CN100455820C - Impeller mechanical wing profile with trailing edge ejection - Google Patents
Impeller mechanical wing profile with trailing edge ejection Download PDFInfo
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- CN100455820C CN100455820C CNB2007100447053A CN200710044705A CN100455820C CN 100455820 C CN100455820 C CN 100455820C CN B2007100447053 A CNB2007100447053 A CN B2007100447053A CN 200710044705 A CN200710044705 A CN 200710044705A CN 100455820 C CN100455820 C CN 100455820C
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Abstract
The invention relates to a wing for an axial-flow fan with tail-edge jetting in the technical field of impeller, which comprises an inputting pipe for the controlling gas, tail-edge jetting holes, a main gas passageway, branch gas passageways, diversion components, and the wing body. The inner of the wing body is a cavity, the main gas passageway and the branch gas passageways are in the cavity; the inputting pipe for the controlling gas is located outside the wing body; one end of the inputting pipe for the controlling gas is communicated with the main gas passageway, another end is communicated with the branch gas passageways; between the branch gas passageways, diversion components are provided. The tail-edge jetting holes are located at the tail edge of the wing body in equi-spaced way, the diameters of the tail-edge jetting holes are arranged in arithmetic progression along the tail edge of the wing body from the end with an inputting pipe for the controlling gas of the wing body to another end of the wing body. The invention fills the speed loss of the tail edge of the wing body, reduces the speed pulse at the tail area, reduces the interference from the downstream blades, and drops the interference noise.
Description
Technical field
The present invention relates to a kind of aerofoil profile of impeller machinery technical field, specifically is the jet impeller mechanical wing profile of a kind of magnetic tape trailer edge.
Background technique
Turbomachine not only is widely used in energy source and power, chemical petroleum, mine metallurgy, communications and transportation, building air conditioning, food medicine, and each production department of national economy such as hydraulic engineering is closely bound up with daily life; And important purposes is also arranged in national defence sophisticated technology fields such as Aero-Space, and use so widely and make turbomachine in national economy and national defense construction, occupy an important position, also therefore attracted people that the performance of turbomachine is extraordinarily paid close attention to.Meanwhile, the high-decibel influence of noise people's that the running of turbomachine, especially aeroengine produce normal life, the noise problem of turbomachine also is subjected to people's attention day by day.Therefore; improve the efficient of turbomachine, the safety that enlarges its range of operation, raising operation and reliability, reduction running noises; not only increase the benefit and environmental protection aspect critical role is arranged, and have important and far-reaching meaning aspect horizontal improving China's industrial development.In the flowing of turbomachines such as compressor, aeroengine, there be separating of boundary layer in the blade trailing edge pressure side with the suction surface place, in the tail district of afterbody formation speed loss.Flowing in the tail district is a kind of pneumatic phenomenon of complexity, and it has very big influence to downstream blade, and non-permanent tail and blade interact, and not only influences the performance of blade, also will produce interaction noise.
Find by prior art documents, Minton proposes can reduce the noise that the sound blade is interfered mutually by the air blowing of aerofoil profile trailing edge at its Master's thesis " Wake FillingTechniques for Reducing Rotor-Stator Interaction Noise " (Virginia Polytechnics master thesis " reducing the tail filling technique of sound interaction noise " in 2005), by open some isodiametric apertures at the aerofoil profile trailing edge, bottom and top while air feed from aerofoil profile, can reduce the speed loss of aerofoil profile trailing edge from the gas of aperture ejection, reduce of the influence of aerofoil profile tail, thereby reduce interaction noise the downstream movable vane.But there is deficiency in it: aperture is isodiametric, makes gas from aperture ejection along the high skewness of leaf, and in addition, the interval between aperture is too big, forms radially inhomogeneous wave moving air flow easily.
Summary of the invention
The present invention is directed to the deficiencies in the prior art, propose the jet impeller mechanical wing profile of a kind of magnetic tape trailer edge, make that its trailing edge is jet to improve flowing of aerofoil profile afterbody effectively, the influence of downstream blade is reduced, improve aeroperformance, reduce the sound interaction noise.
