CN116756864A - Design method of fan, fan and cleaning device applying fan - Google Patents

Design method of fan, fan and cleaning device applying fan Download PDF

Info

Publication number
CN116756864A
CN116756864A CN202310574606.5A CN202310574606A CN116756864A CN 116756864 A CN116756864 A CN 116756864A CN 202310574606 A CN202310574606 A CN 202310574606A CN 116756864 A CN116756864 A CN 116756864A
Authority
CN
China
Prior art keywords
point
blade
impeller
edge profile
leading edge
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Pending
Application number
CN202310574606.5A
Other languages
Chinese (zh)
Inventor
杨伟刚
李斌
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Ningbo Fotile Kitchen Ware Co Ltd
Original Assignee
Ningbo Fotile Kitchen Ware Co Ltd
Priority date (The priority date 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 date listed.)
Filing date
Publication date
Application filed by Ningbo Fotile Kitchen Ware Co Ltd filed Critical Ningbo Fotile Kitchen Ware Co Ltd
Priority to CN202310574606.5A priority Critical patent/CN116756864A/en
Publication of CN116756864A publication Critical patent/CN116756864A/en
Pending legal-status Critical Current

Links

Classifications

    • 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
    • G—PHYSICS
    • G06—COMPUTING; CALCULATING OR COUNTING
    • G06F—ELECTRIC DIGITAL DATA PROCESSING
    • G06F17/00—Digital computing or data processing equipment or methods, specially adapted for specific functions
    • G06F17/10—Complex mathematical operations
    • G—PHYSICS
    • G06—COMPUTING; CALCULATING OR COUNTING
    • G06F—ELECTRIC DIGITAL DATA PROCESSING
    • G06F30/00—Computer-aided design [CAD]
    • G06F30/20—Design optimisation, verification or simulation
    • G—PHYSICS
    • G06—COMPUTING; CALCULATING OR COUNTING
    • G06F—ELECTRIC DIGITAL DATA PROCESSING
    • G06F2119/00—Details relating to the type or aim of the analysis or the optimisation
    • G06F2119/18—Manufacturability analysis or optimisation for manufacturability
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02E—REDUCTION OF GREENHOUSE GAS [GHG] EMISSIONS, RELATED TO ENERGY GENERATION, TRANSMISSION OR DISTRIBUTION
    • Y02E10/00—Energy generation through renewable energy sources
    • Y02E10/70—Wind energy
    • Y02E10/72—Wind turbines with rotation axis in wind direction

Landscapes

  • Engineering & Computer Science (AREA)
  • Physics & Mathematics (AREA)
  • Theoretical Computer Science (AREA)
  • General Physics & Mathematics (AREA)
  • Geometry (AREA)
  • General Engineering & Computer Science (AREA)
  • Computer Hardware Design (AREA)
  • Pure & Applied Mathematics (AREA)
  • Mathematical Optimization (AREA)
  • Evolutionary Computation (AREA)
  • Mathematical Analysis (AREA)
  • Computational Mathematics (AREA)
  • Data Mining & Analysis (AREA)
  • Mathematical Physics (AREA)
  • Algebra (AREA)
  • Databases & Information Systems (AREA)
  • Software Systems (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)

Abstract

The invention discloses a design method of a fan, the fan and a cleaning device applying the fan, wherein the leading edge molded line or the trailing edge molded line of a blade of the fan is obtained through the following steps: 1) Determining the front point position of the blade front edge molded line from the rear point of the blade front edge molded line (tail edge molded line); 2) Determining the intermediate point position of the leading edge profile (trailing edge profile) of the blade in a similar way; 3) Fitting a leading edge molded line (a trailing edge molded line) of the blade by adopting a spline curve according to the front point, the middle point and the rear point to obtain a first scheme of the leading edge molded line (the trailing edge molded line) of the blade; 4) Based on the geometric parameters of the first scheme of the leading edge molded line (the trailing edge molded line) of the blade, an orthogonal test is adopted, the ordinate is taken as an optimization variable, the efficiency and the noise are taken as optimization targets, an optimizing relation is established, the iterative optimization of the leading edge molded line (the trailing edge molded line) of the blade is completed, and the second scheme of the leading edge molded line (the trailing edge molded line) of the blade is obtained, so that the design is completed.

