CN105756975A - Axial flow fan with blade front edges having groove structures and with blade root blowing effect - Google Patents
Axial flow fan with blade front edges having groove structures and with blade root blowing effect Download PDFInfo
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- CN105756975A CN105756975A CN201610263059.9A CN201610263059A CN105756975A CN 105756975 A CN105756975 A CN 105756975A CN 201610263059 A CN201610263059 A CN 201610263059A CN 105756975 A CN105756975 A CN 105756975A
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- 241001669680 Dormitator maculatus Species 0.000 claims description 5
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Classifications
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D29/00—Details, component parts, or accessories
- F04D29/26—Rotors specially for elastic fluids
- F04D29/32—Rotors specially for elastic fluids for axial flow pumps
- F04D29/38—Blades
- F04D29/384—Blades characterised by form
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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
- F04D25/00—Pumping installations or systems
- F04D25/02—Units comprising pumps and their driving means
- F04D25/08—Units comprising pumps and their driving means the working fluid being air, e.g. for ventilation
-
- 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
- F04D29/329—Details of the hub
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D29/00—Details, component parts, or accessories
- F04D29/26—Rotors specially for elastic fluids
- F04D29/32—Rotors specially for elastic fluids for axial flow pumps
- F04D29/38—Blades
- F04D29/384—Blades characterised by form
- F04D29/386—Skewed blades
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D29/00—Details, component parts, or accessories
- F04D29/26—Rotors specially for elastic fluids
- F04D29/32—Rotors specially for elastic fluids for axial flow pumps
- F04D29/38—Blades
- F04D29/388—Blades characterised by construction
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D29/00—Details, component parts, or accessories
- F04D29/40—Casings; Connections of working fluid
- F04D29/52—Casings; Connections of working fluid for axial pumps
- F04D29/54—Fluid-guiding means, e.g. diffusers
- F04D29/541—Specially adapted for elastic fluid pumps
-
- 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
-
- 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
- F04D29/70—Suction grids; Strainers; Dust separation; Cleaning
- F04D29/701—Suction grids; Strainers; Dust separation; Cleaning especially adapted for elastic fluid pumps
- F04D29/703—Suction grids; Strainers; Dust separation; Cleaning especially adapted for elastic fluid pumps specially for fans, e.g. fan guards
Abstract
The invention discloses an axial flow fan with blade front edges having groove structures and with a blade root blowing effect. The axial flow fan comprises a net cover, an impeller, guide vanes, an inner barrel, an outer barrel and a motor. The net cover is woven from iron wires and is fixed to the outer barrel. The impeller comprises a hub and blades, the front edges of the blades have the groove structures, the tail edges of the tops of the blades have protrusion structures, and blowing grooves are formed in the hub of the impeller. The blades are airfoil blades designed through a constant circulation isolated airfoil method, the protrusion structures are additionally arranged the tail edges of the top ends of the blades, guide plates are additionally arranged on suction surfaces of the guide vanes, and the thicknesses of boundary layers of blade root portions can be reduced. Separation of boundary layers of front edge points of the blades is restrained. The size of blade top clearance vortexes and the disengaging frequency of the vortexes are controlled. Radial secondary flow of the guide vanes is reduced. Noise of wake vortexes of the guide vanes is restrained. By improving different positions of the axial flow fan, the axial flow fan is higher in efficiency, lower in noise and more environmentally friendly and saves more energy.
Description
Technical field
The invention belongs to blower fan technical field, particularly to the axial flow blower that a kind of blade inlet edge is blown with groove structure and blade root.