The present invention is achieved by the following technical solutions, the present invention includes: the control gaseous supplying tube, the trailing edge fumarole, the main flow of gas road, the gas branch runner, diversion component, the aerofoil profile body, annexation is: the aerofoil profile body interior is a cavity, the main flow of gas road, the gas branch runner places in this cavity, the control gaseous supplying tube places the aerofoil profile body outside, control gaseous supplying tube one end communicates with main flow of gas road one end, the main flow of gas road the other end communicates with the gas branch runner, be provided with diversion component between the gas branch runner, the equidistant trailing edge that is arranged on the aerofoil profile body of trailing edge fumarole, the diameter of trailing edge fumarole are provided with control gaseous supplying tube one end and become arithmetic progression to distribute to the aerofoil profile body the other end along the trailing edge of aerofoil profile body from the aerofoil profile body.
Described main flow of gas road, its cross section are square structure.
Described gas branch runner, with connecting place cross section, main flow of gas road be square structure, section transitions is a round structure at gas branch runner exit place.
Described trailing edge fumarole is circular spout.
In the described trailing edge fumarole, near the trailing edge fumarole diameter maximum of control gaseous supplying tube, the maximum diameter d size is 1/5～1/4 of an aerofoil profile body maximum ga(u)ge, minimum diameter 〉=0.3d.
Distance is 0.8d～1.2d between the described trailing edge fumarole.
Described diversion component, it is connected control gaseous supplying tube one end with the distance of main flow of gas road inwall and reduces gradually to the main flow of gas road the other end from the main flow of gas road, make the main flow of gas road become tapered configuration, thereby the trailing edge fumarole is radially given vent to anger evenly.
Described diversion component, itself and main flow of gas road connecting place are the crescent shape structure, and diversion component pressure side place radius is 0.5d～1d, and suction surface place radius is 0.8d～1.5d, and pressure side place radius is greater than suction surface place radius.
The present invention is when work, input by control gaseous supplying tube gas, under the effect of diversion component, gas is through main flow of gas road inflow gas branch runner, trailing edge fumarole from trailing edge sprays then, the air-flow and the main flow blending of ejection make the speed loss in tail district reduce, and the outlet of aerofoil profile body is flowed evenly.Because the gas flow of input is less, to the not influence basically of the whole aeroperformance of blower fan, but can reduce interference effect between the sound leaf, reduce interaction noise.
Compared with prior art, the present invention is simple in structure, reasonable in design, under the prerequisite that keeps original airfoil structure parameter, by the trailing edge fumarole that the aperture becomes arithmetic progression to distribute is set at aerofoil profile body trailing edge place, the gas of ejection reduces the speed loss of aerofoil profile body trailing edge, guaranteed original airfoil aerodynamic performances, the jet downstream blade entrance velocity that makes is even simultaneously, reduces the non-permanent pulsating force of blade, thereby reduces the sound interaction noise.When the present invention is used as the entry guide vane use of compressor or aeroengine, can reduce of the shock effect of stator tail, reduce the non-permanent power on movable vane surface the downstream movable vane; When the present invention is used as the rotor use, reduce of the influence of movable vane tail on the one hand, and the higher rotor of temperature is had certain cooling effect at the inner cooled gas that feeds of aerofoil profile to the downstream stator blade.The aerofoil profile of the relative general type of aerofoil profile of the present invention can reduce the interaction noise of sound leaf, and aerofoil profile of the present invention can reduce sound interaction noise 5～10dB, can alleviate simultaneously the pulsating force of downstream blade is impacted.
Description of drawings
Fig. 1 is aerofoil profile overall structure figure of the present invention;
Fig. 2 is an aerofoil profile cut-away view of the present invention;
Fig. 3 is a diversion component partial enlarged drawing of the present invention;
Fig. 4 is an aerofoil profile trailing edge fumarole distributing position of the present invention.
Embodiment
Below in conjunction with accompanying drawing embodiments of the invention are elaborated: present embodiment is being to implement under the prerequisite with the technical solution of the present invention, provided detailed mode of execution and concrete operating process, but protection scope of the present invention is not limited to following embodiment.
As depicted in figs. 1 and 2, present embodiment comprises: control gaseous supplying tube 1, main flow of gas road 2, gas branch runner 3, diversion component 4, trailing edge fumarole 5, aerofoil profile body 6, annexation is: aerofoil profile body 6 inside are cavitys, main flow of gas road 2, gas branch runner 3 places in this cavity, control gaseous supplying tube 1 places aerofoil profile body 6 outsides, control gaseous supplying tube 1 one ends communicate with main flow of gas road 2 one ends, main flow of gas road 2 the other ends communicate with gas branch runner 3, be provided with diversion component 4 between the gas branch runner 3, the trailing edge fumarole 5 equidistant trailing edges that are arranged on aerofoil profile body 6, the diameter of trailing edge fumarole 5 are provided with control gaseous supplying tube 1 one ends and become arithmetic progression to distribute to aerofoil profile body 6 the other ends along the trailing edge of aerofoil profile body 6 from aerofoil profile body 6.
