CN106837867B - Three-way impeller for axial fans with vein-like structure and splitter blades - Google Patents

Abstract

The invention discloses an axial flow fan ternary impeller with a vein structure and splitter blades, which comprises a hub, a shaft sleeve and a connecting piece, wherein the hub is fixed on the hub by the connecting piece; the device also comprises a bending blade and a splitter blade which are fixedly connected to the hub; the bending blade comprises a suction surface and a pressure surface; the top of the bending blade is provided with an airfoil groove; the upper half part of the pressure surface of the bending blade is provided with a vein-shaped groove, and the wing-shaped groove is communicated with the vein-shaped groove through an air outlet; the tail part of the suction surface of the bending blade is provided with a winglet protuberance; parabolic small holes are formed in the bending and twisting blades; a splitter blade is arranged between two adjacent bending blades; the height of the splitter blade is less than half the height of the turning blade.

Description

Three-way impeller for axial fans with vein-like structure and splitter blades

technical field

The invention relates to the design field of an axial flow fan, in particular to a novel three-dimensional impeller of an axial flow fan with a vein-shaped structure and splitter blades.

Background technique

The working principle of the axial flow fan is to use the mechanical energy input by the motor to increase the pressure of the gas to transport and discharge the gas. Axial flow fans play a role in various fields of the national economy, widely used in factories, mines, vehicles, boats and buildings, etc., and play an irreplaceable role in ventilation, dust removal and cooling. According to incomplete statistics, all countries in the country The annual power consumption of wind turbines accounts for 20% of the country's power generation. Many of the wind turbines are either old or low in efficiency, resulting in a serious waste of electricity. It can be seen that improving the performance of wind turbines to achieve energy conservation is important in the national economy. Axial flow fans are usually used in occasions with high flow requirements and low pressure. The structure is relatively simple and easy to install, and it plays an irreplaceable role in the field of fans.

Although the structure of the axial flow fan is simple, the flow situation is indeed quite complicated. The flow is often three-dimensional, viscous and unsteady, and it is rarely or difficult to fully consider these situations in the past fan design. Even with the mature numerical analysis, it is difficult to control the influence of the above factors on the fan, especially the fluid The key factor is viscosity, because the viscosity often causes the blade wake vortex to form at the blade outlet; due to the viscosity, there will be a viscous boundary layer on the blade surface (especially when the blade surface is very smooth), and there will be a strong interaction between the blade surface and the mainstream. Effect, resulting in secondary flow phenomenon; the existence of viscosity will also form aerodynamic noise, mainly including rotational noise and eddy current noise. In addition, the pressure difference between the pressure surface and the suction surface of the blade, the radial clearance between the top of the blade and the casing, and the secondary flow generated by the radial flow in the boundary layer of the blade itself are also the main sources of increased fan losses and reduced efficiency.

In summary, only by controlling and reducing the secondary flow phenomenon, preventing boundary layer separation, suppressing the generation of blade wake vortices, and reducing turbulent dissipation and flow loss can an axial flow fan with high efficiency, good performance, low noise and energy saving be designed , to meet the needs of modern production for fans.

Contents of the invention

The problem to be solved by the present invention is to propose a new type of axial flow fan with vein-like structure and splitter blades by controlling and reducing secondary flow, boundary layer separation, wake vortex and vortex noise. impeller. The invention can reduce secondary flow phenomenon, prevent boundary layer separation, suppress blade wake vortex generation, reduce turbulent flow dissipation and flow loss, and has the characteristics of high efficiency, good performance, low noise and energy saving.

In order to solve the above technical problems, the present invention provides a ternary impeller of an axial flow fan with a vein-like structure and splitter blades, including a hub and a shaft sleeve fixed on the hub with connectors; splitter vane;

The twisted blade includes a suction surface and a pressure surface; the top of the twisted blade is provided with an airfoil groove; the upper half of the pressure surface of the curved blade is provided with a vein-shaped groove, and the airfoil groove passes through the air outlet and The vein-shaped grooves are connected; the tail of the suction surface of the twisted blade is provided with a small wing protrusion; the curved blade is provided with a parabolic small hole;

A splitter vane is arranged between two adjacent twisted vanes; the height of the splitter vane is less than half of the height of the twisted vane.

