CN100470061C - Impeller mechanical wing profile with suction edge injection - Google Patents
Impeller mechanical wing profile with suction edge injection Download PDFInfo
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- CN100470061C CN100470061C CNB2007100447034A CN200710044703A CN100470061C CN 100470061 C CN100470061 C CN 100470061C CN B2007100447034 A CNB2007100447034 A CN B2007100447034A CN 200710044703 A CN200710044703 A CN 200710044703A CN 100470061 C CN100470061 C CN 100470061C
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- suction
- edge injection
- suction edge
- main flow
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Abstract
The invention relates to a wing for an impeller with suction-edge jetting in the technical field of impeller, which comprises a wing body, an inputting pipe for the controlling gas, a main gas passageway, branch gas passageways, diversion components, and suction-edge jetting holes. 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 suction-edge jetting holes are provided with a segment lobe each, so that the suction-edge jetting holes are of segment structure. The suction-edge jetting holes are arranged at the suction edge of the wing body near to the tail edge in an equi-spaced way, the diameters of the suction-edge jetting holes are arranged in arithmetic progression along the tail edge 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 tail width of the wing, 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 a kind of impeller mechanical wing profile with suction edge injection.
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 blade afterbody formation speed loss.Boundary layer separation flows and flow in the tail district is complicated pneumatic phenomenon, and it has very big influence to downstream blade, and non-permanent tail and blade interact, and not only influence the performance of blade, also will produce interaction noise.
Find through literature search prior art, Minton proposes can reduce the noise that the sound blade is interfered mutually by the air blowing of aerofoil profile suction limit 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 suction surface, from the bottom and the top while air feed of aerofoil profile, can reduce the boundary layer separation of aerofoil profile trailing edge from the gas of aperture ejection.But there is deficiency in it: aperture is isodiametric, makes gas from aperture ejection along the high skewness of leaf, in addition, the circular structure of aperture, the gas of ejection and main flow form the horseshoe vortex structure, influence the downstream blade performance, and the penetration rate of aperture jet-stream wind in main flow are bigger.
Summary of the invention
The present invention is directed to the deficiencies in the prior art, a kind of impeller mechanical wing profile with suction edge injection is proposed, make it can improve flowing of aerofoil profile afterbody effectively, improving the boundary layer separation at suction surface place and the afterbody of aerofoil profile flows, reduce influence to downstream blade, 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 main flow of gas road, the gas branch runner, diversion component, the aerofoil profile body, the suction edge injection hole, annexation is: the aerofoil profile body interior is a cavity, the main flow of gas road, the gas branch runner places in the 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 suction edge injection hole is provided with a fan-shaped tab, make the suction edge injection hole be sector structure, the suction edge injection hole is equidistant to be arranged on aerofoil profile body suction limit near the trailing edge place, and the diameter in suction edge injection hole is provided with control gaseous supplying tube one end along the trailing edge of aerofoil profile body from the aerofoil profile body and becomes arithmetic progression to distribute to the aerofoil profile body the other end.
In the described suction edge injection hole, near the suction edge injection bore dia maximum of control gaseous supplying tube, 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 suction edge injection hole.
The distance of the described suction edge injection hole line of centres and aerofoil profile trailing edge is 2.5d-4d.
Described fan-shaped tab, the center of circle in the fan-shaped center of circle and suction edge injection hole overlaps.
Described fan-shaped tab, its fan-shaped central angle angle are 60 °-110 °.
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, thus the suction edge injection aperture is to giving vent to anger evenly.
Described diversion component, it links to each other with the main flow of gas road locates to be the crescent shape structure, and its pressure side place radius is 0.5d-1d, and suction surface place radius is 0.8d-1.5d, and pressure side place radius is less than suction surface place radius.
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.
The present invention is when work, input by control gaseous supplying tube gas, under the effect of diversion component, gas stream is through the main flow of gas road and the gas branch runner, spray from the suction edge injection hole then, the air-flow and the main flow blending of ejection, make the speed loss in tail district reduce, the outlet of aerofoil profile body is flowed evenly, reduces the separation in boundary layer, aerofoil profile body suction limit, and can reduce the resistance and the pressure loss of aerofoil profile, tab at spout place, suction edge injection hole, make circular hole become sector structure, help reducing jet penetration rate in crossing current, avoid the formation of horseshoe vortex.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.