Description

Design method of fan, fan and cleaning device applying fan
Technical Field
The invention relates to a power device, in particular to a design method of a fan, the fan obtained by the method and a cleaning device using the fan.
Background
Cleaning devices, such as floor washers, floor sweeping robots, etc., are becoming cleaning tools for people's daily lives. The working principle of the floor washing machine is as follows: the inlet creates a large vacuum (static pressure greater than 4.5 kpa) to draw in the mixture of water and waste and to separate the waste by impact in the waste tank, so the medium needs to overcome a large flow resistance. The fan needs to have a large vacuum degree in a small design size space, the air quantity is larger than 0.6m3/min, and the efficiency is larger than 50% so as to ensure high endurance. This can present significant challenges and difficulties in the design of fans.
The technical scheme of the fan of the common cleaning device is as follows: 1. the technical scheme is gradually eliminated in the floor cleaning machine by adopting a backward centrifugal impeller (movable impeller) combined with a vaneless diffuser and being commonly used for floor cleaning robots, and is characterized by low inlet vacuum degree and efficiency, high noise and poor sound quality; 2. the advantages of low impeller cost, high efficiency and low noise are increasingly applied in industry due to the small size of the technical proposal of combining the backward centrifugal impeller (movable impeller) with the guide vane type.
With the development of technology, the requirements of the cleaning device on noise are higher and higher, and the fan is used as a main power system and is a main source for generating noise. The working rotation speed of the fan is 65000-75000 rpm, and the sound pressure level of the noise is 70-85 dB. Aerodynamic noise is a major source thereof, and a rotor blade serves as a core component of the fan, and mainly affects air performance (efficiency) and noise of the fan.
Referring to fig. 8, there is shown a meridian plane of a moving blade wheel of a conventional fan, which includes a front plate 21', a rear plate 22', and blades 23' disposed between the front plate 21' and the rear plate 22', and an end point of a leading edge line of the blades 23' near the front plate 21' is denoted as a front point m 5 ' the end point of the leading edge profile of the blade 23' near the rear disc 22' is denoted as the rear point m 1 ' speed of air flow over axial face of impeller C m The distribution law along the front edge of the blade 23' is large near the front disc (at the front point m 5 ' at C 5m ') near the rear discSmall (at the back point m 1 At C 1m ') wherein D 2 Is the outer diameter of the movable impeller, D 0 For the inner diameter of the vane 23, B is the vane 23 'leading edge (inlet) width, B is the vane 23' trailing edge (outlet) width, where the widths are all the axial dimensions of the impeller.
Referring again to FIG. 9, a theoretical leading edge velocity triangle for the vane 23' is shown, with equal axial velocity, C 1m Point a is shown as a point on the leading edge line of blade 23, u 1 For the peripheral speed at point a, ω 1 For the relative speed at point a, the inlet angles of the blades 23 are all equal and satisfy the following formula:
can be obtained according to the above formulaWherein Q is s The air quantity (fan design air quantity) corresponding to the working condition of the highest efficiency point of the movable impeller is obtained, and n is the rotating speed (fan design rotating speed) corresponding to the working condition of the highest efficiency point of the movable impeller.
With respect to the inner diameter D of the blade 23 0 See the following formula:
wherein K is o Is a coefficient, which takes the value and D o In relation, ψ is the flow coefficient, φ t Is the pressure coefficient. This formula can be seen in "handbook of blower" (handbook of blower "is books published by mechanical industry publishers 1 d 2 months in 2011, the authors are Jikui Chang, wang Hongjiang, ganjing) page 154.
From the above, it can be seen that, since the axial velocities of the actual airflows are not equal, referring again to FIG. 10, the front point m 5 The actual inlet flow angle at' beta 5 And beta is 5 >β 1 The actual air flow is at the front point m 5 An angle of attack Δi=β is generated at 5 -β 1 Resulting in impact losses and the same problems with the outlet flow angle, which results in reduced efficiency and increased noise.
Disclosure of Invention
The first technical problem to be solved by the invention is to provide a design method of a fan, which can reduce flow loss, improve efficiency and reduce noise, aiming at the defects existing in the prior art.
The second technical problem to be solved by the invention is to provide a fan, which is obtained by the design method of the fan.
The third technical problem to be solved by the invention is to provide a cleaning device with the fan.
The first technical scheme adopted by the invention for solving the first technical problem is as follows: the design method of the fan comprises a movable impeller, wherein the movable impeller comprises a front disc, a rear disc and blades arranged between the front disc and the rear disc, and the blades are provided with a front edge and a tail edge; the method is characterized in that: the leading edge profile of the blade is obtained through the following steps:
1) Determining a first forward point position of a blade leading edge profile:
establishing a coordinate system XOY, wherein the X axis is the axis of the movable impeller, the Y axis is the radial direction of the movable impeller, the end point of the front edge molded line of the blade, which is close to the front disc, is marked as a first front point, the end point of the front edge molded line of the blade, which is close to the rear disc, is marked as a first rear point, and the coordinates of the first rear point and the first front point are as follows: m is m 1 (0，h 1 )，m 5 (-B，h 5 )，h 1 The first rear point is the vertical distance to the X-axis,h 5 the vertical distance from the first rear point to the X axis is B is the width of the inlet of the blade, D 0 Is the inner diameter of the blade；
Wherein beta is 1 For the inlet flow angle at the first rear point, i=1 to 3 °, C 5m For the axial velocity of the air flow at the first front point C 5m The method comprises the steps of simulating or testing points, with the same abscissa as a first front point, on the front edge molded line of an equal-chord impeller in the same coordinate system, wherein the equal-chord impeller is an impeller with the front edge molded line and the tail edge molded line of the blade respectively parallel to an X axis, and the rear point of the front edge molded line of the equal-chord impeller coincides with the first rear point, so that the position of the first front point is obtained;
2) Determining the position of a middle point of the blade leading edge profile:
j is the number of the middle point, h j The number of the intermediate points is more than or equal to 2 and C is the vertical distance from the intermediate point to the X axis jm For the axial velocity of the air flow at the intermediate point C jm The method comprises the steps of simulating or testing points with the same abscissa as the middle point on the front edge line of the equal chord length impeller under the same coordinate system;
3) According to the first front point, the middle point and the first rear point, fitting a spline curve to obtain a blade front edge molded line, and obtaining a first scheme of the blade front edge molded line;
4) Geometric parameters of a first scheme based on a blade leading edge profile are tested in an orthogonal mode, and the geometric parameters are expressed as h j To optimize variable, efficiency and noise are used as optimization targets, and an optimizing relation is establishedWherein eta ori Is the highest efficiency of the equal chord impeller, SPL ori Is the sound power level, eta corresponding to the working condition of the maximum efficiency of the equal chord length impeller q Is the highest efficiency of the first scheme, SPL q Is the sound power level corresponding to the highest efficiency working condition of the first scheme, M is presetAnd (3) improving the upper limit value of efficiency, wherein N is the upper limit value of noise reduction, and finishing iterative optimization of the leading edge molded line of the blade to obtain a second scheme of the leading edge molded line of the blade, thereby finishing design.
By adopting the design scheme of the blade leading edge molded line with variable chord length, the airflow is led to the blade path at the blade inlet in a mode of being smaller than 90 degrees instead of flowing out in a 90-degree turning mode after entering the movable blade wheel along the axial direction, and the airflow is gradually changed along the axial direction.
Preferably, in step 1), the process comprises, in a first step,wherein Q is s For the design air quantity of the fan, n is the design rotating speed of the fan, and the range of the values of the parameters is as follows: q (Q) s ＝0.4～0.6m 3 /min，n＝64800～79000rpm，D 0 ＝17～23mm，B＝7～10mm，β 1 ＝18～31°。
To facilitate change of h j While iterating, in step 4), h is changed by changing i j And (5) iteration is realized.
