CN103133180B - Low jet flow noise spray pipe and turbofan engine including the same - Google Patents
Low jet flow noise spray pipe and turbofan engine including the same Download PDFInfo
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- CN103133180B CN103133180B CN201110383602.6A CN201110383602A CN103133180B CN 103133180 B CN103133180 B CN 103133180B CN 201110383602 A CN201110383602 A CN 201110383602A CN 103133180 B CN103133180 B CN 103133180B
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Abstract
The invention provides a low jet flow noise spray pipe which comprises an internal duct and an external duct. The internal duct is arranged inside the external duct. A spray pipe plug cone is arranged inside the internal duct. The low jet noise spray pipe further comprises a nacelle runner surrounding the external duct and a core engine shell runner arranged between the external duct and the internal duct. An external duct jet flow nozzle communicated with the external dust is arranged close to the outlet of the external duct and used for jetting high pressure air flow from a gas compressor into the external duct jet flow. An internal duct jet flow nozzle communicated with the internal duct is arranged close to the outlet of the internal duct and used for jetting the high pressure air flow from the gas compressor into the internal duct jet flow. The high pressure air flow, the external duct jet flow and the internal duct jet flow are mixed and therefore jet flow noise is reduced. The invention further provides a turbofan engine including the low jet flow noise spray pipe.
Description
Technical field
The present invention relates to civil aircraft engine components, particularly a kind of low jet noise jet pipe and comprise the turbofan engine of this low jet noise jet pipe.
Background technique
Along with the development of society and improving constantly of human living standard, civil aviation obtains vigorous growth as the convenient and swift trip mode of one.Meanwhile, people have higher requirement to civil aircraft Security, Economy, travelling comfort.Large Bypass Ratio Turbofan Engine is as the power plant of current large-scale airline carriers of passengers, and its noise, oil consumption rate and discharge have become the most important design objective of modern civil aircraft side by side.How reducing engine noise level is one of technical barrier of international airline institute facing.The main noise of large Bypass Ratio Turbofan Engine comprises fan noise, jet noise, turbine noise and firing chamber noise.Wherein jet noise is one of topmost noise source of motor, and therefore, how effectively to reduce jet noise is the key reducing whole engine noise level.
Generally believe at present, jet cutting car flow noise is made up of two-part: a part is, from high-speed gas and the mutual friction of ambient air phase of engine jet pipe ejection, air produces noise under strong shear action; Another part is, because jet cutting car flow creates shock wave in Nozzle Flow, defines shock wave noise.For large Bypass Ratio Turbofan Engine, due to the exhaust velocity of its jet pipe lower (being generally subsonic speed), can not form very strong shock wave, jet noise produced primarily of the shear action of air-flow.
For the formation mechenism of large Bypass Ratio Turbofan Engine jet noise, the multiple jet noise suppression technology of development.Such as, US6505706B2 proposes to devise lower barrier structure in turbofan engine inside and outside culvert outside nozzle, and this barrier structure can reduce the jet noise on some direction effectively.US7065957B2 proposes to devise one section of mixer at nozzle exit, defines Secondary Flow, thus strengthens the blending of jet flow, reduce jet noise by this mixer at nozzle exit.It is zigzag ejector exhaust pipe that US7305817B2 proposes a kind of orifice rim, is strengthened the blending of jet flow and ambient air, thus effectively reduce jet noise by zigzag spout.Generally, the suppression technology of jet noise is all for the purpose of the blending of strong high speed jet and ambient air, and jet pipe aeroperformance can be caused to lower.
Therefore, how while attenuating jet pipe jet noise, keeping the aeroperformance that jet pipe is higher, is the key of large Bypass Ratio Turbofan Engine jet flow noise-reducing design.
Summary of the invention
In order to solve the problem, the invention provides a kind of large Bypass Ratio Turbofan Engine nozzle structure by injecting jet to main jet stream.By this design, effectively can strengthen the blending of jet flow, thus reach the object reducing jet noise, and obviously can not reduce the aeroperformance of jet pipe.