The present invention does not change the external form of original aerofoil profile body, has guaranteed original airfoil aerodynamic performances.When aerofoil profile is used as the entry guide vane use of compressor or aeroengine, can reduce the boundary layer separation of entry guide vane, reduce the shock effect of tail, reduce the non-permanent power on stator surface, reduce interaction noise the downstream movable vane.When aerofoil profile is used as the rotor use, reduces of the influence of rotor tail on the one hand, and the higher rotor of temperature is had certain cooling effect the downstream stator blade.
Compared with prior art, the present invention is simple in structure, reasonable in design, under the prerequisite that keeps original airfoil structure parameter, by arranging the suction edge injection hole that the aperture becomes arithmetic progression to distribute near the trailing edge place at aerofoil profile body suction surface, and at the hole trailing edge tab being set makes the suction edge injection hole become sector structure, gas is after the ejection of suction edge injection hole, penetration rate in main flow is less, and the speed loss of aerofoil profile body trailing edge is reduced, reduce the separation in boundary layer, the jet downstream blade entrance velocity that makes is even simultaneously, reduce the non-permanent pulsating force of blade, thereby reduce the sound interaction noise.The aerofoil profile of the relative general type of aerofoil profile of the present invention can reduce the interaction noise 5-10dB of sound leaf, 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 the shape figure in suction edge injection of the present invention hole;
Fig. 5 is an aerofoil profile trailing edge suction edge injection pore size distribution key plan 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 shown in Figure 1, present embodiment comprises: control gaseous supplying tube 1, main flow of gas road 2, gas branch runner 3, diversion component 4, suction edge injection hole 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 the 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, one tab 7 is set in the suction edge injection hole 5, make suction edge injection hole 5 be sector structure, the equidistant aerofoil profile body 6 suction limits that are arranged on, suction edge injection hole 5 are near the trailing edge places, and the diameter in suction edge injection hole 5 is provided with control gaseous supplying tube 1 one ends along the trailing edge of aerofoil profile body from aerofoil profile body 6 and becomes arithmetic progression to distribute to aerofoil profile body 6 the other ends.
In the described suction edge injection hole 5, near the suction edge injection hole 5 diameter maximums of control gaseous supplying tube 1, maximum diameter d is 1/5-1/4 of aerofoil profile body 6 maximum ga(u)ges, minimum diameter 〉=0.3d.
Distance L is 0.8d-1.2d between the described suction edge injection hole 5.
Described suction edge injection hole 5 lines of centres and aerofoil profile 6 trailing edges be 2.5d-4d apart from S.
Described tab 7 is sector structure, and the center of circle in the fan-shaped center of circle and suction edge injection hole 5 overlaps.
Described tab 7, its fan-shaped central angle angle beta are 60 °-110 °.
Described diversion component 4, it is connected control gaseous supplying tube 1 one ends with the distance D of main flow of gas road 2 inwalls and reduces gradually to main flow of gas road 2 the other ends from main flow of gas road 2, make the 2 one-tenth tapered configuration in main flow of gas road, thereby give vent to anger radially evenly in suction edge injection hole 5.
Described diversion component 4, it links to each other with main flow of gas road 2 locates to be the crescent shape structure, and its pressure side place radius R 1 is 0.5d-1d, suction surface place radius R 2 is 0.8d-1.5d, and R2〉R1.
Described main flow of gas road 2, its cross section are square structure.
Described gas branch runner 3, itself and 2 connecting place cross sections, main flow of gas road are square structures, are round structure in gas branch runner 3 outlet port section transitions.
Present embodiment is when work, input by control gaseous supplying tube 1 gas, under the effect of diversion component 4, gas stream is 2 inflow gas branch runners 3 through the main flow of gas road, 5 ejections from the suction edge injection hole then, the air-flow and the main flow blending of ejection, make the speed loss in tail district reduce, 5 outlets of suction edge injection hole are flowed evenly, reduce the separation in boundary layer, aerofoil profile body 6 suction limit, and can reduce the resistance and the pressure loss of aerofoil profile body 6,5 spout places are provided with tab 7 in the suction edge injection hole, make circular hole become sector structure, help reducing jet penetration rate in crossing current, avoid the formation of horseshoe vortex.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, present embodiment is simple in structure, reasonable in design, under the prerequisite that keeps original airfoil structure parameter, by arranging the suction edge injection hole 5 that the aperture becomes arithmetic progression to distribute near the trailing edge place at aerofoil profile body 6 suction surfaces, and at the hole trailing edge tab 7 is set and makes the 5 one-tenth sector structures in suction edge injection hole, gas is after 5 ejections of suction edge injection hole, penetration rate in main flow is less, and reduce the separation in boundary layer, 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.The aerofoil profile of the relative general type of aerofoil profile of present embodiment can reduce the interaction noise 5-10dB of sound leaf, can alleviate simultaneously the pulsating force of downstream blade is impacted.