As an improvement of the ternary impeller of the axial flow fan with vein-like structure and splitter blades of the present invention: the splitter blades are kudzu wings; the splitter blades are arranged in the middle of adjacent curved and twisted blades.

As a further improvement of the ternary impeller of the axial flow fan with vein-shaped structure and splitter blades of the present invention: the structures on both sides of the splitter blades are the same, and are respectively: at least two radially equidistant Groove groups, each groove group includes at least two bionic circular grooves, the center line of the bionic circular grooves of each groove group is perpendicular to the outer surface of the hub, and the axis line of the bionic groove is perpendicular to the splitter blade .

As a further improvement of the ternary impeller of the axial flow fan with vein-shaped structure and splitter blades of the present invention: the vein-shaped groove includes at least two vein grooves, each vein groove communicates with an air outlet, and the air outlet is connected to the airfoil The slots are connected.

As a further improvement of the ternary impeller of the axial flow fan with vein-like structure and splitter blades of the present invention: the rear end of the suction surface of the twisted blade is equidistantly provided with three winglet protrusions.

As a further improvement of the ternary impeller of the axial flow fan with vein-like structure and splitter blades of the present invention: eight curved twisted blades and eight splitter blades are equidistantly arranged on the hub.

As a further improvement of the ternary impeller of the axial flow fan with a vein-like structure and splitter blades of the present invention: the twisted and twisted blades are 15°-20° and bent 15°-20°.

As a further improvement of the ternary impeller of the axial flow fan with vein-like structure and splitter blades of the present invention: the height of the splitter blades is 30%-40% of the height of the twisted blades.

The invention has the following advantages: the installation angle of the root of the blade is large and the installation angle of the top of the blade is small by using the curved and twisted blade, so as to ensure that the air has a relatively uniform axial velocity at each position in the radial direction and ensure normal operation. Avoid airflow separation, reduce flow loss and effectively suppress the secondary flow inside the cascade (static pressure is C-shaped distribution blade suction surface and pressure surface pressure difference is smaller than conventional blades), while improving the root reaction degree, reducing the top reaction degree, To achieve the purpose of homogenizing the distribution of reaction degree along the blade height, and improve the flow capacity of the root; there are vein-like grooves on the top of the pressure surface of the curved and twisted blades, and there are airfoil grooves, airfoil grooves and vein-shaped grooves on the top of the curved and twisted blades Connected by air outlets, this structure can form a low-speed secondary vortex in the vein-shaped groove. The viscous resistance in the groove is opposite to the total resistance to reduce the viscous resistance, suppress the turbulence intensity, reduce the turbulence dissipation, and can dissipate the high-energy gas on the pressure surface. The lead is introduced into the airfoil groove on the top of the blade through the vein-like groove and the air outlet, preventing some gas from flowing from the pressure surface to the suction surface through the radial gap, causing chaos in the flow near the top of the twisted blade, improving the flow at the top of the twisted blade, and also It can avoid the lateral secondary flow phenomenon caused by the gas flowing from the pressure surface of the twisted blade to the adjacent suction surface, so as to reduce the flow loss. At the same time, the vein-shaped grooves also have the function of ordinary grooves; the parabolic small holes on the twisted blades It can reduce the pressure difference between the suction surface and the pressure surface of the blade, improve the separation of the boundary layer around the blade, and reduce the generation of eddy noise; the small wing protrusion on the tail of the twisted blade can guide the airflow along the chord direction, which can be well controlled Radial flow, reducing the secondary flow of radial movement, preventing wake jets, making the separation point of the boundary layer on the suction surface of the curved and twisted blade move backwards, reducing energy loss; the splitter blade can effectively break the vortex, making the flow in the flow channel more stable , to reduce unstable phenomena such as flow separation and secondary flow, and the bionic round grooves on the splitter blades can reduce wall friction resistance, flow resistance, and flow loss. Relying on the principle to improve the different positions of the impeller of the axial flow fan, the efficiency of the axial flow fan is higher, the performance is better, and it is more energy-saving and environmentally friendly.

