CN203906376U - Airfoil blade for drag reduction through riblet surface - Google Patents
Airfoil blade for drag reduction through riblet surface Download PDFInfo
- Publication number
- CN203906376U CN203906376U CN201420340538.2U CN201420340538U CN203906376U CN 203906376 U CN203906376 U CN 203906376U CN 201420340538 U CN201420340538 U CN 201420340538U CN 203906376 U CN203906376 U CN 203906376U
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- China
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- blade
- ridge
- drag
- drag reduction
- airfoil blade
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Abstract
The utility model relates to an airfoil blade for drag reduction through a riblet surface, particularly to V-shaped riblet structures arranged on the surface of the airfoil blade. The airfoil blade is used for reducing the flow drag and the energy loss during operation of a pump and a fan, relative spacing dimensions among the riblet structures are set as a, h and s, and when air flows flow through blade flow paths, valleys of the riblet structures form stable secondary eddies, so that the viscous drag can be reduced significantly. According to the airfoil blade, the drag between the blade and the air flows is reduced, and the airfoil blade has the advantage of capability of reducing the energy consumption.
Description
Technical field
The utility model belongs to Pumps & Fans drag reduction Synergistic and energy-saving field, specifically refers to a kind of blade that reaches drag-reduction energy-saving effect with non-smooth ridge-like structure surface.
Background technique
Pumps & Fans class fluid machinery, it has also consumed a large amount of energy occupy critical role in national product life in.For example, boiler send, induced draught fan is as the important supplementary equipment in power station, and its power consumption accounts for 30% of station service.For the rotary fluid machines such as Pumps & Fans, because of the rubbing action that viscosity of fluid produces, its performance is had to important impact.In the time that air flow stream is crossed blade passage, because stickiness acts on the boundary layer that blade surface produces, though its thickness is little, the effective cross-sectional flow area of impeller channel is reduced, the phenomenon such as boundary layer separation, Secondary Flow that this external cause stickiness causes, all can cause the flow losses of Pumps & Fans.Reduce as much as possible flow resistance and the energy loss of fluid in Pumps & Fans inside, have great importance to raising the efficiency, reduce energy consumption.Conventional pump and fan blade, processing technology is coarse, simple in structure, affected greatly by viscosity of fluid, even affects Pumps & Fans stable operation.
Summary of the invention
It is a kind of by the airfoil fan of carinate surperficial drag reduction that the purpose of this utility model is to provide, and while reducing Pumps & Fans operation, the impact of suffered viscosity of fluid, reduces flow resistance and energy loss, and then raise the efficiency, reduce energy consumption.
For achieving the above object, it is a kind of by the airfoil fan of carinate surperficial drag reduction that the utility model provides, flow resistance and energy loss while operation in order to reduce Pumps & Fans, comprising: the ridge-like structure of " V " type, between ridge-like structure, relative spacing size can be according to actual conditions adjustment.Compare the ridge-like structure of other various shapes, as " U " type " L " type etc., in the ridge-like structure of " V " type the formation of secondary vortices more stable, the energy loss of generation is less, has better drag-reduction effect.Simultaneously, according to different flow velocitys and fluid, stable, the essentially identical secondary vortices of shape and position that the size of appropriate change relative spacing can make to form in ridge-like structure, make these whirlpools both not to external diffusion, also without significantly influencing each other, the turbulent dissipation producing obviously reduces, and drag-reduction effect is obvious.Meanwhile, the drag-reduction effect of ridge-like structure is affected by multiple factors such as flow velocity, physical properties of fluids parameter, ridge-like structure size and blade dimensions also, and concrete optimum ridge-like structure size needs to determine according to each parameter size in blade actual operating mode.
The airfoil fan of a kind of carinate surperficial drag reduction of the present utility model, in the time that air flow stream is crossed blade passage, in ridge-like structure cheuch inside owing to being subject to stickiness to block the mobile gas of generating portion low speed, form stable secondary vortices, produce the effect of " rolling bearing " in machinery, reached the effect that reduces viscous resistance.Meanwhile, the normal velocity gradient of carinate turbulent surface flow boundary layer near wall is starkly lower than smooth surface, thereby the existence of ridge-like structure has reduced average velocity gradient on wall, and shearing stress is reduced, and produces obvious drag-reduction effect.
Compared with prior art, the utility model can effectively reduce the resistance between blade and air-flow, has advantages of the energy consumption of reduction.
Brief description of the drawings
Below in conjunction with accompanying drawing, the utility model is described further.
Fig. 1 is difform ridge-like structure schematic diagram;
Fig. 2 is the utility model ridge-like structure surface blade schematic diagram;
Fig. 3 is ridge-like structure local flow field schematic diagram;
Fig. 4 is ridge-like structure cell schematics;
Fig. 5 is former airfoil fan two-dimensional representation;
Fig. 6 is carinate surperficial airfoil fan two-dimensional representation;
Fig. 7 is the local enlarged diagram of carinate surperficial airfoil fan two dimension;
In figure: 1-fluid-phase is to blade movement direction, 2-blade, 3-ridge-like structure, 4-secondary vortices.
