CN113309736A - Blade, impeller, centrifugal fan, range hood and blade design method - Google Patents

Blade, impeller, centrifugal fan, range hood and blade design method Download PDF

Info

Publication number
CN113309736A
CN113309736A CN202110779049.1A CN202110779049A CN113309736A CN 113309736 A CN113309736 A CN 113309736A CN 202110779049 A CN202110779049 A CN 202110779049A CN 113309736 A CN113309736 A CN 113309736A
Authority
CN
China
Prior art keywords
blade
profile
pressure surface
point
end ring
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
CN202110779049.1A
Other languages
Chinese (zh)
Inventor
任富佳
鲍明
郑桐福
孟君
余国成
周海昕
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.)
Hangzhou Robam Appliances Co Ltd
Original Assignee
Hangzhou Robam Appliances 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 Hangzhou Robam Appliances Co Ltd filed Critical Hangzhou Robam Appliances Co Ltd
Priority to CN202110779049.1A priority Critical patent/CN113309736A/en
Publication of CN113309736A publication Critical patent/CN113309736A/en
Pending legal-status Critical Current

Links

Images

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D17/00—Radial-flow pumps, e.g. centrifugal pumps; Helico-centrifugal pumps
    • F04D17/08—Centrifugal pumps
    • F04D17/16—Centrifugal pumps for displacing without appreciable compression
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/26—Rotors specially for elastic fluids
    • F04D29/28—Rotors specially for elastic fluids for centrifugal or helico-centrifugal pumps for radial-flow or helico-centrifugal pumps
    • F04D29/30—Vanes
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/40—Casings; Connections of working fluid
    • F04D29/42—Casings; Connections of working fluid for radial or helico-centrifugal pumps
    • F04D29/4206—Casings; Connections of working fluid for radial or helico-centrifugal pumps especially adapted for elastic fluid pumps
    • F04D29/4226—Fan casings
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/66—Combating cavitation, whirls, noise, vibration or the like; Balancing
    • F04D29/661—Combating cavitation, whirls, noise, vibration or the like; Balancing especially adapted for elastic fluid pumps
    • F04D29/666—Combating cavitation, whirls, noise, vibration or the like; Balancing especially adapted for elastic fluid pumps by means of rotor construction or layout, e.g. unequal distribution of blades or vanes
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F24—HEATING; RANGES; VENTILATING
    • F24C—DOMESTIC STOVES OR RANGES ; DETAILS OF DOMESTIC STOVES OR RANGES, OF GENERAL APPLICATION
    • F24C15/00—Details
    • F24C15/20—Removing cooking fumes

Abstract

The invention relates to the technical field of power equipment, in particular to a blade, an impeller, a centrifugal fan, a range hood and a blade design method. The blade provided by the invention comprises a blade body, wherein the blade body comprises a first front edge, a first pressure surface, a first rear edge and a first suction surface which are sequentially connected end to end, the first pressure surface is provided with a first pressure surface profile, the first suction surface is provided with a first suction surface profile, and the first pressure surface profile is an arc curve; and setting a reference airfoil shape, wherein the relative thickness distribution of the blade body along the chord length is the same as that of the reference airfoil shape along the chord length. The blade body is formed by superposing the relative thickness of the selected reference airfoil profile on the pressure surface in a manner of being equivalent to the single-side superposition of the arc plate blade, the blade body has the aerodynamic characteristics of the set reference airfoil profile, the flow control on the pressure surface can be obviously enhanced, the degree of flow separation generated in an impeller flow passage is effectively reduced, the working efficiency of a centrifugal impeller is improved, and the vortex noise is reduced.

