CN106762820A - A kind of method for designing of prismatic blade radial fan impeller - Google Patents
A kind of method for designing of prismatic blade radial fan impeller Download PDFInfo
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- CN106762820A CN106762820A CN201611212113.3A CN201611212113A CN106762820A CN 106762820 A CN106762820 A CN 106762820A CN 201611212113 A CN201611212113 A CN 201611212113A CN 106762820 A CN106762820 A CN 106762820A
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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
- F04D29/28—Rotors specially for elastic fluids for centrifugal or helico-centrifugal pumps for radial-flow or helico-centrifugal pumps
- F04D29/30—Vanes
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- G—PHYSICS
- G06—COMPUTING; CALCULATING OR COUNTING
- G06F—ELECTRIC DIGITAL DATA PROCESSING
- G06F30/00—Computer-aided design [CAD]
- G06F30/10—Geometric CAD
- G06F30/17—Mechanical parametric or variational design
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Abstract
The invention discloses a kind of method for designing of prismatic blade radial fan impeller, including 1, the hub curves and shroud curves of establishment impeller；2nd, the datum curve and datum mark of blade are created；3rd, the leading edge controlling curve of middle cambered surface is built, the datum mark defined in the datum curve starting point and shroud of blade is connected by fair curve, the leading edge controlling curve of cambered surface, leading edge controlling curve is rotated a circle about the z axis in establishment, creates the leading edge trimmed surface of cambered surface in blade；4th, cambered surface root curve in blade is created；5th, cambered surface in final blade is created；6th, spoon of blade is created；7th, impeller is created, this is designed as Full Parameterized Design, in the case where a small amount of control parameter drives, the deformation in maximum magnitude can be just carried out to model, blindness and uncertainty when avoiding modelling and optimization using this method, substantial amounts of manpower and time are directly saved, for the design studies of prismatic blade radial fan impeller provide more scientific approach.
Description
Technical field
The invention belongs to blower fan technical field, more particularly to a kind of method for designing of prismatic blade radial fan impeller.
Background technology
The function of blower fan essentially consists in guiding air flow and then reaches the purpose of radiating, therefore, to make radiating efficiency good
Good, blower fan must be good for the guiding efficiency of air, and at present, the flow direction of air divides during with blower fan work, and blower fan has
Two kinds of axle stream and radial-flow type.Radial fan is the principle that potential energy is converted to according to kinetic energy, using the impeller of high speed rotation by gas
Body accelerates, and then slows down, changes flow direction, kinetic energy is converted into potential energy.When motor impeller works, gas enters from axial direction
Enter impeller, gas is radially redirected when flowing through impeller, subsequently into diffuser.Because air is become in blower fan by axially flowing
Radial Flow, so claiming radial fan, the performance of radial fan is more embodied in the structure in impeller and air channel, so
Industry also focuses mostly at aspects such as structure, materials in exploring.Radial fan is more applied as the important corollary equipment of industry
In the fields such as electric power, cement, petrochemical industry, coal, mine and environmental protection, under new economic development situation, following radial fan
Industry will continue to keep increasing faster.
The Impeller Design of radial fan, the foundation design manual that in the market is mainly used, according to air quantity, blast, rotating speed etc.
Demand data, is derived by substantial amounts of calculating, designs a basic blade wheel structure for substantially meeting demand.The leaf that design is obtained
How is wheel performance, in addition it is also necessary to further checking, and follow-up impeller is improved, and being but that traditional design method is very scabrous asks
Topic, most of designing units use empirically local modification model, but this kind of method exist very big blindness and
Uncertainty, also likely reduce blower fan performance, in a word, blade wheel structure design on, seriously exist at present efficiency it is low, into
The problems such as this is high.
The content of the invention
The present invention, only need to be to mould in view of the shortcomings of the prior art, provide a kind of method for designing of prismatic blade radial fan impeller
Type creates a small amount of parameter, can just make the blade wheel structure of radial fan ever-changing, follow-up to combine CFD simulation analysis, can survey
The performance of every kind of structure is tried out, further according to analysis result to model local optimum optimizing, performance can be rapidly obtained more preferable
Prismatic blade radial fan impeller pattern.
