CN113309736B - Blade, impeller, centrifugal fan, range hood and blade design method - Google Patents

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

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Publication number
CN113309736B
CN113309736B CN202110779049.1A CN202110779049A CN113309736B CN 113309736 B CN113309736 B CN 113309736B CN 202110779049 A CN202110779049 A CN 202110779049A CN 113309736 B CN113309736 B CN 113309736B
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China
Prior art keywords
blade
pressure surface
line
profile
point
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CN113309736A (en
Inventor
任富佳
鲍明
郑桐福
孟君
余国成
周海昕
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Hangzhou Robam Appliances Co Ltd
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Hangzhou Robam Appliances Co Ltd
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    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • 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

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)

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 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 connected end to end in sequence, the first pressure surface is provided with a first pressure surface molded line, the first suction surface is provided with a first suction surface molded line, and the first pressure surface molded line is an arc curve; the reference airfoil is set, and the relative thickness distribution of the blade body along the chord length is the same as the relative thickness distribution of the reference airfoil along the chord length. The blade body is equivalent to the relative thickness of the reference wing profile selected by the single-side superposition of the circular arc plate blade on the pressure surface, has the aerodynamic characteristics of the set reference wing profile, can obviously enhance the flow control on the suction surface, effectively reduce the degree of flow separation generated in the impeller flow channel, improve the working efficiency of the centrifugal impeller and reduce the vortex noise.

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-wing centrifugal fans adopt a circular arc plate vane type centrifugal impeller structure. When the impeller rotates to work, the internal moving airflow is influenced by the fluid viscosity effect, the reverse pressure gradient and the rotating coriolis force to easily generate flow separation, so that secondary vortex is formed, the working efficiency of the impeller is low, and the aerodynamic performance and the working noise of the fan are directly influenced.
In order to solve the problems, the prior art adopts a multi-wing centrifugal impeller structure with wing blades, and the impeller can improve the flow characteristics in an impeller flow channel to a certain extent. When designing airfoil blades, a method of superposing conventional symmetrical airfoil thicknesses on both sides of a camber line is generally adopted.
According to the basic internal flow theory of the centrifugal impeller, flow separation in the impeller channel mostly occurs on the suction surface side, and the aerodynamic characteristics of the wing profile determine that the maximum relative thickness of the selected wing profile cannot be too large, so that the wing profile blades obtained by the design method of overlapping the wing profile thicknesses on two sides have insufficient control over the gas flow on the suction surface in the runner, 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 connected end to end in sequence, the first pressure surface is provided with a first pressure surface molded line, the first suction surface is provided with a first suction surface molded line, and the first pressure surface molded line is an arc curve;
And setting a reference airfoil, wherein the airfoil is in a cross-sectional shape parallel to the symmetrical plane of the aircraft on the wing of the aircraft, and 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.
As a further technical solution, at least one of the two ends of the blade body in the blade height direction is provided with a leakage preventing structure for reducing the leakage flow rate.
As a further technical scheme, the leakage-proof structure comprises a small blade tip wing, wherein the small blade tip wing comprises a second front edge, a second pressure surface, a second rear 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, which faces the first rear edge, and a space is arranged between the first front edge and the second front edge, and the length of the space 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 of the blade is h, and h/M is more than or equal to 0.1 and less than or equal to 0.4.
As a further technical solution, 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 scheme, the blade body protrudes outwards to form the first front edge, the first front edge is provided with a first front edge molded line, and an obtuse angle is formed between the end points of the two ends of the first front edge molded line and a point connecting line on the first front edge molded line.
As a further technical scheme, the first leading edge molded line is a circular arc curve, and the first pressure surface molded line and the first suction surface molded line are respectively tangent with the first leading edge molded line.
As a further technical scheme, the blade body protrudes outwards to form the first trailing edge, the first trailing edge is provided with a first trailing edge molded line, and an obtuse angle is formed between the end points of the two ends of the first trailing edge molded line and a point connecting line on the first trailing edge molded line.