Description of drawings

The specific implementation manners of the present invention will be described in further detail below in conjunction with the accompanying drawings.

Fig. 1 is the overall structure schematic diagram of the novel axial flow fan ternary impeller of the present invention band leaf vein structure and splitter blade;

Fig. 2 is a structural schematic diagram of the suction surface of the curved and twisted blade in Fig. 1;

Fig. 3 is a structural schematic diagram of the pressure surface of the curved and twisted blade in Fig. 1;

Fig. 4 is the structural representation of splitter vane in Fig. 1;

Fig. 5 is a schematic structural view of the B-B surface of the splitter blade in Fig. 4;

Fig. 6 is a structural schematic diagram of the C-C surface of the twisted blade and the winglet protrusion in Fig. 2;

Fig. 7 is a structural schematic diagram of the bionic circular groove of the splitter blade in Fig. 1;

Fig. 8 is a schematic structural view of the airfoil groove in Fig. 1;

Fig. 9 is a schematic diagram of the cascade structure of the curved and twisted blades in Fig. 1;

FIG. 10 is a schematic diagram of the bent and twisted structure of the twisted blade 1 in FIG. 1 .

Detailed ways

The present invention will be further described below in conjunction with specific examples, but the protection scope of the present invention is not limited thereto.

Embodiment 1. A new three-dimensional impeller for an axial flow fan with a vein-like structure and splitter blades, as shown in the figure, includes a hub, a curved and twisted blade 1 fixedly connected to the hub, splitter blades 2, a shaft sleeve 3 and a connecting piece 4 .

The curved and twisted blade 1 includes a suction surface 18 and a pressure surface 19. The top of the suction surface 18 of the curved and twisted blade 1 is provided with a vein-shaped groove 15, and the rear end of the curved and twisted blade 1 is provided with a winglet protrusion 13. The vein-shaped groove 15 includes at least Two veins, the installation angle at the root of the twisted blade 1 is large, and the installation angle at the top is small (the installation angle is the angle between the rotation plane at the radius r of the curved blade 1 and the chord length of the airfoil, determined by β1 and β2), to ensure that the air has a relatively uniform axial velocity at each position in the radial direction, to ensure normal operation, avoid air separation, reduce flow loss and effectively suppress the secondary flow inside the cascade (the static pressure is C-shaped distribution , so that the pressure difference between the suction surface 18 and the pressure surface 19 of the blade is smaller than that of a conventional blade), and at the same time, the degree of reaction at the root of the curved and twisted blade 1 can be increased, and the degree of reaction at the top of the curved and twisted blade 1 can be reduced, so as to achieve the purpose of homogenizing the distribution of the degree of reaction along the blade height. The flow capacity of the root of the curved and twisted blade 1 is improved. The cascade refers to the plane that cuts off the blades with its axial cylindrical surface on a certain radius r, and then develops this section, reflecting the positional relationship of adjacent twisted blades 1, the installation angle of twisted blades 1, etc.

The winglet protrusions 13 are set on the suction surface 18 to enable the fluid to flow in the cascade. Due to the interaction between the twisted blade 1 and the fluid, the pressure on the pressure surface 19 of the blade is greater than that on the suction surface 18, and the fluid flows from the pressure surface 19 of the twisted blade 1 to the suction force. The flow on the surface 18, and the airflow on the suction surface 18 caused by the incoming flow is more turbulent, so the empennage is designed to make the airflow move along the chord direction, control the radial flow, and simultaneously control the size of the channel vortex in the channel of the curved blade 1 and the surface of the blade The boundary layer creeping flow controls the secondary flow of radial movement, reduces the uneven velocity, prevents the wake jet, and makes the separation point of the suction surface 18 of the twisted blade 1 move backward to reduce energy loss.

