CN101769266A - Centrifugal fan blade - Google Patents
Centrifugal fan blade Download PDFInfo
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- CN101769266A CN101769266A CN 201010129447 CN201010129447A CN101769266A CN 101769266 A CN101769266 A CN 101769266A CN 201010129447 CN201010129447 CN 201010129447 CN 201010129447 A CN201010129447 A CN 201010129447A CN 101769266 A CN101769266 A CN 101769266A
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- blade
- suction surface
- pressure side
- leading edge
- trailing edge
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Abstract
The invention relates to a centrifugal fan blade, belonging to the technical field of fluid machinery. The blade comprises a front edge, a pressure surface, a suction surface and a rear edge, wherein the front edge is tangent to the inner diameter of a fan; the rear edge is positioned on the outer diameter of the fan; one end of the pressure surface and one end of the suction surface are respectively connected with the two ends of the front edge, and the other ends of the pressure surface and the suction surface are respectively connected with the two ends of the rear edge; and the blade is formed by the area surrounded by the front edge, the pressure surface, the suction surface and the rear edge. The blade adopts variable thickness forward bending structure, and the pressure surface and the suction surface of blade are controlled by high-order bezier curve, so that higher pressure rise and working efficiency can be ensured under the condition of low flow rate, the situation of a flow channel is improved, and the energy loss is reduced.
Description
Technical field
What the present invention relates to is a kind of blade of dynamic power machine technical field, in particular a kind of centrifugal fan blade.
Background technique
Specific speed occupies crucial status less than 0.25 ultra-low specific speed centrifugal blower in industrial system, be the critical product in the industry drying cycles systems such as food production, chemical fibre manufacturing and Wood Processing.And blade has material impact as the core component of such blower fan service behaviour to impeller internal flow (pressure-speed distribution) and external characteristic curve, its structure and optimization in Properties, to energy saving, reduce cost, increasing the benefit has great significance.
In ultra-low specific speed centrifugal blower running, since the demand of high voltage rise and small flow will guarantee work the time, fan blade exit width (b
2) and external diameter (D
2) ratio can become very little, i.e. b
2/ D
2＜0.03.Ultra-low specific speed centrifugal fan blade of the prior art adopts the equal thickness narrow blades more, this blade manufacture process of wind power generator is simple, practical cost is low, but: because impeller, vane thickness that the spiral case width is narrow and thin, cause the impeller channel equivalent divergent angle very big, significantly also will there be very big separation dissipation district in the viscous effect of impeller channel internal flow, very easily cause big interior stream energy loss; By the turning that axially turns to radially, because the influence of centrifugal inertia force is flowed to exist by the dish side and pointed to the adverse pressure gradient that covers side, add the separation whirlpool influence of impeller internal flow, big secondary flow capacity loss very easily appears between the disk cover side; Viscous flow loss (between impeller channel and disk cover side) relatively high pressure in addition rises the load that brings to blade, can form such blower fan high energy consumption, poor efficiency and the unfavorable phenomenon in short working life.
Find through retrieval prior art, China's utility application number: 200320109618.9, title: a kind of efficient straight-plate-type blade centrifugal blower model, this model structurally adopts taper shroud, prismatic blade, and be used in combination the blade liner plate, the wear resistance and the aeroperformance of blade to a certain degree is provided.But because this kind prismatic blade is difficult to meet the variable curvature motion in the fluid rotary course, particularly very easily form big separation dissipation district under ultra-low specific speed or the small flow situation, and moving fluid and the straight-vaned relative rigidity that contacts, also form big impact loss easily.
Summary of the invention
The objective of the invention is to overcome the deficiencies in the prior art, a kind of centrifugal fan blade is provided, can adapt to the blower fan ultra-low specific speed, the performance characteristic of small flow and high voltage rise.The pressure side of this blade and suction surface adopt the control of high-order Bezier, not only can guarantee higher voltage rise and working efficiency under the small flow situation, can also improve the flow passage situation, reduce energy loss.