The second technical scheme adopted by the invention for solving the first technical problem is as follows: the design method of the fan comprises a movable impeller, wherein the movable impeller comprises a front disc, a rear disc and blades arranged between the front disc and the rear disc, and the blades are provided with tail edges; the method is characterized in that: the tail edge molded line of the blade is obtained through the following steps:
1) Determining a second forward point position of a trailing edge profile of the blade:
establishing a coordinate system XOY, wherein the X axis is the axis of the movable impeller, the Y axis is the radial direction of the movable impeller, the end point of the tail edge molded line of the blade close to the front disc is marked as a second front point, the end point of the tail edge molded line of the blade close to the rear disc is marked as a second rear point, and the coordinates of the second rear point and the second front point are as follows: n is n 1 (0，j 1 )，n 5 (-b，j 5 )；j 1 Is the second oneThe vertical distance of the rear point to the X-axis, j 5 the vertical distance from the second rear point to the X axis is b is the width of the blade outlet, D 2 The outer diameter of the movable impeller is the outer diameter, and a is a constant;
β 2 for the outlet flow angle at the second rear point, i' =0 to 0.8 °, C 5mo For the axial velocity of the air flow at the second front point C 5mo The method comprises the steps of simulating or testing points, on a tail edge profile of an equal-chord impeller, of which the abscissa is the same as a second front point, under the same coordinate system, wherein the equal-chord impeller is an impeller with the front edge profile and the tail edge profile of a blade respectively parallel to an X axis, and the rear point of the tail edge profile of the equal-chord impeller coincides with the second rear point, so that the position of the second front point is obtained;
2) Determining the position of a middle point of a tail edge molded line of the blade:
k is the number of the middle point, j k The number of the intermediate points is more than or equal to 2 and C is the vertical distance from the intermediate point to the X axis kmo For the axial velocity of the air flow at the intermediate point C kmo The method comprises the steps of simulating or testing points with the same abscissa as the middle point on the tail edge profile of the equal-chord impeller under the same coordinate system;
3) Fitting a blade tail edge molded line by adopting a spline curve according to the second front point, the middle point and the second rear point to obtain a first scheme of the blade tail edge molded line;
4) Geometric parameters of a first scheme based on a blade trailing edge profile, using orthogonal tests, j k To optimize variable, efficiency and noise are used as optimization targets, and an optimizing relation is establishedη ori Is the highest efficiency of the equal chord length impeller scheme, SPL ori Is the sound power level, eta corresponding to the highest efficiency working condition of the equal chord length impeller scheme w Is the highest efficiency of the first scheme, SPL w The method is characterized in that the method is a sound power level corresponding to the working condition with the highest efficiency in the first scheme, M is a preset efficiency lifting upper limit value, N is a noise reduction upper limit value, iteration optimization of the tail edge molded line of the blade is completed, a second scheme of the tail edge molded line of the blade is obtained, and therefore design is completed.
By adopting the design scheme of the variable chord length blade trailing edge molded line, airflow does not flow out in a 90-degree turning mode after entering the movable impeller along the axial direction, but is led out of the movable impeller in a form of being smaller than 90 degrees and gradually changing along the axial direction at the blade outlet.
Preferably, in step 1), the process comprises, in a first step,in step 1), wherein Q s For the design air quantity of the fan, n is the design rotating speed of the fan, and the range of the values of the parameters is as follows: q (Q) s ＝0.4～0.6m 3 /min，n＝64800～79000rpm，D 2 ＝32～45mm，b＝4.5～5mm，a＝0.5～1.8mm，β 2 ＝26～30°。
To facilitate change of j k Iterating, in step 4), changing j by changing i k And (5) iteration is realized.
The third technical scheme adopted by the invention for solving the first technical problem is as follows: the design method of the fan comprises a movable impeller, wherein the movable impeller comprises a front disc, a rear disc and blades arranged between the front disc and the rear disc, and the blades are provided with a front edge and a tail edge; the method is characterized in that: the leading edge molded line and the trailing edge molded line of the blade are obtained through the following steps:
firstly, designing the leading edge profile of the blade:
establishing a coordinate system XOY, wherein the X axis is the axis of the movable impeller, the Y axis is the radial direction of the movable impeller, the end point of the front edge molded line of the blade close to the front disc is marked as a first front point, the end point of the front edge molded line of the blade (23) close to the rear disc is marked as a first rear point, and the coordinates of the first rear point and the first front point are as follows: m is m 1 (0，h 1 )，m 5 (-B，h 5 )，h 1 The first rear point is the vertical distance to the X-axis, h 5 the vertical distance from the first rear point to the X axis is B is the width of the inlet of the blade, D 0 Is the inner diameter of the blade;
wherein beta is 1 For the inlet flow angle at the first rear point, i=1 to 3 °, C 5m For the axial velocity of the air flow at the first front point C 5m The method comprises the steps of simulating or testing points, with the same abscissa as a first front point, on the front edge molded line of an equal-chord impeller in the same coordinate system, wherein the equal-chord impeller is an impeller with the front edge molded line and the tail edge molded line of the blade respectively parallel to an X axis, and the rear point of the front edge molded line of the equal-chord impeller coincides with the first rear point, so that the position of the first front point is obtained;
2) Determining the position of a middle point of the blade leading edge profile:
j is the number of the middle point, h j The number of the intermediate points is more than or equal to 2 and C is the vertical distance from the intermediate point to the X axis jm For the axial velocity of the air flow at the intermediate point C jm By simulating or testing the isochrons in the same coordinate systemThe front edge line of the long impeller is obtained by a point with the same abscissa as the middle point;
3) According to the first front point, the middle point and the first rear point, fitting a spline curve to obtain a blade front edge molded line, and obtaining a first scheme of the blade front edge molded line;
4) Geometric parameters of a first scheme based on a blade leading edge profile are tested in an orthogonal mode, and the geometric parameters are expressed as h j To optimize variable, efficiency and noise are used as optimization targets, and an optimizing relation is establishedWherein eta ori Is the highest efficiency of the equal chord impeller, SPL ori Is the sound power level, eta corresponding to the working condition of the maximum efficiency of the equal chord length impeller q Is the highest efficiency of the first scheme, SPL q The method comprises the steps that the sound power level corresponding to the highest efficiency working condition of a first scheme is obtained, M is a preset efficiency lifting upper limit value, N is a noise reduction upper limit value, iterative optimization of a blade leading edge molded line is completed, and a second scheme of the blade leading edge molded line is obtained;
(II) then, designing the trailing edge profile of the blade:
1) Determining a second leading point n of the trailing edge profile of the blade 5 Position:
the end point of the tail edge molded line of the blade, which is close to the front disc, is marked as a second front point, the end point of the tail edge molded line of the blade, which is close to the rear disc, is marked as a second rear point, and the coordinates of the second rear point and the second front point are as follows: n is n 1 (0，j 1 )，n 5 (-b，j 5 )；j 1 The vertical distance from the second rear point to the X-axis,j 5 the vertical distance from the second rear point to the X axis is b is the width of the blade outlet, D 2 The outer diameter of the movable impeller is the outer diameter, and a is a constant;
β 2 is the second back point (n 1 Outlet at the siteFlow angle, i' =0-0.8 °, C 5mo For the axial velocity of the air flow at the second front point C 5mo The position of the second front point is obtained by simulating or testing the point that the abscissa on the tail edge profile of the equal-chord impeller is the same as the second front point under the same coordinate system, and the rear point of the tail edge profile of the equal-chord impeller is overlapped with the second rear point;
2) Determining the position of a middle point of a tail edge molded line of the blade:
k is the number of the middle point, j k The number of the intermediate points is more than or equal to 2 and C is the vertical distance from the intermediate point to the X axis kmo For the axial velocity of the air flow at the intermediate point C kmo The method comprises the steps of simulating or testing points with the same abscissa as the middle point on the tail edge profile of the equal-chord impeller under the same coordinate system;