Description

Blade, impeller, centrifugal fan, range hood and blade design method
Technical Field
The invention relates to the technical field of power equipment, in particular to a blade, an impeller, a centrifugal fan, a range hood and a blade design method.
Background
At present, most of multi-blade centrifugal fans adopt a centrifugal impeller structure of an arc plate blade type. When the impeller works in a rotating mode, the moving air flow in the impeller is easy to flow and separate due to the effect of fluid viscosity effect, inverse pressure gradient and rotary Coriolis force, secondary vortex is formed, the working efficiency of the impeller is low, and the pneumatic performance and the working noise of the fan are directly influenced.
In order to solve the above problems, in the prior art, a multi-wing centrifugal impeller structure with wing-shaped blades is adopted, so that the flow characteristics in an impeller flow channel can be improved to a certain extent. When designing an airfoil blade, a method of superposing the conventional symmetrical airfoil thickness on both sides of a mean camber line is generally adopted.
According to the basic internal flow theory of the centrifugal impeller, the flow separation in the impeller channel is mostly generated on the suction surface side, and the aerodynamic characteristics of the airfoil shape determine that the maximum relative thickness of the selected airfoil shape cannot be too large, so that the airfoil shape blade obtained by the design method of superposing the airfoil shape thicknesses on the two sides has insufficient control on the gas flow on the suction surface in the impeller channel, and the impeller efficiency is improved insufficiently.
Disclosure of Invention
The invention aims to provide a blade to solve the technical problem that the efficiency of an impeller in the prior art is not sufficiently improved.
The invention provides a blade which comprises a blade body, wherein the blade body comprises a first front edge, a first pressure surface, a first rear edge and a first suction surface which are sequentially connected end to end, the first pressure surface is provided with a first pressure surface profile, the first suction surface is provided with a first suction surface profile, and the first pressure surface profile is an arc curve;
and setting a reference airfoil profile, wherein the airfoil profile is in a section shape parallel to the symmetrical plane of the aircraft on the aircraft wing, and the relative thickness distribution of the blade body along the chord length is the same as that of the reference airfoil profile along the chord length.
As a further technical scheme, at least one of two ends of the blade body in the blade height direction is provided with a leakage-proof structure, and the leakage-proof structure is used for reducing leakage flow.
As a further technical solution, the leakage prevention structure comprises a winglet, and the winglet comprises a second leading edge, a second pressure surface, a second trailing edge and a second suction surface which are connected end to end in sequence.
As a further technical solution, the first pressure surface is flush with the second pressure surface, the first trailing edge is flush with the second trailing edge, and the first suction surface is flush with the second suction surface;
the second front edge is located on one side of the first front edge facing the first rear edge, a gap is arranged between the first front edge and the second front edge, and the length of the gap is L.
As a further technical scheme, the chord length of the blade body is M, and L/M is more than or equal to 0.2 and less than or equal to 0.6.
As a further technical scheme, the height between two ends of the winglet along the height direction is h, and h/M is more than or equal to 0.1 and less than or equal to 0.4.
As a further feature, the thickness and shape of the blade body at the first leading edge is the same as the thickness and shape of the winglet at the second leading edge.
As a further technical solution, the blade body protrudes outward to form the first leading edge, the first leading edge has a first leading edge profile, and an obtuse angle is formed between end points of two ends of the first leading edge profile and a point connecting line on the first leading edge profile.
As a further technical solution, the first leading edge profile is an arc curve, and the first pressure surface profile and the first suction surface profile are respectively tangent to the first leading edge profile.
As a further technical solution, the blade body protrudes outward to form the first trailing edge, the first trailing edge has a first trailing edge profile, and an obtuse angle is formed between end points of two ends of the first trailing edge profile and a point connecting line on the first trailing edge profile.
As a further technical solution, the first trailing edge profile is an arc curve, and the first pressure surface profile and the first suction surface profile are respectively tangent to the first trailing edge profile.
As a further technical solution, an included angle is formed between a normal of the molded line at the inlet of the blade body and a normal of the molded line at the outlet of the blade body, and the included angle is a central angle θ, and θ is greater than 90 °.
The impeller provided by the invention comprises the blades, wherein the blades are uniformly arranged at intervals along the circumferential direction of the impeller;
the blade assembly further comprises a first end ring and a second end ring, wherein the first end ring is opposite to the second end ring and is arranged at a distance, and the blade is connected to the first end ring and the second end ring and is positioned between the first end ring and the second end ring.
As a further technical solution, the end ring further comprises a middle disc, wherein the middle disc is arranged between the first end ring and the second end ring and forms a gap with the first end ring and the second end ring respectively;
the blades are arranged between the first end ring and the middle disc, one ends of the blades are connected with the first end ring, and the other ends of the blades are connected with the middle disc;
the blades are arranged between the second end ring and the middle disc, one ends of the blades are connected with the second end ring, and the other ends of the blades are connected with the middle disc.
As a further technical solution, the blades between the first end ring and the central disc and the blades between the second end ring and the central disc are symmetrically arranged or staggered with respect to the central disc.
As a further technical scheme, the included angle between the tangent of the molded line at the inlet of the blade body and the tangent of the circumference of the impeller is an inlet installation angle betab1And beta is not more than 50 DEGb1≤90°；
And/or the included angle between the tangent line of the molded line at the outlet of the blade body and the tangent line of the circumference of the impeller is beta as an outlet installation angleb2And beta is not more than 5 DEGb2≤30°。
The centrifugal fan provided by the invention comprises the impeller.
The range hood provided by the invention comprises the centrifugal fan.
The invention provides a blade design method, which comprises the following steps:
determining a space curve equation of the arc-shaped pressure surface profile of the blade;
selecting a reference wing profile and determining a space curve equation of the reference wing profile;
and converting the relative thickness distribution of the reference airfoil along the chord length into the same relative thickness distribution of the reference airfoil along the chord length by using a space curve coordinate conversion method, thereby obtaining a space curve equation of the suction surface profile of the blade.
As a further technical scheme, the space curve equation for determining the arc-shaped pressure surface profile of the blade comprises the following steps:
according to a method for designing a forward-bent blade of a multi-wing centrifugal impeller, determining a circular arc-shaped pressure surface molded line of the blade, wherein two end points of the pressure surface molded line of the blade are respectively a point A and a point B;
establishing an XY rectangular coordinate system by taking the point A as an origin, wherein an X axis is arranged along the extending direction of a connecting line of the point A and the point B, and converting a space curve equation of a pressure surface molded line of the blade into fp(x) Pressure surface profile of bladeThe center point of the line is O, and the coordinates of the O point are (x)0，y0)。
As a further technical solution, the determining the space curve equation of the reference airfoil profile comprises the following steps:
selecting a reference wing profile of the blade, scaling the reference wing profile according to the chord length proportion, placing the scaled reference wing profile in an XY rectangular coordinate system, enabling the front edge endpoint of the reference wing profile to be positioned on the Y axis, enabling the rear edge endpoint of the reference wing profile to coincide with the point B, and converting a space curve equation of the suction surface molded line of the reference wing profile into fa(x) The space curve equation of the pressure surface profile of the reference airfoil is fb(x)。
As a further technical solution, the step of converting the relative thickness distribution of the blade along the chord length into the same relative thickness distribution of the reference airfoil along the chord length to obtain the space curve equation of the suction surface profile of the blade includes the following steps:
the point crossing O is taken as a straight line OE, the straight line OE is intersected with the pressure surface molded line of the reference airfoil at the point C, the straight line OE is intersected with the pressure surface molded line AB of the blade at the point D, the point crossing O and the point A are taken as a straight line OA, and the included angle theta between the straight line OE and the straight line OA is thetai(0≤θiTheta) or less), determining the X-axis coordinate value X of the C pointcAccording to fa(x) And fb (X), determining the X-axis coordinate value as XcThe distance between the pressure surface molded line of the time reference airfoil and the suction surface molded line of the time reference airfoil is the length of the line segment CF;
the length of the line segment DE is made the same as that of the line segment CF to determine the coordinate (x) of the point EE，yE)；
Connecting through an included angle thetaiAll the points E are determined to obtain the suction surface profile of the cross section of the blade and the space curve equation f of the suction surface profile of the blades(x)。
As a further technical solution, the spatial curve equation f of the pressure surface profile of the bladep(x) Comprises the following steps:
Figure BDA0003156940150000061
Rbis the radius of the pressure surface profile AB of the blade, theta is the central angle of the pressure surface profile AB of the blade,
Figure BDA0003156940150000062
the reference airfoil profile is a plano-convex airfoil profile, so that a straight line part in a pressure surface molded line of the reference airfoil profile is coincident with an X axis, and the length of a line segment AC
Figure BDA0003156940150000063
Is the X-axis coordinate value X of the point Cc，
Figure BDA0003156940150000064
The length of the line segment CF is fa(xc) The coordinate (x) of the point E is obtained by making the length of the line segment CF equal to that of the line segment CDE，yE)；
Wherein:
Figure BDA0003156940150000071
Figure BDA0003156940150000072
compared with the prior art, the blade provided by the invention has the technical advantages that:
the blade provided by the invention comprises a blade body, wherein the blade body comprises a first front edge, a first pressure surface, a first rear edge and a first suction surface which are sequentially connected end to end, the first pressure surface is provided with a first pressure surface profile, the first suction surface is provided with a first suction surface profile, and the first pressure surface profile is an arc curve; and setting a reference airfoil profile, wherein the airfoil profile is in a section shape parallel to the symmetrical plane of the aircraft on the aircraft wing, and the relative thickness distribution of the blade body along the chord length is the same as that of the reference airfoil profile along the chord length.
The relative thickness distribution of the blade body along the chord length is the same as that of the reference airfoil along the chord length, the first pressure surface profile is set to be an arc curve, namely the first pressure surface profile is the same as that of the arc plate blade, the relative thickness distribution of the blade body along the chord length can be determined through the relative thickness distribution of the reference airfoil along the chord length, and then the first suction surface profile is determined. Because the flow separation in the impeller channel is mostly generated at one side of the suction surface, the aerodynamic characteristics of the wing profile determine that the maximum relative thickness of the selected wing profile cannot be too large, the blade body has the set aerodynamic characteristics of the reference wing profile, and simultaneously, the maximum relative thickness of the reference wing profile is reduced to the maximum extent, the flow control on the suction surface can be obviously enhanced, the degree of flow separation generated in an impeller flow channel is effectively reduced, the working efficiency of the centrifugal impeller is improved, and the vortex noise is reduced.
Additional features and advantages of the invention will be set forth in the detailed description which follows.
Drawings
In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings used in the description of the embodiments or the prior art will be briefly described below, and it is obvious that the drawings in the following description are some embodiments of the present invention, and other drawings can be obtained by those skilled in the art without creative efforts.
FIG. 1 is a distribution diagram of a blade provided by an embodiment of the present invention;
FIG. 2 is a schematic structural view of a blade provided in accordance with an embodiment of the present invention;
FIG. 3 is a schematic illustration of a blade having a winglet according to an embodiment of the invention;
FIG. 4 is a schematic structural diagram of an impeller provided in an embodiment of the present invention;
FIG. 5 is an assembly view of an impeller provided in accordance with an embodiment of the present invention;
fig. 6 is a partially enlarged view of fig. 5.
Icon: 1-a blade body; 11-a first suction surface profile; 12-a first pressure face profile; 13-a first leading edge profile; 14-a first trailing edge profile; 15-winglet; 151-second suction surface; 152-a second pressure surface; 153-a second leading edge; 2-a first end ring; 3-a middle disc; 4-a second end ring; 5-centrifugal volute; 6-a scaffold; 7-wind guide ring.
Detailed Description
The technical solutions of the present invention will be described clearly and completely with reference to the following embodiments, and it should be understood that the described embodiments are some, but not all, embodiments of the present invention. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.
In the description of the present invention, it should be noted that the terms "center", "upper", "lower", "left", "right", "vertical", "horizontal", "inner", "outer", etc., indicate orientations or positional relationships based on the orientations or positional relationships shown in the drawings, and are only for convenience of description and simplicity of description, but do not indicate or imply that the device or element being referred to must have a particular orientation, be constructed and operated in a particular orientation, and thus, should not be construed as limiting the present invention. Furthermore, the terms "first," "second," and "third" are used for descriptive purposes only and are not to be construed as indicating or implying relative importance.
In the description of the present invention, it should be noted that, unless otherwise explicitly specified or limited, the terms "mounted," "connected," and "connected" are to be construed broadly, e.g., as meaning either a fixed connection, a removable connection, or an integral connection; can be mechanically or electrically connected; they may be connected directly or indirectly through intervening media, or they may be interconnected between two elements. The specific meanings of the above terms in the present invention can be understood in specific cases to those skilled in the art.
In addition, technical solutions between various embodiments may be combined with each other, but must be realized by a person skilled in the art, and when the technical solutions are contradictory or cannot be realized, such a combination should not be considered to exist, and is not within the protection scope of the present invention.
The present invention will be described in further detail below with reference to specific embodiments and with reference to the attached drawings.
The specific structure is shown in fig. 1 to 6.