The present invention is achieved by the following technical solutions, blade of the present invention comprises: leading edge, pressure side, suction surface and trailing edge, wherein: the internal diameter of leading edge and blower fan is tangent, trailing edge is positioned on the external diameter of blower fan, one end of pressure side and an end of suction surface link to each other with the two ends of leading edge respectively, the other end of pressure side links to each other with the two ends of trailing edge respectively with the other end of suction surface, and the zone that leading edge, pressure side, suction surface and trailing edge surround has constituted blade.
The radial thickness of described blade from the leading edge to the trailing edge increases gradually.
The curvature of described pressure side when identical blower fan radius greater than the curvature of suction surface.
Formed the blade structure of antecurvature formula thickening degree between described pressure side and suction surface.
The radius of described leading edge is half of leading edge radial thickness, is the arc transition of 3 ~ 10mm with radius between trailing edge and the pressure side, is the arc transition of 10 ~ 50mm with radius between trailing edge and the suction surface.
Described pressure side and suction surface shape are that the curve point of high-order Bezier is connected to form, and the pass of curve point is:
Wherein:
Be the function of putting on the Bezier, x is the abscissa of curve point, and y is the y coordinate of curve point,
Be the control point coefficient, t is an independent variable, b
j, c
jBe constant, l is the front and rear edge distance of blade.
The constant b of described pressure side control point coefficient
j, c
jValue is: b
0=0.009, b
1=0.333, b
2=0.179, b
3=0.00876, c
0=0.036, c
1=0.304, c
2=0.629, c
3=0.978;
The constant b of described suction surface control point coefficient
j, c
jValue is: b
0=0.0362, b
1=0.420, b
2=0.286, b
3=0.192, c
0=0.0129, c
1=0.320, c
2=0.656, c
3=0.927.The present invention has the following advantages compared to existing technology:
(1) front end of the present invention adopts the variable curvature pressure side of high-order Bezier control, can reduce airflow breakaway and energy loss.
(2) pressure side and suction surface adopt high-order Bezier continous curve, and good aeroperformance and less internal flow loss are arranged, and obtain high relatively voltage rise and efficient.
(3) increased gradually by the radial thickness of leading edge to the trailing edge blade, the equivalent divergent angle of blade impeller runner reduces compared to existing technology, and boundary layer separation is inhibited during small flow, thereby the performance of blade can be improved on the whole.
(4) during Blade Design, leading edge and trailing edge are all with arc transition, and the blade shape feature is simple, and the processing technology complexity is little, low cost of manufacture.
Description of drawings
Fig. 1 is a structural representation of the present invention;
Fig. 2 is the blade schematic representation of front and rear edge length l of the present invention;
Fig. 3 is the plotted curve of blade stagnation pressure coefficient of the present invention;
Fig. 4 is the plotted curve of blade stagnation pressure efficient of the present invention.
Embodiment
Below 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, the blade of present embodiment is positioned at blower fan, described blade comprises: leading edge 1, pressure side 2, suction surface 3 and trailing edge 4, wherein: the internal diameter 5 of leading edge 1 and blower fan is tangent, trailing edge 4 is positioned on the external diameter 6 of blower fan, one end of pressure side 2 links to each other with the two ends of leading edge 1 respectively with an end of suction surface 3, and the other end of the other end of pressure side 2 and suction surface 3 links to each other with the two ends of trailing edge 4 respectively, and the zone that leading edge 1, pressure side 2, suction surface 3 and trailing edge 4 surround has constituted blade.
Little and the high characteristics of voltage rise at ultra-low specific speed centrifugal blower flow, for weakening the gas shock of inlet front end, adopt the variable curvature pressure side 2 that meets the aeroelasticity principle at the blade front end, when air-flow flows into impeller channel, less airflow breakaway and energy loss are arranged.
Described pressure side 2 and suction surface 3 shapes are that the curve point of high-order Bezier is connected to form, and the rule formula of curve point can be expressed as:
Wherein:
Be the function of putting on the Bezier, x is the abscissa of curve point, and y is the y coordinate of curve point,
Be the control point coefficient, t is an independent variable, b
j, c
jBe constant, l is the chord length of blade.