3) Fitting a blade tail edge molded line by adopting a spline curve according to the second front point, the middle point and the second rear point to obtain a first scheme of the blade tail edge molded line;
4) Geometric parameters of a first scheme based on a blade trailing edge profile, using orthogonal tests, j k To optimize variable, efficiency and noise are used as optimization targets, and an optimizing relation is establishedη q The highest efficiency after adopting the second scheme of the leading edge profile and the first scheme of the trailing edge profile of the blade is SPL q The method comprises the steps of adopting a sound power level corresponding to the highest efficiency working condition after a second scheme of a blade leading edge molded line and a first scheme of a trailing edge molded line to finish iterative optimization of the blade trailing edge molded line and obtain the second scheme of the blade trailing edge molded line, and finishing design through the second scheme of the blade leading edge molded line and the second scheme of the blade trailing edge molded line.
By adopting the design scheme of the leading edge molded line and the trailing edge molded line of the variable chord length blades, airflow does not flow out in a 90-degree turning mode after entering the movable impeller along the axial direction, but flows out of the movable impeller in a form smaller than 90 degrees and gradually changes along the axial direction, and the airflow is guided out of the movable impeller at the inlet of the blades.
Preferably, the method comprises the steps of,wherein Q is s For the design air quantity of the fan, n is the design rotating speed of the fan, and the range of the values of the parameters is as follows: q (Q) s ＝0.4～0.6m 3 /min，n＝64800～79000rpm，D 0 ＝17～23mm，B＝7～10mm，β 1 ＝18～31°，D 2 ＝32～45mm，b＝4.5～5mm，a＝0.5～1.8mm，β 2 ＝26～30°。
The invention solves the second technical problem by adopting the technical proposal that: a fan, characterized in that: obtained by the design method described above.
The technical scheme adopted by the invention for solving the third technical problem is as follows: a cleaning device, characterized in that: the fan as described above is applied.
Compared with the prior art, the invention has the advantages that: through adopting the design scheme of the leading edge molded line and the trailing edge molded line of the blade with variable chord length, airflow does not flow out in a 90-degree turning mode after entering the movable impeller along the axial direction, but flows out of the movable impeller in a form of being smaller than 90 degrees and gradually changing along the axial direction, and the airflow is guided out of the movable impeller at the inlet of the blade, so that the flow impact loss of the airflow can be reduced, the work efficiency of the movable impeller is improved, the noise is reduced, the movable impeller is applicable to fans with different rear guide vane forms, such as guide vanes, vaneless diffusers and the like, and the manufacturability of the impeller is good, and the processing cost is low.
Drawings
FIG. 1 is a schematic diagram of a blower in accordance with an embodiment of the present invention;
FIG. 2 is a schematic diagram of a moving impeller of a blower in accordance with an embodiment of the present invention;
FIG. 3 is a schematic view of a hidden front disk of a movable impeller of a blower in an embodiment of the invention;
FIG. 4 is a schematic view of a variable chord length impeller meridian plane of a movable impeller of a fan according to an embodiment of the present invention;
FIG. 5 is a schematic view of an actual velocity triangle of a leading edge inlet of a moving blade wheel of a fan in accordance with an embodiment of the present invention;
FIG. 6 is a schematic view of a blade leading edge profile fit of a moving impeller of a wind turbine in accordance with an embodiment of the present invention;
FIG. 7 is a schematic view of a blade trailing edge profile fit of a moving impeller of a wind turbine in accordance with an embodiment of the present invention;
FIG. 8 is a schematic view of an equal chord length impeller meridian of a prior art fan's moving impeller;
FIG. 9 is a schematic diagram of a theoretical velocity triangle of a leading edge inlet of a vane of a moving impeller of a prior art fan;
FIG. 10 is a schematic view of the actual velocity triangle of the vane leading edge inlet of the moving impeller of a prior art fan.
Detailed Description
Embodiments of the present invention are described in detail below, examples of which are illustrated in the accompanying drawings, wherein the same or similar reference numerals refer to the same or similar elements or elements having the same or similar functions.
In the description of the present invention, it should be understood that the terms "center", "longitudinal", "lateral", "length", "width", "thickness", "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", "clockwise", "counterclockwise", "axial", "radial", "circumferential", etc. indicate orientations or positional relationships based on the orientations or positional relationships shown in the drawings are merely for purposes of describing the present invention and simplifying the description, and do not indicate or imply that the device or element being referred to must have a specific orientation, be configured and operated in a specific orientation, and because the disclosed embodiments of the present invention may be arranged in different orientations, these directional terms are merely for illustration and should not be construed as limitations, such as "upper", "lower" are not necessarily limited to orientations opposite or coincident with the direction of gravity. Furthermore, features defining "first", "second" may include one or more such features, either explicitly or implicitly.
Referring to fig. 1 to 3, a fan is mainly used for cleaning devices, such as a floor washing machine, a floor sweeping robot and the like, and comprises a shell 1 and a movable impeller 2 arranged in the shell 1, wherein a rear guide vane can be arranged at the downstream of the movable impeller 2, and the form of the rear guide vane is not limited, such as a diffuser, a guide vane and the like.
The impeller 2 is a centrifugal impeller including a front plate 21, a rear plate 22, and blades 23 provided between the front plate 21 and the rear plate 22, the blades 23 having at least two, spaced apart along the circumferential direction of the fan, each blade 23 having a leading edge 231 (inlet) and a trailing edge 232 (outlet). The front plate 21 is formed with an air inlet 211, and the rear plate 22 may have a disk shape. The above structure is the prior art and will not be described here again.
In order to eliminate impact loss generated by a liquid flow angle, the invention adopts a design method of leading edge molded lines and trailing edge molded lines of the variable chord length of the blades 23, and the blades 23 obtained by the method play a role in flow control so as to achieve the purposes of improving the efficiency of the fan and reducing noise.
Specifically, referring to fig. 4 and 5, the design method of the impeller 2, the leading edge profile of the blade 23 is obtained by:
1) Defining a first forward point m of the leading edge profile of the blade 23 5 Position:
establishing a coordinate system XOY, wherein the X axis is the axis of the impeller 2, the forward direction of the X axis is the direction from the front disc 21 to the rear disc 22, the Y axis is the radial direction of the impeller 2, the forward direction of the X axis is the radial direction from the axis of the impeller 2, and the end point of the front edge molded line of the blade 23 close to the front disc 21 is recorded as a first front point m 5 The end point of the leading edge profile of the blade 23 near the rear disc 22 is denoted as the first rear point m 1 First rear point m 1 On the Y-axis, in the coordinate system XOY, a first rear point m 1 And a first front point m 5 The coordinates of (2) are: m is m 1 (0，h 1 )，m 5 (-B，h 5 )，h 1 For the first back point m 1 The vertical distance to the X-axis,h 5 for the first back point m 5 The vertical distance to the X axis, B is the width of the inlet of the blade 23, D 0 Is the inner diameter of the blade 23;
first front point m 5 At an inlet flow angle of beta * 5 And satisfy beta * 5 ＝β 1 +i，β 1 For the first back point m 1 At the inlet flow angle of the liquid,wherein Q is s For the design air quantity of the fan, n is the design rotating speed of the fan, D 2 For the outer diameter, D, of the impeller 2 0 For the inner diameter of the blade 23->The above parameters are known empirical values, such as parameters of an equal chord length impeller (i.e. an impeller in the prior art, as described in the background art, the longitudinal coordinates of the front point and the rear point of the leading edge profile and the trailing edge profile of the impeller are the same, i.e. the leading edge profile and the trailing edge profile are parallel to the X axis), and the values of the above parameters are generally in the range of: q (Q) s ＝0.4～0.6m 3 /min，n＝64800～79000rpm，D 0 From 17 to 23mm, b=7 to 10mm, whereby β can be determined 1 Typically 18 to 31 °; i is a constant, i=1 to 3 °;