According to an aspect of the present invention, provide a kind of low jet noise jet pipe, comprising: main duct and by-pass air duct, described main duct is arranged in described by-pass air duct, and the center of described main duct is provided with nozzle burst diaphragm cone,
Also comprise:
Nacelle runner, it is around described by-pass air duct, and is provided with the outer culvert jet nozzle communicated with described by-pass air duct, for being injected into by the high pressure draught from gas compressor in outer culvert jet flow in the outlet of contiguous described by-pass air duct; And
Core hood runner, it is between described by-pass air duct and described main duct, and is provided with in the outlet of contiguous described main duct the intension jet nozzle communicated with described main duct, for the high pressure draught from gas compressor is injected in intension jet flow,
Described high pressure draught and described outer culvert jet flow and the mutual blending of described intension jet flow, thus lower jet noise.
Wherein, the number of described outer culvert jet nozzle and/or described intension jet nozzle is 4 ~ 16.
Wherein, described outer culvert jet nozzle and described intension jet nozzle are uniformly distributed respectively in the circumferential, and are arranged on from the straight line of described main duct center extension.
Wherein, the length of described intension jet nozzle is not more than one of percentage of the radius of the outlet of described main duct, and/or the length of described outer culvert jet nozzle is not more than one of percentage of the radius of the outlet of described by-pass air duct.
Wherein, the described import of outer culvert jet nozzle and the wall of described by-pass air duct are fitted.Described outer culvert jet nozzle is provided with drag reduction cambered surface, and described drag reduction cambered surface is relative with the outlet of described by-pass air duct, and extends from the wall of described by-pass air duct towards the outlet of described outer culvert jet nozzle.
Or the described outlet of outer culvert jet nozzle and the wall of described by-pass air duct are fitted.
Wherein, the import of described intension jet nozzle and the wall of described main duct are fitted.Described intension jet nozzle is provided with drag reduction cambered surface, and described drag reduction cambered surface is relative with the outlet of described main duct, and extends from the wall of described main duct towards the outlet of described intension jet nozzle.
Or the outlet of described intension jet nozzle and the wall of described main duct are fitted.
According to another aspect of the present invention, a kind of turbofan engine comprising above-mentioned low jet noise jet pipe is provided.
Beneficial effect of the present invention:
(1) strengthen the blending of jet cutting car flow, significantly reduce jet cutting car flow noise;
(2) in aircraft cruising condition, jet nozzle does not work, the engine efficiency loss that jet bleed can be avoided to bring, and the nozzle thrust loss that the disturbance of jet to jet cutting car flow brings;
(3) by jet nozzle optimal design, reduce its resistance to motor runner, improve the aeroperformance of jet pipe;
(4) pressurized gas that temperature is relatively low, can form the cooling to high-temperature components such as intension walls, improve its working life when flowing through core hood runner.
Accompanying drawing explanation
Fig. 1 shows the structural representation of the low jet noise jet pipe of large Bypass Ratio Turbofan Engine, and in figure, arrow represents the flow direction of air-flow;
Fig. 2 shows the enlarged diagram in A portion in Fig. 1;
Fig. 3 shows the enlarged diagram in B portion in Fig. 1;
Fig. 4 shows a kind of arrangement of inside and outside culvert jet nozzle;
Fig. 5 shows the another kind of arrangement of inside and outside culvert jet nozzle;
Fig. 6 shows an embodiment of fluidic nozzle configurations;
Fig. 7 shows another embodiment of fluidic nozzle configurations;
Fig. 8 shows another embodiment of fluidic nozzle configurations.
Description of reference numerals
1 nacelle runner
2 nacelle outer covers
The wall of 3 by-pass air ducts
Jet nozzle is contained outside 4
5 outer culvert jet nozzle imports
6 outer jet nozzles of containing export
7 intension jet nozzles
8 intension jet nozzle imports
9 intension jet nozzle outlets
10 nozzle burst diaphragm cones
11 intension nozzle exits
12 main ducts
The wall of 13 main ducts
14 core hoods
Nozzle exit is contained outside 15
16 core hood runners
17 by-pass air ducts
18 support plates
19 drag reduction cambered surfaces
Embodiment
The preferred embodiment according to the low jet noise jet pipe of large Bypass Ratio Turbofan Engine of the present invention is described in detail below in conjunction with accompanying drawing.
