CN214036248U - High-efficiency low-noise axial flow fan blade profile - Google Patents
High-efficiency low-noise axial flow fan blade profile Download PDFInfo
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- CN214036248U CN214036248U CN202022989424.9U CN202022989424U CN214036248U CN 214036248 U CN214036248 U CN 214036248U CN 202022989424 U CN202022989424 U CN 202022989424U CN 214036248 U CN214036248 U CN 214036248U
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- 230000007704 transition Effects 0.000 claims description 9
- 230000003014 reinforcing effect Effects 0.000 claims description 3
- 238000003466 welding Methods 0.000 claims description 3
- 239000007787 solid Substances 0.000 claims description 2
- 230000008878 coupling Effects 0.000 abstract 2
- 238000010168 coupling process Methods 0.000 abstract 2
- 238000005859 coupling reaction Methods 0.000 abstract 2
- 238000009826 distribution Methods 0.000 description 5
- 238000001816 cooling Methods 0.000 description 4
- 230000003111 delayed effect Effects 0.000 description 3
- 238000005452 bending Methods 0.000 description 2
- 238000005520 cutting process Methods 0.000 description 2
- 238000010586 diagram Methods 0.000 description 2
- 238000004519 manufacturing process Methods 0.000 description 2
- 239000008358 core component Substances 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 230000007812 deficiency Effects 0.000 description 1
- 238000005265 energy consumption Methods 0.000 description 1
- 230000002452 interceptive effect Effects 0.000 description 1
- 239000000463 material Substances 0.000 description 1
- 238000000034 method Methods 0.000 description 1
- 238000000465 moulding Methods 0.000 description 1
- 238000002360 preparation method Methods 0.000 description 1
- 239000002994 raw material Substances 0.000 description 1
- 238000005728 strengthening Methods 0.000 description 1
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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
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- Engineering & Computer Science (AREA)
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- General Engineering & Computer Science (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
The utility model discloses a high-efficient low noise axial fan blade profile, including wing section and front of a garment wing section, the wing section is from the root to the setting of apex position aequilate, the wing section includes wing windward side, wing leeward side, front of a garment wing section includes wing flap windward side, wing flap leeward side, wing windward side and wing leeward side are the arcwall face, the wing windward side is close to wing leading edge position and is the evagination cambered surface, is close to wing trailing edge position and is the indent cambered surface, the evagination cambered surface and the smooth transitional coupling of indent cambered surface of wing windward side, wing leeward side is the evagination cambered surface, wing windward side and wing flap leeward side all are the smooth transitional coupling of circular arc, the utility model has the advantages of novel structure, lift coefficient height, air resistance are little, pneumatic efficiency is high, the operation noise is low.
Description
Technical Field
The utility model relates to an axial fan technical field, specific high-efficient low noise axial fan blade profile that says so.
Background
Compared with the prior version, the energy efficiency improvement is one key updating project, the prior standard energy efficiency grade is divided into five grades, the 5 th grade is the industrial grade of the original edition standard, the 1 st to the 4 th grades are the energy efficiency grades which are newly increased and improved, the new edition standard is pushed out to put higher requirements on each energy consumption part of the cooling tower, in particular to a cooling tower impeller which is a core component, the prior conventional cooling tower fan impeller blade type generally adopts an equal-width hollow fan airfoil blade, the blade type section structure is shown in figure 1, the prior cooling tower fan impeller blade type mainly adopts a hollow fan airfoil structure without a flap, the blade tip and the blade root are equal in width, the windward side adopts a straight surface, and the structure has the advantages of low manufacturing cost, the production efficiency is high; the method has the defects that the distribution difference of airflow along the radial direction is large, the airflow distribution is uneven, the blade profile lift coefficient is yet to be further improved, and increasingly severe technical requirements on energy efficiency and low noise are difficult to meet.