As a further technical scheme, the first trailing edge molded line is a circular arc curve, and the first pressure surface molded line and the first suction surface molded line are respectively tangent to the first trailing edge molded line.
As a further technical scheme, an included angle is formed between the normal line of the molded line at the inlet of the blade body and the normal line of the molded line at the outlet of the blade body, wherein the included angle is a central angle theta, and theta is more than 90 degrees.
The impeller comprises the blades, wherein a plurality of the blades are uniformly arranged at intervals along the circumferential direction of the impeller;
and also 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 intervals, the blades are connected to and located between the first end ring and the second end ring.
As a further technical scheme, the device 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 plate, one end of each blade is connected with the first end ring, and the other end of each blade is connected with the middle plate;
the blades are arranged between the second end ring and the middle plate, one ends of the blades are connected with the second end ring, and the other ends of the blades are connected with the middle plate.
As a further technical solution, the blades between the first end ring and the middle disk and the blades between the second end ring and the middle disk are symmetrically arranged or mutually staggered with respect to the middle disk.
As a further technical scheme, the included angle between the tangent line of the molded line at the inlet of the blade body and the tangent line of the circumference of the impeller is an inlet mounting angle beta b1, and beta b1 is more than or equal to 50 degrees and less than or equal to 90 degrees;
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 b2 degrees, and beta b2 degrees are more than or equal to 5 degrees and less than or equal to 30 degrees.
The centrifugal fan provided by the invention comprises the impeller.
The invention provides a range hood, which comprises the centrifugal fan.
The invention provides a blade design method, which comprises the following steps:
determining a space curve equation of a circular arc pressure surface molded line of the blade;
Selecting a reference airfoil, and determining a space curve equation of the reference airfoil;
And converting the relative thickness distribution of the reference airfoil along the chord length, and 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 by using a space curve coordinate conversion method, thereby obtaining a space curve equation of the suction surface molded line of the blade.
As a further technical solution, the space curve equation for determining the circular arc pressure surface profile of the blade comprises the following steps:
determining a circular arc pressure surface molded line of the blade according to a forward bending blade design method of the multi-wing centrifugal impeller, wherein two end points of the pressure surface molded line of the blade are respectively a point A and a point B;
And (3) 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 the connecting line of the point A and the point B, a space curve equation of the pressure surface molded line of the blade is calculated to be f p (X), the center point of the pressure surface molded line of the blade is O, and the coordinate of the point O is (X 0,y0).
As a further technical solution, determining the space curve equation of the reference airfoil profile comprises the following steps:
and selecting a reference airfoil of the blade, scaling the reference airfoil according to the chord length, placing the reference airfoil in an XY rectangular coordinate system, enabling the front edge end point of the reference airfoil to be positioned on a Y axis, enabling the rear edge end point of the reference airfoil to coincide with a point B, converting a space curve equation of a suction surface molded line of the reference airfoil into f a (x), and converting a space curve equation of a pressure surface molded line of the reference airfoil into f b (x).
As a further technical solution, converting the relative thickness distribution of the blade along the chord length into the same relative thickness distribution along the chord length as the reference airfoil, thereby obtaining a space curve equation of the suction surface profile of the blade, comprising the following steps:
The method comprises the steps of making a straight line OE through an O point, intersecting the straight line OE with a pressure surface molded line of a reference airfoil at a C point, intersecting the straight line OE with a pressure surface molded line AB of a blade at a D point, making a straight line OA through the O point and the A point, wherein the included angle between the straight line OE and the straight line OA is theta i(0≤θi -theta or less, determining an X-axis coordinate value X c of the C point, and determining the distance between the pressure surface molded line of the reference airfoil and a suction surface molded line of the reference airfoil, namely the length of a line segment CF when the X-axis coordinate value is X c according to f a (X) and fb (X);
Making the length of the line segment DE identical to the length of the line segment CF to determine the coordinates (x E,yE) of the E point;
All E points determined by the included angle θ i are connected to obtain the suction side profile of the blade cross section, and the space curve equation f s (x) for the suction side profile of the blade.