Background technology
Axial flow blower is dependent on the mechanical energy of input, improves gas pressure and supplies gas side by side the machinery of body.It is widely used in the ventilation of factory, mine, tunnel, cooling tower, vehicle, boats and ships and building, dust discharge and cooling；The ventilation of boiler and industrial furnace and air inducing；Cooling in the apparatus of air conditioning and domestic electric appliance and ventilation；The drying of corn and selecting and recommending；The propelling etc. of the inflation of wind-tunnel wind regime and aircushion vehicle, all has very important application in national economy every profession and trade.According to statistics, blower fan electricity consumption accounts for the 10% of national generating capacity, and coal master to be led to machine average current drain and be accounted for the 16% of mine power consumption；The blower fan power consumption of metal mine accounts for the 30% of mining electricity consumption；The blower fan power consumption of steel and iron industry accounts for the 20% of its productive power；The blower fan power consumption of coal industry accounts for the 17% of coal industry electricity consumption.As can be seen here, Fan Energy-saving status in each department of national economy and effect are very important.Due to, the specific speed of axial flow blower is higher, and so it has the advantages that flow is big, total head is low, all occupies irreplaceable status in these industries.
Therefore the axial fan that design optimization goes out efficiency height, performance is good, noise is low, energy-conservation is critically important.But axial flow blower flows extremely complex property, is mainly reflected in: 1) flow three-dimensionality；2) viscosity of fluid；3) non-stationarity flowed.Traditional fan design is difficult to consider 3 point above, even if modern Design having been used CFD do Aided Design, but three factors impact on fan performance above cannot be controlled completely, wherein the factor of most critical is the viscosity of fluid, and it is meet the blade wake passing vortex that Kutta-Joukowsky condition is formed that viscosity not only has influence on exit edge of blade.Owing to viscosity, blade surface and ring wall channel surface all can exist viscous boundary layer, between them and and main flow between have strong interaction, produce so-called " Secondary Flow " phenomenon.Secondary flow is the main contributor that axial flow blower loss rises, efficiency declines.Simultaneously as the impact of viscosity, making to exist in axial flow blower aerodynamic noise, the aerodynamic noise of axial flow blower is mainly made up of two parts: rotational noise and eddy current crack.If fan outlet is directly discharged into air, also has exhaust noise.
In sum, the axial fan that design optimization goes out efficiency height, performance is good, noise is low, energy-conservation is wanted, it is simply that will control and reduce secondary flow, control and reduction boundary layer thickness, prevent vortex shedding or control the formation in whirlpool.
Summary of the invention
It is an object of the invention to cannot pass through traditional design for the deficiencies in the prior art and well control the boundary layer thickness in axial flow blower, Secondary Flow and eddy current crack, provide the axial flow blower that a kind of blade inlet edge is blown with groove structure and blade root, edge processes groove structure in front of the blade, blowing groove is being opened on the wheel hub of blade suction surface, blade tip trailing edge adds bulge-structure and stator suction surface adds deflector, it is possible to reduce leaf root part boundary layer thickness；Suppress blade inlet edge point boundary layer separation；Control the size of tip clearance vortex and the shedding frequence in whirlpool；Reduce the flowing of stator radial second；Suppress stator wake's flow field noise.By the improvement of axial flow blower diverse location makes this profile shaft flow fan in hgher efficiency, noise is lower, more energy-conserving and environment-protective.
