CN106949095A - The optimization method of Low-pressure axial fan impeller blade - Google Patents
The optimization method of Low-pressure axial fan impeller blade Download PDFInfo
- Publication number
- CN106949095A CN106949095A CN201710262288.3A CN201710262288A CN106949095A CN 106949095 A CN106949095 A CN 106949095A CN 201710262288 A CN201710262288 A CN 201710262288A CN 106949095 A CN106949095 A CN 106949095A
- Authority
- CN
- China
- Prior art keywords
- line segment
- section
- blade
- line
- circular arc
- 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.)
- Granted
Links
- 238000005457 optimization Methods 0.000 title claims abstract description 21
- 238000000034 method Methods 0.000 title claims abstract description 19
- 230000008676 import Effects 0.000 claims description 7
- 238000009826 distribution Methods 0.000 claims description 6
- 238000004088 simulation Methods 0.000 claims description 6
- 238000004364 calculation method Methods 0.000 claims description 4
- 238000004519 manufacturing process Methods 0.000 claims description 3
- 230000003252 repetitive effect Effects 0.000 claims description 3
- 230000015572 biosynthetic process Effects 0.000 claims 1
- 239000004744 fabric Substances 0.000 claims 1
- 239000010410 layer Substances 0.000 description 6
- 238000004378 air conditioning Methods 0.000 description 1
- 238000001816 cooling Methods 0.000 description 1
- 230000007423 decrease Effects 0.000 description 1
- 230000007812 deficiency Effects 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 239000012530 fluid Substances 0.000 description 1
- 238000000926 separation method Methods 0.000 description 1
- 239000002344 surface layer Substances 0.000 description 1
- 238000009423 ventilation Methods 0.000 description 1
Classifications
-
- 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
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
The invention discloses the optimization method of Low-pressure axial fan impeller blade.Low-pressure axial fan is widely used, but it is low to there is total head, and air quantity is big, the problem of impeller adiabatic efficiency is low.The present invention is radially divided into n section on one piece of blade of impeller pattern to be optimized along impeller, obtains the chord length b in n sectioni, outlet geometry angle beta2A(i)And inlet air flow angle beta1(i).Skeletonizing, sketch includes the first line segment, second line segment, the 3rd line segment, the 4th line segment, the 5th line segment, the 6th line segment, the first circular arc, the second circular arc, the 7th line segment and the 8th line segment.First circular arc and the second circular arc composition Novel wire.N new sections are obtained according to Novel wire, the impeller pattern after being optimized according to n new sections.The present invention need to only know chord length, inlet air flow angle and the outlet geometry angle of blade profile to be optimized, it becomes possible to which the performance to Low-pressure axial fan is optimized, and design time and cost are shortened greatly.
Description
Technical field
The invention belongs to fan impeller technical field, and in particular to a kind of Low-pressure axial fan impeller blade it is excellent
Change method.
Background technology
Low-pressure axial fan is used as ventilation, HVAC, cooling, air-conditioning and the master for industrial equipment and the household electrical appliance such as transporting
Power is wanted, is used widely.The Aerodynamic Characteristics of axial flow blower are that total head is low, and air quantity is big, and impeller adiabatic efficiency is low, and reason is its blade
There is gap between pipeline, there is Secondary Flow on leaf top, and blade root is connected with wheel hub, separation stream is also very serious, has near blade root and leaf top
Substantial amounts of whirlpool, or even backflow, cause very big flow losses.