In the prior art, hollow airfoil blades with flaps also exist, and through search, CN2016207319008 discloses a high-efficiency equal-width axial flow fan blade profile, which is provided with an organic wing part and a flap part, wherein the organic wing part is arranged at equal width from a blade root to a blade tip part, the flap part is arranged at equal width from the blade root to the blade tip part, a windward surface of the organic wing part is a straight surface, and the lift coefficient of an axial flow fan is improved by arranging the flap part; however, the blade profile lift coefficient and the aerodynamic performance of the fan are still to be further improved.
Therefore, a novel blade profile with a structure form which can guarantee the requirements of improving efficiency and reducing noise and can guarantee the cost equivalent to that of a conventional constant-width hollow machine airfoil blade profile is urgently needed to be developed.
Disclosure of Invention
The utility model aims at solving the deficiencies of the prior art, provide a novel structure, lift coefficient is high, air resistance is little, aerodynamic efficiency is high, the high-efficient low noise axial fan blade profile of operation noise is low.
The utility model provides a technical scheme that its technical problem adopted is:
the utility model provides a high-efficient low noise axial fan blade profile, includes wing panel and flap panel, the wing panel is from the blade root to the setting of apex position aequilate, the wing panel includes wing windward side, wing leeward side, the flap panel includes flap windward side, flap leeward side, its characterized in that: the wing windward side and the wing leeward side are both arc surfaces, the part of the wing windward side close to the wing front edge is an outward arc surface, the part of the wing trailing edge is an inward arc surface, the outward arc surface of the wing windward side is in smooth transition connection with the inward arc surface, the wing leeward side is an outward arc surface, the wing windward side and the wing flap windward side are in arc smooth transition connection, the part of the wing windward side close to the wing front edge is an outward arc surface, the radius of the front edge is increased, the stall critical angle is improved, the stall airfoil profile characteristic is delayed, the part close to the wing trailing edge is an inward arc surface, the camber of the windward side trailing edge is increased, the relative camber of the airfoil is increased, the zero lift force angle is improved, the lift force coefficient is improved, the vane aerodynamic characteristic is improved, the vane chord length is increased by arranging the flap section, and the aerodynamic performance is improved, the flap section and the wing section are in smooth transition connection so as to reduce airflow resistance during blade profile operation and reduce aerodynamic noise.
The chord length of front fly wing section strides 20 ~30 circumference to increase the relative camber of leaf profile, increased the leaf profile chord length simultaneously, improved pneumatic performance.
The size proportion range of the chord length of the wing section and the chord length of the flap section is (2.7: 1) - (6.5: 1), and the proportion is matched with the requirements of the diameter of the impeller, the rotating speed and the pneumatic performance so as to achieve the optimal pneumatic performance under the working condition and reduce the pneumatic noise generated during working.
The inner chamber of wing panel is hollow structure, be equipped with the vertical strengthening rib of a plurality of on the inner wall of wing panel, can alleviate the section bar wall thickness on the one hand, reduce section bar weight and raw and other materials cost, on the other hand can improve the vertical bending modulus of section bar, obtains higher structural strength.
The front of a garment wing section adopts the entity structure, the position that front of a garment wing section and wing trailing edge are connected is the linkage segment, and the position of keeping away from the wing trailing edge is the extension section, the equal thickness setting of extension section, the wall thickness of linkage segment is reduced gradually towards the extension section by the wing trailing edge and is equal with the wall thickness of extension section, has guaranteed the intensity of structure and has effectively increased the chord length of leaf type, improves impeller projection reality, extension aerodynamic performance.
The length of the front wing section is equal to the length of the wing section.
The front of a garment wing section is equipped with the apex corner cut at the apex position to improve the air current distribution of the radial direction of leaf type, in order to obtain better aerodynamic performance.
The width of the tip chamfer is less than or equal to the width of the flap section, and the proportion range of the length of the tip chamfer to the length of the flap section is (0.15: 1) - (0.5: 1) so as to further ensure that better pneumatic performance is obtained.
