CN106837867B - Axial flow fan ternary impeller with vein structure and splitter blades - Google Patents
Axial flow fan ternary impeller with vein structure and splitter blades Download PDFInfo
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- CN106837867B CN106837867B CN201710209298.0A CN201710209298A CN106837867B CN 106837867 B CN106837867 B CN 106837867B CN 201710209298 A CN201710209298 A CN 201710209298A CN 106837867 B CN106837867 B CN 106837867B
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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
- F04D29/68—Combating cavitation, whirls, noise, vibration or the like; Balancing by influencing boundary layers
- F04D29/681—Combating cavitation, whirls, noise, vibration or the like; Balancing by influencing boundary layers especially adapted for elastic fluid pumps
- F04D29/682—Combating cavitation, whirls, noise, vibration or the like; Balancing by influencing boundary layers especially adapted for elastic fluid pumps by fluid extraction
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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
- F04D29/325—Rotors specially for elastic fluids for axial flow pumps for axial flow fans
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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
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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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- 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
- F04D29/66—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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- 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
- F04D29/68—Combating cavitation, whirls, noise, vibration or the like; Balancing by influencing boundary layers
- F04D29/681—Combating cavitation, whirls, noise, vibration or the like; Balancing by influencing boundary layers especially adapted for elastic fluid pumps
- F04D29/684—Combating cavitation, whirls, noise, vibration or the like; Balancing by influencing boundary layers especially adapted for elastic fluid pumps by fluid injection
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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 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
Technical Field
The invention relates to the field of axial flow fan design, in particular to a novel three-element impeller of an axial flow fan with a vein-shaped structure and splitter blades.
Background
The working principle of the axial flow fan is that the mechanical energy input by a motor is used for increasing the pressure of gas and conveying and discharging the gas. The axial flow fan plays a role in various fields of national economy, is widely applied to factories, mines, vehicles, ship berths, buildings and the like, plays an irreplaceable role in ventilation, dust discharge and cooling, and according to incomplete statistics, the annual electricity consumption of various fans in the whole country accounts for 20% of the national electricity generation, wherein a plurality of fans are long in time or low in efficiency, serious waste of electric power is caused, and the importance of improving the performance of the fans in national economy is realized. Axial flow fans are generally used in occasions with high flow requirements and low pressure, are relatively simple in structure and convenient to install, and have an irreplaceable effect in the field of fans.
Although the structure of the axial flow fan is simple, the flow situation is indeed quite complex. The flow is often three-dimensional, sticky and unsteady, the conditions are rarely or hardly comprehensively considered in the prior fan design, even if numerical analysis is mature today, the influence of the factors on the fan is hardly controlled, and particularly the fluid is sticky, because the sticky often causes the outlet edge of the blade to form a wake vortex; due to the viscosity, a viscous boundary layer exists on the surface of the blade (particularly in the case of very smooth blade surface), and strong interaction is generated between the viscous boundary layer and the main flow, so that a secondary flow phenomenon is generated; the presence of tackiness also creates aerodynamic noise, including mainly 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 shell and the secondary flow generated by radial flow in the boundary layer of the blade are also main sources for increasing the loss and reducing the efficiency of the fan.
In summary, only the secondary flow phenomenon is controlled and reduced, the boundary layer separation is prevented, the generation of blade wake vortex is restrained, the turbulent dissipation and the flow loss are reduced, the axial flow fan with high efficiency, good performance, low noise and energy saving can be designed, and the requirements of modern production on the fan are met.
Disclosure of Invention
The invention aims to solve the problems of controlling and reducing secondary flow, boundary layer separation, wake vortex and vortex noise generation in the prior art, and provides a novel axial flow fan ternary impeller with a vein structure and a splitter blade. The invention can reduce secondary flow phenomenon, prevent boundary layer separation, inhibit generation of blade wake vortex, reduce turbulence dissipation and flow loss, and has the characteristics of high efficiency, good performance, low noise and energy conservation.
In order to solve the technical problems, the invention provides an axial flow fan ternary impeller with a blade vein structure and a splitter blade, which comprises a hub, a shaft sleeve and a connecting piece, wherein the connecting piece is fixed on the hub; 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.