In propeller fan, air-flow is extremely complex by pressure loss during blade, along the pressure of blade height
Loss distribution is uneven.At blade mean radius, the pressure loss is smaller, and the pressure loss is concentrated mainly on blade
In wake flow in region very narrow；In the Ye Dao center sections close to blade mean radius, the pressure loss is also all smaller, and ratio
It is more uniform；But near wheel hub and casing, the region of the pressure loss is expanded, and the numerical value of the pressure loss has also increased
Plus.That is due to, when air-flow flows through Ye Daoshi, there is relative motion between air-flow and blade, then have active force between them,
And the pressure of forward face is greater than the pressure on blade convex surface.Therefore, between two adjacent blades, from blade
There is transverse-pressure gradient in concave surface, this transverse-pressure gradient is with the increase of lift coefficient between the convex surface of another blade
And increase.On the other hand, air-flow is to pass through leaf grating in curvilinear motion form, then generates centrifugal force, the side of the centrifugal force
To being concave surface that blade is directed towards from the convex surface of a blade.Between the center section along blade height, adjacent blades
Transverse-pressure gradient and the centrifugal force of air-flow balanced, so air-flow will not produce the flowing of horizontal direction.But in blade
Root and top situation are then different.For example, outside stream pressure and boundary-layer in root of blade, hub surface boundary-layer
Stream pressure is identical, and air velocity inside boundary-layer with to hub surface close to and reduce, and be intended to
Zero.Thus there is transverse-pressure gradient inside boundary-layer, but but without or few air-flows centrifugal force, it is then attached
The transverse gradients pressure of surface layer can not be balanced, and the gas in boundary-layer, which occurs from the concave surface of a blade, flows to adjacent blades
Convex surface lateral flow, the pressure in the boundary-layer near forward face decreases, and attached on the convex surface of adjacent blades
Closely, pressure but increased, and then form whirlpool.These whirlpools are taken away by primary air, behind blade tail end, these
Whirlpool is gradually converted into heat energy loss and fallen, and this loss has in root of blade and top.So the design of axial flow blower and excellent
The target of change seeks to reduce radial velocity, makes axial velocity more uniform, the axial velocity at lifting wheel hub and wheel cap, and carries
Acting ability of blade etc. is risen, so that fan efficiency and total head get a promotion.
The content of the invention
In view of the above-mentioned deficiencies in the prior art, it is an object of the present invention to provide a kind of Low-pressure axial fan impeller blade
Optimization method.
The step of the present invention is specific as follows：
Step 1: setting up impeller pattern to be optimized.The wheelboss side wall of impeller and the spacing of blade outer end are n × s.At this
N section and corresponding molded line in n section of vertical impeller radial direction, two neighboring section spacing are taken on one piece of blade of model
S is, the section and wheelboss side wall of most inner side are tangent, 3≤n≤20.The chord length b in n section is measured respectivelyi, i=1,2,
3 ..., n, and outlet geometry angle beta2A(i), i=1,2,3 ..., n.All chamferings and fillet, are simplified mould in removal model
Type.Mesh generation and numerical simulation calculation are carried out to simplified model with mesh generation software, the complete of impeller pattern to be optimized is obtained
Three velocity components at pressure and n section import；Speed triangle is drawn according to three velocity components, is cut so as to obtain n
The inlet air flow angle beta in face1(i), i=1,2,3 ..., n.The total head value of the model is assigned to Z1.
Step 2: being assigned to i by 1.
Step 3: skeletonizing, sketch include the first line segment, second line segment, the 3rd line segment, the 4th line segment, the 5th line segment,
6th line segment, the first circular arc, the second circular arc, the 7th line segment and the 8th line segment.First line segment and second line segment parallel lines each other, the
The two ends end points of three line segments is respectively on the first line segment and second line segment, and the length of the 3rd line segment is bi.4th line segment and the 6th
Line segment is separately positioned on the both sides of the 5th line segment, the two ends end points of the 4th line segment, one end end points of the 6th line segment and the 3rd line segment
It is respectively superposed.The other end end points of 4th line segment is on the 5th line segment.The other end end points of 6th line segment and the one of the 5th line segment
End points is held to overlap, and the 6th line segment and the 5th line segment are isometric.5th line segment and the 3rd line segment intersection.The center of circle of first circular arc is the
The intersection point of four line segments and the 5th line segment, two-end-point is respectively the misaligned end points of the 4th line segment and the 5th line segment.Second circular arc
The center of circle is the intersection point of the 5th line segment and the 6th line segment, and two-end-point is respectively the misaligned end points of the 5th line segment and the 6th line segment.The
One circular arc in the second circular arc clockwise.Tangent line of 7th line segment with the first circular arc on the 4th line segment end points is overlapped,
The angle of 7th line segment and the first line segment is β1(i), tangent line of the 8th line segment with the second circular arc on the 6th line segment end points overlap,
8th line segment and the angle of second line segment are β2A(i).The angle of 7th line segment and the 8th line segment is θc, try to achieve θc=β2A(i)-
β1(i).The angle of 4th line segment and the 5th line segment is α1, take α1=0.6 θc；The angle of 6th line segment and the 5th line segment is α2, take α2
=0.4 θc.The angle of 3rd line segment and the 7th line segment is α1, the angle of the 3rd line segment and the 8th line segment is α2。
Step 4: the first circular arc and the second circular arc composition Novel wire.To Novel wire superposition thickness value a, 1mm≤a≤6mm,
Obtain circular section；Or a kind of aerofoil profile is chosen in airfoil database, obtain the thickness distribution of aerofoil section, the thickness of aerofoil section
Degree distribution obtains aerofoil section with reference to Novel wire.The circular section or aerofoil section of gained are recorded as i-th of section.