Fig. 1 shows the basic structure of the low jet noise jet pipe of large Bypass Ratio Turbofan Engine.Fig. 2 and Fig. 3 respectively illustrates the enlarged diagram in A portion in Fig. 1 and B portion.This jet pipe mainly has nacelle runner 1, by-pass air duct 17, core hood runner 16 and main duct 12 4 air-flow paths.Wherein nacelle runner 1 is formed by the wall 3 of nacelle outer cover 2 and by-pass air duct; By-pass air duct 17 is formed by the wall 3 of core hood 14 and by-pass air duct; Core hood runner 16 is formed by the wall 13 of core hood 14 and main duct; And main duct 12 is formed by the wall 13 of main duct.
Main duct 12 is arranged in by-pass air duct 17, and the center of main duct 12 is provided with nozzle burst diaphragm cone 10.This plug cone is a kind of structure that current most of motor generally adopts, and Main Function is the intension circulation passage jointly forming jet pipe with the wall of jet pipe.Nacelle runner 1 is around by-pass air duct 17, and be provided with at contiguous outer nozzle exit 15 of containing the outer culvert jet nozzle 4 communicated with by-pass air duct 17, for being injected into by the high pressure draught from gas compressor in outer culvert jet flow, outer culvert jet nozzle 4 has outer culvert jet nozzle import 5 and outer culvert jet nozzle outlet 6.Core hood runner 16 is between by-pass air duct 17 and main duct 12, and be provided with at contiguous intension nozzle exit 11 the intension jet nozzle 7 communicated with main duct 12, for being injected in intension jet flow by the high pressure draught from gas compressor, intension jet nozzle 7 has intension jet nozzle import 8 and intension jet nozzle outlet 9.By high pressure draught and outer culvert jet flow and the mutual blending of intension jet flow, thus lower jet noise.
It is P9 that definition intension jet nozzle exports 9 static pressure, it is P6 that outer culvert jet nozzle exports 6 static pressure, intension nozzle exit 11 static pressure is P11, outer culvert nozzle exit 15 static pressure is P15, the radius of intension nozzle exit 11 is R11, the radius of outer culvert nozzle exit 15 is R15, and the length of intension jet nozzle 7 is H7, and the length of outer culvert jet nozzle 4 is H4.Intension jet nozzle length H7 should be not more than 0.01 times of intension nozzle exit radius R 11, and outer culvert jet nozzle length H4 should be not more than 0.01 times of outer culvert nozzle exit radius R 15, and the main purpose arranged like this is the thrust loss reducing jet pipe.
For ensureing that the air-flow in core hood runner 16 sprays from intension jet nozzle outlet 9, intension jet nozzle exit static pressure P9 should be not less than intension nozzle exit static pressure P11.Meanwhile, for reducing jet to the impact of intension jet pipe aeroperformance, intension jet nozzle exit static pressure P9 should be not more than 1.5 times of intension nozzle exit static pressure P11.
Similarly, for ensureing that the air-flow in nacelle runner 1 sprays from outer culvert jet nozzle outlet 6, outer culvert jet nozzle exit static pressure P6 should be not less than outer culvert nozzle exit static pressure P 15.Meanwhile, for reducing the aerodynamic loss of by-pass air duct jet pipe, outer culvert jet nozzle exit static pressure P6 should be not more than 1.2 times of outer culvert nozzle exit static pressure P15.
Preferably, jet nozzle is in the upstream of nozzle exit section, and the profile line outside jet nozzle overlaps with nozzle exit section, to ensure that nozzle gas flow fully mixes with ambient air under the effect of jet.
Preferably, in order to ensure the mixing effect of jet nozzle and nozzle gas flow, inside and outside culvert jet nozzle should be no less than 4 respectively.Meanwhile, in order to the aeroperformance of not obvious reduction jet pipe, inside and outside culvert jet nozzle should be no more than 16 respectively, is best with 8.
Fig. 4 and Fig. 5 shows inside and outside culvert jet nozzle two kinds of arrangements in the circumferential.One be inside and outside culvert jet nozzle not at same (Fig. 4 shown in) in the radial direction, i.e. intension jet nozzle and outer culvert jet nozzle interlaced layout in the circumferential; Two is inside and outside culvert jet nozzles at same (shown in Fig. 5) in the radial direction, and namely outer jet nozzle and the intension jet nozzle contained is arranged on the straight line that extends from main duct center.
Fig. 6 to Fig. 8 shows intension or the outer different embodiments containing jet nozzle, and wherein intension is identical with the structure of outer culvert jet nozzle, contains jet nozzle 4 for example beyond diagram.