As an improvement of the three-element impeller of the axial flow fan with the vein structure and the splitter blade, the invention: the splitter blades are kudzu vine root wings; the splitter blades are disposed midway between adjacent turning blades.
Further improvement of the three-element impeller of the axial flow fan with the vein structure and the splitter blades, which is provided by the invention, comprises the following steps: the structure of both sides face of splitter vane is the same, all is respectively: at least two radial equidistant groove groups are arranged on the side surface, each groove group comprises at least two bionic round grooves, the central line connecting line of the bionic round grooves of each groove group is perpendicular to the outer surface of the hub, and the axial lead of each bionic groove is perpendicular to the splitter blade.
Further improvement of the three-element impeller of the axial flow fan with the vein structure and the splitter blades, which is provided by the invention, comprises the following steps: the vein-shaped groove comprises at least two vein grooves, each vein groove is communicated with one air outlet, and the air outlet is communicated with the wing-shaped groove.
Further improvement of the three-element impeller of the axial flow fan with the vein structure and the splitter blades, which is provided by the invention, comprises the following steps: three winglet protrusions are arranged at the rear end of the suction surface of the bending blade at equal intervals.
Further improvement of the three-element impeller of the axial flow fan with the vein structure and the splitter blades, which is provided by the invention, comprises the following steps: eight turning blades and eight dividing blades are equidistantly arranged on the hub.
Further improvement of the three-element impeller of the axial flow fan with the vein structure and the splitter blades, which is provided by the invention, comprises the following steps: the twisting blade is twisted by 15-20 degrees and bent by 15-20 degrees.
Further improvement of the three-element impeller of the axial flow fan with the vein structure and the splitter blades, which is provided by the invention, comprises the following steps: the height of the splitter blade is 30% -40% of the height of the turning blade.
The invention has the following advantages: according to the invention, the installation angle of the root part is large by adopting the bending blade, the installation angle of the top part of the bending blade is small, so that the air has a relatively uniform axial speed at each position in the radial direction, normal operation is ensured, air flow separation is avoided, flow loss is reduced, secondary flow (the static pressure is smaller than that of a conventional blade due to the fact that the pressure difference between the suction surface and the pressure surface of the C-shaped distributed blade) in the blade grid can be effectively inhibited, the root part reaction degree can be improved, the top part reaction degree is reduced, the purpose that the homogenization reaction degree is distributed along the height of the blade is achieved, and the through flow capacity of the root part is improved; the top of the pressure surface of the bending blade is provided with a blade-shaped groove, the top of the bending blade is provided with an airfoil groove, the airfoil groove is connected with the blade-shaped groove through an air outlet hole, the structure can form a low-speed secondary vortex in the blade-shaped groove, the viscous resistance in the groove is opposite to the total resistance so as to reduce the viscous resistance, inhibit the turbulent flow intensity and reduce the turbulent flow dissipation, high-energy gas at the upper part of the pressure surface can be led into the blade-top airfoil groove through the blade-shaped groove and the air outlet hole, and the high-energy gas is prevented from flowing from the pressure surface to the suction surface through a radial gap, so that the disorder of the flow near the top of the bending blade is caused, the flow condition of the top of the bending blade is improved, the phenomenon of transverse secondary flow generated by the gas flowing from the pressure surface of the bending blade to the adjacent suction surface is avoided, the flow loss is reduced, and meanwhile, the blade-shaped groove also has the function of a common groove; the parabolic small holes on the bending and twisting blades can reduce the pressure difference between the suction surface and the pressure surface of the blades, improve the boundary layer separation around the blades and reduce the generation of vortex noise; the winglet protrusions on the tail of the bending blade can guide airflow to move along the chord direction, so that radial flow can be well controlled, secondary flow of radial movement is reduced, wake jet flow is prevented, the boundary layer separation point of the suction surface of the bending blade moves backwards, and energy loss is reduced; the flow dividing blades can effectively break vortex, so that flow in the flow channel is more stable, unstable phenomena such as flow separation and secondary flow are reduced, in addition, the bionic circular grooves formed in the flow dividing blades can reduce wall friction resistance, flow resistance and flow loss. The axial flow fan impeller is improved at different positions by the principle, so that the efficiency of the axial flow fan is higher, the performance is better, and the energy conservation and the environmental protection are realized.