Step 5: i increases 1, if i≤n, repeat step three and four, section obtained by step 3 is circular arc in repetitive process
Tee section is aerofoil section.Otherwise, into next step.
Step 6: n section of gained is be arranged in parallel per two neighboring section distance s, and be put into two it is coaxial and half
Footpath difference is between the n × s face of cylinder.The geometric center in n section is at one on the straight line in n section, and this is straight
Line is vertically intersected on the axis of two cylindrical surface.N section is arranged successively according to chord length size, and chord length most long section is located at most
Inner side.Chord length most long section and diameter is tangent compared with small cylindrical surface.First line segment in n section is parallel to each other, and with two cylinders
The axis in face is vertical.The First Line section in n section is located at the same side.Blade blank is obtained according to n section.Extended blade blank
Two ends so that the outer end of blade blank, which is passed completely through, is relatively large in diameter the face of cylinder, the inner of blade blank pass completely through diameter compared with
Small cylindrical surface.Blade blank between two cylindrical surface is optimization rear blade.Using two cylindrical surface axis as array center, circumferentially
Uniform array goes out m pieces of blade, 4≤m≤10.Wheel hub, the impeller pattern after being optimized are drawn for m pieces of blade.
Step 7: taking the n section and the n section of vertical impeller radial direction on one piece of blade of step 6 institute established model
Corresponding molded line, adjacent sections spacing is s, and the section and wheelboss side wall of most inner side are tangent.The chord length in n section is measured respectively
bi, i=1,2,3 ..., n, and outlet geometry angle beta2A(i), i=1,2,3 ..., n.It is all in six established models of removal step to fall
Angle and fillet, obtain new simplified model.With mesh generation software to new simplified model mesh generation, and carry out numerical simulation meter
Calculate, obtain step 6 institute established model total head and n section import at three velocity components；Drawn according to three velocity components
Speed triangle, so as to obtain the inlet air flow angle beta in n section1(i), i=1,2,3 ..., n.By the total head value assignment of the model
To Z2.
If Step 8: Z2 subtracts Z1 income values more than k, 3Pa≤k≤8Pa, Z2 value is assigned into Z1, and repeat step
2nd, three, four, five, six and seven.Otherwise, optimization terminates.
Impeller to be optimized described in step one is the SDF-11.2 tunnels of the positive blower fan Co., Ltd production in Shaoxing Shangyu nine
The impeller of formula axial flow blower.
The method that blade blank is obtained in step 6 is as follows：The contour line in n section is carried out in solidworks " to put
Sample curved surface " is operated, and seamlessly transits generation blade blank.
The method at extended blade blank two ends is as follows in step 6：Blade blank is subjected to " curved surface in solidworks
Extension " operation.
The aerofoil profile chosen in step 3 is NACA0012.
K value is 5Pa in step 8.
The invention has the advantages that：
1st, the present invention combines fluid machinery, three-dimensional modeling and CFD, by the chord length of blade profile, inlet air flow angle and goes out
Mouth geometry angle, it becomes possible to which the performance to Low-pressure axial fan is optimized, and substantially reduces design time and cost.
2nd, the present invention has the Optimization Steps unit repeated, repeats Optimization Steps unit, you can complete to low-pressure shaft
Many suboptimization of streaming blower performance.
3rd, the present invention performs Optimization Steps unit for the first time, and the total head of Low-pressure axial fan is substantially improved, but efficiency
It is declined slightly；Follow-up Optimization Steps unit is performed, the efficiency of Low-pressure axial fan is held essentially constant, and total head can be carried persistently
Rise.
Brief description of the drawings
Fig. 1 is the stereogram of impeller pattern to be optimized；
Fig. 2 is the sketch of drafting blade profile molded line in the present invention.
Embodiment
Below in conjunction with accompanying drawing, the invention will be further described.
The optimization method of Low-pressure axial fan impeller blade is comprised the following steps that：
Step 1: setting up impeller pattern to be optimized as shown in figure 1, impeller to be optimized has for the positive blower fan in Shaoxing Shangyu nine
The impeller of the SDF-11.2 tunnel type axial flow fans of limit company production, the wheelboss side wall of impeller and the spacing of blade outer end are 8s.
