CN103133180A - 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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- CN103133180A CN103133180A CN2011103836026A CN201110383602A CN103133180A CN 103133180 A CN103133180 A CN 103133180A CN 2011103836026 A CN2011103836026 A CN 2011103836026A CN 201110383602 A CN201110383602 A CN 201110383602A CN 103133180 A CN103133180 A CN 103133180A
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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 the 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 has obtained vigorous growth as a kind of convenient and swift trip mode.Meanwhile, people have higher requirement to civil aircraft Security, Economy, travelling comfort.Large Bypass Ratio Turbofan Engine is as the power plant of present large-scale airline carriers of passengers, and its noise, oil consumption rate and discharging have become the most important design objective of modern civil aircraft side by side.How to reduce the engine noise level and be 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 reducing jet noise is the key that reduces whole engine noise level.
Generally believe at present, the jet cutting car flow noise is comprised of two-part: a part is that from the 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, produced shock wave in Nozzle Flow due to jet cutting car flow, formed the shock wave noise.For large Bypass Ratio Turbofan Engine, the exhaust velocity lower (being generally subsonic speed) due to its jet pipe can not form very strong shock wave, and jet noise is mainly produced by the shear action of air-flow.
For the formation mechanism of large Bypass Ratio Turbofan Engine jet noise, development multiple jet noise suppress technology.For example, US6505706B2 proposes to have designed time barrier structure in the inside and outside culvert outside nozzle of turbofan engine, and this barrier structure can reduce the jet noise on some direction effectively.US7065957B2 proposes to have designed one section mixer at nozzle exit, has formed Secondary Flow by this mixer at nozzle exit, thereby has strengthened the blending of jet flow, has reduced jet noise.It is zigzag ejector exhaust pipe that US7305817B2 proposes a kind of orifice rim, has strengthened the blending of jet flow and ambient air by zigzag spout, thereby has effectively reduced jet noise.Generally, the inhibition technology of jet noise be all blending take strong high speed jet and ambient air as purpose, and can cause the jet pipe aeroperformance to lower.
Therefore, how when lowering the jet pipe jet noise, keeping the higher aeroperformance of jet pipe, is the key of large Bypass Ratio Turbofan Engine jet flow noise-reducing design.
Summary of the invention
In order to address the above problem, the invention provides a kind of by inject the large Bypass Ratio Turbofan Engine nozzle structure of jet to main jet stream.By this design, can effectively strengthen the blending of jet flow, thereby reach the purpose that reduces jet noise, and can obviously 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 are arranged in described by-pass air duct, and the center of described main duct is provided with the nozzle burst diaphragm cone,
Also comprise:
The nacelle runner, it is around described by-pass air duct, and is provided with in the outlet of contiguous described by-pass air duct the outer culvert jet nozzle that communicates with described by-pass air duct, is used for being injected into from the high pressure draught of gas compressor outer culvert jet flow; And
Core hood runner, it and is provided with in the outlet of contiguous described main duct the intension jet nozzle that communicates with described main duct between described by-pass air duct and described main duct, is used for being injected into from the high pressure draught of gas compressor the intension jet flow,
Described high pressure draught and described outer culvert jet flow and the mutual blending of described intension jet flow, thus jet noise lowered.
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 upwards evenly distribute in week respectively, 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 the percentage of radius of the outlet of described main duct, and/or the length of described outer culvert jet nozzle is not more than one of the percentage of radius of the outlet of described by-pass air duct.
Wherein, the wall of the import of described outer culvert jet nozzle and described by-pass air duct is fitted.Described outer culvert jet nozzle is provided with the drag reduction cambered surface, and described drag reduction cambered surface is relative with the outlet of described by-pass air duct, and extends towards the outlet of described outer culvert jet nozzle from the wall of described by-pass air duct.
Perhaps, the wall of the outlet of described outer culvert jet nozzle and described by-pass air duct is fitted.
Wherein, the wall of the import of described intension jet nozzle and described main duct is fitted.Described intension jet nozzle is provided with the drag reduction cambered surface, and described drag reduction cambered surface is relative with the outlet of described main duct, and extends towards the outlet of described intension jet nozzle from the wall of described main duct.
