CN104912846A - Fan impeller, blade skeleton line fitting method thereof and fan - Google Patents
Fan impeller, blade skeleton line fitting method thereof and fan Download PDFInfo
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- CN104912846A CN104912846A CN201510405155.8A CN201510405155A CN104912846A CN 104912846 A CN104912846 A CN 104912846A CN 201510405155 A CN201510405155 A CN 201510405155A CN 104912846 A CN104912846 A CN 104912846A
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Abstract
The invention discloses a fan impeller, a blade skeleton line fitting method thereof and a fan, wherein the fan impeller comprises: a rear disc, blades arranged on the rear disc; the blade includes blade entry section and blade outlet section that links to each other, and blade entry section and blade outlet section distribute along the length direction of blade in proper order, and the blade entry section is close to the central axis of back dish, and the blade entry section is wing section structure, and the blade outlet section is the equal circulation flow pattern structure. According to the fan impeller disclosed by the invention, the blade outlet section is designed into the equal circulation flow type structure, so that the constant momentum moment at the blade outlet is ensured along the meridian plane of the fan impeller, the pressure gradient of airflow at the blade outlet section is effectively reduced, the airflow separation at the blade outlet is inhibited, and the influence on the aerodynamic performance and the noise level of a fan is reduced.
Description
Technical field
The present invention relates to draught fan impeller technical field, more particularly, relate to a kind of draught fan impeller and mean camberline approximating method, blower fan.
Background technique
At present, draught fan impeller mainly adopts prismatic blade and circular arc airfoil blade, so that die sinking processing.But, adopt the blower fan of above-mentioned blade, air-flow is easier causes local velocity to increase at blade exit section formation Shedding Vortex, produce low pressure area, blade exit place is made more easily to produce larger pressure gradient, the possibility causing exit flow to be separated is comparatively large, has larger impact to the aeroperformance of blower fan and noise level.
In sum, how suppressing blade exit place airflow breakaway, to reduce the impact of aeroperformance on blower fan and noise level, is current those skilled in the art's problem demanding prompt solution.
Summary of the invention
The object of this invention is to provide a kind of draught fan impeller, suppress blade exit place airflow breakaway, to reduce the impact of aeroperformance on blower fan and noise level.Another object of the present invention is to provide a kind of blower fan with above-mentioned draught fan impeller, and a kind of mean camberline approximating method of draught fan impeller.
To achieve these goals, the invention provides following technological scheme:
A kind of draught fan impeller, comprising:
Hub disk, is arranged at the blade on described hub disk;
Wherein, described blade comprises connected blade inlet section and blade exit section, described blade inlet section and described blade exit section distribute successively along the length direction of described blade, described blade inlet section is near the central axis of described hub disk, and described blade inlet section is airfoil structure, described blade exit section is constant circulation flow pattern structure.
Preferably, r>50%R
1, wherein, r is the distance of one end of being connected with described blade inlet section of described blade exit section apart from the central axis of described hub disk, R
1for described blade exit section away from one end of described blade inlet section apart from the distance of the central axis of described hub disk.
Preferably, described blade is straight blade.
Preferably, in the meridional projection figure of described draught fan impeller, the height of described projecting blade increases along with the reduction of a; Wherein, a is the distance of the central axis of hub disk described in described blade pitch.
Preferably, in the meridional projection figure of described draught fan impeller, the top projection of described blade is the first straightway.
Preferably, 3 ° of < θ
1<16 °, θ
1for the angle of the projection of the first straightway described in the meridional projection figure of described draught fan impeller and described hub disk.
Preferably, in the meridional projection figure of described draught fan impeller, the top projection of described blade is curved section, and the recessed projection to described hub disk of described curved section.
Preferably, between the leaf of described draught fan impeller, Flow area is definite value along the length direction of described blade.
Preferably, in the meridional projection figure of described draught fan impeller, described blade inlet section is the second straightway away from the end on projection of described blade exit section, and one end that described second straightway projects away from described hub disk from it tilts to the central axis of described hub disk to it near one end that described hub disk projects.