Taken on one piece of blade of the model between eight sections and corresponding molded line in eight sections of vertical impeller radial direction, adjacent sections
Away from s is, the section and wheelboss side wall of most inner side are tangent.The chord length b in eight sections is measured respectivelyi, i=1,2,3 ..., 8, and
Export geometry angle beta2A(i), i=1,2,3 ..., 8.All chamferings and fillet, are simplified model in removal model.Drawn with grid
Component software carries out mesh generation and numerical simulation calculation to simplified model, obtain impeller pattern to be optimized total head and eight sections
Three velocity components at import；Speed triangle is drawn according to three velocity components, so as to obtain the inlet gas in eight sections
Flow angle beta1(i), i=1,2,3 ..., 8.The total head value of impeller pattern to be optimized is assigned to Z1.
Step 2: being assigned to i by 1.
Step 3: as shown in Fig. 2 skeletonizing, sketch includes the first line segment 1, second line segment 2, the 3rd line segment the 3, the 4th
Line segment 4, the 5th line segment 5, the 6th line segment 6, the first circular arc 7-1, the second circular arc 7-2, the 7th line segment 8 and the 8th line segment 9.First Line
Section 1 and the parallel lines each other of second line segment 2, the two ends end points of the 3rd line segment 3 is respectively on the first line segment 1 and second line segment 2, and the 3rd
The length of line segment 3 is bi.4th line segment 4 and the 6th line segment 6 are separately positioned on the both sides of the 5th line segment 5, the 4th line segment the 4, the 6th
The two ends end points of one end end points and the 3rd line segment 3 of line segment 6 is respectively superposed.The other end end points of 4th line segment 4 is in the 5th line segment 5
On.The other end end points of 6th line segment 6 is overlapped with one end end points of the 5th line segment 5, and the 6th line segment 6 and the 5th line segment 5 are isometric.
5th line segment 5 intersects with the 3rd line segment 3.The first circular arc 7-1 center of circle is the intersection point of the 4th line segment 4 and the 5th line segment 5, two-end-point
The respectively misaligned end points of the 4th line segment 4 and the 5th line segment 5.The second circular arc 7-2 center of circle is the 5th line segment 5 and the 6th line segment
6 intersection point, two-end-point is respectively the misaligned end points of the 5th line segment 5 and the 6th line segment 6.First circular arc 7-1 is in the second circular arc 7-2
Clockwise.Tangent line of 7th line segment 8 with the first circular arc 7-1 on the end points of the 4th line segment 4 is overlapped, the 7th line segment 8 with
The angle of first line segment 1 is β1(i), tangent line of the 8th line segment 9 with the second circular arc 7-2 on the end points of the 6th line segment 6 overlap, and the 8th
The angle of line segment 9 and second line segment 2 is β2A(i).The angle of 7th line segment 8 and the 8th line segment 9 is θc, try to achieve θc=β2A(i)-
β1(i).The angle of 4th line segment 4 and the 5th line segment 5 is α1, take α1=0.6 θc；The angle of 6th line segment 6 and the 5th line segment 5 is α2,
Take α2=0.4 θc.The angle of 3rd line segment 3 and the 7th line segment 8 is α1, the angle of the 3rd line segment 3 and the 8th line segment 9 is α2。
Step 4: the first circular arc 7-1 and the second circular arc 7-2 composition Novel wires.The value that Novel wire is superimposed thickness value a, a is taken
4mm, obtains circular section；Or a kind of aerofoil profile is chosen in airfoil database, the aerofoil profile of selection is NACA0012, obtains aerofoil profile and cuts
The thickness distribution in face, the thickness distribution combination Novel wire of aerofoil section obtains aerofoil section, by the circular section or the wing of gained
Type section is recorded as i-th of section.
Step 5: i increases 1, if i≤8, repeat step three and four, section obtained by step 3 is circular arc in repetitive process
Tee section is aerofoil section.Otherwise, into next step.