first front point m 5 The position of (2) is obtained by the following formula:C 5m for the air flow at the first front point m 5 The axial surface speed at the position is obtained by simulation or test (i.e. simulation or actual measurement) of the speed field at the same abscissa (under the same coordinate system) on the front edge line of the equal chord length impeller>Thereby a first front point m of the leading edge profile of the blade 23 can be obtained 5 Is a position of (2); u (u) 1 For the first back point m 1 The peripheral velocity at which the magnetic field is generated,ω 1 for the first back point m 1 Relative velocity at u 5 For the first front point m 5 Peripheral speed at ω 5 For the first front point m 5 Relative velocity at;
2) Blade 23 leading edge profile intermediate point m j The position is determined in the same way as the first front point m 5 ，j is the number of intermediate points, the number of the intermediate points is equal to or greater than 2,h j For the middle point m j Vertical distance to X-axis, C jm For the middle point m j Testing the intermediate point m by an equal chord length impeller j The velocity field simulation or test (i.e. simulation or actual measurement) at (points with the same abscissa) is obtained, in this embodiment, the intermediate points are taken as three points according to the width of the aliquoting vane outlet, and in the coordinate system XOY, the coordinates of each intermediate point are respectively: m is m 2 (-0.25b，h 2 )，m 3 (-0.5b，h 3 )，m 4 (-0.75b，h 4 ) Wherein b is the width of the outlet of the blade 23, and the typical value range is b=4.5-5 mm;
3) According to the front point, the rear point and the middle point, five points m are adopted in the embodiment 1 、m 2 、m 3 、m 4 And m 5 Fitting the leading edge molded line of the blade 23 by adopting a spline curve to obtain a first scheme P of the leading edge molded line of the blade 23 1 ；
4) First scenario P based on leading edge profile of blade 23 1 Is tested in quadrature, with h j To optimize the variables, the efficiency η max And noise SPL are used as optimization targets to establish an optimizing relationη ori Is the highest efficiency of the equal chord length impeller scheme, SPL ori The sound power level is corresponding to the highest efficiency working condition of the equal chord length impeller scheme; η (eta) q Is the first scheme P 1 Is the highest efficiency of SPL q Is the first scheme P 1 The sound power level corresponding to the highest efficiency working condition of the blade 23 is completedIterative optimization is carried out to obtain a second scheme P 2 This solution is the optimal solution for the leading edge profile of the blade 23; wherein M is a preset upper efficiency improvement limit, N is an upper noise reduction limit, and optionally, m=10, n=2; efficiency increases greater than M% and NbB noise reduction are considered to have iterated to the optimal solution. In the course of the above iteration, h is changed by changing i j And (5) iteration is realized.
Similarly, the trailing edge profile of the blades 23 of the rotor 2 is obtained by:
1) Defining a second leading point n of the trailing edge profile of the blade 23 5 Position:
establishing a coordinate system XOY, wherein the X axis is the axis of the movable impeller 2, the forward direction of the X axis is the direction from the front disc 21 to the rear disc 22, the Y axis is the radial direction of the movable impeller 2, the forward direction of the Y axis is the radial direction from the axis of the movable impeller 2 outwards, and the end point of the tail edge molded line of the blade 23 close to the front disc 21 is recorded as a second front point n 5 The end point of the trailing edge profile of the blade 23 near the rear disc 22 is denoted as the second rear point n 1 In the coordinate system XOY, the coordinates of the second rear point and the second front point are: n is n 1 (0，j 1 )，n 5 (-b，j 5 )；j 1 Is the second back point n 1 Vertical distance to X-axis, j 5 Is the second back point n 5 The vertical distance to the X axis, b being the width of the exit of the blade 23;a is a constant, a=0.5 to 1.8mm;
second front point n 5 At an outlet flow angle of beta' 5 And meet beta' 5 ＝β 2 +i′，β 2 Is the second back point n 1 The angle of the outlet flow at which the flow is directed,D 1 for the outer diameter of the blade 23>The remaining parameters being defined as parameters in the leading edge profile, the parameters being known empirical values, e.g. parameters of an equal chord length impeller, generallyThe value range of each parameter is as follows: d (D) 2 From which β can be determined by =32 to 45mm and b=4.5 to 5mm 2 Typically 26 to 30 °; i 'is a constant, i' =0 to 0.8 °;
second front point n 5 The position of (2) is obtained by the following formula:C 5mo for the air flow at the second front point n 5 The axial surface speed at the position is tested by an equal chord length impeller to test a second front point n 5 Simulation or test (i.e. simulation or actual measurement) of the velocity field at the same abscissa gives +.>From this, a second front point n of the trailing edge profile of the blade 23 can be obtained 5 Is a position of (2); c (C) 1mo For the air flow at the second rear point n 1 An axial surface speed at the location; u (u) 5 Is the second front point n 5 Peripheral speed at;
2) Blade 23 trailing edge profile intermediate point n k The position is determined in the same way as the second front point n 5 ，j nk For a point n on the trailing edge profile of the blade 23 k The vertical distance to the X-axis,k is the number of intermediate points, the number of the intermediate points is more than or equal to 2, C kmo In this embodiment, the intermediate points take three points according to the equal-divided blade outlet width, and in the coordinate system XOY, the coordinates of each intermediate point are respectively: n is n 2 (-0.25b，j 2 )，n 3 (-0.5b，j 3 )，n 4 (-0.75b，j 4 )；
3) According to the front point, the rear point and the middle point, five points n are adopted in the embodiment 1 、n 2 、n 3 、n 4 And n 5 Fitting the tail edge molded line of the blade 23 by adopting a spline curve to obtain a first scheme W of the tail edge molded line of the blade 23 1 ；
4) First scenario W based on blade 23 trailing edge profile 1 Is tested in quadrature, j k To optimize the variables, the efficiency η max And noise SPL w To optimize the target, establish an optimizing relationη ori Is the highest efficiency of the equal chord length impeller scheme, SPL ori The sound power level is corresponding to the highest efficiency working condition of the equal chord length impeller scheme; η (eta) w Is the first scheme W 1 Is the highest efficiency of SPL w Is the first scheme W 1 The sound power level corresponding to the highest efficiency working condition is used for completing iterative optimization of the tail edge molded line of the blade 23, and a second scheme W of the tail edge molded line of the blade 23 is obtained 2 The scheme is the optimal scheme of the tail edge molded line of the blade 23; wherein M is a preset upper efficiency improvement limit, N is an upper noise reduction limit, and optionally, m=10, n=2; efficiency increases greater than M% and MbB noise reduction are considered to have iterated to the optimal solution. In the course of the above iteration, j is changed by changing i k And (5) iteration is realized.
In the invention, the curve equation of the leading edge molded line of the blade 23 in the coordinate system XOY is fitted by a polynomial to obtainh 1 ＝0.01127m，h 5 =0.01247m, e is scientific counter, 10 -14 See fig. 6.
Curve equation of variable chord trailing edge line of blade 23 in coordinate system XOY, this embodimentj 1 ＝0.01778m，j 5 =0.0188 m, see fig. 7.
In the design of the blade 23 of the rotor blade 2 of the present invention, only the design method of the leading edge profile or the trailing edge profile may be adopted, or the design combination of the leading edge profile and the trailing edge profile may be adopted. By adopting the chord-length-variable scheme, the air flow is led out of the movable impeller 2 in a form of gradually changing along the axial direction and less than 90 degrees instead of flowing out in a 90-degree turning way after entering the movable impeller 2 along the axial direction, and the flow impact loss of the air flow can be reduced by the flow way, so that the work efficiency of the movable impeller 2 is improved, and the noise is reduced.
When the leading edge profile and the trailing edge profile both adopt the variable chord length mode, the leading edge profile is designed firstly, and then the trailing edge profile is designed, and the difference between the design method and the independent trailing edge profile is that in the step of establishing the optimizing relationship, the optimizing relationship is adopted as follows:η q adopts a second scheme P of the leading edge profile of the blade 23 2 And trailing edge profile first scheme W 1 The highest efficiency after that, SPL q Adopts a second scheme P of the leading edge profile of the blade 23 2 And trailing edge profile first scheme W 1 The sound power level corresponding to the highest efficiency working condition after the process is completed, the iterative optimization of the tail edge molded line of the blade 23 is completed, and a second scheme W of the tail edge molded line of the blade 23 is obtained 2 。/>