The embodiment provides a blade, which comprises a blade body 1, wherein the blade body 1 comprises a first front edge, a first pressure surface, a first rear edge and a first suction surface which are sequentially connected end to end, the first pressure surface is provided with a first pressure surface molded line 12, the first suction surface is provided with a first suction surface molded line 11, and the first pressure surface molded line 12 is an arc curve;
and setting a reference airfoil profile, wherein the airfoil profile is in a section shape parallel to the symmetrical plane of the aircraft on the aircraft wing, and the relative thickness distribution of the blade body 1 along the chord length is the same as that of the reference airfoil profile along the chord length.
Compared with the arc plate blade in the prior art, the airfoil blade is usually formed by superposing conventional symmetrical airfoil thicknesses on two sides of a mean camber line, and because the lift-drag ratio characteristic of the airfoil is directly related to the relative maximum thickness of the airfoil, an airfoil scheme with an overlarge maximum relative thickness cannot be generally selected. Furthermore, according to the basic internal flow theory of the centrifugal impeller, the moving air flow in the impeller flow channel is simultaneously influenced by the fluid viscosity effect, the inverse pressure gradient and the action of the rotary coriolis force, and the flow separation is easily generated to form a secondary vortex. The basic motion law in the impeller flow channel determines that the pressure on the pressure surface of the blade is larger than that on the suction surface, namely the counter pressure gradient on the suction surface of the blade is more obvious, so that the flow separation in the impeller channel is mostly generated on the suction surface side. Therefore, the airfoil blade obtained by the design method of superposing the airfoil thicknesses on the two sides has insufficient control on gas flow on the suction surface in the flow passage, and the efficiency of the impeller is improved insufficiently.
According to the blade provided by the embodiment, the relative thickness distribution of the blade body 1 along the chord length is the same as that of the reference airfoil along the chord length, the first pressure surface molded line 12 is set to be an arc curve, that is, the first pressure surface molded line 12 is the same as that of the arc plate blade, the relative thickness distribution of the blade body along the chord length can be determined by the reference airfoil along the relative thickness distribution of the chord length, and then the first suction surface molded line 11 is determined, compared with the arc plate blade, the blade body 1 is only different in shape from that of the arc plate blade, that is, the first suction surface molded line 11 is different from that of the arc plate blade, so that the blade body 1 is formed by the relative thickness of the reference airfoil selected by single-side superposition of the arc plate blade on the pressure surface.
Because the flow separation in the impeller flow channel mostly occurs at one side of the suction surface, and the aerodynamic characteristics of the wing profile determine that the maximum relative thickness of the selected wing profile cannot be too large, the blade body 1 has the set aerodynamic characteristics of the reference wing profile, and simultaneously reduces the maximum relative thickness of the reference wing profile to the maximum extent, so that the flow control on the suction surface can be obviously enhanced, the degree of flow separation generated in the impeller flow channel is effectively reduced, the working efficiency of the centrifugal impeller is improved, and the vortex noise is reduced.
Wherein, the wing section is: the shape of a section on an aircraft wing parallel to the plane of symmetry of the aircraft is also known as an aerofoil section or a blade section.
The profile of the suction surface of the airfoil is the profile of the upper surface of the airfoil, and the profile of the pressure surface of the airfoil is the profile of the lower surface of the airfoil.
Relative thickness of the airfoil: perpendicular to the chord line, the maximum distance between the upper and lower curves divided by the chord length is called the relative thickness.
In the optional technical scheme of this embodiment, at least one of the two ends of the blade body 1 in the blade height direction is provided with a leakage-proof structure, the leakage-proof structure is used for reducing leakage flow, in this embodiment, the spanwise direction of the blade body 1, that is, the blade height direction, can also be understood as the length direction of the blade body 1, the maximum sectional area of the leakage-proof structure arranged at the end of the blade body 1 is smaller than the area of the blade section of the end of the blade body 1 corresponding to the maximum sectional area, so, after an impeller composed of a plurality of blade bodies 1 is installed in a volute, a cavity is formed between the end of the impeller and the air guide ring 7, the leakage-proof structure moves along the circumferential direction of the cavity along with the rotation of the impeller, a certain pressure can be formed in the cavity to reduce leakage, the aerodynamic performance of the fan is further improved, and the working noise is reduced.
This embodiment is preferred, and blade body 1 all sets up in having along the both ends of leaf height direction and prevents revealing the structure, and so, blade body 1's entrance point and exit end homoenergetic can reduce or avoid revealing the flow, promote pneumatic effect.
In the optional technical scheme of this embodiment, the tip of blade body 1 continues to extend and forms the extension, and the section area that extension and blade section are parallel diminishes along the extending direction gradually, and the extension forms and prevents leaking the structure and with blade body integrated into one piece, simple structure, and it is convenient to make, structural strength is high. The present embodiment is not limited thereto and the extension may be interconnected with the blade body as a single two-piece component.
As shown in fig. 3, 4 and 6, in an alternative embodiment of the present invention, the leakage-preventing structure includes the winglet 15, and the winglet 15 includes a second leading edge 153, a second pressure surface 152, a second trailing edge and a second suction surface 151 that are sequentially connected end to end, and the winglet 15 may be understood as a blade structure that is smaller than the blade body 1, and the winglet 15 itself has better aerodynamic performance, so that the leakage flow rate is reduced while the influence on the aerodynamic performance of the blade body 1 is reduced.
In addition, after the winglet 15 is adopted, the inlet diameter of the air guide ring 7 can be further enlarged, and the pneumatic performance of the fan can be further improved under the condition of keeping the leakage prevention capacity.
In comparison with the blade body 1, the winglet 15 has a smaller outer contour dimension of the winglet 15, and the outer contour of the winglet 15 is similar to the outer contour of the blade body 1.
As shown in fig. 3, in an alternative embodiment of the present invention, the first pressure surface is flush with the second pressure surface 152, the first trailing edge is flush with the second trailing edge, and the first suction surface is flush with the second suction surface 151;
the second front edge 153 is located on a side of the first front edge facing the first rear edge, and a space is provided between the first front edge and the second front edge 153, and the length of the space is L.
In this embodiment, the upper surface of the winglet 15 is the second suction surface 151, the lower surface is the second pressure surface 152, the upper surface of the blade body 1 is the first suction surface, the lower surface is the first pressure surface, the upper surface of the winglet 15 is flush with the upper surface of the blade body 1, the lower surface of the winglet 15 is flush with the lower surface of the blade body 1, and the corresponding positions of the winglet 15 and the blade body 1 have the same thickness, so that the overall aerodynamic performance of the blade is ensured. Meanwhile, the second front edge 153 is located on one side of the first front edge facing the first rear edge, and a gap is formed between the first front edge and the second front edge 153, so that a cavity is formed between the end of the impeller and the air guide ring 7, and leakage is reduced.
In an optional technical solution of this embodiment, the maximum distance between the first leading edge and the second leading edge of the blade body 1 is a chord length M, that is, the width of the blade body 1, and L/M is greater than or equal to 0.2 and less than or equal to 0.6. Therefore, the pneumatic performance of the fan is good, the working noise is low, the preferred embodiment is that L/M is more than or equal to 0.3 and less than or equal to 0.5, the pneumatic performance of the fan is further improved, and the working noise is reduced.