Fig. 6 shows cylindrical spout, and outer culvert jet nozzle import 5 is fitted with the wall 3 of by-pass air duct, in the situation not having jet to spray, can produce disturbance by nozzle body to nozzle gas flow, strengthens the blending of jet pipe jet flow and ambient air.
Fig. 7 shows a kind of evolved structure of nozzle in Fig. 6.That is, outside nozzle body, add drag reduction cambered surface 19, drag reduction cambered surface 19 is relative with outer culvert nozzle exit 15, and extends from the wall 3 of by-pass air duct towards outer culvert jet nozzle outlet 6.Object reduces nozzle body to the inside and outside resistance containing flowing, improves jet pipe aeroperformance, but slightly poorer than cylindrical spout structure in Fig. 6 to the blending effect (jet noise inhibitory action) of nozzle gas flow when not having air-flow to spray.
Fig. 8 shows the another kind of evolved structure of nozzle in Fig. 6.Outer culvert jet nozzle outlet 6 is fitted with the wall 3 of by-pass air duct, namely the housing of jet nozzle is in nacelle runner completely, the aeroperformance of jet nozzle on jet pipe does not affect substantially, but it does not almost have blending effect to jet pipe jet flow when not having jet to spray, namely there is no jet noise inhibition.
In use, when being in cruising condition away from airport or aircraft, jet nozzle does not work (not having gas to flow out), and jet cutting car flow produces disturbance when flowing through jet nozzle housing, form the blending of jet flow and ambient air, reduce jet noise.
When aircraft needs strict control aircraft noise level in field takeoff or landing etc., jet nozzle work.Draw two bleed conduits at the gas compressor final stage casing opening of motor and install control valve additional on conduit, the outlet of a conduit is in core hood runner 16, and pressurized gas are finally injected into intension air-flow from intension jet nozzle 7 through core hood runner 16; Pressurized gas are then introduced nacelle runner 1 by support plate 18 inner cavity by another root conduit, and are finally injected in outer culvert air-flow from outer culvert jet nozzle 4.Air-flow is injected into intension jet flow and outer culvert jet flow respectively from intension and outer culvert jet pipe jet nozzle, forms mutual blending, reduces jet cutting car flow noise.
Described in the present invention, concrete case study on implementation is only better case study on implementation of the present invention, is not used for limiting practical range of the present invention.Namely all equivalences done according to the content of the present patent application the scope of the claims change and modify, and all belong to protection scope of the present invention.
Claims (7)
1. a low jet noise jet pipe, comprising: main duct and by-pass air duct, and described main duct is arranged in described by-pass air duct, and the center of described main duct is provided with nozzle burst diaphragm cone,
It is characterized in that, described jet pipe also comprises:
Nacelle runner, it is around described by-pass air duct, and be provided with in the outlet of contiguous described by-pass air duct the outer culvert jet nozzle communicated with described by-pass air duct, for being injected into by the high pressure draught from gas compressor in outer culvert jet flow, the described import of outer culvert jet nozzle and the wall of described by-pass air duct are fitted; And
Core hood runner, it is between described by-pass air duct and described main duct, and be provided with in the outlet of contiguous described main duct the intension jet nozzle communicated with described main duct, for the high pressure draught from gas compressor is injected in intension jet flow, the import of described intension jet nozzle and the wall of described main duct are fitted
Described high pressure draught and described outer culvert jet flow and the mutual blending of described intension jet flow, thus lower jet noise.
2. low jet noise jet pipe according to claim 1, is characterized in that, the number of described outer culvert jet nozzle and/or described intension jet nozzle is 4 ~ 16.
3. low jet noise jet pipe according to claim 1 and 2, is characterized in that, described outer culvert jet nozzle and described intension jet nozzle are uniformly distributed respectively in the circumferential, and is arranged on from the straight line of described main duct center extension.
4. low jet noise jet pipe according to claim 1 and 2, it is characterized in that, the length of described intension jet nozzle is not more than one of percentage of the radius of the outlet of described main duct, and/or the length of described outer culvert jet nozzle is not more than one of percentage of the radius of the outlet of described by-pass air duct.