Step 6: eight sections of gained are be arranged in parallel per two neighboring section distance s, and be put into two it is coaxial and half
Footpath difference is between the 8s face of cylinder.The geometric center in eight sections is at one on the straight line in eight sections, and this is straight
Line is vertically intersected on the axis of two cylindrical surface.Eight sections are arranged successively according to chord length size, and chord length most long section is located at
Most inner side.Chord length most long section and the less face of cylinder of diameter is tangent.First line segment 1 in eight sections is parallel to each other, and with
The axis of two cylindrical surface is vertical.First line segment 1 in eight sections is respectively positioned on the same side.The contour line in eight sections is existed
" setting-out curved surface " operation is carried out in solidworks, generation blade blank is seamlessly transitted.By blade blank in solidworks
Carry out " surface extending " operation so that the outer end of blade blank, which is passed completely through, is relatively large in diameter the face of cylinder, blade blank it is inner complete
Entirely through diameter compared with small cylindrical surface.Blade blank between two cylindrical surface is optimization rear blade.Using two cylindrical surface axis as battle array
Row center, 60 ° are array angle, and Circle-Array lists six pieces of blades.Wheel hub, the impeller mould after being optimized are drawn for six pieces of blades
Type.First circular arc of blade profile molded line is close to the import of impeller pattern, and the second circular arc is close to the outlet of impeller pattern.
Step 7: taken on one piece of blade of step 6 institute established model vertical impeller radial direction eight sections and this eight cut
The corresponding molded line in face, two neighboring section spacing is s, and the section and wheelboss side wall of most inner side are tangent.Eight are measured respectively to cut
The chord length b in facei, i=1,2,3 ..., 8, and outlet geometry angle beta2A(i), i=1,2,3 ..., 8.In six established models of removal step
All chamferings and fillet, obtain new simplified model.With mesh generation software to new simplified model mesh generation, line number of going forward side by side value
Simulation calculate, obtain step 6 institute established model total head and eight section imports at three velocity components；According to three speed
Component draws speed triangle, so as to obtain the inlet air flow angle beta in eight sections1(i), i=1,2,3 ..., 8.By step 6 institute
The total head value of established model is assigned to Z2.
Step 8: if Z2 subtracts Z1 income values more than 5Pa, Z2 value is assigned to Z1, and repeat Step 2: three,
4th, five, six and seven.Otherwise, optimization terminates.
Claims (6)
1. the optimization method of Low-pressure axial fan impeller blade, it is characterised in that：Step 1: setting up impeller mould to be optimized
Type；The wheelboss side wall of impeller and the spacing of blade outer end are n × s；The n of vertical impeller radial direction is taken on one piece of blade of the model
Individual section and the corresponding molded line in n section, two neighboring section spacing are s, and the section and wheelboss side wall of most inner side are tangent,
3≤n≤20；The chord length b in n section is measured respectivelyi, i=1,2,3 ..., n, and outlet geometry angle beta2A(i), i=1,2,3 ...,
n；All chamferings and fillet, are simplified model in removal model；Grid is carried out to simplified model with mesh generation software to draw
Point and numerical simulation calculation, obtain impeller pattern to be optimized total head and n section import at three velocity components；According to three
Individual velocity component draws speed triangle, so as to obtain the inlet air flow angle beta in n section1(i), i=1,2,3 ..., n；By the mould
The total head value of type is assigned to Z1；
Step 2: being assigned to i by 1；
Step 3: skeletonizing, sketch includes the first line segment, second line segment, the 3rd line segment, the 4th line segment, the 5th line segment, the 6th
Line segment, the first circular arc, the second circular arc, the 7th line segment and the 8th line segment；First line segment and second line segment parallel lines, the 3rd line each other
The two ends end points of section is respectively on the first line segment and second line segment, and the length of the 3rd line segment is bi；4th line segment and the 6th line segment
It is separately positioned on the both sides of the 5th line segment, the two ends end points difference of the 4th line segment, one end end points of the 6th line segment and the 3rd line segment
Overlap；The other end end points of 4th line segment is on the 5th line segment；The other end end points of 6th line segment and one end end of the 5th line segment
Point is overlapped, and the 6th line segment and the 5th line segment are isometric；5th line segment and the 3rd line segment intersection；The center of circle of first circular arc is the 4th line