As a further technical solution, the space curve equation f p (x) of the pressure surface profile of the blade is:
R b is the radius of the pressure surface line AB of the blade, θ is the center angle of the pressure surface line AB of the blade,
The reference airfoil is a plano-convex airfoil, the straight line part in the pressure surface molded line of the reference airfoil is coincided with the X axis, and the length of the line segment ACNamely the X-axis coordinate value X c of the C point,
At this time, the length of the line segment CF is f a(xc), so that the length of the line segment CF is equal to the length of the line segment CD to obtain the coordinate (x E,yE) of the E point;
Wherein:
compared with the prior art, the blade provided by the invention has the technical advantages that:
The blade 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 connected end to end in sequence, the first pressure surface is provided with a first pressure surface molded line, the first suction surface is provided with a first suction surface molded line, and the first pressure surface molded line is an arc curve; the reference airfoil profile is set, the airfoil profile is a cross 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 the relative thickness distribution 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 the relative thickness distribution of the reference airfoil along the chord length, and the first pressure surface molded line is set to be an arc curve, namely, the first pressure surface molded line is the same as the pressure surface molded line 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 molded line is determined. Since flow separation in the impeller channel mostly occurs on the suction side, and the aerodynamic properties of the airfoil in turn determine that the maximum relative thickness of the selected airfoil cannot be exceeded, while such a blade body has the aerodynamic properties of the set reference airfoil, the maximum relative thickness of the reference airfoil 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 the 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 that are needed in the description of the embodiments or the prior art will be briefly described, and it is obvious that the drawings in the description below are some embodiments of the present invention, and other drawings can be obtained according to the drawings without inventive effort for a person skilled in the art.
FIG. 1 is a graph showing a vane profile provided by an embodiment of the present invention;
FIG. 2 is a schematic view of a blade according to an embodiment of the present invention;
FIG. 3 is a schematic view of a blade with winglets according to an embodiment of the present invention;
fig. 4 is a schematic structural diagram of an impeller according to an embodiment of the present invention;
FIG. 5 is an assembly view of an impeller according to an embodiment of the present invention;
fig. 6 is a partial enlarged view of fig. 5.
Icon: 1-a blade body; 11-a first suction surface profile; 12-a first pressure surface profile; 13-a first leading edge profile; 14-a first trailing edge profile; 15-winglet; 151-a second suction side; 152-a second pressure surface; 153-a second leading edge; 2-a first end ring; 3-middle plate; 4-a second end ring; 5-centrifuging the volute; 6-a bracket; 7-wind guiding ring.
Detailed Description
The technical solutions of the present invention will be clearly and completely described in connection with the embodiments, and it is apparent that the described embodiments are some embodiments of the present invention, but not all embodiments. All other embodiments, which can be made by those skilled in the art based on the embodiments of the invention without making any inventive effort, are intended to be within the scope of the invention.
In the description of the present invention, it should be noted that the directions or positional relationships indicated by the terms "center", "upper", "lower", "left", "right", "vertical", "horizontal", "inner", "outer", etc. are based on the directions or positional relationships shown in the drawings, are merely for convenience of describing the present invention and simplifying the description, and do not indicate or imply that the devices or elements referred to must have a specific orientation, be configured and operated in a specific 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 explicitly specified and limited otherwise, the terms "mounted," "connected," and "connected" are to be construed broadly, and may be either fixedly connected, detachably connected, or integrally connected, for example; can be mechanically or electrically connected; can be directly connected or indirectly connected through an intermediate medium, and can be communication between two elements. The specific meaning of the above terms in the present invention will be understood in specific cases by those of ordinary skill in the art.
In addition, the technical solutions of the embodiments may be combined with each other, but it is necessary to base that the technical solutions can be realized by those skilled in the art, and when the technical solutions are contradictory or cannot be realized, the combination of the technical solutions should be considered to be absent and not within the scope of protection claimed in the present invention.
The invention will now be described in further detail with reference to specific examples thereof in connection with the accompanying 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;
The reference airfoil profile is set, the airfoil profile is a section profile 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 the relative thickness distribution of the reference airfoil profile along the chord length.