The front fly wing section is equipped with the blade root corner cut at the blade root position, through setting up the blade root corner cut to prevent front fly wing leaf root from causing the interference to the fan.
Wing panel and the integrative pultrusion setting of flap panel or riveting fixation or welded fastening, according to the connected mode of impeller diameter in order to select wing panel and flap panel of difference.
The utility model has the advantages that: the part of the windward side of the wing, which is close to the front edge of the wing, is an outward convex cambered surface, so that the radius of the front edge is increased, the stall critical angle is improved, the applicable angle of the blade is increased, the stall characteristic of the wing profile is delayed, the part of the windward side is an inward concave cambered surface, so that the camber of the rear edge of the windward side is increased, the relative camber of the wing profile is increased, the zero lift angle is improved, the lift coefficient is increased, and the aerodynamic characteristic of the blade profile is improved; the flap section is arranged to increase the chord length of the blade profile, the pneumatic performance is improved, and the flap section and the wing section are in smooth transition connection to reduce the airflow resistance during the operation of the blade profile and reduce the pneumatic noise; the flap segment is provided with a cutting angle at the blade tip part so as to improve the airflow distribution in the radial direction of the blade profile and obtain better pneumatic performance.
Drawings
FIG. 1 is a sectional view of a blade profile of a hollow airfoil blade with an equal width in the prior art.
Fig. 2 is the schematic view of the cross-sectional structure of the wing profile of the double cambered surface machine with flap extension of the present invention.
Fig. 3 is an enlarged schematic view of the structure at I in fig. 2.
Fig. 4 is a schematic view of a double cambered surface machine airfoil impeller with flap extension and a blade profile corner cut according to the present invention.
Fig. 5 is a schematic structural view of a double cambered surface airfoil fan with flap extension according to the present invention.
Fig. 6 shows the comparison data of the structure of the present invention with the conventional structure for the full-pressure efficiency and the sound level test.
Fig. 7 is the comparison graph of the total pressure efficiency test of the structure and the conventional structure.
Fig. 8 is a sound level test comparison curve chart of the structure of the utility model compared with the conventional structure.
Reference numerals: hub-1, blade-2, wing section-21, wing windward side-211, wing leeward side-212, wing leading edge-213, wing trailing edge-214, longitudinal reinforcing rib-215, flap section-22, flap windward side-221, flap leeward side-222, blade tip chamfer-223, blade root chamfer-224 and blade handle-3.
Detailed Description
The present invention will be described with reference to the accompanying drawings and examples.
As shown in fig. 2-5, a high-efficiency low-noise axial flow fan blade profile comprises a wing section 21 and a flap section 22, wherein the wing section 21 is arranged in an equal width from a blade root to a blade tip, the wing section 21 comprises a wing windward surface 211 and a wing leeward surface 212, the flap section 22 comprises a flap windward surface 221 and a flap leeward surface 222, the wing windward surface 211 and the wing leeward surface 212 are both arc surfaces, the part of the wing windward surface 211 close to a wing leading edge 213 is an outer convex arc surface, the part close to a wing trailing edge 214 is an inner concave arc surface, the outer convex arc surface of the wing windward surface 211 is in smooth transition connection with the inner concave arc surface, the wing leeward surface 212 is an outer convex arc surface, the wing windward surface 211 is in arc smooth transition connection with the flap windward surface 221, the wing leeward surface 212 and the flap leeward surface 222, and the wing leeward surface 211 close to the wing leading edge 213 is an outer convex arc surface, the radius of the front edge is increased, the stall critical angle is improved, the stall characteristic of the airfoil is delayed, the part, close to the trailing edge 214 of the airfoil, is an inward concave cambered surface so as to increase the camber of the trailing edge of a windward side, increase the relative camber of the airfoil, improve the zero lift angle, increase the lift coefficient, improve the aerodynamic characteristic of the airfoil, and the flap section 22 is arranged to increase the chord length of the airfoil, improve the aerodynamic performance, and the flap section 22 is connected with the airfoil section 21 in a smooth transition manner so as to reduce the airflow resistance when the airfoil operates and reduce the aerodynamic noise.
