine B737, A320, C919(Homemade Commercial) series aircraft, all kinds of type all can carry out test run in training wall.
Effective in order to detect effect of the present invention, applicant has invited Guangzhou mechanotronics environmental monitoring station to carry out noise and air monitoring to the current aircraft B777 training wall the biggest in the world of the present invention, with reference to figure 4, No. 10145th, the report literary name 09 monitoring address of this monitoring is in the aircraft maintenance company of White Cloud Airport Guangzhou, Guangzhou, testing airplane molded breadth body machine B777, engine type: GE90, thrust the biggest in the world is 10.5-11. ten thousand pounds, only drive right driving engine, test run thrust 100%, engine tail nozzle wind speed is 60m/s, noise level is 145dB, normal pressure and temperature is without rain.Test result shows, No. 1 measuring point place (within the walls): monitoring noise level is 116dB, wind speed 13.2m/s; No. 2 monitoring points place (wall is outer): monitoring noise level is 90.3 dB, wind speed 5.6 m/s; No. 3 monitoring points place (within the walls): monitoring noise level 110 dB, wind speed 12.8m/s; No. 4 monitoring points place (wall is outer): monitoring noise level 85.3 dB, wind speed 5.5m/s; No. 5 monitoring points place (wall is outer): monitoring noise level 92.5dB, wind speed 2.7m/s; No. 6 monitoring points place (at the training wall north out-of-bounds 1m): monitoring noise level is: 91.9dB, wind speed are not measured.The effect of reduction noise of the present invention and reduction wind speed clearly as can be seen here.
Applicant also invites Liao Huace detection technique Company Limited by Shares to carry out noise and air monitoring to training wall of the present invention, with reference to figure 5, this report number detected: EDD10G003149, detecting address is aerocraft test run level ground, international airport, Bao'an, Shenzhen, testing airplane model is A330 expanded letter machine, and engine thrust is 7.6 ten thousand pounds, and engine tail nozzle wind speed is 45-50m/s, noise level is 138-140dB, ambient wind velocity 4.2m/s without rain without thunder and lightning.Test result shows, A place, front monitoring point on the right side of training wall, and monitoring noise level is 121.5dB, wind speed 3.7m/s; A ' place, monitoring point after on the right side of training wall, monitoring noise level is 116.1dB, wind speed 5.6m/s; B place, front monitoring point on the left of training wall, monitoring noise level is 119.6dB, wind speed 4.1m/s; B ' place, monitoring point after on the left of training wall, monitoring noise level is 115.4dB, wind speed 5.8m/s; C place, line of centers 3m monitoring point after training wall, monitoring noise level is 87.5dB, wind speed 5.4m/s; C ' place, line of centers 10m monitoring point after training wall, monitoring noise level is 84.5dB, wind speed 5.2m/s.The effect of reduction noise of the present invention and reduction wind speed clearly as can be seen here.
Above-mentioned example is just for illustration of the present invention, and embodiments of the present invention are not limited to these examples, and what those skilled in the art made meets the various detailed description of the invention of inventive concept all within protection scope of the present invention.
Claims (8)
1. the aircraft floor test run concatenation unit of noise reduction training wall, it is characterized in that, by the horizontally-spliced one-tenth body of wall of several concatenation units, the windward side of this concatenation unit is in air-flow being tilted upward the aerial arc of guiding, and concatenation unit is followed successively by corrosion-resistant steel microwell plate, sound-absorbing panel, insulation board and panel, cavity layer and back shrouding from windward side to lee face.
2. concatenation unit as claimed in claim 1, it is characterized in that, described corrosion-resistant steel microwell plate laminates up and down at the join domain of adjacent two described concatenation units.
3. concatenation unit as claimed in claim 1, it is characterized in that, the bottom of concatenation unit is fixed in ground base by chemical anchor bolts.
4. concatenation unit as claimed in claim 1, it is characterized in that, described concatenation unit is fixed on by crab-bolt and is positioned on the sub-truss of its lee face.
5. concatenation unit as claimed in claim 1, it is characterized in that, described corrosion-resistant steel microwell plate is densely covered with the hole that diameter is 0.8-1.0mm, and percentage of perforation is 9%-10%.
6. concatenation unit as claimed in claim 1, it is characterized in that, described sound-absorbing panel is rubber and plastic boards, and its thickness is 20mm; Described insulation board and panel is rubber and plastic boards, and its thickness is 40mm.