Compared with the arc plate blades in the prior art, the airfoil blade is generally formed by superposing conventional symmetrical airfoil thicknesses on two sides of a camber line, and an airfoil scheme with an excessively large maximum relative thickness cannot be generally selected because the lift-drag ratio characteristic of the airfoil is directly related to the maximum relative thickness of the airfoil. Moreover, according to the basic internal flow theory of the centrifugal impeller, the moving airflow in the impeller runner is influenced by the fluid viscosity effect, the reverse pressure gradient and the rotating coriolis force, so that the flow separation is easy to generate and 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 the pressure on the suction surface, namely the reverse pressure gradient on the suction surface of the blade is more obvious, so that the flow separation in the impeller flow channel mostly occurs on the suction surface side. Therefore, the airfoil blade obtained by the design method of overlapping airfoil thickness at two sides has insufficient control over the gas flow on the suction surface in the flow channel, so that the impeller efficiency is not sufficiently improved.
According to the blade provided by the embodiment, as the relative thickness distribution of the blade body 1 along the chord length is the same as the relative thickness distribution of the reference airfoil along the chord length, and the first pressure surface molded line 12 is set to be an arc curve, namely, the first pressure surface molded line 12 is the same as the pressure surface molded line 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 molded line 11 is determined, and the blade body 1 is compared with the arc plate blade, only the shape of the first suction surface is different from the suction surface shape of the arc plate blade, namely, the first suction surface molded line 11 is different from the suction surface molded line of the arc plate blade, so that the blade body 1 is equivalent to the relative thickness of the reference airfoil selected by single-side superposition of the arc plate blade on the pressure surface.
The flow separation in the impeller flow channel mostly occurs on 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, so that the maximum relative thickness of the reference wing profile is reduced to the maximum extent while the blade body 1 has the aerodynamic characteristics of the set reference wing profile, the flow control on the suction surface can be obviously enhanced, the degree of flow separation 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 cross-sectional shape of an aircraft wing parallel to the plane of symmetry of the aircraft is also known as the airfoil profile or blade profile.
The suction surface molded line of the airfoil is the molded line of the upper surface of the airfoil, and the pressure surface molded line of the airfoil is the molded line of the lower surface of the airfoil.
Airfoil relative thickness: perpendicular to the chord line, the maximum distance of the upper and lower curves is divided by the chord length, and is referred to as the relative thickness.
In the alternative technical scheme of this embodiment, at least one of the two ends of blade body 1 along the leaf height direction is provided with the leak protection structure, leak protection structure is used for reducing leakage flow, in this embodiment, the exhibition direction of blade body 1 is leaf height direction, also can understand that the length direction of blade body 1 is leaf height direction, the maximum cross-sectional area of the leak protection structure of setting up at blade body 1 tip is less than the area of the leaf section of blade body 1 tip rather than corresponding, so, after the impeller that comprises a plurality of blade bodies 1 is installed in the spiral case, form the cavity between tip and the wind-guiding circle 7 of impeller, leak protection structure along the circumference removal of this cavity along with the rotation of impeller, can form certain pressure in this cavity and can reduce leakage, further promoted the pneumatic performance of fan, reduce operating noise.
The preferred both ends of this embodiment along the leaf height direction of blade body 1 all set up in having the leak protection structure, so, the entrance point and the exit end of blade body 1 all can reduce or avoid leaking the flow, promotes pneumatic effect.
In the alternative technical scheme of this embodiment, the tip of blade body 1 continues to extend and forms the extension, and the cross-sectional area that extension and blade section are parallel diminishes along extending direction gradually, and the extension forms leak protection structure and with blade body integrated into one piece, simple structure, and manufacturing is convenient, and structural strength is high. The present embodiment is not limited thereto, and the extension may be interconnected with the blade body as separate two parts.
As shown in fig. 3, fig. 4, and fig. 6, in an alternative solution of this embodiment, the leakage preventing structure includes a winglet 15, where 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, the winglet 15 may be understood as a blade structure smaller than the blade body 1, and the winglet 15 itself has better aerodynamic performance, and reduces the influence on the aerodynamic performance of the blade body 1 while reducing the leakage flow.