Preferably, 15 ° of < θ
2<35 °, wherein, θ
2for the angle of the central axis of described second straightway and described hub disk.
Preferably, described blade inlet section is NACA airfoil structure, single circular arc airfoil structure, biconvex aerofoil pro file structure or Bezier airfoil structure.
Preferably, above-mentioned draught fan impeller also comprises shroud, and in the meridional projection of described draught fan impeller, the projection medium line of described shroud and the top projection of described blade are equal space line.
Preferably, described shroud and described blade are integral type structure.
Preferably, described shroud is fixed on the spiral case of described draught fan impeller, and has gap between described shroud and described blade.
Preferably, the gap between described shroud and described blade is 1.5-6mm.
Draught fan impeller provided by the invention, blade exit section is designed to constant circulation flow pattern structure, then ensure that the blade exit place moment of momentum keeps constant along the meridian plane of draught fan impeller, thus effectively reduce the pressure gradient of air-flow in blade exit section, inhibit blade exit place airflow breakaway, reduce the impact of aeroperformance on blower fan and noise level.
Simultaneously, draught fan impeller provided by the invention, the blade inlet section of blade is designed to airfoil structure, the blade exit section of blade is designed to constant circulation flow pattern, then this blade has had both the feature of airfoil structure and constant circulation flow pattern structure, make this draught fan impeller under the prerequisite suppressing blade exit place airflow breakaway, improve the mechanical efficiency of blower fan.
Based on the above-mentioned draught fan impeller provided, present invention also offers a kind of mean camberline approximating method of draught fan impeller, the mean camberline approximating method of this draught fan impeller, comprises step:
Set the center of circle O of described draught fan impeller, set described blade one end away from the central axis of described hub disk apart from the distance R of the central axis of described hub disk
1and the distance R of described blade near one end of the central axis of described hub disk apart from the central axis of described hub disk
2;
With center of circle O for the center of circle, with R
1for radius draws circle, form circle O
1, with center of circle O for the center of circle, with R
2for radius draws circle, form circle O
2;
Set point A, and the distance r of some A and center of circle O;
Picture aerofoil profile bone line by an A, described aerofoil profile bone line and described round O
2meet at a C, aerofoil profile bone line AC is the bone line of described blade inlet section;
Determine the center of circle B of the bone line of described blade exit section, with center of circle B for the center of circle, with the distance AB of an A to some B for radius, picture arc by an A, described arc and circle O
1meet at a D, camber line AD is the bone line of described blade exit section, namely completes matching.
Preferably, determine that the concrete steps of center of circle B are: the tangent line L of bone line at an A making described blade inlet section
1, make tangent line L at an A
1vertical line L
2, the vertical line L of line segment AO is made at an O
3, described vertical line L
2with described vertical line L
3intersection point be described center of circle B.
Preferably, determine that the concrete steps of described center of circle B are:
Make the tangent line L of bone line at an A of described blade inlet section
1,
With center of circle O for the center of circle, be that radius draws circle with r, make round O
3,
Make round O
3at the tangent line L of an A
4, described tangent line L
1with described tangent line L
4between angle be β, determine described center of circle B according to r, ∠ OAB=β, ∠ AOB=90 °.
Preferably, r>50%R
1.
Based on the above-mentioned draught fan impeller provided, present invention also offers a kind of blower fan, this blower fan comprises: impeller, and wherein, described impeller is the draught fan impeller described in above-mentioned any one.
Accompanying drawing explanation
In order to be illustrated more clearly in the embodiment of the present invention or technological scheme of the prior art, be briefly described to the accompanying drawing used required in embodiment or description of the prior art below, apparently, accompanying drawing in the following describes is only embodiments of the invention, for those of ordinary skill in the art, under the prerequisite not paying creative work, other accompanying drawing can also be obtained according to the accompanying drawing provided.