Claims (10)
1, a kind of impeller mechanical wing profile with suction edge injection, comprise the aerofoil profile body, the control gaseous supplying tube, the main flow of gas road, the gas branch runner, diversion component, the suction edge injection hole, the aerofoil profile body interior is a cavity, the main flow of gas road, the gas branch runner places in the 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 suction edge injection hole is provided with a fan-shaped tab, the suction edge injection hole is sector structure, the suction edge injection hole is equidistant to be arranged on aerofoil profile body suction limit near the trailing edge place, and the diameter in suction edge injection hole is provided with control gaseous supplying tube one end along the trailing edge of aerofoil profile body from the aerofoil profile body and becomes arithmetic progression to distribute to the aerofoil profile body the other end.
2. the impeller mechanical wing profile of band suction edge injection according to claim 1, it is characterized in that, described suction edge injection hole, it is a maximum diameter d near the control gaseous supplying tube, the maximum diameter d size is 1/5-1/4 of an aerofoil profile maximum ga(u)ge, minimum diameter 〉=0.3d.
3. the impeller mechanical wing profile of band suction edge injection according to claim 2 is characterized in that, the center distance in two adjacent suction edge injection holes is 0.8d-1.2d.
4. the impeller mechanical wing profile of band suction edge injection according to claim 2 is characterized in that, the line of centres in two adjacent suction edge injection holes and the distance of aerofoil profile trailing edge are 2.5d-4d.
5. the impeller mechanical wing profile of band suction edge injection according to claim 1 is characterized in that, the fan-shaped center of circle of described fan-shaped tab and the center of circle in suction edge injection hole overlap.
6. according to claim 1 or 5 with the impeller mechanical wing profile of suction edge injection, it is characterized in that the fan-shaped central angle of described fan-shaped tab is 60 °-110 °.
7. the impeller mechanical wing profile of band suction edge injection 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.
8. according to the impeller mechanical wing profile of claim 1 or 7 described band suction edge injections, it is characterized in that, described diversion component, itself and main flow of gas road connecting place are the crescent shape structure, 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 less than suction surface place radius, described suction edge injection hole, it is a maximum diameter d near the control gaseous supplying tube.
9. the impeller mechanical wing profile of band suction edge injection according to claim 1 is characterized in that, described main flow of gas road, its cross section are square structure.
10. the impeller mechanical wing profile of band suction edge injection 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.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CNB2007100447034A CN100470061C (en) | 2007-08-09 | 2007-08-09 | Impeller mechanical wing profile with suction edge injection |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CNB2007100447034A CN100470061C (en) | 2007-08-09 | 2007-08-09 | Impeller mechanical wing profile with suction edge injection |
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| Publication Number | Publication Date |
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| CN101109395A CN101109395A (en) | 2008-01-23 |
| CN100470061C true CN100470061C (en) | 2009-03-18 |
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| CNB2007100447034A Expired - Fee Related CN100470061C (en) | 2007-08-09 | 2007-08-09 | Impeller mechanical wing profile with suction edge injection |
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Families Citing this family (7)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN102562414A (en) * | 2012-01-30 | 2012-07-11 | 重庆同利实业有限公司 | Steel and plastic composite bionic blade |
| CN103306892B (en) * | 2012-04-18 | 2016-04-27 | 王政玉 | A kind of power fin |
| CN103016408B (en) * | 2012-12-21 | 2016-03-02 | 大连理工大学 | A kind of one-dimensional linear hollow guide vane |
| CN105221321A (en) * | 2014-06-25 | 2016-01-06 | 上海电气风电设备有限公司 | The open blade structure of ocean current power generation unit inner chamber |
| FR3034145B1 (en) * | 2015-03-26 | 2017-04-07 | Snecma | COMPRESSOR FLOOR |
| JP6634658B2 (en) | 2016-12-20 | 2020-01-22 | 三菱重工業株式会社 | Main nozzle, combustor and method of manufacturing main nozzle |
| CN112145409B (en) * | 2020-08-28 | 2022-04-26 | 江苏大学 | Non-uniform incoming flow suppression device for wing plate at pump inlet |
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Granted publication date: 20090318 Termination date: 20110809 |