In addition, after the tip winglet 15 is adopted, the inlet diameter of the wind guide ring 7 can be further enlarged, and the aerodynamic performance of the fan can be further improved under the condition of keeping the leakage prevention capability.
Wherein, the outer contour dimension of the winglet 15 is smaller than that of the blade body 1, and the outer contour of the winglet 15 is similar to that of the blade body 1.
As shown in fig. 3, in an alternative solution of the present embodiment, 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 at 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 parts of the winglet 15 and the blade body 1 have the same thickness, so as to ensure the aerodynamic performance of the whole blade. Meanwhile, the second front edge 153 is located at one side of the first front edge facing the first rear edge, and a space is arranged between the first front edge and the second front edge 153, so that a cavity is formed between the end part of the impeller and the air guide ring 7, and leakage is reduced.
In an alternative solution of this embodiment, the maximum distance between the first leading edge and the second leading edge of the blade body 1 is the chord length M, i.e. the width of the blade body 1, and 0.2L/M is less than or equal to 0.6. Thus, the air performance of the fan is good, the working noise is low, the preferable L/M is less than or equal to 0.3 and less than or equal to 0.5, the air performance of the fan is further improved, and the working noise is reduced.
As shown in FIG. 3, in the alternative technical scheme of the embodiment, the height between two ends of the winglet 15 along the height direction of the blade is h, and h/M is more than or equal to 0.1 and less than or equal to 0.4, so that the aerodynamic performance of the fan is good, the working noise is low, and the preferred embodiment is that L/h is more than or equal to 0.1 and less than or equal to 0.3, so that the aerodynamic performance of the fan is further improved, and the working noise is low.
In an alternative solution of this embodiment, 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, i.e. the profile of the second leading edge 153 is the same as the shape and size of the first leading edge profile 13, so that the first leading edge and the second leading edge 153 have the same aerodynamic performance, and noise is reduced.
In the alternative technical scheme of this embodiment, the blade body 1 has tip winglet 15 along the equal integrated into one piece in both ends of leaf height direction, and tip winglet 15 and blade body 1 integrated into one piece are convenient for make, have the same intensity, form the cavity between the equal and wind-guiding circle 7 in both ends of blade body 1 simultaneously, further reduce leakage, symmetrical structure simultaneously makes the whole atress of blade balanced.
It should be noted that, the blade body 1 and the winglet 15 may be two separate components connected to each other, and the winglet 15 may be disposed at one end of the blade body 1.
In an alternative solution of this embodiment, the blade body 1 protrudes outwards to form a first leading edge, where the first leading edge has a first leading edge profile 13, and an obtuse angle is formed between the end points of the two ends of the first leading edge profile 13 and the point connection line on the first leading edge profile 13.
In this embodiment, the first leading edge adopts blunt leading edge structure, and when the fan operation is under different inlet air flow operating modes, the first leading edge that has blunt leading edge structure can still keep less impact loss in the scope of great inlet air attack angle to make the impeller keep higher work efficiency, can widen the high-efficient operation interval of fan, promote the performance of range hood under different user operating modes.
The curvature of the blunt front edge structure is larger than that of the sharp front edge structure, and the shape of the blunt front edge structure is more round and blunt.
As shown in fig. 1 and fig. 2, in an alternative solution of this embodiment, 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 respectively tangent to the first leading edge profile 13, so that the circular arc curve is smoother, and the noise generated when contacting with air is smaller.
In an alternative technical solution of this embodiment, the blade body 1 protrudes outwards to form a first trailing edge, the first trailing edge has a first trailing edge molded line 14, an obtuse angle is formed between the end points of two ends of the first trailing edge molded line 14 and a point connecting line on the first trailing edge molded line 14, in this embodiment, a blunt trailing edge structure is adopted, and the blunt trailing edge structure has the same effect as the blunt leading edge structure, and is not repeated here.
In an alternative technical solution of this embodiment, 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 respectively tangent to the first trailing edge profile 14, the circular arc curve is smoother, and noise generated when contacting with air is smaller.