The structural representation of the draught fan impeller that Fig. 1 provides for the embodiment of the present invention;
Fig. 2 is that the A-A of Fig. 1 is to sectional view;
The meridional projection figure of a kind of draught fan impeller that Fig. 3 provides for the embodiment of the present invention;
Fig. 4 is the different cross section velocity profile of draught fan impeller in Fig. 3;
The meridional projection figure of the another kind of draught fan impeller that Fig. 5 provides for the embodiment of the present invention;
The meridional projection figure of the another kind of draught fan impeller that Fig. 6 provides for the embodiment of the present invention;
The mean camberline matching schematic diagram of the draught fan impeller that Fig. 7 provides for the embodiment of the present invention.
In upper Fig. 1-7:
1 be blade, 11 be blade inlet section, 12 be blade exit section, 2 be hub disk, 3 for shroud.
Embodiment
Below in conjunction with the accompanying drawing in the embodiment of the present invention, be clearly and completely described the technological scheme in the embodiment of the present invention, obviously, described embodiment is only the present invention's part embodiment, instead of whole embodiments.Based on the embodiment in the present invention, those of ordinary skill in the art, not making the every other embodiment obtained under creative work prerequisite, belong to the scope of protection of the invention.
Please refer to accompanying drawing 1-6, the draught fan impeller that the embodiment of the present invention provides, comprising: hub disk 2, be arranged at the blade 1 on hub disk 2.Wherein, blade 1 comprises connected blade inlet section 11 and blade exit section 12, blade inlet section 11 and blade exit section 12 distribute successively along the length direction of blade 1, blade inlet section 11 is near the central axis of hub disk 2, and blade inlet section 11 is airfoil structure, blade exit section 12 is constant circulation flow pattern structure.
It should be noted that the structure that airfoil structure and constant circulation flow pattern structure are well known to the skilled person does not explain airfoil structure and constant circulation flow pattern structure herein.
The draught fan impeller that the embodiment of the present invention provides, blade exit section 12 is designed to constant circulation flow pattern structure, then ensure that the outlet port moment of momentum of blade 1 keeps constant along the meridian plane of draught fan impeller, thus effectively reduce the pressure gradient of air-flow in blade exit section 12, inhibit blade 1 outlet port airflow breakaway, reduce the impact of aeroperformance on blower fan and noise level.
Simultaneously, the draught fan impeller that the embodiment of the present invention provides, the blade inlet section 11 of blade 1 is designed to airfoil structure, the blade exit section 12 of blade 1 is designed to constant circulation flow pattern, then this blade 1 has had both the feature of airfoil structure and constant circulation flow pattern structure, make this draught fan impeller under the prerequisite of outlet port airflow breakaway suppressing blade 1, improve the mechanical efficiency of blower fan.
Be understandable that, in above-mentioned draught fan impeller, blade exit section 12 and blade inlet section 11 are integral type structure.
In above-mentioned draught fan impeller, one end that blade exit section 12 is connected with blade inlet section 11 is r apart from the distance of the central axis of hub disk 2, and blade exit section 12 is R away from the distance of the central axis of one end distance hub disk 2 of blade inlet section 11
1.For the ease of the matching of the blade 1 bone line of draught fan impeller, prioritizing selection r>50%R
1.
In order to the suction surface and pressure side both sides that ensure blade 1 all can suppress to export separated flow, prioritizing selection blade 1 is straight blade.Be understandable that, the thickness of any two positions of straight blade is equal.
Be understandable that, above-mentioned draught fan impeller Leaf 1 is in elongated shape.Above-mentioned draught fan impeller, in its meridional projection, the height that blade 1 projects can be definite value, also can change with the distance of blade 1 apart from the central axis of hub disk 2.Preferably, in the meridional projection figure of draught fan impeller, the height that blade 1 projects increases along with the reduction of a; Wherein, a is the distance of blade 1 apart from the central axis of hub disk 2.Like this, increase effectively the entrance of draught fan impeller, thus increase the flow of blower fan.Be understandable that, a is the value of a change, refers to the distance of the arbitrary position of blade 1 apart from the central axis of hub disk 2.