The top of the twisted blade 1 is provided with an airfoil groove 11, and the airfoil groove 11 communicates with the vein-shaped groove 15 on the top of the suction surface 18 of the twisted blade 1 through several air outlets 14. This structure can form a low-speed The secondary vortex, the viscous resistance in the vein-shaped groove 15 is opposite to the total resistance to reduce the viscous resistance, suppress the turbulent flow intensity, reduce the turbulent flow dissipation, and guide the high-energy gas on the upper part of the pressure surface 19 of the twisted blade 1 through the vein-shaped groove 15 and the air outlet 14 into the blade top airfoil groove 11 to prevent some gas from flowing from the pressure surface 19 to the suction surface 18 through the radial gap, causing chaos in the flow near the top of the curved and twisted blade 1, improving the flow at the top of the curved and twisted blade 1, and also It can avoid the lateral secondary flow phenomenon caused by the gas flowing from the pressure surface 19 of the twisted blade 1 to the adjacent suction surface 18, so as to reduce the flow loss. At the same time, the airfoil groove 11 on the top of the twisted blade 1 also has the function of a common groove , can form the vortex pad effect and reduce the turbulence intensity near the wall. The curved and twisted blade 1 is provided with a parabolic small hole 12, which can reduce the pressure difference between the suction surface 18 and the pressure surface 19 of the curved and twisted blade 1, improve the boundary layer separation around the curved and twisted blade 1, and reduce the generation of eddy current noise; The winglet protrusion 13 at the rear end of the twisted blade 1 can guide the airflow to move along the chord direction, which can well control the radial flow, reduce the secondary flow of the radial movement, prevent the wake jet, and make the suction surface 18 of the twisted blade 1 The boundary layer separation point moves backwards to reduce energy loss. The splitter blade 2 is a kudzu wing, which is set in the middle of two adjacent twisted blades 1, and the two sides are provided with radially equidistant groove groups, and each groove group contains more than two bionic circular grooves 23. The bionic circular grooves 23 are arranged on the same straight line, the center line of the bionic circular grooves 23 of each groove group is perpendicular to the outer surface of the hub, and the axis of the bionic circular grooves 23 is perpendicular to the splitter blade 2 . The splitter vane 2 can effectively break the vortex, make the flow in the flow channel more stable, and reduce instability such as flow separation and secondary flow. In addition, the bionic circular groove 23 on the curved and twisted vane 1 can reduce wall friction resistance and flow resistance. , to reduce flow loss. The height of the splitter vane 2 is less than that of the curved and twisted vane 1, and the shaft sleeve 3 is fixed on the hub with a standard connector 4. The splitter vanes 2 are used to block the transverse flow from the pressure surface 19 of the twisted blade 1 to the suction surface 18 of the twisted blade 1 and vortex breaking at the blade root of the twisted blade 1 .