In this embodiment, the first leading edge may be a blunt leading edge structure, and the first trailing edge may be a sharp trailing edge structure; the first front edge can also adopt 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; alternatively, the first leading edge adopts a sharp leading edge structure, and the first trailing edge adopts a blunt trailing edge structure.
As shown in fig. 2, in the alternative solution of this embodiment, the first pressure surface profile 12 has a central angle θ, and θ >90 °, so that the blade has better aerodynamic performance and lower noise under such central angle.
The center angle of the blade body 1 is: the angle between the normal of the line at the inlet of the blade body 1 and the normal of the line at the outlet of the blade body 1.
The impeller provided by the embodiment of the invention comprises the blades, the blades are uniformly arranged at intervals along the circumferential direction of the impeller, namely, the same flow channels are arranged between the adjacent blades, when the impeller rotates, the air flow in each flow channel is the same, the noise is reduced, and meanwhile, the impeller provided by the embodiment adopts the blades, so that the technical advantages and effects achieved by the impeller comprise the technical advantages and effects achieved by the blades, and the technical advantages and effects are not repeated here.
As shown in fig. 4, in an alternative solution of this embodiment, the device further includes a first end ring 2 and a second end ring 4, where the first end ring 2 is opposite to and spaced from the second end ring 4, and the blades are connected to the first end ring 2 and the second end ring 4 and located between the first end ring 2 and the second end ring 4. One end of the vane is connected to the first end ring 2 and the other end is connected to the second end ring 4.
In an alternative technical scheme of the embodiment, the motor further comprises a middle disc 3, wherein the middle disc 3 is connected with the transmission motor, the middle disc 3 is arranged between the first end ring 2 and the second end ring 4, and gaps are formed between the middle disc 3 and the first end ring 2 and between the middle disc and the second end ring 4 respectively;
Blades are arranged between the first end ring 2 and the middle disc 3, one ends of the blades are connected with the first end ring 2, and the other ends of the blades are connected with the second end ring 4;
blades are arranged between the second end ring 4 and the middle plate 3, one ends of the blades are connected with the second end ring 4, and the other ends of the blades are connected with the middle plate 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 with respect to the middle disc 3, so that the blades on two sides of the middle disc 3 are on a straight line, or are arranged in a staggered manner on two sides of the middle disc 3, preferably, one blade on one side of the middle disc 3 is located at the middle position of two adjacent blades on the other side of the middle disc 3, and thus, central angles between the adjacent blades in 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 the alternative technical scheme of the embodiment, the inlet mounting angle of the blade body 1 is beta b1, and the angle of the inlet mounting angle is 50 degrees or more and less than or equal to beta b1 degrees or less than or equal to 90 degrees, so that the air-moving performance of the fan is good, the working noise is low, and the preferred angle of the embodiment is 60 degrees or less and less than or equal to beta b1 degrees or less, the air-moving performance of the fan is further improved, and the working noise is low.
In the alternative technical scheme of the embodiment, the outlet mounting angle of the blade body 1 is beta b2, and the angle beta b2 is more than or equal to 5 degrees and less than or equal to 30 degrees, so that the air-powered performance of the fan is good, the working noise is low, the preferred angle beta b2 is more than or equal to 5 degrees and less than or equal to 20 degrees, the air-powered performance of the fan is further improved, and the working noise is low.
The inlet mounting angle of the blade body 1 is: the blade angle at the inlet of the blade body 1, namely the included angle between the molded line tangent line and the circumference tangent line at the inlet of the blade body 1; the outlet mounting angle of the blade body 1 is: the blade angle at the outlet of the blade body 1, namely the included angle between the line tangent and the circumference tangent at the outlet of the blade body 1.
The centrifugal fan provided by the invention 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 the technical advantages and effects are not repeated here.
As shown in fig. 5, in an alternative technical scheme of the embodiment, the centrifugal volute 5, the bracket 6 and the air guide ring 7 are further included, the impeller is arranged in the centrifugal volute 5, the bracket 6 is connected to the outer side wall of the volute, an air inlet is formed in at least one side of the volute, the air guide ring 7 is arranged at the air inlet, and the bracket 6 penetrates through the air inlet to be connected with the impeller.