5. low jet noise jet pipe according to claim 1, it is characterized in that, described outer culvert jet nozzle is provided with drag reduction cambered surface, and described drag reduction cambered surface is relative with the outlet of described by-pass air duct, and extends from the wall of described by-pass air duct towards the outlet of described outer culvert jet nozzle.
6. low jet noise jet pipe according to claim 1, it is characterized in that, described intension jet nozzle is provided with drag reduction cambered surface, and described drag reduction cambered surface is relative with the outlet of described main duct, and extends from the wall of described main duct towards the outlet of described intension jet nozzle.
7. a turbofan engine, is characterized in that, comprises the low jet noise jet pipe according to any one of claim 1 to 6.
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| Application Number | Priority Date | Filing Date | Title |
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| CN201110383602.6A CN103133180B (en) | 2011-11-25 | 2011-11-25 | Low jet flow noise spray pipe and turbofan engine including the same |
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| CN201110383602.6A CN103133180B (en) | 2011-11-25 | 2011-11-25 | Low jet flow noise spray pipe and turbofan engine including the same |
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| CN103133180A CN103133180A (en) | 2013-06-05 |
| CN103133180B true CN103133180B (en) | 2015-06-10 |
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Families Citing this family (12)
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|---|---|---|---|---|
| CN103423030B (en) * | 2013-08-13 | 2015-07-29 | 中国航空工业集团公司沈阳发动机设计研究所 | A kind of Sai Zhui mechanism realizing axisymmetric nozzle omnidirectional vector and regulate |
| CN104943530B (en) * | 2014-03-27 | 2017-07-28 | 中航商用航空发动机有限责任公司 | The ventilation cooling device in engine core cabin |
| CN106014686A (en) * | 2016-05-30 | 2016-10-12 | 西北工业大学 | S-shaped spray pipe structure for turbofan engine |
| CN106988928B (en) * | 2017-05-16 | 2019-05-07 | 北京理工大学 | A kind of Secondary Flow larynx bolt rocket engine with anti-ablation and cooling function |
| CN107023420B (en) * | 2017-05-16 | 2018-09-21 | 北京理工大学 | A kind of Secondary Flow larynx bolt rocket engine with thrust controllable function |
| CN108019295B (en) * | 2017-12-15 | 2021-03-30 | 中国航发沈阳发动机研究所 | Turbulent flow noise reduction device for aircraft engine |
| CN108216617B (en) * | 2017-12-29 | 2020-04-24 | 厦门大学 | Method for suppressing helicopter propeller-vortex interference noise |
| RU2728577C2 (en) * | 2018-10-03 | 2020-07-31 | Акционерное общество "Объединенная двигателестроительная корпорация" (АО "ОДК") | Turbojet two-circuit engine with separate flow out of nozzles |
| CN109885871B (en) * | 2019-01-09 | 2023-07-04 | 同济大学 | Design method of jet test pipeline system |
| CN109772607A (en) * | 2019-03-13 | 2019-05-21 | 大连大学 | Nozzle structure applied to installation for fermenting |
| CN114518229A (en) * | 2020-11-20 | 2022-05-20 | 北京航天试验技术研究所 | Double-duct diffuser for supersonic free jet test of air-breathing engine |
| CN113107703A (en) * | 2021-04-08 | 2021-07-13 | 西北工业大学 | Spray tube air hole flow control structure |
Family Cites Families (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US6505706B2 (en) * | 2001-06-14 | 2003-01-14 | Pratt & Whitney Canada Corp. | Exhaust flow guide for jet noise reduction |
| US7305817B2 (en) * | 2004-02-09 | 2007-12-11 | General Electric Company | Sinuous chevron exhaust nozzle |
| US7246481B2 (en) * | 2004-03-26 | 2007-07-24 | General Electric Company | Methods and apparatus for operating gas turbine engines |
| US7614210B2 (en) * | 2006-02-13 | 2009-11-10 | General Electric Company | Double bypass turbofan |
| JP5459317B2 (en) * | 2009-10-28 | 2014-04-02 | 株式会社Ｉｈｉ | Noise reduction device |
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Address after: 200241 Minhang District Lianhua Road, Shanghai, No. 3998 Patentee after: China Hangfa commercial aviation engine limited liability company Address before: 201109 Shanghai city Minhang District Hongmei Road No. 5696 Room 101 Patentee before: AVIC Commercial Aircraft Engine Co.,Ltd. |