Perhaps, the wall of the outlet of described intension jet nozzle and described main duct is fitted.
According to another aspect of the present invention, provide a kind of turbofan engine that comprises above-mentioned low jet noise jet pipe.
Beneficial effect of the present invention:
(1) strengthen the blending of jet cutting car flow, effectively reduced the jet cutting car flow noise;
(2) in the aircraft cruising condition, jet nozzle is not worked, and can avoid the engine efficiency loss that the jet bleed brings, and jet jet pipe thrust loss that the disturbance of jet cutting car flow is brought;
(3) by to the jet nozzle optimal design, reduce its resistance to the motor runner, improved the aeroperformance of jet pipe;
(4) the relatively low pressurized gas of temperature can form cooling to high temperature parts such as intension walls during the core of flowing through hood runner, improve its working life.
Description of drawings
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 of the section of A in Fig. 1;
Fig. 3 shows the enlarged diagram of the section of B 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 jet nozzle structure;
Fig. 7 shows another embodiment of jet nozzle structure;
Fig. 8 shows another embodiment of jet nozzle structure.
Description of reference numerals
1 nacelle runner
2 nacelle outer covers
The wall of 3 by-pass air ducts
4 outer culvert jet nozzles
5 outer culvert jet nozzle imports
6 outer culvert jet nozzle outlets
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
15 outer culvert nozzle exits
16 core hood runners
17 by-pass air ducts
18 support plates
19 drag reduction cambered surfaces
Embodiment
Below in conjunction with the preferred embodiment of accompanying drawing detailed description according to the low jet noise jet pipe of large Bypass Ratio Turbofan Engine of the present invention.
Fig. 1 shows the basic structure of the low jet noise jet pipe of large Bypass Ratio Turbofan Engine.Fig. 2 and Fig. 3 show respectively A section in Fig. 1 and the enlarged diagram of B section.This jet pipe mainly has nacelle runner 1, by-pass air duct 17, core hood runner 16 and 12 4 air-flow paths of main duct.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.
Definition intension jet nozzle outlet 9 static pressure are P9, outer culvert jet nozzle outlet 6 static pressure are P6, intension nozzle exit 11 static pressure are P11, outer culvert nozzle exit 15 static pressure are 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 that arranges like this is the thrust loss that reduces jet pipe.
For guaranteeing that the air-flow in core hood runner 16 sprays from intension jet nozzle outlet 9, intension jet nozzle outlet static pressure P9 should be not less than intension nozzle exit static pressure P11.Simultaneously, for reducing jet to the impact of intension jet pipe aeroperformance, intension jet nozzle outlet static pressure P9 should be not more than 1.5 times of intension nozzle exit static pressure P11.
Similarly, spray from outer culvert jet nozzle outlet 6 for guaranteeing the air-flow in nacelle runner 1, outer culvert jet nozzle outlet static pressure P6 should be not less than outer culvert nozzle exit static pressure P 15.Simultaneously, for reducing the aerodynamic loss of by-pass air duct jet pipe, outer culvert jet nozzle outlet 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 in the jet nozzle outside overlaps with the nozzle exit section, to guarantee that nozzle gas flow fully mixes with ambient air under the effect of jet.
Preferably, in order to guarantee the mixing effect of jet nozzle and nozzle gas flow, inside and outside culvert jet nozzle should be no less than respectively 4.Simultaneously, for the aeroperformance of not obvious reduction jet pipe, inside and outside culvert jet nozzle should be no more than respectively 16, take 8 as best.
Fig. 4 and Fig. 5 show two kinds of arrangements that inside and outside culvert jet nozzle is making progress in week.The one, inside and outside culvert jet nozzle is not in same (shown in Figure 4) in the radial direction, and namely intension jet nozzle and outer culvert jet nozzle are in the interlaced layout that makes progress in week; The 2nd, inside and outside culvert jet nozzle is in same (shown in Figure 5) in the radial direction, and namely outer culvert jet nozzle and intension jet nozzle are arranged on from the straight line of main duct center extension.
