CN116398471A - Sweepforward blade impeller and constitute axial fan - Google Patents
Sweepforward blade impeller and constitute axial fan Download PDFInfo
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- CN116398471A CN116398471A CN202310380226.8A CN202310380226A CN116398471A CN 116398471 A CN116398471 A CN 116398471A CN 202310380226 A CN202310380226 A CN 202310380226A CN 116398471 A CN116398471 A CN 116398471A
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- 230000007423 decrease Effects 0.000 claims description 2
- 238000013461 design Methods 0.000 abstract description 11
- 238000009826 distribution Methods 0.000 description 5
- 230000005484 gravity Effects 0.000 description 5
- 238000005452 bending Methods 0.000 description 4
- 230000008859 change Effects 0.000 description 4
- 239000012530 fluid Substances 0.000 description 2
- 238000009434 installation Methods 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
- 238000005457 optimization Methods 0.000 description 2
- 238000010408 sweeping Methods 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 238000011161 development Methods 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 230000036541 health Effects 0.000 description 1
- 230000006872 improvement Effects 0.000 description 1
- 230000003993 interaction Effects 0.000 description 1
- 238000004519 manufacturing process Methods 0.000 description 1
- 239000000463 material Substances 0.000 description 1
- 238000000034 method Methods 0.000 description 1
- 230000009467 reduction Effects 0.000 description 1
- 238000011160 research Methods 0.000 description 1
- 238000004088 simulation Methods 0.000 description 1
- 230000007480 spreading Effects 0.000 description 1
- 238000003892 spreading Methods 0.000 description 1
- 238000009423 ventilation Methods 0.000 description 1
- 239000002699 waste material Substances 0.000 description 1
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Classifications
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D29/00—Details, component parts, or accessories
- F04D29/26—Rotors specially for elastic fluids
- F04D29/32—Rotors specially for elastic fluids for axial flow pumps
- F04D29/38—Blades
- F04D29/384—Blades characterised by form
- F04D29/386—Skewed blades
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D29/00—Details, component parts, or accessories
- F04D29/26—Rotors specially for elastic fluids
- F04D29/32—Rotors specially for elastic fluids for axial flow pumps
- F04D29/38—Blades
- F04D29/388—Blades characterised by construction
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D29/00—Details, component parts, or accessories
- F04D29/66—Combating cavitation, whirls, noise, vibration or the like; Balancing
- F04D29/661—Combating cavitation, whirls, noise, vibration or the like; Balancing especially adapted for elastic fluid pumps
- F04D29/666—Combating cavitation, whirls, noise, vibration or the like; Balancing especially adapted for elastic fluid pumps by means of rotor construction or layout, e.g. unequal distribution of blades or vanes
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02E—REDUCTION OF GREENHOUSE GAS [GHG] EMISSIONS, RELATED TO ENERGY GENERATION, TRANSMISSION OR DISTRIBUTION
- Y02E10/00—Energy generation through renewable energy sources
- Y02E10/70—Wind energy
- Y02E10/72—Wind turbines with rotation axis in wind direction
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
The invention relates to the field of high-efficiency axial flow fan impellers, in particular to a forward-swept blade impeller and an axial flow fan formed by the impeller, wherein the impeller comprises blades and a hub, the blades are radially arranged on the hub, the front edges of the blades are in a forward-swept shape, the blades are divided into a plurality of sections along the radial direction when seen from the axial direction of the impeller, the connecting line of the sections from the root center to the front end center is in a curved shape, the root center of the blades and the circle center of the hub are connected into a radial line, and an included angle gamma between the connecting line of the centers of the sections and the root center and the radial line is 15-25 degrees. The axial flow fan adopting the forward-swept blade impeller is a forward-swept axial flow fan. The design of the fan blade adopts a sweep technology, so that the air flow state can be effectively changed, the turbulence intensity is reduced, the noise is reduced, and the performance is improved.
Description
Technical Field
The invention relates to an axial flow fan impeller, in particular to a forward-swept axial flow fan impeller, and belongs to the field of efficient axial flow fan impellers.
Background
At present, the problems of high noise and low efficiency in the field of axial flow fans used in industries such as ships, air conditioners and ventilation exist generally, the noise is too large to directly influence the concealment of the ships, the damage is generated to the health of human bodies, and the low efficiency also causes huge waste of energy sources. The sweep technique is firstly used for designing and applying military aircrafts, and with the development of the theory and experimental study of bent sweep blades, the advantages of the bent sweep blades serving as propeller and compressor blades in aerodynamic performance and acoustic performance are confirmed by researchers.