The intersection point of the line segments of Duan Yu five, two-end-point is respectively the misaligned end points of the 4th line segment and the 5th line segment；The center of circle of second circular arc
For the 5th line segment and the intersection point of the 6th line segment, two-end-point is respectively the misaligned end points of the 5th line segment and the 6th line segment；First circle
Arc in the second circular arc clockwise；Tangent line of 7th line segment with the first circular arc on the 4th line segment end points is overlapped, and the 7th
The angle of line segment and the first line segment is β1(i), tangent line of the 8th line segment with the second circular arc on the 6th line segment end points overlap, and the 8th
Line segment and the angle of second line segment are β2A(i)；The angle of 7th line segment and the 8th line segment is θc, try to achieve θc=β2A(i)-β1(i)；The
The angle of four line segments and the 5th line segment is α1, take α1=0.6 θc；The angle of 6th line segment and the 5th line segment is α2, take α2=0.4
θc；The angle of 3rd line segment and the 7th line segment is α1, the angle of the 3rd line segment and the 8th line segment is α2；
Step 4: the first circular arc and the second circular arc composition Novel wire；To Novel wire superposition thickness value a, 1mm≤a≤6mm, obtain
Circular section；Or a kind of aerofoil profile is chosen in airfoil database, obtain the thickness distribution of aerofoil section, the thickness point of aerofoil section
Cloth combination Novel wire obtains aerofoil section；The circular section or aerofoil section of gained are recorded as i-th of section；
Step 5: i increases 1, if i≤n, repeat step three and four, section obtained by step 3 is circular arc and cut in repetitive process
Face is aerofoil section；Otherwise, into next step；
Step 6: n section of gained is be arranged in parallel per two neighboring section distance s, and it is put into two coaxial and semidiameters
For between the n × s face of cylinder；The geometric center in n section at one on the straight line in n section, and the straight line hang down
The straight axis for intersecting at two cylindrical surface；N section is arranged successively according to chord length size, and chord length most long section be located at it is most interior
Side；Chord length most long section and diameter is tangent compared with small cylindrical surface；First line segment in n section is parallel to each other, and and two cylindrical surface
Axis it is vertical；The First Line section in n section is located at the same side；Blade blank is obtained according to n section；Extended blade blank
Two ends so that the outer end of blade blank, which is passed completely through, is relatively large in diameter the face of cylinder, it is smaller that the inner of blade blank passes completely through diameter
The face of cylinder；Blade blank between two cylindrical surface is optimization rear blade；Using two cylindrical surface axis as array center, circumferentially
Structure the formation and list m pieces of blade, 4≤m≤10；Wheel hub, the impeller pattern after being optimized are drawn for m pieces of blade；
Step 7: taking n section and n section correspondence of vertical impeller radial direction on one piece of blade of step 6 institute established model
Molded line, adjacent sections spacing is s, and the section and wheelboss side wall of most inner side are tangent；The chord length b in n section is measured respectivelyi, i
=1,2,3 ..., n, and outlet geometry angle beta2A(i), i=1,2,3 ..., n；In six established models of removal step all chamferings and
Fillet, obtains new simplified model；With mesh generation software to new simplified model mesh generation, and numerical simulation calculation is carried out, obtained
Three velocity components at the total head of step 6 institute established model and n section import；Speed is drawn according to three velocity components
Triangle, so as to obtain the inlet air flow angle beta in n section1(i), i=1,2,3 ..., n；The total head value of the model is assigned to
Z2；
Step 8: if Z2 subtracts Z1 income values more than k, 3Pa≤k≤8Pa, Z2 value is assigned to Z1, and repeat Step 2:
3rd, four, five, six and seven；Otherwise, optimization terminates.
2. the optimization method of Low-pressure axial fan impeller blade according to claim 1, it is characterised in that：Step one
Described in impeller to be optimized for the SDF-11.2 tunnel type axial flow fans of the positive blower fan Co., Ltd production in Shaoxing Shangyu nine leaf
Wheel.
3. the optimization method of Low-pressure axial fan impeller blade according to claim 1, it is characterised in that：Step 6
In obtain blade blank method it is as follows：The contour line in n section is carried out to " setting-out curved surface " operation in solidworks, put down
Slip over and cross generation blade blank.
4. the optimization method of Low-pressure axial fan impeller blade according to claim 1, it is characterised in that：Step 6
The method at middle extended blade blank two ends is as follows：Blade blank is carried out to " surface extending " operation in solidworks.
5. the optimization method of Low-pressure axial fan impeller blade according to claim 1, it is characterised in that：Step 3
The aerofoil profile of middle selection is NACA0012.