The constant b of described pressure side 2 control point coefficients
j, c
jValue is: b
0=0.009, b
1=0.333, b
2=0.179, b
3=0.00876, c
0=0.036, c
1=0.304, c
2=0.629, c
3=0.978;
The constant b of described suction surface 3 control point coefficients
j, c
jValue is: b
0=0.0362, b
1=0.420, b
2=0.286, b
3=0.192, c
0=0.0129, c
1=0.320, c
2=0.656, c
3=0.927.
Described pressure side 2 and suction surface 3 shapes are high-order Bezier continous curves, can guarantee the flow losses that good aerodynamic properties (high relatively voltage rise and efficient) and impeller channel are inner less.
The curvature of described pressure side 2 when identical blower fan radius greater than the curvature of suction surface 3.Can reach the purpose of the boundary layer separation when improving voltage rise and reducing small flow like this.
The radial thickness of described blade is increased to trailing edge 4 gradually by leading edge 1.
Equal thickness fan blade compared to existing technology, the suitable equivalent divergent angle that reduces impeller channel of distribution energy of thickening degree more meets impeller channel different flow features radially, can effectively suppress the internal flow separation and reduce energy loss.Consider the manufacture cost of centrifugal fan blade, vane type line does not have axial twist, and blade inlet edge 1 and trailing edge 4 are with arc transition, and processing technology is simple.
The blade shape type is a forward curved vane, and is stronger relatively in identical operating mode lower blade acting ability, also can easily obtain the required high voltage rise requirement of ultra-low specific speed centrifugal blower under the prerequisite of small flow satisfying.
In the present embodiment, the internal diameter 5 of blower fan is 0.165m, and external diameter 6 is 0.5m.Blade circumferencial direction maximum ga(u)ge is 0.05m, and length of blade l is 0.335m.
The radius of leading edge 1 is 31.7mm, is the arc transition of 7mm with the radius between trailing edge 4 and the pressure side 2, is the arc transition of 20mm with the radius between trailing edge 4 and the suction surface 3.
The pressure side 2 of the blade of present embodiment and the coordinate of suction surface 3 are as shown in table 1:
During calculating, find the solution and the converted coordinate axle, just can obtain the coordinate of pressure side 2 and suction surface 3 according to the high-order Bezier control curve of pressure side 2 and suction surface 3.
Table 1 blade coordinate (m)
As shown in Figure 3, curve a is the stagnation pressure coefficient of the blade of present embodiment, and curve b is the stagnation pressure coefficient of the blade of prior art, and curve c is stagnation pressure coefficient reference value position.
As shown in Figure 4, curve d is the stagnation pressure efficient of the blade of present embodiment, and curve e is the stagnation pressure efficient of the blade of prior art, and curve f is stagnation pressure efficient reference value position.
The number of blade is that 13 same centrifugal blower performance comparison test's result proves: because the viscosity separated region in the impeller channel of the blade of present embodiment reduces than equal thickness prismatic blade, the internal flow condition improved, the also corresponding minimizing of energy loss makes every aeroperformance index (total voltage rise and efficient) of blade of present embodiment all be better than the equal thickness prismatic blade of prior art.
The blade of present embodiment has thickening degree forward curved vane, and the equivalent divergent angle of blade impeller runner reduces compared to existing technology, and boundary layer separation is inhibited during small flow, thereby the performance of blade can be improved on the whole; During Blade Design, front and rear edge makes foreign object reduce to minimum to the damage of blade with arc transition, and the blade shape feature is simple, and the processing technology complexity is little, low cost of manufacture.
Claims (4)
1. centrifugal fan blade, comprise: leading edge, pressure side, suction surface and trailing edge, wherein: the internal diameter of leading edge and blower fan is tangent, trailing edge is positioned on the external diameter of blower fan, one end of pressure side and an end of suction surface link to each other with the two ends of leading edge respectively, the other end of pressure side links to each other with the two ends of trailing edge respectively with the other end of suction surface, and the zone that leading edge, pressure side, suction surface and trailing edge surround has constituted blade, it is characterized in that:
The radial thickness of described blade from the leading edge to the trailing edge increases gradually;
The curvature of described pressure side when identical blower fan radius greater than the curvature of suction surface.