In order to solve the above technical problems, the present invention is addressed by following technical proposals：A kind of prismatic blade radial fan
The method for designing of impeller, comprises the following steps：1st, a kind of method for designing of prismatic blade radial fan impeller, it is characterised in that bag
Include following steps：1：Create impeller hub curves and shroud curves, in Y-X-Z planes create impeller hub curves and
Shroud curves, hub curves and shroud curves are rotated a circle about the z axis respectively, create hub curved surfaces and shroud curved surfaces, if
Put the control point parameter of hub curves and shroud curves；2：The datum curve and datum mark of blade are created, is selected on hub curves
One section of datum curve as blade therein is selected, benchmark of the point as blade extreme higher position is defined on shroud curves
Point, sets the parameter of reference point location in the parameter and shroud curves of blade datum curve start-stop position；3：Arc in establishment
The leading edge controlling curve in face, the datum mark defined in the datum curve starting point and shroud of blade, wound are connected by fair curve
The leading edge controlling curve of middle cambered surface is built, leading edge controlling curve is rotated a circle about the z axis, the leading edge for creating cambered surface in blade cuts song
Face；4：Cambered surface root curve in blade is created, by the equation controlling curve of middle arc shape, control blade datum curve is along leaf
Wheel is circumferential to be changed, and creates the root curve of cambered surface in blade, sets control point parameter and the shape ginseng of equation controlling curve A
Number；5：Create cambered surface, the reference point location holding plane on shroud curves, by cambered surface root in blade in final blade
Then curve projection is connected come cambered surface initial surface in creating, the cambered surface in using root curve in plane with drop shadow curve
Leading edge trimmed surface cut in cambered surface initial surface, obtain cambered surface in real blade；6：Spoon of blade is created, blade is used
The equation controlling curve of section thickness, makes each molded line inside middle cambered surface all be offset to both sides, generates the section wheel of blade
Wide curve, a spoon of blade is combined into by all of sectional profile curve lin, set equation controlling curve B control point parameter and
Form parameter；7：Impeller is created, the trailing edge sideline of cambered surface rotates a circle generate blade trailing edge trimmed surface about the z axis in use, with
Hub curved surfaces and shroud curved surfaces cut to blade together, create blade entity, by blade entity about the z axis circumference array after,
With hub and shroud curved surface Boolean calculations, whole impeller is created, lobe numbers parameter is set.
In such scheme, it is preferred that the hub curve control points parameter includes radius, the height of the hub origins of curve, hub
The radius of End of Curve, height, the angle of hub curve initiating terminals.
In such scheme, it is preferred that the shroud curve control points parameter includes radius, the height of the shroud origins of curve
Degree, the radius of shroud End of Curves, height, the angle of shroud curve initiating terminals and the angle of clearing end, shroud curves
The radius of middle part fillet.
In such scheme, it is preferred that the parameter of the blade datum curve start-stop position, including the starting of blade datum curve
The residing ratio on hub curves of the residing ratio on hub curves in position, blade datum curve final position.
In such scheme, it is preferred that the parameter of reference point location includes base on shroud curves on the shroud curves
The residing ratio on shroud curves in position on schedule.
In such scheme, it is preferred that the control point parameter of equation controlling curve A includes that equation controls song in the step 4
The starting point height and terminal of line A are highly.
In such scheme, it is preferred that the form parameter of equation controlling curve A includes equation controlling curve A in the step 4
Initiating terminal curvature and clearing end curvature.
In such scheme, it is preferred that the control point parameter of equation controlling curve B includes that equation controls song in the step 6
Starting point height, the terminal of line B are highly.
In such scheme, it is preferred that the form parameter of equation controlling curve B includes equation controlling curve B in the step 6
Initiating terminal curvature and clearing end curvature.