Referring to the working principle of the blade, the twisting of the curved and twisted blade 1 can ensure that the air has a relatively uniform axial velocity at all positions in the radial direction, ensure normal work, avoid air separation, and reduce flow loss. The boundary layer migration theory proposed based on the static blowing experiments and numerical calculation results of the blade annular cascade, that is, after the twisted blade 1 is bent in the circumferential direction, the radial component of the force between the surface of the twisted blade 1 and the airflow is not equal to zero, Thus, the distribution of pressure along the height of the curved blade 1 is controlled. After the curved blade 1 is bent in the circumferential direction, the radial component of the force between the surface of the curved blade 1 and the airflow is not equal to zero, thereby controlling the pressure along the curved blade 1. The distribution of the height makes the pressure distribution with high pressure at both ends and low pressure in the middle formed on the surface of the curved and twisted blade 1, especially the suction surface 18, that is, the "C" type pressure distribution. The layer is sucked to the middle and taken away by the main flow, which reduces the accumulation of low-energy fluid at the corner formed by the two end walls and the suction surface 18, avoids the occurrence of separation, and thus reduces the flow loss at both ends, followed by bending The pressure difference between the pressure surface 19 and the suction surface 18 of the twisted blade 1 is obviously smaller than that of the conventional blade, the lateral secondary flow on the end wall is weakened, and the corresponding lateral secondary flow loss is reduced. Excellent performance, can improve stage reaction and increase stage flow capacity, delay channel vortex formation time and reduce channel vortex size and strength, twisted blade 1 is designed to twist 15°-20°, bend 15°-20° °, at the same time, in order to more effectively reduce the secondary flow, suppress the thickness of the boundary layer, control the formation of the wake tip vortex, and reduce the dissipation of turbulent flow, the vein-shaped groove 15, airfoil groove 11, parabolic small hole 12 and winglet protrusions are designed 13 etc.

In the present invention, the blades on the hub are first designed to be bent and twisted to ensure that the air flow has a relatively uniform axial velocity at each position in the radial direction, to ensure normal operation, to avoid air separation, to reduce flow loss and to effectively suppress the internal diameter of the cascade. At the same time, it can increase the degree of reaction at the root, reduce the degree of reaction at the top, achieve the purpose of equalizing the distribution of the degree of reaction along the blade height, improve the flow capacity of the root, delay the formation time of channel vortex and reduce the time of channel vortex Size and strength; the vein-shaped groove 15 on the upper half of the pressure surface 19 of the twisted blade 1 is connected to the airfoil groove 11 on the top of the twisted blade 1 through the air outlet 14, and this structure can be formed in the vein-shaped groove 15 Low-speed secondary vortex, the viscous resistance in the groove is opposite to the total resistance to reduce viscous resistance, suppress turbulent flow intensity, reduce turbulent flow dissipation, and can guide the high-energy gas on the upper part of the pressure surface 19 to the blade tip through the vein-shaped groove 15 and the gas outlet 14 The airfoil groove 11 prevents some gas from flowing from the pressure surface 19 to the suction surface 18 through the radial gap, causing chaos in the flow near the top of the twisted blade 1, improving the flow of the blade tip, and also avoiding the pressure of the gas from the curved blade 1 Surface 19 flows to the lateral secondary flow phenomenon that adjacent suction surface 18 produces, thereby reduces flow loss, and at the same time, the vein-shaped groove 15 on the top of the curved and twisted blade 1 also has the effect of a common groove, which can form a vortex pad effect, making the near The turbulence intensity in the wall area is reduced; the parabolic small hole 12 on the twisted blade 1 can reduce the pressure difference between the suction surface 18 and the pressure surface 19, improve the boundary layer separation around the twisted blade 1, and reduce the generation of eddy current noise; the empennage can guide the airflow Moving along the chord direction can well control the radial flow, reduce the secondary flow of the radial movement, prevent the wake jet, and make the separation point of the suction surface 18 of the twisted blade 1 move backward to reduce energy loss; The splitter blade 2 can effectively break the vortex, make the flow in the flow channel more stable, and reduce the unstable phenomena such as flow separation and secondary flow. loss, while suppressing the generation of eddy noise. Relying on the principle to improve the different positions of the impeller of the axial flow fan, the efficiency of the axial flow fan is higher, the performance is better, and it is more energy-saving and environmentally friendly.