2. centrifugal fan blade according to claim 1, it is characterized in that, the radius of described leading edge is half of leading edge radial thickness, is the arc transition of 3 ~ 10mm with radius between trailing edge and the pressure side, is the arc transition of 10 ~ 50mm with radius between trailing edge and the suction surface.
3. centrifugal fan blade according to claim 1 is characterized in that, described pressure side and suction surface shape are that the curve point of high-order Bezier is connected to form, and the pass of curve point is:
Wherein:
Be the function of putting on the Bezier, x is the abscissa of curve point, and y is the y coordinate of curve point,
Be the control point coefficient, t is an independent variable, b
j, c
jBe constant, l is the chord length of blade.
4. centrifugal fan blade according to claim 3 is characterized in that, the constant b of described pressure side control point coefficient
j, c
jValue is: b
0=0.009, b
1=0.333, b
2=0.179, b
3=0.00876, c
0=0.036, c
1=0.304, c
2=0.629, c
3=0.978; The constant b of described suction surface control point coefficient
j, c
jValue is: b
0=0.0362, b
1=0.420, b
2=0.286, b
3=0.192, c
0=0.0129, c
1=0.320, c
2=0.656, c
3=0.927.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2010101294470A CN101769266B (en) | 2010-03-23 | 2010-03-23 | Centrifugal fan blade |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2010101294470A CN101769266B (en) | 2010-03-23 | 2010-03-23 | Centrifugal fan blade |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN101769266A true CN101769266A (en) | 2010-07-07 |
| CN101769266B CN101769266B (en) | 2011-08-31 |
Family
ID=42502314
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN2010101294470A Expired - Fee Related CN101769266B (en) | 2010-03-23 | 2010-03-23 | Centrifugal fan blade |
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Cited By (16)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102410250A (en) * | 2011-11-25 | 2012-04-11 | 上海交通大学 | Blade of centrifugal compressor applicable to gas with low molecular weight and compressor |
| GB2486021A (en) * | 2010-12-02 | 2012-06-06 | Agustawestland Ltd | Helicopter rotor blade with curved tip |
| CN102684285A (en) * | 2012-06-05 | 2012-09-19 | 田应官 | Float charging machine for load and storage battery pack |
| CN103438022A (en) * | 2013-09-16 | 2013-12-11 | 江苏大学 | Centrifugal pump with greatly distorted blades |
| CN104638837A (en) * | 2015-01-22 | 2015-05-20 | 宁波金锐机械有限公司 | Motor |
| CN104638867A (en) * | 2015-01-22 | 2015-05-20 | 宁波金锐机械有限公司 | Novel DC (Direct Current) motor |
| CN105715585A (en) * | 2014-12-05 | 2016-06-29 | 上海电气集团股份有限公司 | Variable geometric outlet vane |
| CN106321511A (en) * | 2016-09-20 | 2017-01-11 | 南京华顺精密模具有限公司 | Turbofan of turbine and manufacturing method thereof |
| CN106704258A (en) * | 2016-09-12 | 2017-05-24 | 东莞市卓奇电子科技有限公司 | Centrifugal impeller guide vane and centrifugal impeller |
| CN107559234A (en) * | 2017-09-05 | 2018-01-09 | 广东美的制冷设备有限公司 | Tubular wine wheel and there is its indoor apparatus of air conditioner |
| CN108386383A (en) * | 2018-02-24 | 2018-08-10 | 西安交通大学 | A kind of intersection bionic blade and preparation method thereof of combination Scad section's fish bodies and pinion |
| CN110555214A (en) * | 2018-05-30 | 2019-12-10 | 中国航发商用航空发动机有限责任公司 | compressor blade profile construction method and compressor blade |