Claims (10)

1. A design method of a fan, the fan comprising a movable impeller (2), the movable impeller (2) comprising a front disc (21), a rear disc (22) and blades (23) arranged between the front disc (21) and the rear disc (22), the blades (23) having a leading edge (231) and a trailing edge (232); the method is characterized in that: the leading edge profile of the blade (23) is obtained by the steps of:
1) Determining a first forward point (m) of a leading edge profile of the blade (23) 5 ) Position:
establishing a coordinate system XOY, wherein the X axis is the axis of the movable impeller (2), the Y axis is the radial direction of the movable impeller (2), and the end point of the front edge molded line of the blade (23) close to the front disc (21) is marked as a first front point (m 5 ) The end point of the leading edge profile of the blade (23) near the rear disk (22) is marked as a first rear point (m 1 ) First rear point (m 1 ) And a first front point (m 5 ) The coordinates of (2) are: m is m 1 (0，h 1 )，m 5 (-B，h 5 )，h 1 Is the first back point (m 1 ) The vertical distance to the X-axis,h 5 is the first back point (m 5 ) The vertical distance to the X axis, B is the inlet width of the blade (23), D 0 Is the inner diameter of the blade (23);
wherein beta is 1 Is the first back point (m 1 ) Inlet flow angle at i=1 to 3 °, C 5m For the air flow at a first front point (m 5 ) The axial surface speed at C 5m By simulating or testing the abscissa on the leading edge line of the equal chord length impeller in the same coordinate system with the first front point (m 5 ) The same point is obtained, the equal chord length impeller is an impeller with the leading edge profile and the trailing edge profile of the blade (23) respectively parallel to the X axis, and the rear point of the leading edge profile of the equal chord length impeller is connected with the first rear point (m 1 ) And overlap, thereby obtaining a first front point (m 5 ) Is a position of (2);
2) Defining a mid-point (m) of the leading edge profile of the blade (23) j ) Position:
j is the number of the middle point, h j Is the middle point (m j ) The vertical distance to the X axis, the number of intermediate points is more than or equal to 2, C jm For the air flow at an intermediate point (m j ) The axial surface speed at C jm By simulating or testing the front edge line of the equal chord impeller in the same coordinate system, the abscissa and the middle point (m j ) The same points;
3) According to the first front point (m 5 ) Intermediate point (m) j ) And a first back point (m 1 ) Fitting a spline curve to obtain a leading edge profile of the blade (23) to obtain a first scheme (P) of the leading edge profile of the blade (23) 1 )；
4) First solution (P) based on the leading edge profile of the blade (23) 1 ) Is tested in quadrature, with h j To optimizeThe variable, the efficiency and the noise are taken as optimization targets, and an optimizing relation is establishedWherein eta ori Is the highest efficiency of the equal chord impeller, SPL ori Is the sound power level, eta corresponding to the working condition of the maximum efficiency of the equal chord length impeller q Is the first scheme (P 1 ) Is the highest efficiency of SPL q Is the first scheme (P 1 ) And (3) the sound power level corresponding to the highest efficiency working condition, M is a preset efficiency lifting upper limit value, N is a noise reduction upper limit value, and the iterative optimization of the leading edge molded line of the blade (23) is completed to obtain a second scheme (P) of the leading edge molded line of the blade (23) 2 ) Thereby completing the design.
2. The method of designing a blower according to claim 1, wherein: in the step (1) of the process,wherein Q is s For the design air quantity of the fan, n is the design rotating speed of the fan, and the range of the values of the parameters is as follows: q (Q) s ＝0.4～0.6m 3 /min，n＝64800～79000rpm，D 0 ＝17～23mm，B＝7～10mm，β 1 ＝18～31°。
3. The method of designing a blower according to claim 1, wherein: in step 4), h is changed by changing i j And (5) iteration is realized.
4. A design method of a fan, the fan comprising a movable impeller (2), the movable impeller (2) comprising a front disc (21), a rear disc (22) and blades (23) arranged between the front disc (21) and the rear disc (22), the blades (23) having a trailing edge (232); the method is characterized in that: the trailing edge profile of the blade (23) is obtained by the steps of:
1) Determining a second forward point (n) of the trailing edge profile of the blade (23) 5 ) Position:
establishing a coordinate system XOY, wherein the X axis is the axis of the movable impeller (2)The Y axis is the radial direction of the movable impeller (2), and the end point of the tail edge molded line of the blade (23) close to the front disc (21) is marked as a second front point (n) 5 ) The end point of the trailing edge profile of the blade (23) near the rear disk (22) is marked as a second rear point (n) 1 ) A second rear point (n 1 ) And a second front point (n 5 ) The coordinates of (2) are: n is n 1 (0，j 1 )，n 5 (-b，j 5 )；j 1 Is the second back point (n 1 ) The vertical distance to the X-axis,j 5 is the second back point (n 5 ) The vertical distance to the X-axis, b is the width of the outlet of the blade (23), D 2 The outer diameter of the movable impeller (2), a is a constant;
β 2 is the second back point (n 1 ) Outlet flow angle at i' =0 to 0.8 °, C 5mo For the air flow at a second front point (n 5 ) The axial surface speed at C 5mo By simulating or testing the tail edge profile of an equal chord length impeller in the same coordinate system with the second forward point (n 5 ) The same point is obtained, the equal chord length impeller is an impeller with the leading edge profile and the trailing edge profile of the blade (23) respectively parallel to the X axis, and the rear point of the trailing edge profile of the equal chord length impeller is connected with the second rear point (n 1 ) And overlap, thereby obtaining a second front point (n 5 ) Is a position of (2);
2) Determining the intermediate point (n) of the trailing edge profile of the blade (23) k ) Is defined by the position of:
k is the number of the middle point, j k Is the middle point (n k ) The vertical distance to the X axis, the number of intermediate points is more than or equal to 2, C kmo For the air flow at the intermediate point (n k ) The axial surface speed at C kmo By simulating or testing impellers of equal chord length in the same coordinate systemThe abscissa and the middle point (n) k ) The same points;
3) According to the second front point (n 5 ) Intermediate point (n) k ) And a second back point (n 1 ) Fitting a spline curve to obtain a trailing edge profile of the blade (23) to obtain a first scheme (W) 1 )；
4) A first solution (W) based on the trailing edge profile of the blade (23) 1 ) Is tested in quadrature, j k To optimize variable, efficiency and noise are used as optimization targets, and an optimizing relation is establishedη ori Is the highest efficiency of the equal chord length impeller scheme, SPL ori Is the sound power level, eta corresponding to the highest efficiency working condition of the equal chord length impeller scheme w Is a first scheme (W 1 ) Is the highest efficiency of SPL w Is a first scheme (W 1 ) The sound power level corresponding to the highest efficiency working condition, M is a preset efficiency lifting upper limit value, N is a noise reduction upper limit value, and the iterative optimization of the trailing edge molded line of the blade (23) is completed to obtain a second scheme (W 2 ) Thereby completing the design.