The technical solution used in the present invention is such that a kind of blade inlet edge axial flow blower with groove structure and blade root air blowing and includes guard, impeller, stator, inner core, urceolus, motor；Described guard is to have iron wire braiding to form, and is fixed on urceolus；It is characterized in that: described impeller includes wheel hub and blade, the fluted structure of blade inlet edge, vane tip trailing edge has bulge-structure, has blowing groove on impeller hub；Described blade is the airfoil fan design of circular rector Isolated Airfoil method such as passing through, turn round speed to reduce along with the increase of reducing, pressure is radially constant, vane thickness distribution is identical with NACA 4-digit number profile thickness distribution, relative thickness of airfoil is 10% 15%, blade quantity is 59, and blade blade tip clearance is 1% the 2% of blade height；Described blade inlet edge groove structure, center is dropped on the shape line of aerofoil cross section, and being uniformly distributed, channel section is shaped as circular arc, and groove runs through whole blade inlet edge, groove is from leading edge point, to both sides, equidistant limit extends, and groove diameter is the same, and the quantity of groove is 4 10, diameter is 1% the 3% of chord length, and the distance between groove is 3% the 8% of chord length；Described vane tip trailing edge bulge-structure be shaped as cuboid, bulge-structure is perpendicular to blade suction surface, and protruding width is 3% 6% that leaf is high, and length is 24 times of width, and thickness is width is 1/4 1/2；Described blowing groove structure, it is positioned on wheel hub, the suction surface of close blade is once, blowing groove is to have the skew of blade also wheel hub suction surface intersection to obtain, the length of blowing groove is 20% the 30% of blade root cross section chord length, the width of blowing groove is 5 10mm, and blowing groove is completely through wheel hub wall, and the distance of blowing groove afterbody and blade root trailing edge is 20% the 40% of blade root chord length；Described stator is fixed on above inner core and urceolus, stator blade is circular arc plate blade, is 7 17 along radially not reversing stator quantity, the axial gap of stator impeller and impeller be sized to 5 10mm, the thickness of stator blade is 2 4mm, and stator has deflector near the suction surface of trailing edge；Described deflector is evenly distributed on suction surface trailing edge part, it is perpendicular to stator surface, equal in magnitude, with stator trailing edge apart from identical, the position of relative guide vane height is respectively 20%, 40%, 60% and 80%, and deflector length is 20% the 30% of vane root chord length, and the height of deflector is the 1/3 1/2 of length, the thickness of deflector is identical with stator, and the distance of deflector and blade trailing edge is 3% the 5% of vane root chord length；Described motor is threephase asynchronous machine, and motor is fixed on the web of inner core, and impeller is connected with motor shaft by axle sleeve.
Beneficial effects of the present invention:
The present invention by having blowing groove on impeller hub, it is possible to reduces and suppresses the thickness of boundary region, controlled the separation of boundary region, made eddy region reduce, slow down the shedding frequence of eddy current, reduced energy loss and eddy current crack；Simultaneously in the leading edge of blade added with cylinder shape groove structure, it is possible to suppress the separation of leading edge point boundary region, make air-flow in runner more steady, improve efficiency, reduce overall noise grade；The bulge-structure being perpendicular to blade surface is added, it is possible to the effective leaf top regional edge interlayer that controls separates the shedding frequence with whirlpool, reduces blower fan Trailing Edge Loss and eddy current crack at leaf top portion trailing edge；Rear section deflector is added at stator suction surface, the Radial Flow owing to pressure and the centrifugal force imbalance of fluid cause can well be controlled, the size in pair of channels whirlpool in blade passage can also be controlled simultaneously, flow with blade surface boundary-layer creep, also the Secondary Flow of radial motion has just been controlled, reduce the uneven of speed, reduce jet Trailing Edge Loss, control boundary layer thickness, make stator suction surface boundary layer separation point rearward movement, reduce energy loss, control vortex shedding, it is suppressed that due to the eddy current crack that stator tail causes.By the improvement of axial flow blower diverse location makes this profile shaft flow fan in hgher efficiency, noise is lower, more energy-conserving and environment-protective.
Accompanying drawing explanation
Fig. 1 is the axial flow blower graphics of the present invention.
Fig. 2 is the blade wheel structure figure of the present invention.
Fig. 3 is the wheel hub blowing structure schematic diagram of the present invention.
Fig. 4 is the impeller leading edge groove structure schematic diagram of the present invention.
Fig. 5 is the leading edge groove location schematic diagram of the present invention.
Fig. 6 is the blade tip trailing edge bulge-structure figure of the present invention.
Fig. 7 is the stator level graphics of the present invention.
Fig. 8 is the deflector position view of the present invention.