In this embodiment, the both sides of centrifugal spiral case 5 all are provided with the air intake, and the air intake department of both sides all is provided with support 6, and the impeller can be through support 6 and centrifugal spiral case 5 fixed connection that centrifugal spiral case 5 both sides were arranged when assembling in centrifugal spiral case 5, sets up wind-guiding circle 7 on the centrifugal spiral case 5 to play the effect of intake water conservancy diversion.
The range hood provided by the invention comprises the centrifugal fan, so that the technical advantages and effects achieved by the range hood comprise the technical advantages and effects achieved by the centrifugal fan, and are not repeated here.
The invention provides a blade design method, which comprises the following steps:
determining a space curve equation of a circular arc pressure surface molded line of the blade;
Selecting a reference airfoil, and determining a space curve equation of the reference airfoil;
And converting the relative thickness distribution of the reference airfoil along the chord length, and 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 by using a space curve coordinate conversion method, thereby obtaining a space curve equation of the suction surface molded line of the blade.
A blade profile design coordinate system is established based on a forward bending type blade design method of a traditional multi-wing centrifugal fan, and a blade profile with good aerodynamic performance can be quickly and effectively obtained by constructing a space curve equation f s (x) of a suction surface profile and a space curve equation f p (x) of a pressure surface profile, so that the aerodynamic performance of an impeller can be improved.
In an alternative solution of this embodiment, determining a space curve equation of a circular arc pressure surface profile of the blade includes the following steps:
determining a circular arc pressure surface molded line of the blade according to a forward bending blade design method of the multi-wing centrifugal impeller, wherein two end points of the pressure surface molded line of the blade are respectively a point A and a point B;
And (3) 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 the connecting line of the point A and the point B, a space curve equation of the pressure surface molded line of the blade is calculated to be f p (X), the center point of the pressure surface molded line of the blade is O, and the coordinate of the point O is (X 0,y0).
In an alternative solution of this embodiment, determining the space curve equation of the reference airfoil includes the following steps:
and selecting a reference airfoil of the blade, scaling the reference airfoil according to the chord length, placing the reference airfoil in an XY rectangular coordinate system, enabling the front edge end point of the reference airfoil to be positioned on a Y axis, enabling the rear edge end point of the reference airfoil to coincide with a point B, converting a space curve equation of a suction surface molded line of the reference airfoil into f a (x), and converting a space curve equation of a pressure surface molded line of the reference airfoil into f b (x).
In an alternative solution of this embodiment, converting the relative thickness distribution of the blade along the chord length into the same relative thickness distribution as the reference airfoil along the chord length, so as to obtain a space curve equation of the suction surface profile of the blade includes the following steps:
The method comprises the steps of making a straight line OE through an O point, intersecting the straight line OE with a pressure surface molded line of a reference airfoil at a C point, intersecting the straight line OE with a pressure surface molded line AB of a blade at a D point, making a straight line OA through the O point and the A point, wherein the included angle between the straight line OE and the straight line OA is theta i(0≤θi -theta or less, determining an X-axis coordinate value X c of the C point, and determining the distance between the pressure surface molded line of the reference airfoil and a suction surface molded line of the reference airfoil, namely the length of a line segment CF when the X-axis coordinate value is X c according to f a (X) and fb (X);
Making the length of the line segment DE identical to the length of the line segment CF to determine the coordinates (x E,yE) of the E point;
All E points determined by the included angle θ i are connected to obtain the suction side profile of the blade cross section, and the space curve equation f s (x) for the suction side profile of the blade.
The pressure surface molded line of the blade is an arc line, and can be designed according to a forward bending blade design method of a traditional centrifugal multi-wing centrifugal impeller, and the design is determined according to the following design parameters: the impeller comprises an impeller inner diameter R 1, an impeller outer diameter R 2, an inlet mounting angle beta b1 of the blades, an outlet mounting angle beta b2 of the blades and a center angle theta of the blades.