The prior art publication No. (CN 211174768U) is examined to provide a forward-bending and forward-sweeping type blade, wherein the blade adopts a middle-upper part to bend and sweep, the bending and sweeping is close to the front edge, the starting point is approximately positioned between 40% and 50% of the length of the blade, the relative width of the blade is reduced, materials are saved, the wind quantity and the wind pressure are ensured, the noise reduction effect is achieved, the wind pressure loss is reduced, and the performance of a fan is improved. Through setting up the connector of multiple structure, can dismantle the connection, adjustable installation angle matches different mounting means. But the forward-curved blades are easier to start at low wind speeds and stall at high wind speeds.
In order to solve the problems, the application provides a high-efficiency low-noise forward-swept blade impeller, which carries out brand-new three-way flow design on blades, adopts backward bending forward-swept design on fan blades, gradually widens the blades from blade root to blade tip, can effectively change air flow state, reduces turbulence intensity, reduces noise, can stably run at high wind speed and improves performance.
Disclosure of Invention
The invention aims to provide a forward-swept blade impeller and an axial flow fan formed by the forward-swept blade impeller, and solves the problems of high noise, low efficiency, high wind speed, easy stall and the like of a common axial flow fan impeller.
The invention aims to achieve the aim, and the aim is achieved by the following technical scheme:
the utility model provides a blade impeller, includes blade and wheel hub, and the blade is radial setting on wheel hub, its characterized in that: the front edge of the blade is in a forward-swept shape, the blade is divided into a plurality of sections along the radial direction when seen from the axial direction of the impeller, the connecting line of the section blade from the root center to the front end center is in a curved shape, the root center of the blade and the center of the hub are connected into radial lines, and the included angle gamma between the connecting line of the root center of each section and the root center and the radial lines is 15-25 degrees.
Preferably, the blade width from the blade root to the outermost edge of the blade is gradually increased, the blade cross section width b0 of the blade root is taken as a reference, the blade cross section width b at different positions is 0.45-0.6, the hub ratio is 0.45-2.5, and the blade width ratio b' =b/b 0 is 1.5.
Preferably, the relative thickness of the section blade profile, namely the ratio of the blade thickness t to the blade section width b, is between 4% and 12%, and the blade tip thickness gradually increases from the front end to the root.
Preferably, the relative torsion angle theta between the blade tip and the blade root is 15-35.8 degrees.
Preferably, the relative camber of each section of the blade, namely the ratio of the chord height f of the section blade profile to the thickness t of the blade, is 4.23-9.85%, and the camber gradually decreases from the blade root to the blade tip.
Preferably, the hub is of a two-piece symmetrical structure, and the joint surface of the root of the blade and the hub is spherical.
Preferably, the number of the blades is 6-12, and the root of the blade is provided with a blade handle connected with the hub.
Preferably, the axial flow fan adopting the blade impeller is a forward-swept axial flow fan.
The invention has the beneficial effects that:
(1) According to the invention, through optimizing parameters such as the forward-sweep angle of the blade, the width of the blade, the torsion rule, the thickness of the blade profile, the curvature of the blade profile and the like, the impeller efficiency is improved, and the pneumatic noise is effectively reduced.
(2) The impeller designed by the invention has the advantages of narrow blade root, adjustable angle and adjustable blade number, is suitable for impeller multi-blade installation, has wide air volume and pressure coverage range, and can be widely applied to the requirements of different industries.
Drawings
The accompanying drawings are included to provide a further understanding of the invention and are incorporated in and constitute a part of this specification, illustrate the invention and together with the embodiments of the invention, serve to explain the invention.
Fig. 1 is a front view of an axial flow fan impeller according to the present invention;
FIG. 2 is a perspective view of an axial flow fan impeller blade according to the present invention;
FIG. 3 is a front view of a full blade layout and hub of an axial flow fan impeller according to the present invention;
FIG. 4 is a front view of an axial flow fan impeller blade according to the present invention;
FIG. 5 is a cross-sectional view of an axial flow fan impeller blade according to the present invention;
FIG. 6 is a schematic illustration of a fluid flow diagram of an axial flow fan impeller blade in accordance with the present invention;
FIG. 7 is a graph showing a vane stress distribution of an axial flow fan impeller according to the present invention;
FIG. 8 is a graph showing the vane pressure and efficiency of an axial flow fan impeller according to the present invention
In the figure: 1. blade 2, hub 3, blade root 4, shank 5, blade root 6, apex.