Fig. 9 is the vane airfoil profile Cross section Design schematic diagram of the present invention.
Detailed description of the invention
Below in conjunction with drawings and Examples, the invention will be further described.
As it is shown in figure 1, this axial fan is made up of 6 parts, including 1, impeller 2, stator 3, inner core 4, motor 5, urceolus 6, guard；Urceolus 5, stator 2 and inner core 3 are fixed together by welding, and motor 4 is fixed on the web of inner core 3, and wherein the running parameter of motor 4 is 720r/min, and power is 4KW;Impeller 1 is fixed on motor 4 axle by axle sleeve, and the gap of the wheel hub of impeller 1 and inner core 3 is 10mm；Guard 6 is arranged on urceolus 5, has rectification and the effect preventing foreign body from entering.
As shown in Figure 1,2,3, 4, impeller 1 has motor 4 to drive to air work, improve dynamic pressure and the static pressure of gas, blade 1-1 on impeller 1 is the airfoil fan design of circular rector Isolated Airfoil method such as passing through, turning round speed to reduce along with the increase of reducing, pressure is radially constant, and blade relative thickness is 10%, blade quantity is 6, and blade blade tip clearance is the 2% of blade height.
Impeller blade design concrete grammar is as follows:
The simple radial equilibrium equation of axial fan internal flow:
Wherein P represents fluid micellar pressure experienced, and Cu is the speed that fluid micellar pivots, and r is the radius of turn of fluid micellar.Formula represents that axial flow blower is internal and assumes do not have Radial Flow, then the centrifugal force balance that optional position fluid micellar pressure experienced P diametrically and fluid micellar rotary motion produce.
In formula (2)-(3), Pt is the stagnation pressure of gas, and ρ is the density of gas, C is the sum velocity of gas, the circumferential speed of Cu, Ca, Cr respectively gas, circumferential speed, radial velocity, but there is known Cr=0 assumed above, and the stagnation pressure of gas adds static pressure equal to dynamic pressure.
The differential relationship such as formula (4) of Pt, P, Cu, Ca can be obtained by formula (2)-(3). formula (4) back substitution is entered formula (1) can be obtained by another kind of more general simple radial equilibrium equation (5).
Assuming that stagnation pressure Pt is radially constant etc. circular rector method for designing, axial velocity Ca is also radially constant, substitutes in formula (5) known:
By formula above it can be seen that etc. circular rector method for designing assume blower interior Cr=0 exactly, and stagnation pressure Pt is radially constant, and axial velocity Ca is also radially constant, and circumferential speed reduces along with the increase of radius.
Formula (7) is derived by Theories of Cascades, and one about solidity of blades, blade turns round speed, leaf grating lift coefficient, and average relative in leaf gratingBetween relation.
Isolated Airfoil method for designing just assumes that the lift coefficient of leaf gratingNot by the interference of blade, the namely lift coefficient of leaf grating between leaf gratingThe lift coefficient of Isolated AirfoilIdentical.
It is exactly described above etc. circular rector Isolated Airfoil method for designing, chord length and the established angle in each cross section of blade just can be calculated by above method, vane inlet airflow machine and blade exit airflow machine, just can calculate the shape of mean camber line plus some empirical equations by parameter above, taking relative thickness of airfoil is 10%, then, the mean camber line superposition NACA 4-digit number profile thickness in each cross section is distributed, and obtains each aerofoil section.NACA aerofoil profile is the profile set that American National aviation information committee (NationalAdvisoryCommitteeforAeronautics) is delivered, and 4-digit number aerofoil profile is its conventional profile set, and method for designing is as follows:
NACA 4-digit number profile thickness distribution function equation is:
Wherein: t represents relative thickness,, b is chord length, and with the profound line of aerofoil profile for X-axis, zero is placed in airfoil fan leading edge point,。
Method is as follows, and first, taking relative thickness is 10%, obtains N number of discrete point of blade different cross section thickness profile function, then, each cross section mean camber line is also carried out decile obtains N number of discrete point simultaneously, and the slope of each point normal is asked for by calculus of finite differences, then obtain inclination angle, so can be obtained by the coordinate points of aerofoil profile upper and lower surface after convertingThen can be obtained by aerofoil profile needed for cross section with coupling together of line smoothing, as it is shown in figure 9, a1 is thickness profile function, a4 is blade mean camber line, and a2 and a3 is normal and the tangent line of mean camber line any point.