Drawings
The following describes the embodiments of the present invention in further detail with reference to the accompanying drawings.
FIG. 1 is a schematic diagram of the overall structure of a novel axial flow fan three-element impeller with a vein structure and splitter blades of the present invention;
FIG. 2 is a schematic view of the suction side of the cambered vane of FIG. 1;
FIG. 3 is a schematic view of the pressure surface of the cambered vane of FIG. 1;
FIG. 4 is a schematic view of the splitter blade of FIG. 1;
FIG. 5 is a schematic view of the structure of the B-B side of the splitter blade of FIG. 4;
FIG. 6 is a schematic view of the C-C face of the twist blade and winglet projection of FIG. 2;
FIG. 7 is a schematic view of a bionic circular groove of the splitter vane of FIG. 1;
FIG. 8 is a schematic view of the configuration of the airfoil slot of FIG. 1;
FIG. 9 is a schematic view of a cascade structure of the cambered vane of FIG. 1;
fig. 10 is a schematic view showing the structure of the bending blade 1 of fig. 1 in bending and twisting.
Detailed Description
The invention will be further described with reference to specific examples, but the scope of the invention is not limited thereto.
The bending blade 1 comprises a suction surface 18 and a pressure surface 19, the top of the suction surface 18 of the bending blade 1 is provided with a vein-shaped groove 15, the rear end of the bending blade 1 is provided with a winglet protrusion 13, the vein-shaped groove 15 comprises at least two vein grooves, the root part of the bending blade 1 is large in installation angle, the top installation angle is small (the installation angle is the included angle between the rotation plane at the radius r of the bending blade 1 and the chord length of an airfoil profile, and is represented by beta 1 and beta 2 in the figure), the air is ensured to have a relatively uniform axial speed at each position in the radial direction, normal work is ensured, airflow separation is avoided, flow loss is reduced, secondary flow inside a blade grid can be effectively restrained (static pressure is distributed in a C shape, 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), the root part of the bending blade 1 is improved, the top reaction degree of the bending blade 1 is reduced, the purpose of homogenizing reaction degree is achieved, and the flow capacity of the root part of the bending blade 1 is improved. The blade grid refers to a plane which is formed by cutting off the blade on a certain radius r by using an axial cylindrical surface and then generating the section, and the position relation of the adjacent bending blade 1, the installation angle of the bending blade 1 and the like are reflected.
The winglet protrusions 13 are arranged on the suction surface 18, so that fluid can flow in the blade grid, the pressure of the blade pressure surface 19 is larger than that of the suction surface 18 due to the interaction of the bending blade 1 and the fluid, the fluid flows from the pressure surface 19 of the bending blade 1 to the suction surface 18, and the airflow of the suction surface 18 is more disturbed due to the flow, so that the fin is designed to enable the airflow to move along the chord direction to control the radial flow, the size of channel vortex in the flow channel of the bending blade 1 and the surface boundary layer submerging flow of the blade can be controlled, the secondary flow of the radial movement can be controlled, the speed non-uniformity can be reduced, the wake jet can be prevented, the boundary layer separation point of the suction surface 18 of the bending blade 1 can be moved backwards, and the energy loss can be reduced.