Meet above-mentioned requirements, in the meridional projection figure of draught fan impeller, the top projection of blade 1 can straight line, also can be curve.
Preferably, in the meridional projection figure of draught fan impeller, the top projection of blade 1 is the first straightway.Be understandable that, this first straightway is skew lines section.In order to increase the entrance of draught fan impeller to greatest extent, prioritizing selection 3 ° of < θ
1<16 °, wherein, θ
1for the angle of the projection of the first straightway and hub disk 2 in the meridional projection figure of draught fan impeller, as shown in Figure 3 and Figure 4.
Preferably, in the meridional projection figure of draught fan impeller, the top projection of blade 1 is curved section, and the recessed projection to hub disk 2 of this curved section, as shown in Figure 4.Concrete, this curved section can be hyperbola, camber line or other forms of curve.
Further, between the leaf of draught fan impeller, Flow area is definite value along the length direction of blade 1.Like this, effectively improve blower fan go out to flow uniformity, further increase fan performance.It should be noted that, realizing Flow area between leaf along the length direction of blade 1 is definite value, is technology well-known to those skilled in the art, concrete, keeps constant by the angle that adjusts blade 1 to realize Flow area between leaf along the length direction of blade 1.
In order to reduce blade 1 ingress along velocity gradient between blade 1 short transverse each point, in the meridional projection figure of prioritizing selection draught fan impeller, blade inlet section 11 is the second straightway away from the end on projection of blade exit section 12, one end that second straightway projects away from hub disk 2 from it tilts to its one end near hub disk 2 projection to the central axis of hub disk 2, as seen in figures 3-6.Further, θ
2<85 °, wherein, θ
2it is the angle of the central axis of the second straightway and hub disk 2.In actual application, θ can be set as required
2occurrence.Preferably, 15 ° of < θ
2<35 °.
In above-mentioned draught fan impeller, blade 1, on the advantage basis of following constant circulation flow pattern structure, by reducing blade 1 ingress air velocity gradient, improve blower fan and going out to flow uniformity, reaches the effect that fan performance promotes.
In above-mentioned draught fan impeller, blade inlet section 11 is airfoil structure, and wherein, airfoil structure exists multiple, can select comparatively to commonly use, also can select according to actual needs.Preferably, blade inlet section 11 is NACA airfoil structure, single circular arc airfoil structure, biconvex aerofoil pro file structure or Bezier airfoil structure.It should be noted that, NACA airfoil structure is a series of aerofoil profiles that National Advisory Committee for Aeronautics (NACA) is developed.Bezier airfoil structure refers to, along the central axis cut-off blade 1 of hub disk 2, cross section upper limb and the lower edge of the blade 1 of acquisition are Bezier.Herein, cross section upper limb refers to the edge of this cross section away from hub disk 2, and cross section lower edge refers to the edge of this cross section near hub disk 2.Certainly, also the optional sheet entrance 11 that gets rid of leaves is for other airfoil structures, is not limited to above-mentioned several.
Preferably, above-mentioned draught fan impeller also comprises shroud 3, in order to ensure fan performance, requires in the meridional projection of draught fan impeller, and the projection medium line of shroud 3 and the top projection of blade 1 are equal space line, as shown in Figure 6.It should be noted that, the projection medium line of shroud 3 refers to the line of shroud 3 in the meridional projection figure of draught fan impeller between upper sideline and lower sideline, middle molded line and upper sideline and middle molded line and lower sideline are equal space line, and middle molded line is equal with the distance of lower sideline with molded line in the Distance geometry of upper sideline.Upper sideline and shroud 3 in the meridional projection figure of draught fan impeller away from hub disk 2 project edge line, lower sideline and shroud 3 in the meridional projection figure of draught fan impeller near hub disk 2 project edge line.
Be understandable that, equal space line refers to, in two lines, any two points on a bar line is equal to the distance of another line.