The present invention compared with prior art, has the advantages that：The structure of this prismatic blade runoff radial fan impeller
Design, using the thinking completely different with traditional design method, this is designed as Full Parameterized Design, can be in any desired control
Position addition parameter carry out Controlling model, it is also possible to the equation controlling curve using model carrys out Controlling model, can be succinctly quick
One prismatic blade radial fan impeller of establishment, and in the case where a small amount of control parameter drives, can just carry out maximum model to model
Interior deformation is enclosed, afterwards using driving instruments such as CAESES, batch control CFD analyses, and the analysis result conclusion of CFD is sentenced
It is disconnected, then the control parameter of model is changed again according to certain rule, model is finally reached an optimal state, adopt
With this method avoid modelling and optimization when blindness and uncertainty, directly save substantial amounts of manpower and when
Between, for the design studies of prismatic blade radial fan impeller provide more scientific approach.
Specific embodiment
The present invention is described in further detail with reference to specific embodiment.
Embodiment 1：By taking the prismatic blade runoff radial fan impeller that the number of blade is 5 as an example, method for designing is：1st, leaf is created
The hub curves and shroud curves of wheel, create the hub curves and shroud curves of impeller, by hub curves in Y-X-Z planes
Rotated a circle about the z axis respectively with shroud curves, create hub curved surfaces and shroud curved surfaces, hub origin of curve radiuses are set
45mm, height 10mm, hub End of Curve radius 125mm, 20 ° of height 0mm, hub curve initiating terminal angle；Shroud curves rise
Point radius 90mm, height 100mm, shroud End of Curve radiuses 125mm, height 60mm；The angle of shroud curve initiating terminals
50 ° and 10 ° of the angle of clearing end, the radius 10mm of shroud curves middle part fillet；2nd, the datum curve and base of blade are created
On schedule, one section of datum curve as blade therein is selected on hub curves, length of curve side is defined on shroud curves
To 0.15 times of location point of shroud curves overall length as blade extreme higher position datum mark, set blade datum curve start bit
It is the residing ratio 0.88 on hub curves of 0.15, blade datum curve final position to put residing ratio on hub curves,
The residing ratio 0.4 on shroud curves of reference point location on shroud curves；3rd, the leading edge controlling curve of cambered surface in creating,
By the datum mark in the datum curve starting point and shroud curves of the blade set in fair curve Connection Step 2, in establishment
The leading edge controlling curve of cambered surface, leading edge controlling curve is rotated a circle about the z axis, creates the leading edge trimmed surface of cambered surface in blade；
4th, cambered surface root curve in blade is created, the starting point of arc shape equation controlling curve A highly is that 0.69mm, terminal are high in setting
Degree 0.23mm, -90 ° of initiating terminal angle, 10 ° of clearing end angle and controlling curve factor of influence 60；5th, final blade is created
Middle cambered surface, the reference point location holding plane on shroud curves, by cambered surface root curve projection in blade to plane, so
It is connected with drop shadow curve using root curve afterwards come cambered surface initial surface in creating, during the leading edge trimmed surface of cambered surface cuts in
Cambered surface initial surface, obtains cambered surface in real blade；6th, spoon of blade is created, blade sectional thickness equation controlling curve is set
0 ° of the starting point height 5mm of B, terminal height 3mm, 0 ° of initiating terminal angle and clearing end angle, make each stripe shape inside middle cambered surface
Line is all offset to both sides, generates the sectional profile curve lin of blade, and all of sectional profile curve lin is combined into a spoon of blade；
7th, create impeller, in use the trailing edge sideline of cambered surface rotate a circle about the z axis generation blade trailing edge trimmed surface, with hub curved surfaces and
Shroud curved surfaces cut to blade together, create blade entity, by blade entity about the z axis circumference array after, with hub and
Shroud curved surface Boolean calculations, create whole impeller, and it is 5 finally to set lobe numbers parameter, and it is 5 to obtain fan impeller blade
Draught fan impeller.