Twisted blade 1 is an airfoil blade designed by the isocircular isolated airfoil method. The thickness distribution of curved and twisted blade 1 is the same as that of the NACA four-digit airfoil. The relative thickness of the airfoil is 10%-15%. The number of 1 is 8; the groove depth of the airfoil groove 11 on the top of the curved blade 1 is 1%-2% of the height of the curved blade 1, and the thickness of the airfoil groove 11 is 50%-60 of the top surface of the curved blade 1 %; On the rear end of the twisted blade 1, there are winglet protrusions 13 equidistantly distributed, the spacing d1 of the winglet protrusions 13 is 18%-22% of the height H of the twisted blade 1, and the length d4 of the winglet protrusion 13 is the twisted blade 15%-17% of the chord length, the angle ω with the chord length is 30°-40°, and the distance d5 from the rear edge of the curved blade 1 is 1%-3% of the chord length of the curved blade 1; Distributed in the twisted blade 1 are parabolic small holes 12 with a diameter of 1-2mm; the depth of the vein-shaped groove 15 on the top of the pressure surface 19 of the twisted blade 1 is 1-2mm, and the maximum groove length is 30% of the height of the twisted blade 1 -40%, the pitch of the veins is 20-30mm, and each vein is connected to an air outlet 14 independently, and the specific number of veins depends on the size of the twisted blade 1; the twisted blade 1 is twisted by 15°-20° , bend 15°-20°. Bending means that the twisted blade 1 bends along the horizontal mid-section (the surface perpendicular to the height of the twisted blade 1) when it is designed with the equal circulation isolated airfoil method, that is, the airfoil sections at different radii Corresponding pitch; Twist refers to that the twisted blade 1 twists along the vertical middle section (the plane parallel to the height of the twisted blade 1) when the twisted blade 1 is designed with the equal circulation isolated airfoil method, that is, the airfoil sections at different radii wrap around The vertical direction is twisted by the corresponding angle. Twisting benefits: not only makes the installation angle of the blade root of the curved and twisted blade 1 large, but the installation angle of the blade tip is small, but also ensures that the air has a relatively uniform axial velocity at all positions in the radial direction, ensuring normal operation and avoiding air separation , to reduce flow loss. Benefits of bending and twisting: it can effectively suppress the secondary flow inside the cascade (the pressure difference between the suction surface 18 and the pressure surface 19 of the curved and twisted blade 1 is smaller than that of a conventional blade), and at the same time, it can increase the degree of root reaction and reduce the top pressure. The degree of reaction can achieve the purpose of homogenizing the distribution of degree of reaction along the height of the blade, improving the flow capacity of the root, delaying the formation time of channel vortex and reducing the size and strength of channel vortex.

The splitter vane 2 is a kudzu wing, and the height of the splitter vane 2 is 30%-40% of the height of the twisted vane 1. Both sides of the splitter vane 2 are provided with radially equidistant n groove groups (radial means Along the direction of the height of the splitter vane 2), each groove group contains c bionic circular grooves 23, and the minimum distance between the bionic round groove 23 and the top, root, leading edge and rear end of the splitter vane 2 is the length of the arc-shaped plate. 6%-12%, the distance d between adjacent bionic circular grooves 23 is 5-8mm, the radius of the bionic circular grooves 23 is 1-2mm, and the values of n and c depend on the height and width of the splitter blade 2; The grooves 23 are distributed in a straight line, and the distance between different bionic circular grooves 23 is fixed, so is the distance between them. The above-mentioned connecting piece 4 is fixed on the wheel hub with the axle sleeve 3, the axle sleeve 3 adopts a conventional axle sleeve, and the connecting piece 4 adopts standard bolts to connect with the wheel hub through the axle sleeve 3.

Experiment 1. The "three-dimensional impeller of a new axial flow fan with leaf vein structure and splitter blades" described in Example 1 was simply verified using CFD technology. Under the boundary conditions of inlet speed 2m/s and rotation speed 100rad/s In the case of consistency, the performance is judged by measuring the static pressure at the outlet, because the axial flow fan mainly converts mechanical energy into the static pressure of the wind. In the case of the same input power, a large static pressure indicates high efficiency, turbulence dissipation and flow The loss is less, that is, the secondary flow, wake vortex, etc. have been effectively controlled.