Described main flow of gas road 2, its cross section are square structure.
Described gas branch runner 3, with 2 connecting place cross sections, main flow of gas road are square structures, be round structure in gas branch runner 3 outlet port section transitions.
Described trailing edge fumarole 5 is circular spout.
In the described trailing edge fumarole 5, near the trailing edge fumarole 5 diameter maximums of control gaseous supplying tube 1, maximum diameter d is 1/5～1/4 of an aerofoil profile body maximum ga(u)ge, minimum diameter 〉=0.3d.
Distance is 0.8d～1.2d between the described trailing edge fumarole 5.
Described diversion component 4, it reduces to main flow of gas road 2 the other ends gradually with the distance of main flow of gas road 2 inwalls is connected control gaseous supplying tube 1 from main flow of gas road 2 a end, make the 2 one-tenth tapered configuration in main flow of gas road, thereby trailing edge fumarole 5 is given vent to anger radially evenly.
Described diversion component 4, it links to each other with main flow of gas road 2 locates to be the crescent shape structure.
Described diversion component 4, its pressure side place radius R 1 is 0.5d～1d, suction surface place radius R 2 is 0.8d～1.5d, and R1＞R2.
Present embodiment is when work, input by control gaseous supplying tube 1 gas, under the effect of diversion component 4, gas is 2 inflow gas branch runners 3 through the main flow of gas road, trailing edge fumarole 5 from wing body 6 sprays then, the air-flow and the main flow blending of ejection make the speed loss in tail district reduce, and the outlet of wing body 6 is flowed evenly.Because the gas flow of input is less, to the not influence basically of the whole aeroperformance of blower fan, but can reduce interference effect between the sound leaf, reduce interaction noise.
Present embodiment is simple in structure, reasonable in design, and under the prerequisite that keeps original airfoil structure parameter, by the trailing edge fumarole 5 that the aperture becomes arithmetic progression to distribute is set at aerofoil profile body 6 trailing edge places, the gas of ejection reduces the speed loss of wing body 6 trailing edges.When present embodiment is used as the entry guide vane use of compressor or aeroengine, can reduce of the shock effect of stator tail, reduce the non-permanent power on movable vane surface the downstream movable vane; When present embodiment is used as the rotor use, reduces of the influence of movable vane tail on the one hand, and the higher movable vane of temperature is had certain cooling effect the downstream stator blade.The aerofoil profile of present embodiment increases on reduction noise ability than the aerofoil profile of general type, and present embodiment can reduce sound interaction noise 5～10dB, the pulsating force of downstream blade is impacted to alleviate simultaneously.
Claims (7)
1. impeller mechanical wing profile that the magnetic tape trailer edge is jet, comprise the aerofoil profile body, the control gaseous supplying tube, the main flow of gas road, the gas branch runner, diversion component, the trailing edge fumarole, the aerofoil profile body interior is a cavity, the main flow of gas road, the gas branch runner places in this cavity, the control gaseous supplying tube places the aerofoil profile body outside, control gaseous supplying tube one end communicates with main flow of gas road one end, the main flow of gas road the other end communicates with the gas branch runner, be provided with diversion component between the gas branch runner, it is characterized in that, the equidistant trailing edge that is arranged on the aerofoil profile body of trailing edge fumarole, the diameter of trailing edge fumarole is provided with control gaseous supplying tube one end and becomes arithmetic progression to distribute to the aerofoil profile body the other end along the trailing edge of aerofoil profile body from the aerofoil profile body, described main flow of gas road, its cross section are square structure.
2. the jet impeller mechanical wing profile of magnetic tape trailer edge according to claim 1 is characterized in that, described gas branch runner, and itself and connecting place cross section, main flow of gas road are square structures, section transitions is a round structure at gas branch runner exit place.
3. the jet impeller mechanical wing profile of magnetic tape trailer edge according to claim 1 is characterized in that, described trailing edge fumarole is circular spout.