The chord length of the flap section 22 spans 20-30 DEG of circumference to increase the relative camber of the blade profile, increase the chord length of the blade profile and improve the pneumatic performance.
The size proportion range of the chord length of the wing section to the chord length of the flap section is (2.7: 1) - (6.5: 1), and the proportion is matched with the diameter of the impeller, the rotating speed and the pneumatic performance requirements, so that the optimal pneumatic performance is achieved under the working condition, and the pneumatic noise generated during working is reduced. The wing section chord length in this embodiment is designated L1 and the flap section chord length is designated L2.
The inner cavity of the wing panel 21 is of a hollow structure, and the inner wall of the wing panel 21 is provided with a plurality of longitudinal reinforcing ribs 215, so that the wall thickness of the section can be reduced, the weight of the section and the cost of raw materials can be reduced, the longitudinal bending modulus of the section can be improved, and higher structural strength can be obtained.
The flap section 22 is of a solid structure, the part of the flap section 22 connected with the trailing edge of the wing is a connecting section, the part far away from the trailing edge of the wing is an expanding section, the expanding section is arranged in an equal thickness, the wall thickness of the connecting section is gradually reduced from the trailing edge of the wing to the expanding section and is equal to that of the expanding section, the structural strength is ensured, the chord length of a blade shape is effectively increased, the projection compactness of the impeller is improved, and the aerodynamic performance is expanded.
The flap panel 22 has a length equal to the length of the wing panel 21. In the embodiment, the lengths of the flap panel and the wing panel are equal, and when the diameter of the impeller is larger, the flap panel can be arranged at the position of the blade root.
The flap segment 22 is provided with a blade tip cut angle 223 at the blade tip part, and the cutting adopts a beveling mode to improve the airflow distribution in the radial direction of the blade profile so as to obtain better pneumatic performance. In this embodiment, the flap 22 is made with the same width from the blade root to the blade tip, and the blade tip chamfer is formed at the blade tip after molding.
The width of the tip chamfer 223 is smaller than that of the flap segment 22, and the ratio range of the length of the tip chamfer 223 to the length of the flap segment 22 is (0.15: 1) - (0.5: 1), so as to further ensure that better aerodynamic performance is obtained. The length of the tip cut in this embodiment is designated as W1, and the length of the flap and wing sections is W, with the width of the tip cut in this embodiment being slightly less than the width of the flap section.
The flap panel 22 is provided with a blade root chamfer 224 at the blade root, and the blade root chamfer 224 is arranged to prevent the flap blade root from interfering with the fan. The width of the root chamfer is less than or equal to the width of the flap segment, and the width of the root chamfer in this embodiment is also slightly less than the width of the flap segment.
The wing panel 21 and the flap panel 22 are integrally formed by pultrusion, riveting or welding, and the connection mode of the wing panel and the flap panel is selected according to different diameters of impellers. In the embodiment, the wing section and the flap section are designed through integral pultrusion, when the diameter of the impeller is larger, the wing section and the flap section can be formed in a split mode and then riveted and fixed, and welding and fixing can be carried out according to actual use requirements.
Fig. 4 is a structural schematic diagram of an impeller, and a blade 2 is connected with a hub 1 through a blade handle 3, and fig. 5 is a structural schematic diagram of a whole fan.
FIG. 6, FIG. 7, and FIG. 8 show the test data of the same model machine with the same model machine number, the same performance, and the same rotation speed, in this embodiment, the blade chord length (the total chord length of the wing section and the flap section) of the model machine is 300mm, the number of the blades is 4, the diameter of the impeller is 1800mm, the motor power is 11kW, the rotation speed of the impeller is 720RPM, the actual test air volume range is 90000m ^ 3/h-1800000 m ^3/h, and the pressure is 150 Pa-300 Pa. Data and curve show in the follow attached drawing, this utility model's structure aerodynamic performance improves 2% ~5%, and noise reduction 2dB ~6dB has excellent aerodynamic performance and lower aerodynamic noise in actual test and application.