Comparative Example 1: Cancel the airfoil groove 11 on the top of the twisted blade 1 and the vein-like groove 15 on the top of the suction surface 18 of the twisted blade 1 in Example 1.

Comparative Example 2: Cancel the parabolic small hole 12 in Example 1, the rest is the same as Example 1, and carry out Comparative Example 2.

Comparative example 3: cancel the splitter blade 2 in the embodiment 1, the rest is the same as the embodiment 1, and carry out the comparative example 3.

Comparative Example 4: The twisted blade 1 in Embodiment 1 was replaced with an ordinary straight blade, and the rest was the same as Embodiment 1, and Comparative Example 4 was carried out.

All of the above comparative examples 1-4 were detected as described in Experiment 1, the input power was the same, and the obtained results (reference atmospheric pressure) were respectively:

Condition outlet static pressure experiment one 190.03Pa Comparative example 1 164.11Pa Comparative example 2 183.61Pa Comparative example 3 156.32Pa Comparative example 4 133.22Pa

Under the same conditions, the static pressure at the outlet of the present invention is significantly improved compared with Comparative Examples 1-4, indicating that turbulence dissipation and flow loss are significantly reduced.

Finally, it should be noted that: the above embodiments are only used to illustrate the technical solutions of the present invention, rather than to limit them; although the present invention has been described in detail with reference to signing each embodiment, those of ordinary skill in the art should understand that: It is still possible to modify the technical solutions described in the foregoing embodiments, or perform equivalent replacements for some or all of the technical features; and these modifications or replacements do not make the essence of the corresponding technical solutions depart from the scope of the embodiments of the invention. .

Claims (5)

1. The axial flow fan ternary impeller with the blade vein structure and the splitter blades comprises a hub, and a shaft sleeve (3) is fixed on the hub by a connecting piece (4); the method is characterized in that: the device also comprises a bending blade (1) and a splitter blade (2) which are fixedly connected to the hub;

the bending blade (1) comprises a suction surface (18) and a pressure surface (19); the top of the bending blade (1) is provided with an airfoil groove (11); the upper half part of the pressure surface of the bending blade (1) is provided with a vein-shaped groove (15), and the wing-shaped groove (11) is communicated with the vein-shaped groove (15) through an air outlet (14); the tail part of the suction surface of the bending blade (1) is provided with a winglet protuberance (13); parabolic small holes (12) are formed in the bending and twisting blades (1);

a splitter blade (2) is arranged between two adjacent bending blades (1); the height of the splitter blade (2) is smaller than the height of half of the bending blade (1);

the splitter blade (2) is a Gettin root wing; the splitter blade (2) is arranged in the middle of the adjacent bending blade (1);

the two side surfaces of the splitter blade (2) have the same structure and are respectively: at least two radial equidistant groove groups are arranged on the side surface, each groove group comprises at least two circular grooves (23), the central line connecting line of the circular grooves (23) of each groove group is perpendicular to the outer surface of the hub, and the axial lead of the circular grooves (23) is perpendicular to the splitter blade (2);

the vein-shaped groove (15) comprises at least two vein grooves, each vein groove is communicated with one air outlet (14), and the air outlet (14) is communicated with the wing-shaped groove (11).

2. The impeller of axial flow fan with impeller vein structure and splitter blades according to claim 1, characterized in that: three winglet protrusions (13) are equidistantly arranged at the rear end of the suction surface (18) of the bending blade (1).

3. The impeller of axial flow fan with impeller vein structure and splitter blades according to claim 2, characterized in that: eight turning blades (1) and eight splitter blades (2) are equidistantly arranged on the hub.

4. The impeller of axial flow fan with impeller vein structure and splitter blades according to claim 3, characterized in that: the twisting blade (1) is twisted by 15-20 degrees and bent by 15-20 degrees.

5. The impeller of axial flow fan with impeller vein structure and splitter vane as set forth in claim 4, wherein: the height of the splitter blade (2) is 30% -40% of the height of the bending blade (1).

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