CN208153385U - A kind of cooling fan of blade inlet edge protrusion - Google Patents
A kind of cooling fan of blade inlet edge protrusion Download PDFInfo
- Publication number
- CN208153385U CN208153385U CN201820284336.9U CN201820284336U CN208153385U CN 208153385 U CN208153385 U CN 208153385U CN 201820284336 U CN201820284336 U CN 201820284336U CN 208153385 U CN208153385 U CN 208153385U
- Authority
- CN
- China
- Prior art keywords
- blade
- wheel hub
- edge protrusion
- cooling fan
- leading edge
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Expired - Fee Related
Links
Landscapes
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
The utility model discloses a kind of cooling fans of blade inlet edge protrusion, including wheel hub, the constant outer ring of axial radii and several blades, the blade is uniformly distributed along the circumferencial direction of wheel hub, the outer ring and wheel hub be coaxially disposed and by be linked together at the top of each blade, the leading edge of each blade, that is, indent camber line is equipped with wave blade leading edge protrusion, a guiding rib is disposed between the one side root of the blade and wheel hub, one end of the guiding rib is connected with wheel hub, the root that the other end passes through the rear camber line of the blade extends towards the middle part outside the rear camber line of adjacent blades.The cooling fan structure of the blade inlet edge protrusion of the utility model is simple, can reduce resistance and increases lift, improves gas flowing to reduce noise, the accuracy of result is effectively guaranteed in calculation method, the characteristics of with shortening the development cycle, improving simulation efficiency, reduce cost.
Description
Technical field
The utility model relates to engine-cooling system technical field, in particular to a kind of cooling wind of blade inlet edge protrusion
Fan.
Background technique
Important component of the aerofoil fan as car engine cooling system, to its cooling performance and acoustical behavior
It is required that also increasingly harsher.Noise brought by aerofoil fan can not only reduce fan efficiency, also will affect people and using
Comfort and physical and mental health in journey.Therefore noise has been increasingly becoming an important indicator for measuring fan performance.
Fan noise is reduced, can start with from the structure of optimization fan, develop the more excellent cooling fan of performance, this is
The main path for promoting fan cooling effect includes to change blade number, improve blade shape and section, make blade Unequal distance
The structures corrective measure such as distribution and blade perforation.
Traditional noise calculation method needs to obtain data, the week of research by carrying out many experiments in semianechoic room
Phase is long, and the cost of investment is also relatively high, and in recent years, with the development of computer technology and numerical computation method, CFD technology starts
The work of designing and developing of fan is introduced by people, simulation accuracy is high, and it is high-efficient, therefore fan is carried out by numerical method
The research of aerodynamic noise is of great significance.
Utility model content
The purpose of this utility model is to provide a kind of low noise cooling fan of blade inlet edge protrusion, this kind of fan can be with
Reduce resistance and increase lift, improves gas and flow to reduce noise,
In order to achieve the above objectives, on the one hand the utility model adopts the following technical scheme that realization：
A kind of cooling fan of blade inlet edge protrusion, it is described including the constant outer ring of wheel hub, axial radii and several blades
Blade is uniformly distributed along the circumferencial direction of wheel hub, the outer ring and wheel hub be coaxially disposed and by with connect at the top of each blade
It is integrated, leading edge, that is, indent camber line of each blade is equipped with wave blade leading edge protrusion, the one side root of the blade
A guiding rib is disposed between wheel hub, one end of the guiding rib is connected with wheel hub, and the other end passes through the rear of the blade
The root of camber line extends towards the middle part outside the rear camber line of adjacent blades.
Further, the wave blade leading edge protrusion is alternately formed by connecting by peak potion and valley, the peak potion and paddy
The number in portion and the size of blade are proportional, and the purpose is to reduce aerodynamic noise.
Further, the start-stop position of the wave blade leading edge protrusion is respectively the 25% of the blade axial length
~100%, guarantee the working performance of fan.
Further, the geometry of the wave blade leading edge protrusion is sine wave curve, using bionical theory,
Reduce eddy current loss.
Further, the blade and wheel hub are integrally formed, and facilitate processing.
Further, the guiding rib is four sections of curvilinear structures of indentation, the guiding rib axial projection width not
More than the projection width of trailing edge, guarantee the stability by air-flow.