As shown in fig. 3, in the optional technical solution of this embodiment, the height between the two ends of the winglet 15 in the blade height direction is h, and h/M is greater than or equal to 0.1 and less than or equal to 0.4, so that the aerodynamic performance of the fan is good, and the operating noise is low, and in this embodiment, L/h is greater than or equal to 0.1 and less than or equal to 0.3 is preferred, so as to further improve the aerodynamic performance of the fan and reduce the operating noise.
In an alternative embodiment of the present invention, the thickness and shape of the blade body 1 at the first leading edge are the same as the thickness and shape of the winglet 15 at the second leading edge 153, i.e. the profile of the second leading edge 153 is the same as the profile of the first leading edge 13, so that the first leading edge and the second leading edge 153 have the same aerodynamic performance and reduce noise.
In the optional technical scheme of this embodiment, blade body 1 has winglet 15 along the equal integrated into one piece in both ends of leaf height direction, and winglet 15 and blade body 1 integrated into one piece are convenient for make, have the same intensity, and the cavity forms between the both ends of blade body 1 and wind-guiding circle 7 simultaneously, further reduces and leaks, and symmetrical structure makes the whole atress of blade balanced simultaneously.
It should be noted that the blade body 1 and the winglet 15 may be two separate parts connected to each other, and the winglet 15 may be provided at one end of each of the two ends of the blade body 1.
In an optional technical solution of this embodiment, the blade body 1 protrudes outward to form a first leading edge, the first leading edge has a first leading edge profile 13, and an obtuse angle is formed between end points of two ends of the first leading edge profile 13 and a point connection line on the first leading edge profile 13.
In this embodiment, first leading edge adopts blunt leading edge structure, and when the fan operation was under different inlet air flow operating modes, the first leading edge that has blunt leading edge structure can still keep less impact loss in great inlet air attack angle range to make the impeller keep higher work efficiency, can widen the high-efficient operation interval of fan, promote range hood performance under different user's operating modes.
Compared with a sharp front edge structure, the blunt front edge structure has larger curvature and more round and blunt shape.
As shown in fig. 1 and fig. 2, in an alternative technical solution of the present embodiment, the first leading edge profile 13 is an arc curve, and the first pressure surface profile 12 and the first suction surface profile 11 are respectively tangent to the first leading edge profile 13, the arc curve is relatively smooth, and noise generated when the arc curve contacts air is smaller.
In an optional technical solution of this embodiment, the blade body 1 protrudes outward to form a first trailing edge, the first trailing edge has a first trailing edge profile 14, and an obtuse angle is formed between end points of two ends of the first trailing edge profile 14 and a point connecting line on the first trailing edge profile 14.
In the optional technical solution of this embodiment, the first trailing edge profile 14 is an arc curve, and the first pressure surface profile 12 and the first suction surface profile 11 are respectively tangent to the first trailing edge profile 14, the arc curve is smooth, and noise generated when the arc curve contacts air is less.
In this embodiment, the first leading edge may adopt a blunt leading edge structure, and the first trailing edge adopts a sharp trailing edge structure; or the first front edge adopts a blunt front edge structure, and the first rear edge adopts a blunt rear edge structure; the first front edge can also adopt a sharp front edge structure, and the first rear edge adopts a sharp rear edge structure; or the first front edge adopts a sharp front edge structure, and the first rear edge adopts a blunt rear edge structure.
As shown in fig. 2, in the alternative of this embodiment, the central angle of the first pressure profile 12 is θ, and θ >90 °, so that the blade at such a central angle has better aerodynamic performance and lower noise.
Note that, the central angle of the blade body 1 is: the angle between the normal of the molded line at the inlet of the blade body 1 and the normal of the molded line at the outlet of the blade body 1 is formed.
The impeller provided by the invention comprises the blades, wherein the blades are uniformly arranged at intervals along the circumferential direction of the impeller, namely the adjacent blades are provided with the same flow channel, when the impeller rotates, the airflow in each flow channel is the same, and the noise is reduced.
As shown in fig. 4, in an alternative embodiment of the present invention, the first end ring 2 and the second end ring 4 are further included, the first end ring 2 is opposite to and spaced apart from the second end ring 4, and the vane is connected to the first end ring 2 and the second end ring 4 and is located between the first end ring 2 and the second end ring 4. One end of the blade is connected to the first end ring 2 and the other end is connected to the second end ring 4.
In an optional technical scheme of the embodiment, the motor-driven shaft further comprises a middle disc 3, wherein the middle disc 3 is connected with a transmission motor, the middle disc 3 is arranged between the first end ring 2 and the second end ring 4, and gaps are respectively formed between the middle disc 3 and the first end ring 2 and between the middle disc 3 and the second end ring 4;
a blade is arranged between the first end ring 2 and the middle disc 3, one end of the blade is connected with the first end ring 2, and the other end of the blade is connected with the second end ring 4;
and a blade is arranged between the second end ring 4 and the middle disc 3, one end of the blade is connected with the second end ring 4, and the other end of the blade is connected with the middle disc 3.
In an alternative solution of this embodiment, the blades between the first end ring 2 and the middle disc 3 and the blades between the second end ring 4 and the middle disc 3 are symmetrically arranged or staggered with respect to the middle disc 3.
In this embodiment, the blades between the first end ring 2 and the middle disc 3 and the blades between the second end ring 4 and the middle disc 3 are all located on the same circumference of the impeller and are symmetrical relative to the middle disc 3, so that the blades on both sides of the middle disc 3 are on the same straight line, or are arranged in a staggered manner on both sides of the middle disc 3, preferably, one blade on one side of the middle disc 3 is located in the middle of two adjacent blades on the other side of the middle disc 3, and so that the central angles between the adjacent blades in the staggered manner are equal. The blades on the two sides of the middle disc 3 are arranged in the two modes, so that the pneumatic performance is better.
As shown in fig. 1, in an alternative embodiment of the present invention, the installation angle of the inlet of the blade body 1 is βb1And beta is not more than 50 DEGb1Less than or equal to 90 degrees, thus the pneumatic performance of the fan is good, the working noise is low, and the preferred embodiment is that the angle is less than or equal to 60 degreesb1Less than or equal to 80 degrees, further improves the pneumatic performance of the fan, and reduces the working noise.
In an optional technical scheme of the embodiment, an outlet installation angle of the blade body 1 is betab2And beta is not more than 5 DEGb2Less than or equal to 30 degrees, thus the pneumatic performance of the fan is good, the working noise is low, and the preferred embodiment is that the angle beta is less than or equal to 5 degreesb2Less than or equal to 20 degrees, further improves the pneumatic performance of the fan, and reduces the working noise.
It should be noted that the inlet installation angle of the blade body 1 is: the blade angle at the inlet of the blade body 1 is the included angle between the molded line tangent line at the inlet of the blade body 1 and the circumference tangent line; the outlet mounting angle of the blade body 1 is: the blade angle at the outlet of the blade body 1 is the included angle between the profile tangent and the circumference tangent at the outlet of the blade body 1.
The centrifugal fan comprises the impeller, so that the technical advantages and effects achieved by the centrifugal fan comprise the technical advantages and effects achieved by the impeller, and are not repeated herein.