Embodiment
Below in conjunction with the drawings and specific embodiments, the utility model is described further
As Fig. 1 to Fig. 7, a kind of airfoil fan of carinate surperficial drag reduction, " V-type " ridge-like structure 3 is arranged on surface at blade 2, the groove trend of ridge-like structure 3 is vertical to blade movement direction 1 with fluid-phase, its groove dimensions feature is determined by groove depth h, groove width s and pitch of grooves a, because this drag reduction technology is only applicable to turbulent condition, ridge-like structure need be arranged in to the mid-rear portion of blade at blade surface, reach the abundant development part of turbulent flow when fluid winding flow blade.Simultaneously, for the layout that makes ridge-like structure can better adapt to the streamlined of blade itself, the aerodynamic characteristic of blade is not produced to considerable influence, arrange as follows: unit of single ridge-like structure called after as shown in Figure 4, calculate through strict, ensure should " V-type " unit both sides be symplex structure and size does not change with surface; Be defined as 10～50 unit according to one section of continuous ridge-like structure of large young pathbreaker of ridge-like structure size, between each unit along aerofoil profile molded line direction end-to-end; Whole ridge-like structure layout area is divided into several continuous ridge-like structure sections according to actual size, and every section of Origin And Destination position is determined by the streamline profile coordinate position of blade surface.Adopt such method for arranging can reduce the difficulty that complicated ridge-like structure is arranged continuously at airfoil fan surface uniform, can make again large-area ridge-like structure region adapt to as far as possible fully the streamlined of airfoil fan surface, not change the aerodynamic characteristic of blade design itself.In the time of fluid and blade generation relative movement, can be because of the interaction in ridge-like structure and flow field in the groove of this ridge-like structure surface blade, and form stable, the essentially identical secondary vortices of shape and position, between these whirlpools, nothing significantly influences each other, its that in ridge-like structure, cause and backflow former fluid motion opposite direction, cause direction and the drag overall opposite direction of viscous resistance in ridge-like structure, the effect of " rolling bearing " in the similar machinery producing, can reduce viscous resistance, produce obvious drag-reduction effect.More specifically, in order to adapt to different type of fluid and blade structure, the layout scope on this carinate surface and size characteristic h, a and the s of ridge-like structure, all can need to adjust and optimize according to practical application, to reach more excellent drag-reduction effect.
Claims (4)
1. an airfoil fan for carinate surperficial drag reduction, is characterized in that: " V " type ridge-like structure is arranged on the surface at blade, and the groove trend of ridge-like structure is vertical to blade movement direction with fluid-phase, and its groove dimensions feature is determined by groove depth, groove width and pitch of grooves.
2. the airfoil fan of a kind of carinate surperficial drag reduction according to claim 1, is characterized in that: described " V " type ridge-like structure is arranged in airfoil fan surface.
3. the airfoil fan of a kind of carinate surperficial drag reduction according to claim 1, is characterized in that: the groove trend of described " V " type ridge-like structure is vertical to blade movement direction with fluid-phase.
4. the airfoil fan of a kind of carinate surperficial drag reduction according to claim 1, it is characterized in that: the size characteristic of described " V " type ridge-like structure is determined by groove depth, groove width and pitch of grooves, and can need to adjust and optimize according to practical application, to reach more excellent drag-reduction effect.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201420340538.2U CN203906376U (en) | 2014-06-25 | 2014-06-25 | Airfoil blade for drag reduction through riblet surface |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201420340538.2U CN203906376U (en) | 2014-06-25 | 2014-06-25 | Airfoil blade for drag reduction through riblet surface |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN203906376U true CN203906376U (en) | 2014-10-29 |
Family
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201420340538.2U Expired - Fee Related CN203906376U (en) | 2014-06-25 | 2014-06-25 | Airfoil blade for drag reduction through riblet surface |
Country Status (1)
| Country | Link |
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| CN (1) | CN203906376U (en) |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105317734A (en) * | 2014-06-25 | 2016-02-10 | 华北电力大学（保定） | Aerofoil blade of ridged surface drag reduction |
| CN106944935A (en) * | 2017-04-28 | 2017-07-14 | 济南大学 | A kind of shot blasting device blades and impeller body component |
| CN112644691A (en) * | 2021-01-04 | 2021-04-13 | 西安理工大学 | Stepped traveling wave-following plasma exciter capable of being used for drag reduction |
| KR20230003881A (en) * | 2021-06-30 | 2023-01-06 | 충남대학교산학협력단 | A high-effective pump whose impeller engraved riblets pattern |
-
2014
- 2014-06-25 CN CN201420340538.2U patent/CN203906376U/en not_active Expired - Fee Related
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105317734A (en) * | 2014-06-25 | 2016-02-10 | 华北电力大学（保定） | Aerofoil blade of ridged surface drag reduction |
| CN106944935A (en) * | 2017-04-28 | 2017-07-14 | 济南大学 | A kind of shot blasting device blades and impeller body component |
| CN112644691A (en) * | 2021-01-04 | 2021-04-13 | 西安理工大学 | Stepped traveling wave-following plasma exciter capable of being used for drag reduction |
| CN112644691B (en) * | 2021-01-04 | 2023-02-03 | 西安理工大学 | Stepped traveling wave-following plasma exciter capable of being used for drag reduction |
| KR20230003881A (en) * | 2021-06-30 | 2023-01-06 | 충남대학교산학협력단 | A high-effective pump whose impeller engraved riblets pattern |
| KR102560264B1 (en) | 2021-06-30 | 2023-07-26 | 충남대학교산학협력단 | A high-effective pump whose impeller engraved riblets pattern |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20141029 Termination date: 20150625 |
|
| EXPY | Termination of patent right or utility model |