The top of the bending blade 1 is provided with an airfoil groove 11, the airfoil groove 11 is communicated with a vein-shaped groove 15 at the top of a suction surface 18 of the bending blade 1 through a plurality of air outlets 14, the structure can form low-speed secondary vortex in the vein-shaped groove 15, the viscous resistance in the vein-shaped groove 15 is opposite to the total resistance so as to reduce the viscous resistance, inhibit the turbulence intensity, reduce the turbulence dissipation, high-energy gas at the upper part of the pressure surface 19 of the bending blade 1 can be introduced into the blade top airfoil groove 11 through the vein-shaped groove 15 and the air outlets 14, prevent some gas from flowing from the pressure surface 19 to the suction surface 18 through radial gaps, cause the disorder of the flow near the top of the bending blade 1, improve the flow condition of the top of the bending blade 1, and also avoid the phenomenon of transverse secondary flow generated by the gas flowing from the pressure surface 19 of the bending blade 1 to the adjacent suction surface 18, thereby achieving the purposes of reducing the flow loss, and meanwhile, the airfoil groove 11 at the top of the bending blade 1 also has the function of a common groove, can form a vortex pad effect, so that the turbulence intensity in a near wall area is reduced. The parabolic small holes 12 are arranged on the bending blade 1, the parabolic small holes 12 can reduce the pressure difference between the suction surface 18 and the pressure surface 19 of the bending blade 1, improve the boundary layer separation around the bending blade 1 and reduce the generation of vortex noise; the winglet protrusions 13 at the rear end of the turning vane 1 can guide airflow to move along the chord direction, can well control radial flow, reduce secondary flow of radial movement, prevent wake jet flow, enable the boundary layer separation point of the suction surface 18 of the turning vane 1 to move backwards, and reduce energy loss. The splitter blade 2 is a kudzu vine root wing, is arranged in the middle of two adjacent bent blades 1, two side faces are provided with radial equidistant groove groups, each groove group comprises more than two bionic round grooves 23, the bionic round grooves 23 are arranged on the same straight line, the central line connecting line of the bionic round grooves 23 of each groove group is perpendicular to the outer surface of the hub, and the axial lead of the bionic round grooves 23 is perpendicular to the splitter blade 2. The splitter blade 2 can effectively break vortex, so that the flow in the flow channel is more stable, unstable phenomena such as flow separation and secondary flow are reduced, in addition, the bionic circular groove 23 formed in the bending blade 1 can reduce wall friction resistance, flow resistance and flow loss. The height of the splitter blade 2 is smaller than the general height of the turning blade 1, and the hub 3 is fixed to the hub by means of standard connectors 4. The splitter blade 2 is designed to block the flow of the blade root portion of the turning blade 1 laterally from the pressure surface 19 of the turning blade 1 to the blade suction surface 18, and to break a vortex or the like.
By referring to the working principle of the blades, the twisting of the bending blade 1 can ensure that the air has a relatively uniform axial speed at each position in the radial direction, ensure normal work, avoid air flow separation and reduce flow loss, and by referring to the boundary layer migration theory proposed by Wang Zhongji (yard) according to the static blowing experiment and numerical calculation results of the annular blade grid of the small-diameter-height ratio blades, namely, after the bending blade 1 is circumferentially bent, the component force of the acting force of the surface of the bending blade 1 and the air flow in the radial direction is unequal to zero, thereby controlling the distribution of the pressure along the height of the bending blade 1, after the bending blade 1 is circumferentially bent, the component force of the acting force of the surface of the bending blade 1 and the air flow in the radial direction is unequal to zero, thereby forming the pressure distribution with high pressure at both ends and low intermediate pressure on the surface of the bending blade 1, particularly the suction surface 18, i.e. "C" type pressure distribution, under its effect, both end boundary layers are sucked to the middle part and taken away by the main flow, thus have reduced the accumulation of the low-energy fluid at the corner that both end walls and suction surface 18 make up, have avoided the emergence of separating, therefore the flow loss of both end is reduced, second the pressure difference of the pressure surface 19 and suction surface 18 of the bending blade 1 is obviously smaller than the conventional blade, the horizontal secondary flow on the end wall weakens, the corresponding horizontal secondary flow loss reduces, the rational matching bending will make the impeller fan obtain the excellent performance, can improve stage reaction degree and raise stage through-flow ability, delay the channel vortex formation time and reduce the size and intensity of the channel vortex, the bending blade 1 twists 15-20 degrees in the design, bend 15-20 degrees, in order to reduce the secondary flow more effectively at the same time, inhibit the boundary layer thickness, the formation of wake wingtip vortex is controlled, and the vane vein grooves 15, the wing grooves 11, the parabolic small holes 12, the winglet protrusions 13 and the like are designed for reducing turbulence dissipation and the like.