As shown in fig. 5, in the optional technical solution of this embodiment, the centrifugal scroll casing further includes a centrifugal scroll casing 5, a support 6, and an air guiding ring 7, the impeller is disposed in the centrifugal scroll casing 5, the support 6 is connected to an outer side wall of the scroll casing, an air inlet is disposed on at least one side of the scroll casing, the air guiding ring 7 is disposed at the air inlet, and the support 6 penetrates through the air inlet and is connected to the impeller.
In this embodiment, both sides of the centrifugal volute 5 are provided with air inlets, the air inlets on both sides are provided with the support 6, when the impeller is assembled into the centrifugal volute 5, the impeller can be fixedly connected with the centrifugal volute 5 through the supports 6 arranged on both sides of the centrifugal volute 5, and the centrifugal volute 5 is provided with the air guide ring 7 to play a role in air intake and flow guide.
The range hood provided by the invention comprises the centrifugal fan, so the technical advantages and effects of the range hood comprise the technical advantages and effects of the centrifugal fan, and the technical advantages and effects are not repeated herein.
The invention provides a blade design method, which comprises the following steps:
determining a space curve equation of the arc-shaped pressure surface profile of the blade;
selecting a reference wing profile and determining a space curve equation of the reference wing profile;
and converting the relative thickness distribution of the reference airfoil along the chord length into the same relative thickness distribution of the reference airfoil along the chord length by using a space curve coordinate conversion method, thereby obtaining a space curve equation of the suction surface profile of the blade.
A blade profile design coordinate system is established based on a forward-bent blade design method of a traditional multi-wing centrifugal fan, and a space curve equation f of a suction surface profile is establisheds(x) And the space curve equation of the pressure surface profile is fp(x) The blade profile with good pneumatic performance can be obtained quickly and effectively, and the pneumatic performance of the impeller can be improved.
In an optional technical solution of this embodiment, determining a space curve equation of a circular arc pressure surface profile of the blade includes the following steps:
according to a method for designing a forward-bent blade of a multi-wing centrifugal impeller, determining a circular arc-shaped pressure surface molded line of the blade, wherein two end points of the pressure surface molded line of the blade are respectively a point A and a point B;
establishing an XY rectangular coordinate system by taking the point A as an origin, wherein an X axis is arranged along the extending direction of a connecting line of the point A and the point B, and converting a space curve equation of a pressure surface molded line of the blade into fp(x) The central point of the pressure surface molded line of the blade is O, and the coordinate of the O point is (x)0，y0)。
In an optional technical solution of this embodiment, determining the space curve equation of the reference airfoil includes the following steps:
selecting a reference wing profile of the blade, scaling the reference wing profile according to the chord length proportion, placing the scaled reference wing profile in an XY rectangular coordinate system, enabling the front edge endpoint of the reference wing profile to be positioned on the Y axis, enabling the rear edge endpoint of the reference wing profile to coincide with the point B, and converting a space curve equation of the suction surface molded line of the reference wing profile into fa(x) The space curve equation of the pressure surface profile of the reference airfoil is fb(x)。
In an optional technical solution of this embodiment, converting the relative thickness distribution of the blade along the chord length into the same relative thickness distribution of the reference airfoil along the chord length, so as to obtain the space curve equation of the suction surface profile of the blade includes the following steps:
the point crossing O is taken as a straight line OE, the straight line OE is intersected with the pressure surface molded line of the reference airfoil at the point C, the straight line OE is intersected with the pressure surface molded line AB of the blade at the point D, the point crossing O and the point A are taken as a straight line OA, and the included angle theta between the straight line OE and the straight line OA is thetai(0≤θiTheta) or less), determining the X-axis coordinate value X of the C pointcAccording to fa(x) And fb (X), determining the X-axis coordinate value as XcThe distance between the pressure surface molded line of the time reference airfoil and the suction surface molded line of the time reference airfoil is the length of the line segment CF;
the length of the line segment DE is made the same as that of the line segment CF to determine the coordinate (x) of the point EE，yE)；
Connecting through an included angle thetaiAll the points E are determined to obtain the suction profile line of the cross section of the blade,and the space curve equation f of the profile line of the suction surface of the blades(x)。
The pressure surface molded line of the blade is an arc line, and can be designed according to a design method of a forward-bent blade of a traditional centrifugal multi-wing centrifugal impeller and determined according to the following design parameters: impeller bore R1Outer diameter R of impeller2Inlet setting angle beta of bladeb1Outlet setting angle beta of bladeb2The center angle θ of the blade.
As a further technical solution, the spatial curve equation f of the pressure surface profile of the bladep(x) Comprises the following steps:
Figure BDA0003156940150000191
Rbis the radius of the pressure surface profile AB of the blade, theta is the central angle of the pressure surface profile AB of the blade,
Figure BDA0003156940150000201
the reference airfoil profile is a plano-convex airfoil profile, so that a straight line part in a pressure surface molded line of the reference airfoil profile is coincident with an X axis, and the length of a line segment AC
Figure BDA0003156940150000202
Is the X-axis coordinate value X of the point Cc，
Figure BDA0003156940150000203
The length of the line segment CF is fa(xc) The coordinate (x) of the point E is obtained by making the length of the line segment CF equal to that of the line segment CDE，yE)；
Wherein:
Figure BDA0003156940150000204
Figure BDA0003156940150000205
the lift-drag ratio of the plano-convex airfoil profile is high, the relative thickness of the airfoil profile is between 10% and 20%, and the plano-convex airfoil profile can be any suitable plano-convex airfoil profile such as ClarkY series or NACA44 series.
In this example fa(x) Using cubic polynomial equations
fa(x)＝a1x3+a2x2+a3x+a4
Figure BDA0003156940150000206
Wherein, a1、a2、a3、a4The characteristic coefficient of the equation is determined by the actually selected airfoil space curve.
Further, the method comprises the following step of making an arc line with the front edge endpoint of the reference airfoil as the center of a circle, and respectively tangent with the suction surface molded line of the blade and the pressure surface molded line of the blade at the point A and the point G, wherein the corresponding radius of the arc line is RLEI.e. the leading edge radius of the blade; and making an arc line passing through the point B, wherein the arc line is respectively tangent to the suction surface molded line of the blade and the pressure surface molded line of the blade, and the arc line passing through the point B is the trailing edge of the blade.
The reference airfoil may be a plano-convex airfoil, or may be any suitable form such as a biconvex airfoil or a concave-convex airfoil.
fa(x) And fb(x) Any suitable form of multi-order polynomial, exponential or logarithmic equations may be used.
The blade provided by the invention is designed by the blade design method provided by the invention.
Finally, it should be noted that: the above embodiments are only used to illustrate the technical solution of the present invention, and not to limit the same; while the invention has been described in detail and with reference to the foregoing embodiments, it will be understood by those skilled in the art that: the technical solutions described in the foregoing embodiments may still be modified, or some or all of the technical features may be equivalently replaced; and the modifications or the substitutions do not make the essence of the corresponding technical solutions depart from the scope of the technical solutions of the embodiments of the present invention.