The another aspect of the utility model adopts the following technical scheme that realization：
Compared with prior art, the beneficial good effect of the utility model is：
A kind of cooling fan of blade inlet edge protrusion provided by the utility model, structure is simple, is increased by edge in front of the blade
Add sinusoidal undulations protrusion and arrangement guiding rib, can reduce resistance and increase lift, improves gas flowing and make an uproar to reduce
Sound.The utility model proposes cooling fan aerodynamic noise calculation method, it is easy to operate, reduce calculation amount, shorten exploitation
Period；Simultaneously by fluid emulation curve graph and emulation animation, the kinetic characteristics of fluid can be showed visual and clearly, ensure that
The high-precision of calculated result greatly improves the efficiency of simulation calculation, has very strong Practical significance.
Detailed description of the invention
Fig. 1 is the cooling fan three-dimensional structure view of blade inlet edge protrusion provided by the utility model；
Fig. 2 is the cooling fan main view of blade inlet edge protrusion provided by the utility model；
Fig. 3 is the cooling fan right view of blade inlet edge protrusion provided by the utility model；
Fig. 4 is the cooling fan rearview of blade inlet edge protrusion provided by the utility model；
Fig. 5 is the simulation flow schematic diagram of cooling fan aerodynamic noise calculation method described in the utility model；
Fig. 6 is model grid computing region division schematic diagram described in the utility model；
Fig. 7 a is flow field regions grid schematic diagram in specific embodiment；
Fig. 7 b is the sectional view that flow field regions grid shown in Fig. 7 a prolongs axis；
Fig. 8 is the aerodynamic noise simulated spectrum figure with rib cooling fan in specific embodiment；
In figure：1- blade, 2- outer ring, 3- guiding rib, 4- wheel hub, 5- wave blade leading edge protrusion, 6- rotating fluid area,
7- grid transition region, 8- circulating line area, 9- inlet pipeline area, 10- outlet conduit area.
Specific embodiment
The content of the present invention is described in further detail with attached drawing with reference to embodiments, embodiment cannot herein one
One repeats, but therefore the embodiments of the present invention is not limited to the following examples.
Embodiment 1
As shown in Figures 1 to 4, a kind of cooling fan of blade inlet edge protrusion, including constant outer of wheel hub 4, axial radii
Ring 2 and several blades 1, the blade 1 are uniformly distributed along the circumferencial direction of wheel hub 4, and the outer ring 2 is coaxially disposed with wheel hub 4
And by being linked together with the top of each blade 1, leading edge, that is, indent camber line of each blade 1 is equipped with wave blade leading edge
Protrusion 5, is disposed with a guiding rib 3, one end of the guiding rib 3 and wheel between the one side root and wheel hub of the blade 1
Hub 4 is connected, and the root that the other end passes through the rear camber line of the blade 1 is prolonged towards the middle part outside the rear camber line of adjacent blades 1
It stretches.
The wave blade leading edge protrusion 5 is alternately formed by connecting by peak potion and valley, the number and wind of peak potion and valley
The size of fan leaf is related, i.e., the number of the described peak potion and valley and the size of blade 1 are proportional.
The start stop bit of the wave blade leading edge protrusion 5 is set at the 25%~100% of 1 axial length of blade,
I.e. the length maximum of wave blade leading edge protrusion 5 is consistent with 1 axial length of blade, and the minimum blade 1 is axial
3/4ths of length.
The geometry of the wave blade leading edge protrusion 5 is sine wave curve.
The blade 1 is integrally formed with wheel hub 4.
The guiding rib 3 is four sections of curvilinear structures of indentation, and the guiding rib 3 is no more than blade in axial projection width
The projection width of 1 rear.
Embodiment 2
With reference to the accompanying drawings shown in the simulation flow schematic diagram of the 5 cooling fan aerodynamic noise calculation methods provided, a kind of blade
The aerodynamic noise calculation method of the cooling fan of leading edge protrusion, includes the following steps：
Step 1, fan mock-up are established：
The geometrical model that the cooling fan is established using 3 d modeling software UG, taking Z axis is the rotary shaft of fan, according to
The right-hand rule, fan direction of rotation are forward rotation direction, and fan downstream direction is Z axis positive direction.The present embodiment modeling uses diameter
For 720mm, the cooling fan for certain blade inlet edge protrusion that the number of blade is 11, as shown in Figure 1.