7. concatenation unit as claimed in claim 1, it is characterized in that, described cavity layer is that 40mm is thick, and its inside is provided with latticed skeleton.
8. concatenation unit as claimed in claim 1, it is characterized in that, described back shrouding is zincing steel sheet.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510332483.XA CN104908972A (en) | 2015-06-16 | 2015-06-16 | Splicing units of noise reduction flow guide wall for aircraft ground test |
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| Application Number | Priority Date | Filing Date | Title |
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| CN201510332483.XA CN104908972A (en) | 2015-06-16 | 2015-06-16 | Splicing units of noise reduction flow guide wall for aircraft ground test |
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| CN104908972A true CN104908972A (en) | 2015-09-16 |
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| CN201510332483.XA Pending CN104908972A (en) | 2015-06-16 | 2015-06-16 | Splicing units of noise reduction flow guide wall for aircraft ground test |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112144431A (en) * | 2020-09-26 | 2020-12-29 | 威海广泰空港设备股份有限公司 | Airport runway sound insulation system |
| CN113815889A (en) * | 2021-10-15 | 2021-12-21 | 北京海航通达航空设备有限公司 | Shutter type aircraft engine wake flow protection special equipment |
Citations (7)
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| US3656576A (en) * | 1970-11-19 | 1972-04-18 | Gunter Gubela | Noise shield panels and method of fabrication |
| US4566558A (en) * | 1985-02-21 | 1986-01-28 | Marine Systems, Inc. | Noise barrier |
| CN1030389A (en) * | 1987-07-03 | 1989-01-18 | 赖恩荷德·E·马拉股份有限公司 | Under the stationary state of ground, eliminate because the protective device of the aero-engine noise that high-speed fuel gas stream causes |
| US5127609A (en) * | 1991-02-25 | 1992-07-07 | Lynn B Stanley | Jet blast deflector fence |
| JPH10278892A (en) * | 1997-04-01 | 1998-10-20 | Shimizu Corp | Sound absorption construction and aircraft engine test facility using it |
| US20100243369A1 (en) * | 2009-03-31 | 2010-09-30 | Nuform Building Technologies Inc. | Highway noise barrier |
| CN204750591U (en) * | 2015-06-16 | 2015-11-11 | 崔乃盛 | Take a trial run with concatenation unit that falls training wall of making an uproar in aircraft ground |
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2015
- 2015-06-16 CN CN201510332483.XA patent/CN104908972A/en active Pending
Patent Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3656576A (en) * | 1970-11-19 | 1972-04-18 | Gunter Gubela | Noise shield panels and method of fabrication |
| US4566558A (en) * | 1985-02-21 | 1986-01-28 | Marine Systems, Inc. | Noise barrier |
| CN1030389A (en) * | 1987-07-03 | 1989-01-18 | 赖恩荷德·E·马拉股份有限公司 | Under the stationary state of ground, eliminate because the protective device of the aero-engine noise that high-speed fuel gas stream causes |
| US5127609A (en) * | 1991-02-25 | 1992-07-07 | Lynn B Stanley | Jet blast deflector fence |
| JPH10278892A (en) * | 1997-04-01 | 1998-10-20 | Shimizu Corp | Sound absorption construction and aircraft engine test facility using it |
| US20100243369A1 (en) * | 2009-03-31 | 2010-09-30 | Nuform Building Technologies Inc. | Highway noise barrier |
| CN204750591U (en) * | 2015-06-16 | 2015-11-11 | 崔乃盛 | Take a trial run with concatenation unit that falls training wall of making an uproar in aircraft ground |
Non-Patent Citations (1)
| Title |
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| 齐文泉等: "飞机发动机地面试车强噪音和高速尾流的防护治理", 《2008中国航空维修论坛论文集》 * |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112144431A (en) * | 2020-09-26 | 2020-12-29 | 威海广泰空港设备股份有限公司 | Airport runway sound insulation system |
| CN112144431B (en) * | 2020-09-26 | 2021-09-07 | 威海广泰空港设备股份有限公司 | Airport runway sound insulation system |
| CN113815889A (en) * | 2021-10-15 | 2021-12-21 | 北京海航通达航空设备有限公司 | Shutter type aircraft engine wake flow protection special equipment |
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Application publication date: 20150916 |
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