Claims (22)

1. A blade is characterized by comprising a blade body (1), wherein the blade body (1) comprises a first front edge, a first pressure surface, a first rear edge and a first suction surface which are sequentially connected end to end, the first pressure surface is provided with a first pressure surface molded line (12), the first suction surface is provided with a first suction surface molded line (11), and the first pressure surface molded line (12) is a circular arc curve;
setting a reference airfoil profile, wherein the airfoil profile is in a section shape parallel to the symmetrical plane of the aircraft on the aircraft wing, and the relative thickness distribution of the blade body (1) along the chord length is the same as that of the reference airfoil profile along the chord length.
2. Blade according to claim 1, characterized in that at least one of the two ends of the blade body (1) in the direction of the blade height is provided with a leakage prevention structure for reducing the leakage flow.
3. The blade of claim 2, wherein the leakage prevention structure comprises a winglet (15), the winglet (15) comprising, connected in series end to end, a second leading edge (153), a second pressure face (152), a second trailing edge, and a second suction face (151).
4. The blade of claim 3, wherein the first pressure surface is flush with the second pressure surface (152), the first trailing edge is flush with the second trailing edge, and the first suction surface is flush with the second suction surface (151);
the second front edge (153) is located on one side of the first front edge facing the first rear edge, and a gap is arranged between the first front edge and the second front edge (153), and the length of the gap is L.
5. Blade according to claim 4, characterized in that the chord length of the blade body (1) is M and 0.2. ltoreq. L/M. ltoreq.0.6;
and/or the height between two ends of the winglet (15) along the height direction is h, and h/M is more than or equal to 0.1 and less than or equal to 0.4.
6. The blade of claim 4, wherein the thickness and shape of the blade body (1) at the first leading edge is the same as the thickness and shape of the winglet (15) at the second leading edge (153).
7. Blade according to any of claims 1-6, characterized in that the blade body (1) is convex outwards forming the first leading edge, which has a first leading edge profile (13), the end points of both ends of the first leading edge profile (13) forming an obtuse angle with a point line on the first leading edge profile (13).
8. Blade according to claim 7, characterized in that the first leading edge profile (13) is a circular arc curve and the first pressure surface profile (12) and the first suction surface profile (11) are tangent to the first leading edge profile (13), respectively.
9. The blade according to any of the claims 1 to 6, characterized in that the blade body (1) bulges outwards forming the first trailing edge with a first trailing edge profile (14), the end points of both ends of the first trailing edge profile (14) forming an obtuse angle with a point line on the first trailing edge profile (14).
10. The blade according to claim 9, wherein the first trailing edge profile (14) is a circular arc curve, and the first pressure surface profile (12) and the first suction surface profile (11) are tangent to the first trailing edge profile (14), respectively.
11. A blade according to any of claims 1-6, characterized in that the angle between the normal of the profile at the inlet of the blade body (1) and the normal of the profile at the outlet of the blade body (1) is a central angle θ, and θ >90 °.
12. An impeller comprising a plurality of blades according to any one of claims 1 to 11, the plurality of blades being evenly spaced in the circumferential direction of the impeller;
the novel stator blade is characterized by further comprising a first end ring (2) and a second end ring (4), wherein the first end ring (2) is opposite to the second end ring (4) and is arranged at a distance, and the blade is connected to the first end ring (2) and the second end ring (4) and is positioned between the first end ring (2) and the second end ring (4).
13. The impeller according to claim 12, further comprising a central disc (3), the central disc (3) being disposed between the first end ring (2) and the second end ring (4) with gaps formed between the first end ring (2) and the second end ring (4), respectively;
the vanes are arranged between the first end ring (2) and the middle disc (3), one ends of the vanes are connected with the first end ring (2), and the other ends of the vanes are connected with the middle disc (3);
the vanes are arranged between the second end ring (4) and the middle disc (3), one end of each vane is connected with the second end ring (4), and the other end of each vane is connected with the middle disc (3).
14. The impeller according to claim 13, characterized in that the vanes between the first end ring (2) and the central disc (3) and the vanes between the second end ring (4) and the central disc (3) are arranged symmetrically or staggered with respect to the central disc (3).
15. The impeller according to claim 12, characterized in that the angle between the tangent of the profile at the inlet of the blade body (1) and the tangent of the circumference of the impeller is the inlet setting angle βb1And beta is not more than 50 DEGb1≤90°；
And/or the included angle between the tangent line of the molded line at the outlet of the blade body (1) and the tangent line of the circumference of the impeller is beta as an outlet installation angleb2And beta is not more than 5 DEGb2≤30°。
16. A centrifugal fan comprising an impeller according to any one of claims 12 to 15.
17. A range hood comprising the centrifugal fan of claim 16.
18. A method of designing a blade, comprising the steps of:
determining a space curve equation of the arc-shaped pressure surface profile of the blade;
selecting a reference wing profile and determining a space curve equation of the reference wing profile;
and converting the relative thickness distribution of the reference airfoil along the chord length into the same relative thickness distribution of the reference airfoil along the chord length by using a space curve coordinate conversion method, thereby obtaining a space curve equation of the suction surface profile of the blade.
19. The method of claim 18, wherein determining the spatial profile equation for the radiused pressure face profile of the blade comprises the steps of:
according to a method for designing a forward-bent blade of a multi-wing centrifugal impeller, determining a circular arc-shaped pressure surface molded line of the blade, wherein two end points of the pressure surface molded line of the blade are respectively a point A and a point B;
establishing an XY rectangular coordinate system by taking the point A as an origin, wherein an X axis is arranged along the extending direction of a connecting line of the point A and the point B, and converting a space curve equation of a pressure surface molded line of the blade into fp(x) The central point of the pressure surface molded line of the blade is O, and the coordinate of the O point is (x)0，y0)。
20. The blade design method of claim 19, wherein determining the spatial curve equation for the reference airfoil comprises the steps of:
selecting a reference airfoil profile of the blade, and carrying out referenceThe reference wing profile is placed in an XY rectangular coordinate system after being scaled according to the chord length proportion, the front edge endpoint of the reference wing profile is positioned on the Y axis, the rear edge endpoint of the reference wing profile is coincided with the point B, and the space curve equation of the suction surface molded line of the reference wing profile is converted into fa(x) The space curve equation of the pressure surface profile of the reference airfoil is fb(x)。
21. A method for designing a blade according to claim 20, wherein the step of scaling the relative thickness distribution of the blade along the chord length to be the same as the relative thickness distribution of the reference airfoil along the chord length to obtain the spatial curve equation of the suction surface profile of the blade comprises the steps of:
the point crossing O is taken as a straight line OE, the straight line OE is intersected with the pressure surface molded line of the reference airfoil at the point C, the straight line OE is intersected with the pressure surface molded line AB of the blade at the point D, the point crossing O and the point A are taken as a straight line OA, and the included angle theta between the straight line OE and the straight line OA is thetai(0≤θiTheta) or less), determining the X-axis coordinate value X of the C pointcAccording to fa(x) And fb (X), determining the X-axis coordinate value as XcThe distance between the pressure surface molded line of the time reference airfoil and the suction surface molded line of the time reference airfoil is the length of the line segment CF;
the length of the line segment DE is made the same as that of the line segment CF to determine the coordinate (x) of the point EE，yE)；
Connecting through an included angle thetaiAll the points E are determined to obtain the suction surface profile of the cross section of the blade and the space curve equation f of the suction surface profile of the blades(x)。
22. A method of designing a blade according to claim 21, characterised in that the spatial curve equation f of the pressure surface profile of the bladep(x) Comprises the following steps:
Figure FDA0003156940140000051
Rbis the radius of the pressure surface profile AB of the blade, theta is the central angle of the pressure surface profile AB of the blade,
Figure FDA0003156940140000052
the reference airfoil profile is a plano-convex airfoil profile, so that a straight line part in a pressure surface molded line of the reference airfoil profile is coincident with an X axis, and the length of a line segment AC
Figure FDA0003156940140000053
Is the X-axis coordinate value X of the point Cc，
Figure FDA0003156940140000054
The length of the line segment CF is fa(xc) The coordinate (x) of the point E is obtained by making the length of the line segment CF equal to that of the line segment CDE，yE)；
Wherein:
Figure FDA0003156940140000055
Figure FDA0003156940140000056
CN202110779049.1A 2021-07-09 2021-07-09 Blade, impeller, centrifugal fan, range hood and blade design method Pending CN113309736A (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
CN202110779049.1A CN113309736A (en) 2021-07-09 2021-07-09 Blade, impeller, centrifugal fan, range hood and blade design method