6. the optimization method of Low-pressure axial fan impeller blade according to claim 1, it is characterised in that：Step 8
Middle k value is 5Pa.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710262288.3A CN106949095B (en) | 2017-04-20 | 2017-04-20 | The optimization method of Low-pressure axial fan impeller blade |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710262288.3A CN106949095B (en) | 2017-04-20 | 2017-04-20 | The optimization method of Low-pressure axial fan impeller blade |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN106949095A true CN106949095A (en) | 2017-07-14 |
| CN106949095B CN106949095B (en) | 2018-12-07 |
Family
ID=59475931
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201710262288.3A Expired - Fee Related CN106949095B (en) | 2017-04-20 | 2017-04-20 | The optimization method of Low-pressure axial fan impeller blade |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN106949095B (en) |
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107013490A (en) * | 2017-04-20 | 2017-08-04 | 浙江理工大学 | A kind of optimization method of Low-pressure axial fan impeller blade |
| CN108507017A (en) * | 2018-03-15 | 2018-09-07 | 珠海格力电器股份有限公司 | Blade structure and air conditioner with it |
| CN109737098A (en) * | 2019-03-01 | 2019-05-10 | 上海诺地乐通用设备制造有限公司 | A kind of axial wheel with cleavable blade |
| CN110864485A (en) * | 2019-12-20 | 2020-03-06 | 海信容声(广东)冰箱有限公司 | Low-temperature storage device |
| CN117182288A (en) * | 2023-11-07 | 2023-12-08 | 中国航发沈阳黎明航空发动机有限责任公司 | Welding joint shape design method for linear friction welding of titanium alloy of blisk |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN1598325A (en) * | 2004-08-19 | 2005-03-23 | 保定多田冷却设备有限公司 | Low-noise strong blast volume axial-flow fan |
| WO2008042251A2 (en) * | 2006-09-29 | 2008-04-10 | Pax Streamline, Inc. | Axial flow fan |
| CN103541774A (en) * | 2013-11-14 | 2014-01-29 | 上海汽轮机厂有限公司 | Method for designing turbine blades |
| CN104376162A (en) * | 2014-11-12 | 2015-02-25 | 中国航空动力机械研究所 | Blade modeling method |
| CN106089801A (en) * | 2016-08-11 | 2016-11-09 | 中国航空工业集团公司沈阳发动机设计研究所 | A kind of compressor blade formative method |
-
2017
- 2017-04-20 CN CN201710262288.3A patent/CN106949095B/en not_active Expired - Fee Related
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN1598325A (en) * | 2004-08-19 | 2005-03-23 | 保定多田冷却设备有限公司 | Low-noise strong blast volume axial-flow fan |
| WO2008042251A2 (en) * | 2006-09-29 | 2008-04-10 | Pax Streamline, Inc. | Axial flow fan |
| CN103541774A (en) * | 2013-11-14 | 2014-01-29 | 上海汽轮机厂有限公司 | Method for designing turbine blades |
| CN104376162A (en) * | 2014-11-12 | 2015-02-25 | 中国航空动力机械研究所 | Blade modeling method |
| CN106089801A (en) * | 2016-08-11 | 2016-11-09 | 中国航空工业集团公司沈阳发动机设计研究所 | A kind of compressor blade formative method |
Cited By (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107013490A (en) * | 2017-04-20 | 2017-08-04 | 浙江理工大学 | A kind of optimization method of Low-pressure axial fan impeller blade |
| CN107013490B (en) * | 2017-04-20 | 2018-12-18 | 浙江理工大学 | A kind of optimization method of Low-pressure axial fan impeller blade |
| CN108507017A (en) * | 2018-03-15 | 2018-09-07 | 珠海格力电器股份有限公司 | Blade structure and air conditioner with it |
| CN109737098A (en) * | 2019-03-01 | 2019-05-10 | 上海诺地乐通用设备制造有限公司 | A kind of axial wheel with cleavable blade |
| CN109737098B (en) * | 2019-03-01 | 2023-09-19 | 英飞同仁风机股份有限公司 | Axial flow impeller with cuttable blades |
| CN110864485A (en) * | 2019-12-20 | 2020-03-06 | 海信容声(广东)冰箱有限公司 | Low-temperature storage device |
| CN117182288A (en) * | 2023-11-07 | 2023-12-08 | 中国航发沈阳黎明航空发动机有限责任公司 | Welding joint shape design method for linear friction welding of titanium alloy of blisk |
| CN117182288B (en) * | 2023-11-07 | 2024-01-05 | 中国航发沈阳黎明航空发动机有限责任公司 | Welding joint shape design method for linear friction welding of titanium alloy of blisk |
Also Published As
| Publication number | Publication date |
|---|---|
| CN106949095B (en) | 2018-12-07 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN106949095A (en) | The optimization method of Low-pressure axial fan impeller blade | |