Embodiment 2：By taking the prismatic blade runoff radial fan impeller that the number of blade is 8 as an example, method for designing is：1st, leaf is created
The hub curves and shroud curves of wheel, create the hub curves and shroud curves of impeller, by hub curves in Y-X-Z planes
Rotated a circle about the z axis respectively with shroud curves, create hub curved surfaces and shroud curved surfaces, hub origin of curve radiuses are set
100mm, the radius 200mm of height 50mm, hub End of Curve, 50 ° of the angle of height 0mm, hub curve initiating terminal, including
The radius 150mm of the shroud origins of curve, radius 200mm, the height 100mm of height 160mm, shroud End of Curve,
20 ° of the angle of 80 ° of the angle of shroud curve initiating terminals and clearing end, the radius 30mm of shroud curves middle part fillet；2nd, create
The datum curve and datum mark of blade are built, one section of datum curve as blade therein is selected on hub curves, in shroud
0.16 times of location point of shroud curves overall length in length of curve direction is defined on curve as the datum mark of blade extreme higher position, if
The residing ratio on hub curves of blade datum curve original position is put for 0.16, blade datum curve final position is bent in hub
Ratio 0.92 residing on line, the residing ratio 0.4 on shroud curves of reference point location on shroud curves；3rd, in creating
The leading edge controlling curve of cambered surface, the datum curve starting point of the blade by being set in fair curve Connection Step 2 is bent with shroud
Datum mark on line, the leading edge controlling curve of cambered surface, leading edge controlling curve is rotated a circle about the z axis in establishment, in establishment blade
The leading edge trimmed surface of cambered surface；4th, cambered surface root curve, the starting point of arc shape equation controlling curve A in setting in blade are created
Highly it is 0.9mm, terminal height 0.3mm, -80 ° of initiating terminal angle, 30 ° of clearing end angle and controlling curve factor of influence 40；
5th, cambered surface in final blade is created, the reference point location holding plane on shroud curves is bent by cambered surface root in blade
Then line projection is connected come cambered surface initial surface in creating, the cambered surface in using root curve in plane with drop shadow curve
Cambered surface initial surface in the cutting of leading edge trimmed surface, obtains cambered surface in real blade；6th, spoon of blade is created, blade is set and is cut
0 ° of the starting point height 7mm of face thickness equation controlling curve B, terminal height 5mm, 0 ° of initiating terminal angle and clearing end angle, in making
Each molded line inside cambered surface all offsets to both sides, the sectional profile curve lin of blade is generated, by all of sectional profile curve lin
It is combined into a spoon of blade；7th, impeller is created, the trailing edge sideline of cambered surface rotates a circle generate blade trailing edge sanction about the z axis in use
Curved surface is cut, blade is cut together with hub curved surfaces and shroud curved surfaces, create blade entity, blade entity is justified about the z axis
After all arrays, with hub and shroud curved surface Boolean calculations, whole impeller is created, it is 8 finally to set lobe numbers parameter, is obtained
Blade is the draught fan impeller of 8.
Blade under different parameters can be obtained, after the success of blower fan model construction, just by the setting to different designs parameter
Beginning model is general all without being best performance, as long as by finely tuning parameter, identical CFD points is carried out to each mutation model
Analysis, with reference to appropriate optimized algorithm, finally can search out the model of best performance in the range of parameter restriction.
Protection scope of the present invention includes but is not limited to embodiment of above, and protection scope of the present invention is with claims
Be defined, any replacement being readily apparent that to those skilled in the art that this technology is made, deformation, improvement each fall within it is of the invention
Protection domain.