Step 2 collects related data and carries out parameterized treatment：
The basic size that semianechoic room is calculated according to field condition, the basic outer dimension including semianechoic room, disengaging
The corresponding position of mouth size and fan, empirically primarily determines the position of each inlet and outlet, by the basic ruler of semianechoic room model
The location parameter of very little and each inlet and outlet.Fan noise measuring point high 1m from the ground in the present embodiment, away from cooling fan center 1m
Place and rotation axis angle at 45 °, and with cooling fan rotation axis in same level.
Step 3, building semianechoic room model simultaneously divide zoning：
In order to keep simulation calculated case and actual conditions consistent as far as possible, the geometrical model of foundation has ignored fan actively
The influence of the accessories such as axis, bracket, wind shelling cover.As shown in figure 3, will be calculated for convenience of the setting of boundary condition and the division of grid
Domain is divided into 5 sub-regions：Diameter is 1.2 times of fan diameters, and width is the rotating fluid area 6 of 1.2 times of fan axial widths, net
The outlet conduit area 10 that inlet pipeline area 9 that lattice transition region 7, circulating line area 8, length are 6D, length are 10D；Computational domain is most
Major diameter is 6D.
Step 4, simulation model grid dividing：
Finite element grid is divided to geometrical model using Hypermesh software, forms the model of parametrization based on subsequent
It calculates, since Flow Field Distribution is irregular around fan, takes the partition mode " by face to body ", first dividing surface grid application platform
Volume mesh；Because fan and its surrounding flow field parameter gradient are big, fan surface texture is more complex, thus fan and surrounding rotation
Turn the key component that domain is fan grid dividing, mesh quality and division division mode are directly related to numerical result
Reliability.Therefore, different division modes are taken from inlet and outlet farther away with a distance from fan region to fan peripheral region：Rotation
Fluid zone 6 and grid transition region 7 use tetrahedral grid to guarantee mesh quality and computational accuracy, it is desirable that tetrahedral grid
Vol skew is lower than 0.75；It is more steady to pass in and out mouth region fluid, therefore inlet pipeline area 9 and outlet conduit area 10 are respectively adopted five
Face volume mesh and hexahedral mesh, it is intended to reduce number of grid, shorten emulation cycle, it is desirable that the jacobian high of hexahedral mesh
In 0.6；Circulating line area 8 then carries out transition using pentahedron grid.
In the present embodiment, it is the triangular mesh of 2.5mm, 6 net of rotating fluid area that wafter blade surface grids, which take size,
Lattice size is 6mm, and volume mesh generating mode controls it using linear increment mode and gradually rises to 6mm from 2.5mm.According to grid
Independence verifying, 6 grid number of rotating fluid area are 1,300,000 or so, and grid transition region 7 and 8 grid number of circulating line area are about 70
Ten thousand, inlet pipeline area 9 and 10 grid number of outlet conduit area are about 600,000, and the total grid number of computation model is 2,600,000 or so.Such as attached drawing
7a and 7b show the flow field regions grid schematic diagram of the present embodiment.
Step 5, pre-treatment boundary condition determine：
Model obtained in step 4 is exported to imported into pre-processing software Gambit for NASTRAN formatted file and is set up
Boundary condition, including fan surface boundary condition, interface, entrance boundary condition, export boundary condition and rotary body perimeter strip
Part.Wherein, inletpiston is set as pressure entrance boundary, and pelvic outlet plane is set as pressure export boundary, and other wall surfaces are set as fixed
The interface of wall surface boundary, rotating fluid area 6 and grid transition region 7 is set as INTERFACE interface, and final output fluent is soft
The mesh formatted file that the solver of part can identify.