Such as Fig. 2, 3, 4, shown in 5, the fluted structure 1-5 of blade 1-1 leading edge, blade 1-1 leading edge groove structure 1-5 drops on the shape line of aerofoil cross section in center, and it is uniformly distributed, groove 1-5 cross sectional shape is circular arc, groove runs through whole blade 1-1 leading edge, groove is from leading edge point A1, equidistantly extend to both sides, leading edge point is the intersection point of vane type line and string of a musical instrument A2, groove diameter is the same, the quantity of groove is 5, suction surface has 3, pressure face has 1, leading edge point has 1, diameter d1 is the 1.5% of leaf top chord length, it is of a size of 3mm, distance d2 between groove is the 4% of leaf top chord length, it is of a size of 8mm.
As shown in Figure 2,3, 4, the wheel hub 1-2 of impeller 1 there is blowing groove structure 1-3, blowing groove structure 1-3 is the suction surface side at blade, blowing groove 1-3 has blade to obtain with the skew of wheel hub suction surface intersection, the length of blowing groove is the 25% of blade root cross section chord length, and length is 70mm, and the width of blowing groove 1-3 is 7mm, blowing groove 1-3 is completely through wheel hub wall, blowing groove 1-3 afterbody and distance is blade root chord length the 30% of blade root trailing edge.
As shown in Fig. 2,3,4,6, at the top trailing edge of blade 1-1 added with bulge-structure 1-4, bulge-structure 1-4 is shaped as cuboid, bulge-structure 1-4 is perpendicular to blade suction surface, and protruding width d5 is 4% that leaf is high, for 10mm, height d4 is 2 times of width, and thickness d 3 is width is 1/2.
As shown in Fig. 2,3,4,6, stator 2 is fixed on above inner core 3 and urceolus 5, stator 2 is circular arc plate blade, it it is 9 along radially not reversing stator quantity, the axial gap of stator 2 impeller and impeller be sized to 10mm, the thickness of stator 2 blade is 4mm, and stator 2 has deflector 2-1 near the suction surface of trailing edge；Described deflector 2-1 is evenly distributed on suction surface trailing edge part, it is perpendicular to stator surface, equal in magnitude, with stator trailing edge apart from identical, the position of relative guide vane height is respectively 20%, 40%, 60% and 80%, spacing a3 is 53mm, and deflector length a2 is the 25% of vane root chord length, and length is 80mm, height a4 is length a2 the 1/3 of deflector, the thickness a5 of deflector is all 4mm, deflector and distance a1 is vane root chord length the 3% of blade trailing edge mutually with stator, is of a size of 10mm.