| CN106446324B (en) | Design method of final-stage twisted blade of large industrial steam turbine | |
| CN109598081B (en) | Radial-flow turbine pneumatic optimization method based on data dimension reduction and multi-two-dimensional flow surface | |
| CN105781626B (en) | Three-dimensional orthogonal unsteady design method of large meridian expansion turbine | |
| CN107061329A (en) | A kind of axial flow blower | |
| CN105756975A (en) | Axial flow fan with blade front edges having groove structures and with blade root blowing effect | |
| CN107092763A (en) | The three-dimensional design method of turbomachinery impeller with Castability | |
| CN112974734A (en) | Manufacturing method of integrally formed swept combined blade | |
| CN107013490B (en) | A kind of optimization method of Low-pressure axial fan impeller blade | |
| CN106939902B (en) | Energy-saving straight-wall front and rear disk variable-curvature curve element ternary impeller and centrifugal fan adopting same | |
| CN103321957A (en) | Optimized design method for impeller blade of axial flow fan | |
| CN108980103B (en) | Design method of forward multi-wing centrifugal ventilator impeller with inlet winglet | |
| CN100370148C (en) | Blade type optimized designing method of turbine compression fluid machine | |
| CN101749052B (en) | Last-stage moving blade of air-cooling feed pump turbine | |
| CN202348525U (en) | Axial-flow rotary propeller type water turbine | |
| CN206738198U (en) | A kind of axial flow blower | |
| CN115758629A (en) | High-speed centrifugal fan special for sweeping robot and design method and device thereof | |
| CN205638999U (en) | Blade area wing section guide plate and stator have bionical tail edge's axial fan | |
| CN205639001U (en) | Axial fan that winglet and ye ding have air -blowing structure is worn to blade pressure | |
| CN109711047B (en) | Design method for aerodynamic performance of S2 flow surface of helium compressor | |
| CN102979764A (en) | Axial flow fan blade and fan | |
| CN107461361B (en) | A kind of design method of multistage pump first-stage double suction impeller | |
| CN100357610C (en) | Axial ventilating machine impellor | |
| CN204458540U (en) | The flow guide device of bidirectional reversible propeller fan | |
| CN116595725A (en) | Method for designing variable-annular-flow type blade of agricultural axial-flow fan |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant | ||
| EE01 | Entry into force of recordation of patent licensing contract | ||
| EE01 | Entry into force of recordation of patent licensing contract |
Application publication date: 20170714 Assignee: ZHEJIANG SCI-TECH UNIVERSITY SHANGYU INDUSTRIAL TECHNOLOGY RESEARCH INSTITUTE Co.,Ltd. Assignor: ZHEJIANG SCI-TECH University Contract record no.: X2020330000077 Denomination of invention: Optimization method for impeller blade of low pressure axial flow fan Granted publication date: 20181207 License type: Common License Record date: 20201022 |
|
| TR01 | Transfer of patent right |
Effective date of registration: 20220107 Address after: Room 503, building 3, No. 133, development avenue, Tongxiang Economic Development Zone, Tongxiang City, Jiaxing City, Zhejiang Province Patentee after: ZHEJIANG MAIZHI NETWORK TECHNOLOGY CO.,LTD. Address before: 310018 No. 2 street, Xiasha Higher Education Park, Hangzhou, Zhejiang, 928 Patentee before: ZHEJIANG SCI-TECH University |
|
| TR01 | Transfer of patent right | ||
| TR01 | Transfer of patent right |
Effective date of registration: 20230306 Address after: 314500 Room 635-708, Fengrun International Business Center, Zhenxing East Road, wutong Street, Tongxiang City, Jiaxing City, Zhejiang Province Patentee after: JIAXING LONGLIE ELECTRONIC COMMERCE Co.,Ltd. Address before: Room 503, building 3, No. 133, development avenue, Tongxiang Economic Development Zone, Tongxiang City, Jiaxing City, Zhejiang Province Patentee before: ZHEJIANG MAIZHI NETWORK TECHNOLOGY CO.,LTD. |
|
| TR01 | Transfer of patent right | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20181207 |
|
| CF01 | Termination of patent right due to non-payment of annual fee |