Step 6 submits software to carry out solution calculating：
The mesh formatted file that step 5 obtains is imported into the business software Fluent based on finite volume method, is calculated
When set the temperature of air as 298K (25 DEG C), air pressure is 1 standard atmospheric pressure, density 1.225kg/m3, ignore temperature
With the influence of gravity logarithm simulation.Calculate the Navier Stokes equation of fluid under given rotation speed of the fan, including following three
Point：
Pulsatile flow field calculating is carried out first, and scale Scale becomes mm, and average speed unit unit selects rpm, using RNG κ-
Epsilon turbulence model selects pressure base solver, pressure-velocity coupled wave equation is solved using SIMPLE algorithm, using standard
The discrete solution continuity equation of format, it is discrete using Second-order Up-wind format using the discrete solution equation of momentum of single order upstreame scheme
Turbulent Kinetic and turbulence dissipation rate are solved, inlet and outlet boundary turbulence intensity and diameter are set as 5% and 10m；It calculates and uses multiple ginseng
The computation model for examining coordinate system MRF coupling sound component carries out the pulsatile flow field analysis of computational domain, i.e. fan and rotating fluid area
Rotating coordinate system of the domain using consolidation thereon, and other regions use absolute rest coordinate system, carry out stable state calculating respectively, are handing over
Interface is then converted using relative velocity equation.Residual error Residuals, torque Moment, exit volume flow rate are set
Volume Flow Rate and the vertex average static pressure Vertex Average Static of monitoring point Pressure tetra- monitorings
Face, calculating convergence criterion is every residual error less than 1 × 10-5。
After stable state calculates convergence, the transient state that the result that stable state is calculated carries out second step as first field is calculated, by RNG κ-
Epsilon turbulence model is changed to the big whirlpool model of LES, and the moving reference system in rotating fluid area is changed to dynamic mesh, is asked using PISO algorithm
Decompression force-speed coupled wave equation, solves Turbulent Kinetic using PRESTO format, convergence factor is reduced to 0.5, at monitoring surface
Iteration is changed to Time step, and the setting of time step will follow the distance that a time step is passed by and be no more than Rotary District two
The distance of a node, iterative steps will make the total distance of calculating process be greater than Rotary District two weeks.
Specifying entire fan surface is noise source, sets 4 noise Rx points and is located at fan downstream apart from fan center 1m
Place, specific coordinate value is shown in Table 1, finally on the basis of large eddy simulation, introduces Ffowcs-Williams&HawkingsFW-H) it makes an uproar
Sound solving model calculates, and obtains the distribution character of fan aerodynamic noise.
1 noise Rx point coordinate of table
Step 7：Parameterized results post-processing：
Pressure parameter at each monitoring point is changed with time and carries out Fast Fourier Transform (FFT) FFT, each monitoring can be obtained
The spectrogram that the spectrum curve of point, i.e. sound pressure level (SPL) change with frequency (f).Cooling fan sets operating condition in the present embodiment
Aerodynamic noise spectrogram under 2100RPM is as shown in Figure 8.
The utility model is exemplarily described above in conjunction with attached drawing, it is clear that the utility model specific implementation not by
The limitation of aforesaid way, if the method concept of the utility model and the various improvement of technical solution progress are used, or without
Improvement directly applies to other occasions, both is within the protection scope of the present invention.
Claims (6)
1. a kind of cooling fan of blade inlet edge protrusion, it is characterised in that：
Including the outer ring (2) and several blades (1) that wheel hub (4), axial radii are constant, the blade (1) along wheel hub (4) circle
Circumferential direction is uniformly distributed, the outer ring (2) and wheel hub (4) be coaxially disposed and by be linked together at the top of each blade (1),
Leading edge, that is, indent camber line of the blade (1) is equipped with wave blade leading edge protrusion (5), the one side root of the blade (1)
A guiding rib (3) is disposed between wheel hub, one end of the guiding rib (3) is connected with wheel hub (4), and the other end passes through the leaf
The root of the rear camber line of piece (1) extends towards the middle part outside the rear camber line of adjacent blades (1).
2. the cooling fan of blade inlet edge protrusion according to claim 1, it is characterised in that：The wave blade leading edge
Raised (5) are alternately formed by connecting by peak potion and valley, and the number of the peak potion and valley and the size of blade (1) are proportional.
3. the cooling fan of blade inlet edge protrusion according to claim 1, it is characterised in that：The wave blade leading edge
The start-stop position of raised (5) is respectively the 25% ~ 100% of the blade (1) axial length.
4. the cooling fan of blade inlet edge protrusion according to claim 1, it is characterised in that：The wave blade leading edge
The geometry of raised (5) is sine wave curve.
5. the cooling fan of blade inlet edge protrusion according to claim 1, it is characterised in that：The blade (1) and wheel hub
(4) it is integrally formed.