Detailed Description
The following description of the embodiments of the present invention will be made clearly and completely with reference to the accompanying drawings, in which it is apparent that the embodiments described are only some embodiments of the present invention, but not all embodiments. All other embodiments, which can be made by those skilled in the art based on the embodiments of the invention without making any inventive effort, are intended to be within the scope of the invention.
The following examples set the impeller diameter of 800mm and the hub ratio of 57.5% as the technical basis for the design.
Embodiment one:
referring to fig. 1, the invention discloses a blade impeller for an axial flow fan, which comprises a blade 1 and a hub 2, wherein the blade is radially arranged on the hub, the front edge of the blade is in a forward-swept shape, the blade is divided into a plurality of sections along the radius direction when seen from the axial direction of the impeller, the connecting line of the sections from the root center to the front end center is in a curved shape, the center of the root 5 of the blade and the center of the hub 2 of the blade are connected into a radius line, and an included angle gamma between the connecting line of the center of each section and the root center and the radius line is 15-25 degrees.
In the embodiment, the blades adopt a forward-swept structure, the design defect that vortex interaction and superposition are caused on the same straight line generally by the front edge of the traditional blade to generate larger noise is overcome, the forward-swept part is contacted with incoming flow firstly, the airflow can be effectively guided, vortex generation is reduced, noise is reduced, the center of gravity of the blade is offset due to the fact that the larger forward-swept angle is the same, the bending stress of the root 5 of the blade is overlarge, and the stress uniformity and the pneumatic noise performance are comprehensively considered, so that the invention adopts gamma to be 18.3 degrees.
Referring to fig. 2-5, in this embodiment, considering the problem that the circumference of the blade root 3 is smaller, and the blade is too wide, so that the blade solidity is easy to be too large, and the blade overlap interference is caused, the invention adopts a scheme that the blade width from the blade root 3 to the outermost edge of the blade gradually becomes large, and uses the blade width b0 of the blade root section as a reference, the blade section width at different positions is b, the hub ratio is 0.45-0.6, and the blade width ratio b' =b0 is 1.5-2.5.
The blade profile is the most important characteristic affecting the performance of the fan, and comprises key parameters such as section wing profile, width, thickness, camber, blade torsion rule and the like, and the specific design parameters are as follows:
in order to control the thickness of the blade to meet the performance requirement, the invention adopts the scheme that the thickness of the blade tip 6 gradually increases from the front end to the root by adopting the relative thickness of the section blade profile, namely the ratio of the thickness t of the blade to the section width b of the blade, and the design can effectively reduce the weight, reduce the stress concentration of the blade root 3 and reduce the manufacturing cost of products.
In this embodiment, the blade root section is taken as a first section as a reference, the blade profile torsion angle of the blade root 3 section is 0 degrees, the torsion angles of other sections and the blade root 3 section are theta, and the design range of the relative torsion angle theta between the blade tip 6 and the blade root 3 is 15-35.8 degrees. The data research shows that the change rule of the torsion angle is a key parameter affecting the aerodynamic performance of the impeller, the linear speed is increased along the radial direction, the torsion angle of the blade shape is increased, and the change gradient of the torsion angle is reduced. The fan blade tip 6 has a gap, so that the blade tip 6 is in gap backflow, the torsion angle gradient of the front area of the blade tip 6 is reduced to 0 or a negative value, and the design can reduce impeller noise by 1-3 dB (A).
The relative camber of each section of the blade, namely the ratio of the chord height f of the blade profile of the section to the thickness t of the blade, is 4.23-9.85%, the camber gradually reduces from the blade root 3 to the blade tip 6, the blade profile in the blade root area is considered to be narrow, the camber is large, the functional force can be effectively improved, the blade in the blade tip 6 area is wide, the linear speed is high, and the camber is small, so that vortex flow and aerodynamic noise can be effectively reduced.
In this embodiment, the hub 2 is of two symmetrical structures, the interface between the root 5 of the blade and the hub 2 is spherical, the blade root and the hub gap at any mounting angle of the blade cannot be changed, the loss caused by the gap change is reduced, and the efficiency is improved. The number of the blades is 6-12, the root of each blade is provided with a blade handle 4 connected with the hub, and any angle adjustment can be carried out between the blades and the hub so as to obtain the desired aerodynamic performance.
According to the embodiment, pneumatic optimization of the blade is performed through fluid simulation, parameters such as width, torsion angle, camber and thickness of the blade after optimization are perfectly matched, and the blade is uniform in pressure distribution on the pressure surface of the blade, smooth in pressure line distribution on the suction surface and the like, and uniformity of blade tip pressure distribution is damaged due to backflow of a blade tip clearance, so that pressure loss can be effectively reduced by the blade tip clearance, and efficiency is improved. The performance curve and the efficiency curve are shown in fig. 8, and the highest efficiency is 85%.