Claims (9)
1. a kind of method for designing of prismatic blade radial fan impeller, it is characterised in that comprise the following steps：1：Create impeller
Hub curves and shroud curves, create the hub curves and shroud curves of impeller in Y-X-Z planes, by hub curves and
Shroud curves rotate a circle about the z axis respectively, create hub curved surfaces and shroud curved surfaces, set hub curves and shroud curves
Control point parameter；2：The datum curve and datum mark of blade are created, one section of base as blade therein is selected on hub curves
Directrix curve, defines datum mark of the point as blade extreme higher position on shroud curves, sets blade datum curve start-stop
The parameter of reference point location in the parameter and shroud curves of position；3：The leading edge controlling curve of cambered surface in establishment, by light
The datum mark defined in the datum curve starting point and shroud of fair curve connection blade, the leading edge controlling curve of cambered surface in establishment,
Leading edge controlling curve is rotated a circle about the z axis, the leading edge trimmed surface of cambered surface in blade is created；4：Create cambered surface root in blade
Curve, by the equation controlling curve of middle arc shape, control blade datum curve is circumferentially changed along impeller, creates blade
The root curve of middle cambered surface, sets the control point parameter and form parameter of equation controlling curve A；5：Create arc in final blade
Face, the reference point location holding plane on shroud curves, by cambered surface root curve projection in blade to plane, then makes
It is connected with drop shadow curve with root curve come cambered surface initial surface in creating, cambered surface during the leading edge trimmed surface of cambered surface cuts in
Initial surface, obtains cambered surface in real blade；6：Spoon of blade is created, using the equation controlling curve of blade sectional thickness,
Each molded line inside cambered surface is all offset to both sides, the sectional profile curve lin of blade is generated, by all of cross section profile
Curve combination sets the control point parameter and form parameter of equation controlling curve B into a spoon of blade；7：Impeller is created, is made
Rotated a circle about the z axis with the trailing edge sideline of middle cambered surface and generate blade trailing edge trimmed surface, together with hub curved surfaces and shroud curved surfaces
Blade is cut, create blade entity, by blade entity about the z axis circumference array after, with hub and shroud curved surfaces boolean transport
Calculate, create whole impeller, lobe numbers parameter is set.
2. a kind of method for designing of prismatic blade radial fan impeller according to claim 1, it is characterised in that the hub
Curve control point parameter includes radius, the height of the hub origins of curve, the radius of hub End of Curves, height, hub curve initiating terminals
Angle.
3. the method for designing of a kind of prismatic blade radial fan impeller according to claim 1, it is characterised in that described
Radius, height of the shroud curve control points parameter including the shroud origins of curve, the radius of shroud End of Curves, height,
The angle of shroud curve initiating terminals and the angle of clearing end, the radius of shroud curves middle part fillet.
4. a kind of method for designing of prismatic blade radial fan impeller according to claim 1, it is characterised in that the blade
The parameter of datum curve start-stop position, including the residing ratio on hub curves of blade datum curve original position, blade benchmark
The residing ratio on hub curves of curve final position.
5. the method for designing of a kind of prismatic blade radial fan impeller according to claim 1, it is characterised in that described
The parameter of reference point location includes the residing ratio on shroud curves of reference point location on shroud curves on shroud curves
Rate.
6. a kind of method for designing of prismatic blade radial fan impeller according to claim 1, it is characterised in that the step
The control point parameter of equation controlling curve A includes the starting point height of equation controlling curve A and terminal highly in 4.
7. a kind of method for designing of prismatic blade radial fan impeller according to claim 1, it is characterised in that the step
The form parameter of equation controlling curve A includes the initiating terminal curvature and clearing end curvature of equation controlling curve A in 4.
8. a kind of method for designing of prismatic blade radial fan impeller according to claim 1, it is characterised in that the step
Starting point height, the terminal of the control point parameter of equation controlling curve B including equation controlling curve B be highly in 6.
9. a kind of method for designing of prismatic blade radial fan impeller according to claim 1, it is characterised in that the step
The form parameter of equation controlling curve B includes the initiating terminal curvature and clearing end curvature of equation controlling curve B in 6.
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| CN118105618A (en) * | 2024-04-29 | 2024-05-31 | 生命盾医疗技术(苏州)有限公司 | Impeller for catheter pump, manufacturing method and inspection method of impeller, and catheter pump |
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| CN118105618B (en) * | 2024-04-29 | 2024-07-02 | 生命盾医疗技术(苏州)有限公司 | Impeller for catheter pump, manufacturing method and inspection method of impeller, and catheter pump |
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| Publication number | Publication date |
|---|---|
| CN106762820B (en) | 2018-11-23 |
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