Fig. 6 to Fig. 8 shows intension or contains the different embodiments of jet nozzle outward, and wherein intension is identical with the structure of outer culvert jet nozzle, contains jet nozzle 4 beyond diagram and is example.
Fig. 6 shows cylindrical spout, and outer culvert jet nozzle import 5 is fitted with the wall 3 of by-pass air duct, can produce disturbance by nozzle body to nozzle gas flow in the situation that there is no the jet ejection, strengthens the blending of jet pipe jet flow and ambient air.
Fig. 7 shows a kind of evolution structure of nozzle in Fig. 6.That is, increased drag reduction cambered surface 19 outside nozzle body, drag reduction cambered surface 19 is relative with outer culvert nozzle exit 15, and extends towards outer culvert jet nozzle outlet 6 from the wall 3 of by-pass air duct.Purpose is to reduce the resistance that nozzle body flows to inside and outside culvert, improves the jet pipe aeroperformance, but when there is no the air-flow ejection to the blending effect (jet noise inhibitory action) of nozzle gas flow than Fig. 6 in the cylindrical spout structure slightly poor.
Fig. 8 shows the another kind evolution structure of nozzle in Fig. 6.Outer culvert jet nozzle outlet 6 is fitted with the wall 3 of by-pass air duct, the housing that is jet nozzle is in the nacelle runner fully, jet nozzle does not have impact substantially on the aeroperformance of jet pipe, but it does not almost have the blending effect to the jet pipe jet flow when there is no the jet ejection, namely there is no the jet noise inhibition.
In use, when being in cruising condition away from airport or aircraft, jet nozzle is not worked (not having gas to flow out), and jet cutting car flow produces disturbance when flowing through the jet nozzle housing, form the blending of jet flow and ambient air, the reduction jet noise.
When aircraft need in field takeoff or landing etc. strict when controlling the aircraft noise level, jet nozzle work.Gas compressor final stage casing opening at motor is drawn two bleed conduits and install control valve additional on conduit, the outlet of a conduit is in core hood runner 16, and pressurized gas finally are injected into the intension air-flow from intension jet nozzle 7 through core hood runner 16; Another root conduit is introduced nacelle runner 1 by support plate 18 inner cavities with pressurized gas, and finally is injected into outer culvert air-flow from outer culvert jet nozzle 4.Air-flow is injected into respectively intension jet flow and outer culvert jet flow from intension and outer culvert jet pipe jet nozzle, forms mutual blending, reduces the 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 to limit practical range of the present invention.Be that all equivalences of doing according to the content of the present patent application the scope of the claims change and modify, all belong to protection scope of the present invention.
Claims (11)
1. one kind low jet noise jet pipe, comprising: main duct and by-pass air duct, described main duct are arranged in described by-pass air duct, and the center of described main duct is provided with the nozzle burst diaphragm cone,
It is characterized in that, described jet pipe also comprises:
The nacelle runner, it is around described by-pass air duct, and is provided with in the outlet of contiguous described by-pass air duct the outer culvert jet nozzle that communicates with described by-pass air duct, is used for being injected into from the high pressure draught of gas compressor outer culvert jet flow; And
Core hood runner, it and is provided with in the outlet of contiguous described main duct the intension jet nozzle that communicates with described main duct between described by-pass air duct and described main duct, is used for being injected into from the high pressure draught of gas compressor the intension jet flow,
Described high pressure draught and described outer culvert jet flow and the mutual blending of described intension jet flow, thus jet noise lowered.
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 upwards evenly distribute in week respectively, and be 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 the percentage of radius of the outlet of described main duct, and/or the length of described outer culvert jet nozzle is not more than one of the percentage of radius of the outlet of described by-pass air duct.
5. low jet noise jet pipe according to claim 1 and 2, is characterized in that, the import of described outer culvert jet nozzle and the wall of described by-pass air duct are fitted.
6. low jet noise jet pipe according to claim 5, it is characterized in that, described outer culvert jet nozzle is provided with the drag reduction cambered surface, and described drag reduction cambered surface is relative with the outlet of described by-pass air duct, and extends towards the outlet of described outer culvert jet nozzle from the wall of described by-pass air duct.