First the present invention has blowing groove 1-3 on impeller 1 wheel hub 1-2, blowing groove 1-3 is positioned at the side of blade root place blade 1-1 suction surface, due in the process that impeller 1 rotates, the suction surface making blade 1-1 produces negative pressure, and such gas just can blow into the suction surface side at blade root place by wheel hub 1-2 axial face.The reason that blade root fluting is blown is the fluid of suction surface is flow in the environment of an adverse pressure gradient, and constantly increase along tangential adverse pressure gradient, so can cause border, specific pressure face, suction surface boundary region thickness many, and also have fluid and the fricative end wall bounda layer of wheel hub arc surface at leaf root part, two kinds of boundary region mix at the suction surface of blade root, form extremely complex flowing, and along with the thickening of boundary region can cause boundary layer separation, turn and twist formation eddy flow district, cause impeller channel obstruction, energy loss and broadband sound source noise.Blade root pressure face is blown, and makes the gas of higher-energy enter root boundary layer region, it is possible to reduce and suppress the thickness of boundary region, controlled the separation of boundary region, made eddy region reduce, slow down the shedding frequence of eddy current, reduced energy loss and eddy current crack.Then the leading edge of blade 1-1 added with cylinder shape groove structure 1-5, groove 1-5 from leading edge point A1, center is dropped on the molded line of aerofoil cross section, to two back gauge limits extend, groove 1-5 diameter is the same.Leading edge adds groove structure 1-5 and is because air-flow entrance leaf road mostly with certain impact, the reduction air-flow angle of attack particular with flow constantly increases, so can cause that leading edge point A1 and front stationary point A3 is misaligned, and front stationary point A3 is on pressure face, the radius of leading edge roundlet is only small, the curvature of leading edge blade profile is very big, create the acceleration Flow Around around leading edge roundlet that angular acceleration is very big, in the past stationary point A3 is big around the angle streamed to the air-flow of suction surface, create bigger acceleration, so it is easily caused gas to separate in leading edge point, have a strong impact on the flowing of bucket rear main flow, result even in rotating stall and surge, cause very big noise and loss.Leading edge adds groove structure 1-5 can suppress the separation of leading edge point boundary region, makes air-flow in runner more steady, improves efficiency, reduce overall noise grade.The bulge-structure 1-4 being perpendicular to blade 1-1 surface is added again at leaf top portion trailing edge, reason be blade 1-1 top there is end wall annular edge interlayer and wing surfaces simultaneously also have blade tip clearance flowing to cause the flowing in Ye Ding region complexity very around laminar boundary layer, and it is maximum owing to pushing up rotary speed in the axial flow blower middle period, it is add the region that merit amount is maximum, it is necessary to the energy loss of this part controlled well could improve efficiency and the pressure of blower fan.Bulge-structure 1-4 can well reduce this partial loss, because complex flow boundary region, Ye Ding region growth rate is fast, very easily there is boundary layer separation, form vortex, particularly in suction surface side, can effectively controlling leaf top regional edge interlayer by this bulge-structure 1-4 and separate the shedding frequence with whirlpool, big Gap cirele can be cut, be carded to countless little eddy current by this structure simultaneously, reduces blower fan Trailing Edge Loss and eddy current crack.nullFinally after the convex surface of stator 2 grades, add rectangular guiding plate 2-1 near rear section，Because stator 2 is not only subject to the impact of oneself boundary layer，Also to be subject to the impact that above impeller wakes is interfered，Simultaneously because the flowing that gas is in impeller 1 is extremely complex，Cause that stator 2 inlet air flow angle is radially very big with circumference fluctuation，Fluid in stator 2 runner very unstable and border, specific pressure face, suction surface boundary region thickness many，Cause that suction surface flowing is increasingly complex，And along with fluid from stator 2 leading edge to the process of trailing edge，Boundary region constantly thickeies，So controlling the mobility status of stator 2 suction surface latter half fluid，To improving, fan performance is also critically important，The effect of deflector 2-1 is to guide air-flow to move along tangential，The Radial Flow owing to pressure and the centrifugal force imbalance of fluid cause can well be controlled，The size in pair of channels whirlpool in blade passage can also be controlled simultaneously，Flow with blade surface boundary-layer creep，Also the Secondary Flow of radial motion has just been controlled，Reduce the uneven of speed，Reduce jet Trailing Edge Loss，Control boundary layer thickness，Make stator suction surface boundary layer separation point rearward movement，Reduce energy loss、Control vortex shedding，Inhibit the eddy current crack owing to stator tail causes.By the improvement of axial flow blower diverse location makes this profile shaft flow fan in hgher efficiency, noise is lower, more energy-conserving and environment-protective.