6. the cooling fan of blade inlet edge protrusion according to claim 1, it is characterised in that：The guiding rib (3) is low
Four sections of recessed curvilinear structures, the guiding rib (3) are no more than the projection width of blade (1) rear in axial projection width.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201820284336.9U CN208153385U (en) | 2018-02-28 | 2018-02-28 | A kind of cooling fan of blade inlet edge protrusion |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201820284336.9U CN208153385U (en) | 2018-02-28 | 2018-02-28 | A kind of cooling fan of blade inlet edge protrusion |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN208153385U true CN208153385U (en) | 2018-11-27 |
Family
ID=64383376
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201820284336.9U Expired - Fee Related CN208153385U (en) | 2018-02-28 | 2018-02-28 | A kind of cooling fan of blade inlet edge protrusion |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN208153385U (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108167229A (en) * | 2018-02-28 | 2018-06-15 | 华南理工大学 | A kind of cooling fan and its aerodynamic noise computational methods of blade inlet edge protrusion |
| CN111156195A (en) * | 2020-01-07 | 2020-05-15 | 哈尔滨工程大学 | Novel compressor blade leading edge structure |
-
2018
- 2018-02-28 CN CN201820284336.9U patent/CN208153385U/en not_active Expired - Fee Related
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108167229A (en) * | 2018-02-28 | 2018-06-15 | 华南理工大学 | A kind of cooling fan and its aerodynamic noise computational methods of blade inlet edge protrusion |
| CN111156195A (en) * | 2020-01-07 | 2020-05-15 | 哈尔滨工程大学 | Novel compressor blade leading edge structure |
| CN111156195B (en) * | 2020-01-07 | 2023-11-17 | 哈尔滨工程大学 | Compressor blade leading edge structure |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN108167229A (en) | A kind of cooling fan and its aerodynamic noise computational methods of blade inlet edge protrusion | |
| Li et al. | Effect of the blade loading distribution on hydrodynamic performance of a centrifugal pump with cylindrical blades | |
| Liu et al. | Computational and experimental investigations of performance curve of an axial flow fan using downstream flow resistance method | |
| Nemnem et al. | A smooth curvature-defined meanline section option for a general turbomachinery geometry generator | |
| Sorensen et al. | Aerodynamic predictions for the unsteady aerodynamics experiment phase-II rotor at the National Renewable Energy Laboratory | |
| CN208153385U (en) | A kind of cooling fan of blade inlet edge protrusion | |
| Sahili et al. | 3-D modeling of axial fans | |
| CN111159941A (en) | Method for simulating transient numerical value of flow field in automobile hydraulic torque converter | |
| Lu et al. | Simulation and experimental research on aerodynamic noise of gas turbine 1.5-stage axial compressor | |
| Tian et al. | Effects of bionic blades inspired by the butterfly wing on the aerodynamic performance and noise of the axial flow fan used in air conditioner | |
| Yang et al. | Optimization Design and Experimental Study of Low‐Pressure Axial Fan with Forward‐Skewed Blades | |
| Wang et al. | Aerodynamic performance improvement and noise control for the multi-blade centrifugal fan by using bio-inspired blades | |
| Dong et al. | Effects of bionic volute tongue bioinspired by leading edge of owl wing and its installation angle on performance of multi-blade centrifugal fan | |
| Jiang et al. | Large eddy simulation on the vortex evolution in a squirrel-cage fan based on a slice computational model | |
| Liu et al. | Bionic volute tongue optimization design of multi-blade centrifugal fan inspired by the wave leading-edge of humpback whale flippers | |
| CN112199777B (en) | Method suitable for modeling bionic leading edge flow field characteristics | |
| Jiang et al. | A literature review on the squirrel-cage fans using in HVAC equipment: Powerful, efficient, and quiet operation | |
| Qingyi et al. | Experimental and numerical study on a new noise reduction design for a small axial fan | |
| Liu et al. | Redesign of axial fan using viscous inverse design method based on boundary vorticity flux diagnosis | |
| Jin | Numerical simulation of wind turbine wakes based on actuator line method in NEK5000 | |
| Tan et al. | Coupling bionic design and numerical simulation of the wavy leading-edge and seagull airfoil of axial flow blade for air-conditioner | |
| Basson | Design methodology of an axial-flow turbine for a micro jet engine | |
| Krzemianowski | Engineering design of the low-head Kaplan hydraulic turbine blades using the inverse problem method | |
| CN111859567B (en) | Volumetric force constructing method, computing device and readable storage medium | |
| Aydin et al. | Optimisation of a mixed flow fan with NACA profiled blades using computational fluid dynamics |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| GR01 | Patent grant | ||
| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20181127 Termination date: 20190228 |