The blade handle 4 of the embodiment is designed to combine gravity distribution, so that the gravity center of the blade is near the center of the section of the blade handle, and the gravity center correspondingly moves forward due to forward sweep of the blade, the center of the example blade handle is positioned at 30% of the section of the 0-0 blade profile, the conventional blade design is generally positioned at 40%, as shown in fig. 6, the whole gravity center of the blade is basically coincident with the center of the blade handle, the maximum stress is 43.537MPa, and the stress concentration is reduced by about 30% compared with the conventional design.
Example two
The embodiment provides an axial flow fan adopting the vane impeller in the first embodiment, which is a forward-swept axial flow fan and is mainly characterized in that the vane is a chord-long vane, the vane tip part is wide, the vane root part is narrow, and the vane tip part protrudes gradually towards the vane tip along the vane spreading front edge, and the section is in a curved thin airfoil shape.
Finally, it should be noted that: the foregoing description is only a preferred embodiment of the present invention, and the present invention is not limited thereto, but it is to be understood that modifications and equivalents of some of the technical features described in the foregoing embodiments may be made by those skilled in the art, although the present invention has been described in detail with reference to the foregoing embodiments. Any modification, equivalent replacement, improvement, etc. made within the spirit and principle of the present invention should be included in the protection scope of the present invention.
Claims (9)
1. The utility model provides a blade impeller, includes blade (1) and wheel hub (2), and blade (1) are radial setting on wheel hub, its characterized in that: the front edge of the blade (1) is in a forward-swept shape, the blade is divided into a plurality of sections along the radial direction when seen from the axial direction of the impeller, the connecting line of the sections from the root center to the front end center is in a curved shape, the center of the root (5) of the blade and the center of the hub are connected into radial lines, and the included angle gamma between the connecting line of the center of each section and the root center and the radial lines is 15-25 degrees.
2. The vane wheel of claim 1, wherein: blade root (3) to blade outermost edge leaf width grow gradually, regard blade root cross-section blade width b0 as the reference, different position blade cross-section width is b, and the hub ratio is 0.45 ~ 0.6, and blade width ratio b' =b/b 0 is 1.5 ~ 2.5.
3. The vane wheel of claim 1, wherein: the relative thickness of the section blade profile, namely the ratio of the blade thickness t to the blade section width b is 4-12%, and the thickness of the blade tip (6) is gradually thickened from the front end to the root.
4. The vane wheel of claim 1, wherein: the relative torsion angle theta between the blade tip (6) and the blade root (3) is 15-35.8 degrees.
5. The vane wheel of claim 1, wherein: the relative camber of each section of the blade, namely the ratio of the chord height f of the section blade profile to the thickness t of the blade, is 4.23-9.85%, and the camber gradually decreases from the blade root to the blade tip.
6. The vane wheel of claim 1, wherein: the hub (2) is of two symmetrical structures, and the joint surface of the root (5) of the blade and the hub (2) is a spherical surface.
7. The vane wheel of claim 1, wherein: the number of the blades is 6-12, and the root (5) of the blade is provided with a blade handle (4) connected with the hub (2).