Claims (1)
1. the axial flow blower that a blade inlet edge is blown with groove structure and blade root includes guard, impeller, stator, inner core, urceolus, motor；Described guard is to have iron wire braiding to form, and is fixed on urceolus；It is characterized in that: described impeller includes wheel hub and blade, the fluted structure of blade inlet edge, vane tip trailing edge has bulge-structure, has blowing groove on impeller hub；Described blade is the airfoil fan design of circular rector Isolated Airfoil method such as passing through, turn round speed to reduce along with the increase of reducing, pressure is radially constant, vane thickness distribution is identical with NACA 4-digit number profile thickness distribution, relative thickness of airfoil is 10% 15%, blade quantity is 59, and blade blade tip clearance is 1% the 2% of blade height；Described blade inlet edge groove structure, center is dropped on the shape line of aerofoil cross section, and being uniformly distributed, channel section is shaped as circular arc, and groove runs through whole blade inlet edge, groove is from leading edge point, to both sides, equidistant limit extends, and groove diameter is the same, and the quantity of groove is 4 10, diameter is 1% the 3% of chord length, and the distance between groove is 3% the 8% of chord length；Described vane tip trailing edge bulge-structure be shaped as cuboid, bulge-structure is perpendicular to blade suction surface, and protruding width is 3% 6% that leaf is high, and length is 24 times of width, and thickness is width is 1/4 1/2；Described blowing groove structure, it is positioned on wheel hub, the suction surface of close blade is once, blowing groove is to have the skew of blade also wheel hub suction surface intersection to obtain, the length of blowing groove is 20% the 30% of blade root cross section chord length, the width of blowing groove is 5 10mm, and blowing groove is completely through wheel hub wall, and the distance of blowing groove afterbody and blade root trailing edge is 20% the 40% of blade root chord length；Described stator is fixed on above inner core and urceolus, stator blade is circular arc plate blade, is 7 17 along radially not reversing stator quantity, the axial gap of stator impeller and impeller be sized to 5 10mm, the thickness of stator blade is 2 4mm, and stator has deflector near the suction surface of trailing edge；Described deflector is evenly distributed on suction surface trailing edge part, it is perpendicular to stator surface, equal in magnitude, with stator trailing edge apart from identical, the position of relative guide vane height is respectively 20%, 40%, 60% and 80%, and deflector length is 20% the 30% of vane root chord length, and the height of deflector is the 1/3 1/2 of length, the thickness of deflector is identical with stator, and the distance of deflector and blade trailing edge is 3% the 5% of vane root chord length；Described motor is threephase asynchronous machine, and motor is fixed on the web of inner core, and impeller is connected with motor shaft by axle sleeve.