| CN111828383A (en) * | 2020-08-06 | 2020-10-27 | 苏州顶裕节能设备有限公司 | Impeller with dolphin-like streamline blades |
| CN113446260A (en) * | 2020-03-27 | 2021-09-28 | 三菱重工压缩机有限公司 | Impeller and centrifugal compressor |
| CN113883093A (en) * | 2021-09-22 | 2022-01-04 | 哈尔滨工业大学 | Low-reaction-force compressor blade design method, movable blade and compressor |
| CN116186945A (en) * | 2023-04-27 | 2023-05-30 | 中国航发四川燃气涡轮研究院 | Method for realizing variable-thickness distribution curve of blade modeling |
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|---|---|---|---|---|
| GB2486021B (en) * | 2010-12-02 | 2017-07-19 | Agustawestland Ltd | Aerofoil |
| GB2486021A (en) * | 2010-12-02 | 2012-06-06 | Agustawestland Ltd | Helicopter rotor blade with curved tip |
| US9085359B2 (en) | 2010-12-02 | 2015-07-21 | Agustawestland Limited | Rotor blade tip planform |
| CN102410250B (en) * | 2011-11-25 | 2013-06-19 | 上海交通大学 | Blade of centrifugal compressor applicable to gas with low molecular weight and compressor |
| CN102410250A (en) * | 2011-11-25 | 2012-04-11 | 上海交通大学 | Blade of centrifugal compressor applicable to gas with low molecular weight and compressor |
| CN102684285A (en) * | 2012-06-05 | 2012-09-19 | 田应官 | Float charging machine for load and storage battery pack |
| CN103438022A (en) * | 2013-09-16 | 2013-12-11 | 江苏大学 | Centrifugal pump with greatly distorted blades |
| CN105715585A (en) * | 2014-12-05 | 2016-06-29 | 上海电气集团股份有限公司 | Variable geometric outlet vane |
| CN105715585B (en) * | 2014-12-05 | 2019-06-28 | 上海电气集团股份有限公司 | Variable-geometry exit guide blade |
| CN104638837A (en) * | 2015-01-22 | 2015-05-20 | 宁波金锐机械有限公司 | Motor |
| CN104638867A (en) * | 2015-01-22 | 2015-05-20 | 宁波金锐机械有限公司 | Novel DC (Direct Current) motor |
| CN106704258A (en) * | 2016-09-12 | 2017-05-24 | 东莞市卓奇电子科技有限公司 | Centrifugal impeller guide vane and centrifugal impeller |
| CN106321511A (en) * | 2016-09-20 | 2017-01-11 | 南京华顺精密模具有限公司 | Turbofan of turbine and manufacturing method thereof |
| CN107559234A (en) * | 2017-09-05 | 2018-01-09 | 广东美的制冷设备有限公司 | Tubular wine wheel and there is its indoor apparatus of air conditioner |
| CN108386383A (en) * | 2018-02-24 | 2018-08-10 | 西安交通大学 | A kind of intersection bionic blade and preparation method thereof of combination Scad section's fish bodies and pinion |
| CN110555214A (en) * | 2018-05-30 | 2019-12-10 | 中国航发商用航空发动机有限责任公司 | compressor blade profile construction method and compressor blade |
| CN110555214B (en) * | 2018-05-30 | 2023-08-11 | 中国航发商用航空发动机有限责任公司 | Construction method of blade profile of compressor blade and compressor blade |
| CN113446260A (en) * | 2020-03-27 | 2021-09-28 | 三菱重工压缩机有限公司 | Impeller and centrifugal compressor |
| CN113446260B (en) * | 2020-03-27 | 2023-11-21 | 三菱重工压缩机有限公司 | Impeller and centrifugal compressor |
| CN111828383A (en) * | 2020-08-06 | 2020-10-27 | 苏州顶裕节能设备有限公司 | Impeller with dolphin-like streamline blades |
| CN113883093A (en) * | 2021-09-22 | 2022-01-04 | 哈尔滨工业大学 | Low-reaction-force compressor blade design method, movable blade and compressor |
| CN116186945A (en) * | 2023-04-27 | 2023-05-30 | 中国航发四川燃气涡轮研究院 | Method for realizing variable-thickness distribution curve of blade modeling |
| CN116186945B (en) * | 2023-04-27 | 2023-08-18 | 中国航发四川燃气涡轮研究院 | Method for realizing variable-thickness distribution curve of blade modeling |
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