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
CN202110779049.1A CN113309736A (en) 2021-07-09 2021-07-09 Blade, impeller, centrifugal fan, range hood and blade design method

Publications (1)

Publication Number Publication Date
CN113309736A true CN113309736A (en) 2021-08-27

Family

ID=77381474

Family Applications (1)

Application Number Title Priority Date Filing Date
CN202110779049.1A Pending CN113309736A (en) 2021-07-09 2021-07-09 Blade, impeller, centrifugal fan, range hood and blade design method

Country Status (1)

Country Link
CN (1) CN113309736A (en)

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN114198324A (en) * 2021-12-10 2022-03-18 西安交通大学 Multi-element coupling centrifugal fan collector, centrifugal fan and preparation method of centrifugal fan collector
CN114491868A (en) * 2022-02-14 2022-05-13 西安交通大学 Rapid design method for multi-wing centrifugal fan wing-shaped blade impeller
CN114483648A (en) * 2022-01-27 2022-05-13 杭州老板电器股份有限公司 Blade design method, blade and centrifugal fan

Cited By (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN114198324A (en) * 2021-12-10 2022-03-18 西安交通大学 Multi-element coupling centrifugal fan collector, centrifugal fan and preparation method of centrifugal fan collector
CN114483648A (en) * 2022-01-27 2022-05-13 杭州老板电器股份有限公司 Blade design method, blade and centrifugal fan
CN114483648B (en) * 2022-01-27 2024-04-09 杭州老板电器股份有限公司 Blade design the method is blade and centrifugal fan
CN114491868A (en) * 2022-02-14 2022-05-13 西安交通大学 Rapid design method for multi-wing centrifugal fan wing-shaped blade impeller
CN114491868B (en) * 2022-02-14 2024-02-13 西安交通大学 Quick design method for airfoil blade impeller of multi-wing centrifugal fan

Similar Documents

Publication Publication Date Title
CN113309736A (en) Blade, impeller, centrifugal fan, range hood and blade design method
US11506211B2 (en) Counter-rotating fan
AU2007209185A1 (en) Improved impeller and fan
WO2021208496A1 (en) Mixed flow wind wheel, fan assembly, power system, and fan
CN113719471A (en) Noise-reduction centrifugal impeller with bionic type trailing edge blades for breathing machine
CN108412809A (en) A kind of baffle liner, centrifugal blower and air conditioner
CN113738694B (en) High-performance centrifugal impeller of breathing machine with round head-shaped front edge blade profile
CN113266592A (en) Blade, impeller and fan
CN111878455A (en) Centrifugal impeller, centrifugal fan and refrigeration equipment
CN215293004U (en) Blade, impeller, centrifugal fan and range hood
CN216044508U (en) Blade, impeller and centrifugal fan
CN114483648B (en) Blade design the method is blade and centrifugal fan
CN215719605U (en) Blade, impeller and centrifugal fan
CN216447178U (en) Backward centrifugal fan
CN114370428A (en) Fan blade and centrifugal fan
CN215762421U (en) Centrifugal fan blade, fan and air conditioning system comprising same
CN115263775A (en) High mach number centrifugal compressor model stage
CN113738695A (en) High-performance centrifugal impeller with parabolic front edge blades for breathing machine
CN114718904A (en) Pneumatic structure, compressor, dust catcher
WO2019006971A1 (en) Impeller, fan and motor
CN108953222B (en) Centrifugal impeller
CN209704915U (en) Centrifugation blade, courtyard machine and the air-conditioning system with it
CN215860865U (en) Blade, impeller and fan
CN113550930A (en) Centrifugal fan blade, fan and air conditioning system comprising same
CN216767853U (en) Fan blade and centrifugal fan

Legal Events

Date Code Title Description
PB01 Publication
PB01 Publication
SE01 Entry into force of request for substantive examination
SE01 Entry into force of request for substantive examination