The invention firstly carries out bending and twisting design on the blades on the hub, ensures that the air flow has a relatively uniform axial speed at each position in the radial direction, ensures normal operation, avoids air flow separation, reduces flow loss, can effectively inhibit radial and transverse secondary flows in the blade grid, can improve root reaction degree, reduce top reaction degree, achieve the purpose of homogenizing reaction degree to be distributed along the height of the blades, improves the through-flow capacity of the root, delays the formation time of the channel vortex and reduces the size and strength of the channel vortex; the upper half part of the pressure surface 19 of the bending blade 1 is provided with a blade vein-shaped groove 15 and an airfoil groove 11 at the top of the bending blade 1 which are connected through an air outlet 14, the structure can form a low-speed secondary vortex in the blade vein-shaped groove 15, the viscous resistance in the groove is opposite to the total resistance so as to reduce the viscous resistance, inhibit the turbulence intensity, reduce the turbulence dissipation, guide the high-energy gas at the upper part of the pressure surface 19 into the blade top airfoil groove 11 through the blade vein-shaped groove 15 and the air outlet 14, prevent some gas from flowing from the pressure surface 19 to the suction surface 18 through a radial gap, cause the disorder of the flow near the top of the bending blade 1, improve the flow condition of the blade top, and also avoid the phenomenon of transverse secondary flow generated by the gas flowing from the pressure surface 19 of the bending blade 1 to the adjacent suction surface 18, thereby achieving the effect of reducing the flow loss, and simultaneously the blade vein-shaped groove 15 at the top of the bending blade 1 also has the function of a common groove, can form a vortex pad effect, and reduce the turbulence intensity in a near-wall area; the parabolic small holes 12 on the bending blade 1 can reduce the pressure difference between the suction surface 18 and the pressure surface 19, improve the boundary layer separation around the bending blade 1 and reduce the generation of vortex noise; the tail fin can guide airflow to move along the chord direction, so that radial flow can be well controlled, secondary flow of radial movement is reduced, wake jet flow is prevented, a boundary layer separation point of the suction surface 18 of the bending and twisting blade 1 moves backwards, and energy loss is reduced; the splitter blade 2 can effectively break vortex, so that the flow in a flow channel is more stable, unstable phenomena such as flow separation and secondary flow are reduced, the bionic circular groove 23 is formed in the splitter blade 2, the wall friction resistance can be reduced, the flow resistance is reduced, the flow loss is reduced, and meanwhile, the generation of vortex noise is inhibited. The axial flow fan impeller is improved at different positions by the principle, so that the efficiency of the axial flow fan is higher, the performance is better, and the energy conservation and the environmental protection are realized.
The bending blade 1 is an airfoil blade designed by adopting an equal-annular-quantity isolated airfoil method, the thickness distribution of the bending blade 1 is the same as that of an NACA four-digit airfoil, the relative thickness of the airfoil is 10% -15%, and the number of the bending blades 1 is 8; the depth of the airfoil groove 11 at the top of the bending blade 1 is 1% -2% of the height of the bending blade 1, and the thickness of the airfoil groove 11 is 50% -60% of the top surface of the bending blade 1; winglet protrusions 13 are equidistantly distributed on the rear end of the bending blade 1, the distance d1 between the winglet protrusions 13 is 18% -22% of the height H of the bending blade 1, the length d4 of the winglet protrusions 13 is 15% -17% of the chord length of the bending blade 1, the included angle omega between the winglet protrusions and the chord length is 30% -40 degrees, and the distance d5 from the edge of the rear end of the bending blade 1 is 1% -3% of the chord length of the bending blade 1; parabolic small holes 12 are distributed in the bending blade 1, and the aperture is 1-2mm; the depth of the vein-shaped groove 15 at the top of the pressure surface 19 of the bending blade 1 is 1-2mm, the maximum groove length is 30-40% of the height of the bending blade 1, the interval of the vein grooves is 20-30mm, each vein groove is independently communicated with one air outlet 14, and the specific number of the vein grooves depends on the size of the bending blade 1; the bending blade 1 is twisted by 15-20 degrees and bent by 15-20 degrees. Bending means that the bending blade 1 is bent along a horizontal middle section (a plane perpendicular to the height of the bending blade 1) when designed by an equal-annular-quantity isolated airfoil method, i.e., airfoil sections at different radii have corresponding distances from each other in the horizontal direction; twisting refers to twisting of the cambered vane 1 along a vertical mid-section (a plane parallel to the high side of the cambered vane 1) when designed with an equal-turn isolated airfoil approach, i.e., the airfoil sections at different radii are twisted by corresponding angles about the vertical direction. Distortion benefits: the blade root of the bending blade 1 is large in installation angle, the blade tip is small in installation angle, the air can be ensured to have a relatively uniform axial speed at each position in the radial direction, normal operation is ensured, air flow separation is avoided, and flow loss is reduced. Bending and twisting benefits: the secondary flow inside the blade cascade can be effectively restrained (the pressure difference between the suction surface 18 and the pressure surface 19 of the static pressure C-shaped distributed bent and twisted blade 1 is smaller than that of a conventional blade), the root reaction degree can be improved, the top reaction degree is reduced, the purpose that the homogenization reaction degree is distributed along the height of the blade is achieved, the through-flow capacity of the root is improved, the channel vortex forming time is delayed, and the size and the strength of the channel vortex are reduced.