In above-mentioned draught fan impeller, shroud 3 fixedly there is various ways, conveniently manufacture, prioritizing selection shroud 3 and blade 1 are integral type structure.
Certainly, shroud 3 also can be selected to be fixed on the spiral case of draught fan impeller, in order to avoid the play that becomes a mandarin, require, between shroud 3 and blade 1, there is gap.Further, the gap between shroud 3 and blade 1 is 1.5-6mm.Certainly, this gap also can be selected according to actual needs for other values, be not limited to above-mentioned numerical value.
Based on the draught fan impeller that above-described embodiment provides, the embodiment of the present invention additionally provides a kind of mean camberline approximating method of draught fan impeller, and as shown in Figure 7, the mean camberline approximating method of this draught fan impeller specifically comprises step:
S01: the center of circle O of setting draught fan impeller, setting blade 1 is away from the distance R of the central axis of one end distance hub disk 2 of the central axis of hub disk 2
1and blade 1 is near the distance R of the central axis of one end of the central axis of hub disk 2 distance hub disk 2
2;
In actual application, set the center of circle O, R according to actual needs
1, R
2, the embodiment of the present invention does not limit this.
S02: with center of circle O for the center of circle, with R
1for radius draws circle, form circle O
1, with center of circle O for the center of circle, with R
2for radius draws circle, form circle O
2;
S03: set point A, and the distance r of some A and center of circle O:
In actual application, the position of set point A and the size of r according to actual needs, the embodiment of the present invention does not limit this.For the ease of matching, prioritizing selection r>50%R
1.
S04: picture aerofoil profile bone line by an A, aerofoil profile bone line and described round O
2meet at a C, aerofoil profile bone line AC is the bone line of blade inlet section 11;
It should be noted that, picture aerofoil profile bone line by an A, this aerofoil profile bone line designs according to actual needs, and the embodiment of the present invention does not limit this.
S05: the center of circle B determining the bone line of blade exit section 12, with center of circle B for the center of circle, with the distance AB of an A to some B for radius, picture arc by A, this arc and circle O
1meet at a D, camber line AD is the bone line of blade exit section 12, namely completes matching:
There is multiple method in the determination of center of circle B, preferably, makes the tangent line L of bone line at an A of blade inlet section 11
1, make tangent line L at an A
1vertical line L
2, the vertical line L of line segment AO is made at an O
3, vertical line L
2with vertical line L
3intersection point be center of circle B, as shown in Figure 6.
Certainly, also can adopt additive method, such as, make the tangent line L of bone line at an A of blade inlet section 11
1; With center of circle O for the center of circle, be that radius draws circle with r, make round O
3; Make round O
3at the tangent line L of an A
4, tangent line L
1with tangent line L
4between angle be β, determine center of circle B according to r, ∠ OAB=β, ∠ AOB=90 °.
In actual application, additive method also can be adopted to obtain center of circle B, be not limited to above-mentioned two kinds of methods.
The mean camberline approximating method of the draught fan impeller that above-described embodiment provides, achieves the matching of blade.Be understandable that, step 04 and step 05 can change order.Action in other steps also can change order under the prerequisite meeting movement content, is not limited to a kind of order that above-described embodiment describes.
It should be noted that, the bone line of blade inlet section 11 and the bone linear light slip of blade exit section 12.
Be understandable that, after obtaining the bone line of matching blade 1, be distributed in the bone line both sides of blade 1 with vane thickness, form blade 1.
Based on the draught fan impeller that above-described embodiment provides, the embodiment of the present invention additionally provides a kind of blower fan, and this blower fan comprises: impeller, and wherein, this impeller is the draught fan impeller described in above-described embodiment.
The draught fan impeller provided due to above-described embodiment has above-mentioned technique effect, and the blower fan that the embodiment of the present invention provides has above-mentioned draught fan impeller, then the blower fan that the embodiment of the present invention provides also has corresponding technique effect, repeats no more herein.