8. An axial flow fan, characterized in that: comprising a bladed impeller according to any one of claims 1 to 7.
9. The axial flow fan according to claim 8, wherein: the axial flow fan is a forward-swept axial flow fan.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202310380226.8A CN116398471A (en) | 2023-04-11 | 2023-04-11 | Sweepforward blade impeller and constitute axial fan |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202310380226.8A CN116398471A (en) | 2023-04-11 | 2023-04-11 | Sweepforward blade impeller and constitute axial fan |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN116398471A true CN116398471A (en) | 2023-07-07 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202310380226.8A Pending CN116398471A (en) | 2023-04-11 | 2023-04-11 | Sweepforward blade impeller and constitute axial fan |
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Citations (16)
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| CN1232143A (en) * | 1998-04-14 | 1999-10-20 | 松下电器产业株式会社 | Impeller of fan |
| CN1534200A (en) * | 2003-03-28 | 2004-10-06 | 中国科学院工程热物理研究所 | Axial ventilating machine impellor |
| CN2767722Y (en) * | 2004-10-20 | 2006-03-29 | 深圳市风百胜风机制造有限公司 | Highly effective low-noise condensing axial flow fan of air conditioner for automobile |
| CN1793667A (en) * | 2006-01-12 | 2006-06-28 | 上海交通大学 | Biimpeller axial fan of traction electric machine brake cooling system |
| CN1793665A (en) * | 2006-01-12 | 2006-06-28 | 上海交通大学 | Low noise axial fan with rotary deflecting ring |
| CN1793664A (en) * | 2006-01-12 | 2006-06-28 | 上海交通大学 | Low noise axial fan for train air-conditioning condenser |
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| CN201241864Y (en) * | 2008-08-15 | 2009-05-20 | 新昌县科贸实业有限公司 | Wind impeller for fan |
| CN201496290U (en) * | 2009-08-12 | 2010-06-02 | 南京意航新技术发展有限公司 | Low consumption high efficiency automatable axial flow cooling fan |
| CN201599250U (en) * | 2009-12-28 | 2010-10-06 | 邱荣泉 | Mini cooling fan |
| CN201679745U (en) * | 2010-03-29 | 2010-12-22 | 新昌县科贸实业有限公司 | Low-noise axial flow fan for cooling air conditioner |
| CN202048031U (en) * | 2011-04-21 | 2011-11-23 | 株洲联诚集团有限责任公司 | Sweepforward-type axial-flow ventilator for locomotive converter |
| CN111255743A (en) * | 2020-03-02 | 2020-06-09 | 广东美的厨房电器制造有限公司 | Fan blade, cooling fan and microwave oven |
| CN211525182U (en) * | 2019-11-14 | 2020-09-18 | 浙江盾安轨道交通设备有限公司 | Swept-curved blade and axial flow fan |
| CN115263802A (en) * | 2022-09-09 | 2022-11-01 | 江苏朗信电气有限公司 | Axial fan for automobile heat dissipation |
| CN115717611A (en) * | 2022-09-30 | 2023-02-28 | 欧普照明股份有限公司 | Fan blade, fan and fan lamp |
-
2023
- 2023-04-11 CN CN202310380226.8A patent/CN116398471A/en active Pending
Patent Citations (16)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN1232143A (en) * | 1998-04-14 | 1999-10-20 | 松下电器产业株式会社 | Impeller of fan |
| CN1534200A (en) * | 2003-03-28 | 2004-10-06 | 中国科学院工程热物理研究所 | Axial ventilating machine impellor |
| CN2767722Y (en) * | 2004-10-20 | 2006-03-29 | 深圳市风百胜风机制造有限公司 | Highly effective low-noise condensing axial flow fan of air conditioner for automobile |
| CN1793667A (en) * | 2006-01-12 | 2006-06-28 | 上海交通大学 | Biimpeller axial fan of traction electric machine brake cooling system |
| CN1793665A (en) * | 2006-01-12 | 2006-06-28 | 上海交通大学 | Low noise axial fan with rotary deflecting ring |
| CN1793664A (en) * | 2006-01-12 | 2006-06-28 | 上海交通大学 | Low noise axial fan for train air-conditioning condenser |
| CN201034090Y (en) * | 2007-05-09 | 2008-03-12 | 新昌县科贸实业有限公司 | Energy-saving low-noise air-conditioner cooling shaft axialflown fan |
| CN201241864Y (en) * | 2008-08-15 | 2009-05-20 | 新昌县科贸实业有限公司 | Wind impeller for fan |
| CN201496290U (en) * | 2009-08-12 | 2010-06-02 | 南京意航新技术发展有限公司 | Low consumption high efficiency automatable axial flow cooling fan |
| CN201599250U (en) * | 2009-12-28 | 2010-10-06 | 邱荣泉 | Mini cooling fan |
| CN201679745U (en) * | 2010-03-29 | 2010-12-22 | 新昌县科贸实业有限公司 | Low-noise axial flow fan for cooling air conditioner |
| CN202048031U (en) * | 2011-04-21 | 2011-11-23 | 株洲联诚集团有限责任公司 | Sweepforward-type axial-flow ventilator for locomotive converter |
| CN211525182U (en) * | 2019-11-14 | 2020-09-18 | 浙江盾安轨道交通设备有限公司 | Swept-curved blade and axial flow fan |
| CN111255743A (en) * | 2020-03-02 | 2020-06-09 | 广东美的厨房电器制造有限公司 | Fan blade, cooling fan and microwave oven |
| CN115263802A (en) * | 2022-09-09 | 2022-11-01 | 江苏朗信电气有限公司 | Axial fan for automobile heat dissipation |
| CN115717611A (en) * | 2022-09-30 | 2023-02-28 | 欧普照明股份有限公司 | Fan blade, fan and fan lamp |
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