The splitter blade 2 is a kudzu vine root wing, the height of the splitter blade 2 is 30-40% of the height of the bending blade 1, n radial equidistant groove groups (radial refers to the direction along the height of the splitter blade 2) are arranged on two side surfaces of the splitter blade 2, each groove group further comprises c bionic round grooves 23, the minimum distance between each bionic round groove 23 and the top, root, front edge and rear end of the splitter blade 2 is 6-12% of the length of a circular arc-shaped plate, the distance d between every two adjacent bionic round grooves 23 is 5-8mm, the radius of each bionic round groove 23 is 1-2mm, and the values of n and c are specifically determined according to the height and width of the splitter blade 2; the bionic circular grooves 23 are distributed in a straight line, the distances between the bionic circular grooves 23 are fixed, and the distances between the bionic circular grooves and the periphery are also fixed. The connecting piece 4 is fixed on the hub by the shaft sleeve 3, the shaft sleeve 3 adopts a conventional shaft sleeve, and the connecting piece 4 adopts a standard piece bolt to be connected with the hub through the shaft sleeve 3.
Experiment one, the novel axial flow fan three-way impeller with the vein structure and the splitter blade described in the embodiment 1 is simply verified by adopting the CFD technology, and under the condition that boundary conditions such as the inlet speed is 2m/s and the rotation speed is 100rad/s are consistent, the performance is judged by measuring the static pressure of the outlet, because the axial flow fan mainly converts mechanical energy into the static pressure of wind, under the condition that the input power is the same, the static pressure has high explanation efficiency, and the turbulence dissipation and the flow loss are less, namely, the secondary flow, wake vortex and the like are effectively controlled.
Comparative example 1: the airfoil grooves 11 on the top of the turning vane 1 and the vein grooves 15 on the top of the suction surface 18 of the turning vane 1 in example 1 were eliminated, and the remainder was the same as in example 1, to carry out comparative example 1.
Comparative example 2: the parabolic aperture 12 of example 1 was eliminated and comparative example 2 was performed with the remainder being identical to example 1.
Comparative example 3: the splitter blade 2 of example 1 was omitted and comparative example 3 was performed in the same manner as in example 1.
Comparative example 4: comparative example 4 was conducted in the same manner as in example 1 except that the bent blade 1 in example 1 was replaced with a normal straight blade.
All of the above comparative examples 1 to 4 were tested as described in experiment one, with the same input power, and the results (reference atmospheric pressure) were:
| working conditions of | Static pressure at outlet |
| 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 outlet static pressure is obviously improved compared with comparative examples 1-4, which shows that turbulent dissipation and flow loss are obviously reduced.
Finally, it should be noted that: the above embodiments are only for illustrating the technical solution of the present invention, and are not limiting; while the invention has been described in detail with reference to signing embodiments, those of ordinary skill in the art will appreciate that: the technical scheme described in the previous embodiments can be modified or some or all technical features in the technical scheme can be replaced equivalently; such modifications and substitutions do not depart from the spirit of the corresponding technical solutions 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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| CN201611118397 | 2016-12-07 | ||
| CN201611118397X | 2016-12-07 |
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| CN108005949B (en) * | 2017-07-18 | 2024-05-14 | 宁波方太厨具有限公司 | Impeller of open type water pump |
| CN113653672B (en) * | 2021-08-31 | 2023-11-10 | 佛山市南海九洲普惠风机有限公司 | Axial flow impeller with splitter blades |
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| CN106837867A (en) | 2017-06-13 |
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