To the above-mentioned explanation of the disclosed embodiments, those skilled in the art are realized or uses the present invention.To be apparent for a person skilled in the art to the multiple amendment of these embodiments, General Principle as defined herein can without departing from the spirit or scope of the present invention, realize in other embodiments.Therefore, the present invention can not be restricted to these embodiments shown in this article, but will meet the widest scope consistent with principle disclosed herein and features of novelty.
Claims (20)
1. a draught fan impeller, is characterized in that, comprising:
Hub disk (2), is arranged at the blade (1) on described hub disk (2);
Wherein, described blade (1) comprises connected blade inlet section (11) and blade exit section (12), described blade inlet section (11) and described blade exit section (12) distribute successively along the length direction of described blade (1), described blade inlet section (11) is near the central axis of described hub disk (2), and described blade inlet section (11) is airfoil structure, described blade exit section (12) is constant circulation flow pattern structure.
2. draught fan impeller according to claim 1, is characterized in that, r>50%R
1, wherein, r is the distance of one end of being connected with described blade inlet section (11) of described blade exit section (12) apart from the central axis of described hub disk (2), R
1for described blade exit section (12) away from one end of described blade inlet section (11) apart from the distance of the central axis of described hub disk (2).
3. draught fan impeller according to claim 1, is characterized in that, described blade (1) is straight blade.
4. draught fan impeller according to claim 1, is characterized in that, in the meridional projection figure of described draught fan impeller, the height that described blade (1) projects increases along with the reduction of a; Wherein, a is the distance of described blade (1) apart from the central axis of described hub disk (2).
5. draught fan impeller according to claim 4, is characterized in that, in the meridional projection figure of described draught fan impeller, the top projection of described blade (1) is the first straightway.
6. draught fan impeller according to claim 5, is characterized in that, 3 ° of < θ
1<16 °, θ
1for the angle of the projection of the first straightway described in the meridional projection figure of described draught fan impeller and described hub disk (2).
7. draught fan impeller according to claim 4, is characterized in that, in the meridional projection figure of described draught fan impeller, the top projection of described blade (1) is curved section, and the recessed projection to described hub disk (2) of described curved section.
8. draught fan impeller according to claim 4, is characterized in that, between the leaf of described draught fan impeller, Flow area is definite value along the length direction of described blade (1).
9. draught fan impeller according to claim 1, it is characterized in that, in the meridional projection figure of described draught fan impeller, described blade inlet section (11) is the second straightway away from the end on projection of described blade exit section (12), and one end that described second straightway projects away from described hub disk (2) from it tilts to the central axis of described hub disk (2) to it near one end that described hub disk (2) projects.
10. draught fan impeller according to claim 9, is characterized in that, 15 ° of < θ
2<35 °, wherein, θ
2for the angle of the central axis of described second straightway and described hub disk (2).
11. draught fan impellers according to claim 1, is characterized in that, described blade inlet section (11) is NACA airfoil structure, single circular arc airfoil structure, biconvex aerofoil pro file structure or Bezier airfoil structure.
12. according to the draught fan impeller in claim 1-11 described in any one, it is characterized in that, also comprise shroud (3), in the meridional projection of described draught fan impeller, the projection medium line of described shroud (3) and the top projection of described blade (1) are equal space line.
13. draught fan impellers according to claim 12, is characterized in that, described shroud (3) and described blade (1) are integral type structure.
14. draught fan impellers according to claim 12, is characterized in that, described shroud (3) is fixed on the spiral case of described draught fan impeller, and have gap between described shroud (3) and described blade (1).
15. draught fan impellers according to claim 14, is characterized in that, the gap between described shroud (3) and described blade (1) is 1.5-6mm.