5. The method for designing a fan according to claim 4, wherein: in the step (1) of the process, in step 1), wherein Q s For the design air quantity of the fan, n is the design rotating speed of the fan, and the range of the values of the parameters is as follows: q (Q) s ＝0.4～0.6m 3 /min，n＝64800～79000rpm，D 2 ＝32～45mm，b＝4.5～5mm，a＝0.5～1.8mm，β 2 ＝26～30°。
6. The fan arrangement of claim 4The counting method is characterized in that: in step 4), j is changed by changing i k And (5) iteration is realized.
7. A design method of a fan, the fan comprising a movable impeller (2), the movable impeller (2) comprising a front disc (21), a rear disc (22) and blades (23) arranged between the front disc (21) and the rear disc (22), the blades (23) having a leading edge (231) and a trailing edge (232); the method is characterized in that: the leading edge profile and the trailing edge profile of the blade (23) are obtained by the steps of:
firstly, designing the leading edge profile of the blade (23):
establishing a coordinate system XOY, wherein the X axis is the axis of the movable impeller (2), the Y axis is the radial direction of the movable impeller (2), and the end point of the front edge molded line of the blade (23) close to the front disc (21) is marked as a first front point (m 5 ) The end point of the leading edge profile of the blade (23) near the rear disk (22) is marked as a first rear point (m 1 ) First rear point (m 1 ) And a first front point (m 5 ) The coordinates of (2) are: m is m 1 (0，h 1 )，m 5 (-B，h 5 )，h 1 Is the first back point (m 1 ) The vertical distance to the X-axis,h 5 is the first back point (m 5 ) The vertical distance to the X axis, B is the inlet width of the blade (23), D 0 Is the inner diameter of the blade (23);
wherein beta is 1 Is the first back point (m 1 ) Inlet flow angle at i=1 to 3 °, C 5m For the air flow at a first front point (m 5 ) The axial surface speed at C 5m By simulating or testing the abscissa on the leading edge line of the equal chord length impeller in the same coordinate system with the first front point (m 5 ) The same point is obtained, the equal chord length impeller is an impeller with the front edge molded line and the tail edge molded line of the blade (23) respectively parallel to the X axis, and the rear point of the front edge molded line of the equal chord length impeller is connected with the first rear partPoint (m) 1 ) And overlap, thereby obtaining a first front point (m 5 ) Is a position of (2);
2) Defining a mid-point (m) of the leading edge profile of the blade (23) j ) Position:
j is the number of the middle point, h j Is the middle point (m j ) The vertical distance to the X axis, the number of intermediate points is more than or equal to 2, C jm For the air flow at an intermediate point (m j ) The axial surface speed at C jm By simulating or testing the front edge line of the equal chord impeller in the same coordinate system, the abscissa and the middle point (m j ) The same points;
3) According to the first front point (m 5 ) Intermediate point (m) j ) And a first back point (m 1 ) Fitting a spline curve to obtain a leading edge profile of the blade (23) to obtain a first scheme (P) of the leading edge profile of the blade (23) 1 )；
4) First solution (P) based on the leading edge profile of the blade (23) 1 ) Is tested in quadrature, with h j To optimize variable, efficiency and noise are used as optimization targets, and an optimizing relation is establishedWherein eta ori Is the highest efficiency of the equal chord impeller, SPL ori Is the sound power level, eta corresponding to the working condition of the maximum efficiency of the equal chord length impeller q Is the first scheme (P 1 ) Is the highest efficiency of SPL q Is the first scheme (P 1 ) And (3) the sound power level corresponding to the highest efficiency working condition, M is a preset efficiency lifting upper limit value, N is a noise reduction upper limit value, and the iterative optimization of the leading edge molded line of the blade (23) is completed to obtain a second scheme (P) of the leading edge molded line of the blade (23) 2 )；
(II) then, designing the trailing edge profile of the blade (23):
1) Determining a second forward point (n) of the trailing edge profile of the blade (23) 5 ) Position:
the tail edge molded line of the blade (23) is close to the frontThe end point of the disk (21) is denoted as the second front point (n 5 ) The end point of the trailing edge profile of the blade (23) near the rear disk (22) is marked as a second rear point (n) 1 ) A second rear point (n 1 ) And a second front point (n 5 ) The coordinates of (2) are: n is n 1 (0，j 1 )，n 5 (-b，j 5 )；j 1 Is the second back point (n 1 ) The vertical distance to the X-axis,j 5 is the second back point (n 5 ) The vertical distance to the X-axis, b is the width of the outlet of the blade (23), D 2 The outer diameter of the movable impeller (2), a is a constant;
β 2 is the second back point (n 1 ) Outlet flow angle at i' =0 to 0.8 °, C 5mo For the air flow at a second front point (n 5 ) The axial surface speed at C 5mo By simulating or testing the tail edge profile of an equal chord length impeller in the same coordinate system with the second forward point (n 5 ) The same point results in a trailing point of the trailing edge profile of the equal chord length impeller and the second trailing point (n 1 ) And overlap, thereby obtaining a second front point (n 5 ) Is a position of (2);
2) Determining the intermediate point (n) of the trailing edge profile of the blade (23) k ) Is defined by the position of:
k is the number of the middle point, j k Is the middle point (n k ) The vertical distance to the X axis, the number of intermediate points is more than or equal to 2, C kmo For the air flow at the intermediate point (n k ) The axial surface speed at C kmo By simulating or testing the tail edge profile of an equal chord length impeller in the same coordinate system with the abscissa and the midpoint (n k ) The same points;
3) According to the second front point (n 5 ) IntermediatePoint (n) k ) And a second back point (n 1 ) Fitting a spline curve to obtain a trailing edge profile of the blade (23) to obtain a first scheme (W) 1 )；
4) A first solution (W) based on the trailing edge profile of the blade (23) 1 ) Is tested in quadrature, j k To optimize variable, efficiency and noise are used as optimization targets, and an optimizing relation is establishedη q Adopts a second scheme (P) of the leading edge profile of the blade (23) 2 ) And trailing edge profile first scheme (W 1 ) The highest efficiency after that, SPL q Adopts a second scheme (P) of the leading edge profile of the blade (23) 2 ) And trailing edge profile first scheme (W 1 ) The sound power level corresponding to the highest efficiency working condition after the process is completed, the iterative optimization of the tail edge molded line of the blade (23) is completed, and a second scheme (W) of the tail edge molded line of the blade (23) is obtained 2 ) Whereby the second pattern (P) of the leading edge profile of the blade (23) is passed 2 ) And a second version (W) of the trailing edge profile of the blade (23) 2 ) And (5) completing the design.
8. The method of designing a blower according to claim 7, wherein: wherein Q is s For the design air quantity of the fan, n is the design rotating speed of the fan, and the range of the values of the parameters is as follows: q (Q) s ＝0.4～0.6m 3 /min，n＝64800～79000rpm，D 0 ＝17～23mm，B＝7～10mm，β 1 ＝18～31°，D 2 ＝32～45mm，b＝4.5～5mm，a＝0.5～1.8mm，β 2 ＝26～30°。
9. A fan, characterized in that: obtained by the design method according to any one of claims 1 to 8.
10. A cleaning device, characterized in that: use of a fan according to claim 9.
CN202310574606.5A 2023-05-19 2023-05-19 Design method of fan, fan and cleaning device applying fan Pending CN116756864A (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
CN202310574606.5A CN116756864A (en) 2023-05-19 2023-05-19 Design method of fan, fan and cleaning device applying fan