The utility model discloses when the preparation, with the integrative pultrusion setting of wing panel and front of a garment wing panel, rethread leaf profile processing forms apex corner cut and blade root corner cut behind the leaf profile pultrusion of aequilate.
Claims (10)
1. The utility model provides a high-efficient low noise axial fan blade profile, includes wing panel and flap panel, the wing panel is from the blade root to the setting of apex position aequilate, the wing panel includes wing windward side, wing leeward side, the flap panel includes flap windward side, flap leeward side, its characterized in that: the wing windward side and the wing leeward side are both arc surfaces, the part of the wing windward side, which is close to the wing front edge, is an outward convex arc surface, the part of the wing rear edge is an inward concave arc surface, the outward convex arc surface of the wing windward side is in smooth transition connection with the inward concave arc surface, the wing leeward side is an outward convex arc surface, and the wing windward side and the wing flap windward side, and the wing leeward side and the wing flap leeward side are in arc smooth transition connection.
2. The blade profile of an axial flow fan with high efficiency and low noise as claimed in claim 1, wherein: the chord length of the flap section spans 20-30 DEG of circumference.
3. The blade profile of an axial flow fan with high efficiency and low noise as claimed in claim 1 or 2, wherein: the size ratio range of the chord length of the wing section to the chord length of the flap section is (2.7: 1) - (6.5: 1).
4. The blade profile of an axial flow fan with high efficiency and low noise as claimed in claim 3, wherein: the inner cavity of the wing panel is of a hollow structure, and a plurality of longitudinal reinforcing ribs are arranged on the inner wall of the wing panel.
5. The blade profile of an axial flow fan with high efficiency and low noise as claimed in claim 4, wherein: the flap panel is of a solid structure, the part of the flap panel, which is connected with the trailing edge of the wing, is a connecting section, the part far away from the trailing edge of the wing is an expanding section, the expanding section is arranged in an equal thickness mode, and the wall thickness of the connecting section is gradually reduced from the trailing edge of the wing to the expanding section and is equal to that of the expanding section.
6. An efficient low noise axial flow fan blade according to claim 2 or 4 or 5, wherein: the length of the flap segment is equal to the length of the wing segment.
7. The blade profile of an axial flow fan with high efficiency and low noise as claimed in claim 6, wherein: and the flap section is provided with a blade tip corner cut at the blade tip part.
8. The blade profile of an axial flow fan with high efficiency and low noise as claimed in claim 7, wherein: the width of the tip chamfer is less than or equal to the width of the flap section, and the ratio range of the length of the tip chamfer to the length of the flap section is (0.15: 1) - (0.5: 1).
9. A high efficiency low noise axial flow fan blade profile according to claim 7 or 8, wherein: and the flap panel is provided with a blade root chamfer at the blade root.
10. A high efficiency, low noise axial flow fan blade according to claim 1, 2, 4 or 5, wherein: the wing panel and the flap panel are integrally formed by pultrusion, riveting or welding.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202022989424.9U CN214036248U (en) | 2020-12-14 | 2020-12-14 | High-efficiency low-noise axial flow fan blade profile |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202022989424.9U CN214036248U (en) | 2020-12-14 | 2020-12-14 | High-efficiency low-noise axial flow fan blade profile |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN214036248U true CN214036248U (en) | 2021-08-24 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202022989424.9U Active CN214036248U (en) | 2020-12-14 | 2020-12-14 | High-efficiency low-noise axial flow fan blade profile |
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|---|---|
| CN (1) | CN214036248U (en) |
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2020
- 2020-12-14 CN CN202022989424.9U patent/CN214036248U/en active Active
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