16. 1 kinds, as the mean camberline approximating method of the draught fan impeller in claim 1-15 as described in any one, is characterized in that, comprise step:
Set the center of circle O of described draught fan impeller, set described blade (1) one end away from the central axis of described hub disk (2) apart from the distance R of the central axis of described hub disk (2)
1and the distance R of described blade (1) near one end of the central axis of described hub disk (2) apart from the central axis of described hub disk (2)
2;
With center of circle O for the center of circle, with R
1for radius draws circle, form circle O
1, with center of circle O for the center of circle, with R
2for radius draws circle, form circle O
2;
Set point A, and the distance r of some A and center of circle O;
Picture aerofoil profile bone line by an A, described aerofoil profile bone line and described round O
2meet at a C, aerofoil profile bone line AC is the bone line of described blade inlet section (11);
Determine the center of circle B of the bone line of described blade exit section (12), with center of circle B for the center of circle, with the distance AB of an A to some B for radius, picture arc by an A, described arc and circle O
1meet at a D, camber line AD is the bone line of described blade exit section (12), namely completes matching.
The mean camberline approximating method of 17. draught fan impellers according to claim 16, is characterized in that, determines that the concrete steps of center of circle B are: the tangent line L of bone line at an A making described blade inlet section (11)
1, make tangent line L at an A
1vertical line L
2, the vertical line L of line segment AO is made at an O
3, described vertical line L
2with described vertical line L
3intersection point be described center of circle B.
The mean camberline approximating method of 18. draught fan impellers according to claim 16, is characterized in that, determines that the concrete steps of described center of circle B are:
Make the tangent line L of bone line at an A of described blade inlet section (11)
1,
With center of circle O for the center of circle, be that radius draws circle with r, make round O
3,
Make round O
3at the tangent line L of an A
4, described tangent line L
1with described tangent line L
4between angle be β, determine described center of circle B according to r, ∠ OAB=β, ∠ AOB=90 °.
The mean camberline approximating method of 19. draught fan impellers according to claim 16, is characterized in that, r>50%R
1.
20. 1 kinds of blower fans, comprising: impeller, it is characterized in that, described impeller is for as the draught fan impeller in claim 1-15 as described in any one.
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| CN201510405155.8A CN104912846B (en) | 2015-07-10 | 2015-07-10 | Fan impeller, blade skeleton line fitting method thereof and fan |
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| CN201510405155.8A CN104912846B (en) | 2015-07-10 | 2015-07-10 | Fan impeller, blade skeleton line fitting method thereof and fan |
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| 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 |
| CN112160937A (en) * | 2020-09-21 | 2021-01-01 | 华中科技大学 | Cross-flow fan blade |
| CN113007135A (en) * | 2021-04-25 | 2021-06-22 | 华中科技大学 | Axial flow blade and axial flow fan |
| CN113431804A (en) * | 2021-07-23 | 2021-09-24 | 珠海格力电器股份有限公司 | Centrifugal fan blade, fan and air conditioner indoor unit |
| CN117932817A (en) * | 2024-01-25 | 2024-04-26 | 威海克莱特菲尔风机股份有限公司 | Blade design method, three-dimensional flow blade of centrifugal fan and its application |
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| 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 |
| CN112160937A (en) * | 2020-09-21 | 2021-01-01 | 华中科技大学 | Cross-flow fan blade |
| CN112160937B (en) * | 2020-09-21 | 2021-08-20 | 华中科技大学 | A cross-flow fan |
| CN113007135A (en) * | 2021-04-25 | 2021-06-22 | 华中科技大学 | Axial flow blade and axial flow fan |
| CN113431804A (en) * | 2021-07-23 | 2021-09-24 | 珠海格力电器股份有限公司 | Centrifugal fan blade, fan and air conditioner indoor unit |
| CN117932817A (en) * | 2024-01-25 | 2024-04-26 | 威海克莱特菲尔风机股份有限公司 | Blade design method, three-dimensional flow blade of centrifugal fan and its application |
| CN117932817B (en) * | 2024-01-25 | 2024-11-22 | 威海克莱特菲尔风机股份有限公司 | Blade design method, three-dimensional flow blade of centrifugal fan and its application |
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