4. according to claim 1 or the jet impeller mechanical wing profile of 3 described magnetic tape trailer edge, it is characterized in that, in the described trailing edge fumarole, near the trailing edge fumarole diameter maximum of control gaseous supplying tube.
5. according to claim 1 or the jet impeller mechanical wing profile of 3 described magnetic tape trailer edge, it is characterized in that, described trailing edge fumarole, its maximum diameter d is 1/5～1/4 of an aerofoil profile maximum ga(u)ge, minimum diameter 〉=0.3d.
6. the jet impeller mechanical wing profile of magnetic tape trailer edge according to claim 1 is characterized in that, described diversion component, and it is connected control gaseous supplying tube one end with the distance of main flow of gas road inwall and reduces gradually to the main flow of gas road the other end from the main flow of gas road.
7. according to claim 1 or the jet impeller mechanical wing profile of 6 described magnetic tape trailer edge, it is characterized in that, described diversion component, itself and main flow of gas road connecting place are the crescent shape structure.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CNB2007100447053A CN100455820C (en) | 2007-08-09 | 2007-08-09 | Impeller mechanical wing profile with trailing edge ejection |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CNB2007100447053A CN100455820C (en) | 2007-08-09 | 2007-08-09 | Impeller mechanical wing profile with trailing edge ejection |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN101109396A CN101109396A (en) | 2008-01-23 |
| CN100455820C true CN100455820C (en) | 2009-01-28 |
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| Application Number | Title | Priority Date | Filing Date |
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| CNB2007100447053A Expired - Fee Related CN100455820C (en) | 2007-08-09 | 2007-08-09 | Impeller mechanical wing profile with trailing edge ejection |
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Families Citing this family (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103306892B (en) * | 2012-04-18 | 2016-04-27 | 王政玉 | A kind of power fin |
| CN103982462B (en) * | 2014-05-15 | 2016-03-30 | 北京理工大学 | A kind of waveform jetting method of blade trailing edge |
| CN106151113B (en) * | 2016-07-01 | 2018-07-24 | 中航空天发动机研究院有限公司 | A kind of self-loopa multi stage axial flow compressor |
| CN113418139A (en) * | 2021-06-23 | 2021-09-21 | 中国航空工业集团公司沈阳空气动力研究所 | High-speed wind tunnel gust generating device based on trailing edge blowing form |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4188906A (en) * | 1959-08-25 | 1980-02-19 | Miller Marlin L | Supercavitating propeller with air ventilation |
| JPS585500A (en) * | 1981-07-03 | 1983-01-12 | Nikkiso Co Ltd | Low-noise inducer |
| JP2001123993A (en) * | 1999-10-25 | 2001-05-08 | Daikin Ind Ltd | Impeller for blower and method of manufacturing it |
| CN1616798A (en) * | 2003-11-10 | 2005-05-18 | 通用电气公司 | Method and apparatus for distributing fluid into a turbomachine |
| CN2864168Y (en) * | 2005-12-26 | 2007-01-31 | 海信集团有限公司 | Tube-axial fan |
-
2007
- 2007-08-09 CN CNB2007100447053A patent/CN100455820C/en not_active Expired - Fee Related
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4188906A (en) * | 1959-08-25 | 1980-02-19 | Miller Marlin L | Supercavitating propeller with air ventilation |
| JPS585500A (en) * | 1981-07-03 | 1983-01-12 | Nikkiso Co Ltd | Low-noise inducer |
| JP2001123993A (en) * | 1999-10-25 | 2001-05-08 | Daikin Ind Ltd | Impeller for blower and method of manufacturing it |
| CN1616798A (en) * | 2003-11-10 | 2005-05-18 | 通用电气公司 | Method and apparatus for distributing fluid into a turbomachine |
| CN2864168Y (en) * | 2005-12-26 | 2007-01-31 | 海信集团有限公司 | Tube-axial fan |
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| CN101109396A (en) | 2008-01-23 |
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| C06 | Publication | ||
| PB01 | Publication | ||
| C10 | Entry into substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| EE01 | Entry into force of recordation of patent licensing contract |
Assignee: AVIC Commercial Aircraft Engine Co Ltd Assignor: Shanghai Jiao Tong University Contract record no.: 2010310000075 Denomination of invention: Impeller mechanical wing profile with trailing edge ejection Granted publication date: 20090128 License type: Exclusive License Open date: 20080123 Record date: 20100525 |
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| C17 | Cessation of patent right | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20090128 Termination date: 20110809 |