7. low jet noise jet pipe according to claim 1 and 2, is characterized in that, the outlet of described outer culvert jet nozzle and the wall of described by-pass air duct are fitted.
8. low jet noise jet pipe according to claim 1 and 2, is characterized in that, the import of described intension jet nozzle and the wall of described main duct are fitted.
9. low jet noise jet pipe according to claim 8, it is characterized in that, described intension jet nozzle is provided with the drag reduction cambered surface, and described drag reduction cambered surface is relative with the outlet of described main duct, and extends towards the outlet of described intension jet nozzle from the wall of described main duct.
10. low jet noise jet pipe according to claim 1 and 2, is characterized in that, the outlet of described intension jet nozzle and the wall of described main duct are fitted.
11. a turbofan engine is characterized in that, comprises according to claim 1 the described low jet noise jet pipe of any one in 10.
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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 true CN103133180A (en) | 2013-06-05 |
| CN103133180B CN103133180B (en) | 2015-06-10 |
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Cited By (12)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103423030A (en) * | 2013-08-13 | 2013-12-04 | 中国航空工业集团公司沈阳发动机设计研究所 | Tapered plug mechanism realizing axial symmetry spray pipe all-direction vector regulation |
| CN104943530A (en) * | 2014-03-27 | 2015-09-30 | 中航商用航空发动机有限责任公司 | Ventilation cooling device of engine core bin |
| CN106014686A (en) * | 2016-05-30 | 2016-10-12 | 西北工业大学 | S-shaped spray pipe structure for turbofan engine |
| CN106988928A (en) * | 2017-05-16 | 2017-07-28 | 北京理工大学 | A kind of Secondary Flow larynx bolt rocket engine with anti-yaw damper and cooling function |
| CN107023420A (en) * | 2017-05-16 | 2017-08-08 | 北京理工大学 | A kind of Secondary Flow larynx bolt rocket engine with thrust controllable function |
| CN108019295A (en) * | 2017-12-15 | 2018-05-11 | 中国航发沈阳发动机研究所 | A kind of aero-engine flow-disturbing denoising device |
| CN108216617A (en) * | 2017-12-29 | 2018-06-29 | 厦门大学 | A kind of method for inhibiting helicopter paddle-vortex interaction noise |
| CN109772607A (en) * | 2019-03-13 | 2019-05-21 | 大连大学 | Nozzle structure applied to installation for fermenting |
| CN109885871A (en) * | 2019-01-09 | 2019-06-14 | 同济大学 | A kind of design method of jet test pipe-line system |
| 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 |
| CN113107703A (en) * | 2021-04-08 | 2021-07-13 | 西北工业大学 | Spray tube air hole flow control structure |
| 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 |
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Cited By (18)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| 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 |
| CN103423030A (en) * | 2013-08-13 | 2013-12-04 | 中国航空工业集团公司沈阳发动机设计研究所 | Tapered plug mechanism realizing axial symmetry spray pipe all-direction vector regulation |
| CN104943530A (en) * | 2014-03-27 | 2015-09-30 | 中航商用航空发动机有限责任公司 | Ventilation cooling device of engine core bin |
| 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 |
| CN106988928A (en) * | 2017-05-16 | 2017-07-28 | 北京理工大学 | A kind of Secondary Flow larynx bolt rocket engine with anti-yaw damper and cooling function |
| CN107023420A (en) * | 2017-05-16 | 2017-08-08 | 北京理工大学 | A kind of Secondary Flow larynx bolt rocket engine with thrust controllable 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 |
| CN108019295A (en) * | 2017-12-15 | 2018-05-11 | 中国航发沈阳发动机研究所 | A kind of aero-engine flow-disturbing denoising device |
| CN108216617A (en) * | 2017-12-29 | 2018-06-29 | 厦门大学 | A kind of method for inhibiting helicopter paddle-vortex interaction noise |
| 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 |
| CN109885871A (en) * | 2019-01-09 | 2019-06-14 | 同济大学 | A kind of design method of jet test pipe-line system |
| 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 |
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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. |