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| CN201610263059.9A CN105756975B (en) | 2016-04-26 | 2016-04-26 | The axial flow blower that a kind of blade inlet edge is blown with groove structure and blade root |
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| CN201610263059.9A CN105756975B (en) | 2016-04-26 | 2016-04-26 | The axial flow blower that a kind of blade inlet edge is blown with groove structure and blade root |
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Cited By (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107050542A (en) * | 2017-04-28 | 2017-08-18 | 浙江理工大学 | Minitype centrifugal blood pump and its circulation blood supply method that a kind of anti-haemocyte is damaged |
| CN107366022A (en) * | 2017-08-04 | 2017-11-21 | 中国农业科学院麻类研究所 | A kind of anti-seizing mechanism of Pneumatic type fiber |
| CN108343637A (en) * | 2017-01-19 | 2018-07-31 | 安萨尔多能源公司 | For the blade or guide vane of compressor and the compressor including the blade or guide vane |
| CN108426318A (en) * | 2018-06-19 | 2018-08-21 | 奥克斯空调股份有限公司 | air channel structure and air conditioner |
| CN110173451A (en) * | 2019-07-07 | 2019-08-27 | 代元军 | A kind of blade tip is in the mining partial axial ventilator of W type structure |
| IT201800005779A1 (en) * | 2018-05-28 | 2019-11-28 | OPERATING MACHINE | |
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| CN114282327A (en) * | 2022-03-08 | 2022-04-05 | 中国空气动力研究与发展中心计算空气动力研究所 | Vortex generator cavity design method for efficiently promoting transition and vortex generator |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN1249408A (en) * | 1998-09-30 | 2000-04-05 | 东芝开利株式会社 | Axial blower |
| EP1681439A1 (en) * | 2004-12-24 | 2006-07-19 | ROLLS-ROYCE plc | A composite blade |
| US20130323098A1 (en) * | 2012-05-31 | 2013-12-05 | Denso Corporation | Axial flow blower |
| CN104696278A (en) * | 2013-12-06 | 2015-06-10 | 日本电产株式会社 | Impeller and air blower |
| CN205639000U (en) * | 2016-04-26 | 2016-10-12 | 浙江理工大学 | Blade leading edge takes axial fan that groove structure and blade root blew |
-
2016
- 2016-04-26 CN CN201610263059.9A patent/CN105756975B/en active Active
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN1249408A (en) * | 1998-09-30 | 2000-04-05 | 东芝开利株式会社 | Axial blower |
| EP1681439A1 (en) * | 2004-12-24 | 2006-07-19 | ROLLS-ROYCE plc | A composite blade |
| US20130323098A1 (en) * | 2012-05-31 | 2013-12-05 | Denso Corporation | Axial flow blower |
| CN104696278A (en) * | 2013-12-06 | 2015-06-10 | 日本电产株式会社 | Impeller and air blower |
| CN205639000U (en) * | 2016-04-26 | 2016-10-12 | 浙江理工大学 | Blade leading edge takes axial fan that groove structure and blade root blew |
Cited By (11)
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|---|---|---|---|---|
| CN108343637A (en) * | 2017-01-19 | 2018-07-31 | 安萨尔多能源公司 | For the blade or guide vane of compressor and the compressor including the blade or guide vane |
| CN107050542A (en) * | 2017-04-28 | 2017-08-18 | 浙江理工大学 | Minitype centrifugal blood pump and its circulation blood supply method that a kind of anti-haemocyte is damaged |
| CN107050542B (en) * | 2017-04-28 | 2023-07-04 | 浙江理工大学 | Miniature centrifugal blood pump capable of preventing blood cells from being damaged and circulating blood supply method thereof |
| CN107366022A (en) * | 2017-08-04 | 2017-11-21 | 中国农业科学院麻类研究所 | A kind of anti-seizing mechanism of Pneumatic type fiber |
| IT201800005779A1 (en) * | 2018-05-28 | 2019-11-28 | OPERATING MACHINE | |
| WO2019229586A1 (en) * | 2018-05-28 | 2019-12-05 | Orlandi Thermal Systems Europe S.R.L. | Working machine |
| CN108426318A (en) * | 2018-06-19 | 2018-08-21 | 奥克斯空调股份有限公司 | air channel structure and air conditioner |
| CN110173451A (en) * | 2019-07-07 | 2019-08-27 | 代元军 | A kind of blade tip is in the mining partial axial ventilator of W type structure |
| CN113153803A (en) * | 2021-04-21 | 2021-07-23 | 江苏大学 | Mixed flow pump stall operating mode impeller wake vortex dissipation device |
| CN114282327A (en) * | 2022-03-08 | 2022-04-05 | 中国空气动力研究与发展中心计算空气动力研究所 | Vortex generator cavity design method for efficiently promoting transition and vortex generator |
| CN114282327B (en) * | 2022-03-08 | 2022-05-03 | 中国空气动力研究与发展中心计算空气动力研究所 | Vortex generator cavity design method for efficiently promoting transition and vortex generator |
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