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
CN202310574606.5A CN116756864A (en) 2023-05-19 2023-05-19 Design method of fan, fan and cleaning device applying fan

Publications (1)

Publication Number Publication Date
CN116756864A true CN116756864A (en) 2023-09-15

Family

ID=87956164

Family Applications (1)

Application Number Title Priority Date Filing Date
CN202310574606.5A Pending CN116756864A (en) 2023-05-19 2023-05-19 Design method of fan, fan and cleaning device applying fan

Country Status (1)

Country Link
CN (1) CN116756864A (en)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN117910172A (en) * 2024-03-20 2024-04-19 广东顺威精密塑料股份有限公司 Design method and design device for axial flow fan blade

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN117910172A (en) * 2024-03-20 2024-04-19 广东顺威精密塑料股份有限公司 Design method and design device for axial flow fan blade

Similar Documents

Publication Publication Date Title
US8668460B2 (en) Turbo fan and air conditioner with turbo fan
US10550855B2 (en) Axial flow fan
CN105332952B (en) A kind of adjustable stator design method of small camber
CN101173676A (en) Electric axial flow fan
CN116756864A (en) Design method of fan, fan and cleaning device applying fan
CN115717604B (en) Backward centrifugal wind wheel with front blades and blade profile design method thereof
CN106939902B (en) Energy-saving straight-wall front and rear disk variable-curvature curve element ternary impeller and centrifugal fan adopting same
JP3677214B2 (en) Axial fan
CN110566503B (en) Centrifugal fan blade, centrifugal fan, air conditioner and transportation means
CN211259115U (en) Blade, multi-wing centrifugal fan blade and multi-wing centrifugal fan
JP3754244B2 (en) Wing design method for axial flow fan and axial flow fan
WO2020125128A1 (en) Axial flow fan blade, ventilation device and air conditioner
CN110566500A (en) Impeller of centrifugal ventilator
CN108757568B (en) Axial flow fan blade
CN114483648B (en) Blade design the method is blade and centrifugal fan
CN211009265U (en) Impeller of centrifugal ventilator
CN114909325A (en) Low-noise axial flow fan blade and axial flow fan
JPH08312589A (en) Structure of air blowing fan
CN113202814A (en) Blade structure for bidirectional multi-wing centrifugal fan and multi-wing centrifugal fan impeller
CN112096656A (en) Axial flow fan blade, axial flow fan and air conditioner
CN209724796U (en) A kind of return channel blade
CN109209989B (en) Centrifugal fan and range hood
CN112528397A (en) Optimized design method for rear fluid director of jet fan
CN213360556U (en) Axial flow fan blade, axial flow fan and air conditioner
JPS6165096A (en) Axial flow blade

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