As a further technical solution, the space curve equation f p (x) of the pressure surface profile of the blade is:
R b is the radius of the pressure surface line AB of the blade, θ is the center angle of the pressure surface line AB of the blade,
The reference airfoil is a plano-convex airfoil, the straight line part in the pressure surface molded line of the reference airfoil is coincided with the X axis, and the length of the line segment ACNamely the X-axis coordinate value X c of the C point,
At this time, the length of the line segment CF is f a(xc), so that the length of the line segment CF is equal to the length of the line segment CD to obtain the coordinate (x E,yE) of the E point;
Wherein:
The lift-drag ratio of the plano-convex airfoil is high, the relative thickness of the airfoil is between 10% and 20%, and any suitable plano-convex airfoil such as Clark Y series or NACA44 series can be adopted.
In this embodiment, f a (x) uses a cubic polynomial equation
Where a 1、a2、a3、a4 is the equation coefficient of characteristics, determined by the airfoil space curve actually selected.
Further, the method further comprises the steps that an arc line is made by taking the front edge end point of the reference airfoil as a circle center and is tangent to the suction surface molded line of the blade and the pressure surface molded line of the blade to be intersected with the point A and the point G respectively, and the corresponding radius of the arc line is R LE, namely the front edge radius of the blade; and the arc line passing through the point B is tangent to the suction surface molded line of the blade and the pressure surface molded line of the blade respectively, 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.
F a (x) and f b (x) may take any suitable form, such as polynomial equations, exponential equations or logarithmic equations of multiple orders.
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 for illustrating the technical solution of the present invention, and not for limiting the same; although the invention has been described in detail with reference to the foregoing embodiments, it will be understood by those of ordinary skill in the art that: the technical scheme described in the foregoing embodiments can be modified or some or all of the technical features thereof can be replaced by equivalents; such modifications and substitutions do not depart from the spirit of the invention.

Claims (17)

1. The 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 an arc curve;
setting a reference airfoil, wherein the reference airfoil is in a cross-sectional 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 the relative thickness distribution of the reference airfoil along the chord length;
at least one of the two ends of the blade body (1) along the blade height direction is provided with a leakage-proof structure which is used for reducing leakage flow;
the leakage-proof structure comprises a small blade tip wing (15), wherein the small blade tip wing (15) comprises a second front edge (153), a second pressure surface (152), a second rear edge and a second suction surface (151) which are connected end to end in sequence;
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 towards the first rear edge, and a space is arranged between the first front edge and the second front edge (153), and the length of the space is L;
the chord length of the blade body (1) is M, and L/M is more than or equal to 0.2 and less than or equal to 0.6;
And/or the height between two ends of the small blade tip wing (15) along the height direction of the blade is h, and h/M is more than or equal to 0.1 and less than or equal to 0.4;
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).
2. A blade according to claim 1, characterized in that the blade body (1) bulges outwards forming the first leading edge with a first leading edge profile (13), the end points of the two ends of the first leading edge profile (13) forming an obtuse angle with the point connection line on the first leading edge profile (13).
3. A blade according to claim 2, 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 each tangential to the first leading edge profile (13).
4. A blade according to claim 1, 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 the two ends of the first trailing edge profile (14) forming an obtuse angle with the point connection on the first trailing edge profile (14).
5. A blade according to claim 4, characterized in that 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 each tangential to the first trailing edge profile (14).
6. A blade according to claim 1, characterized in that an angle is formed between the normal of the line at the inlet of the blade body (1) and the normal of the line at the outlet of the blade body (1), said angle being the central angle θ, and θ >90 °.
7. An impeller comprising a plurality of the blades of any one of claims 1-6, the plurality of blades being evenly spaced along a circumferential direction of the impeller;
The novel blade structure comprises 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 intervals, and the blade is connected with 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).
8. The impeller of claim 7, further comprising a middle disc (3), the middle disc (3) being disposed between the first end ring (2) and the second end ring (4) with gaps formed between the middle disc and the first end ring (2) and between the second end ring (4), respectively;
The blades are arranged between the first end ring (2) and the middle disc (3), one ends of the blades are connected with the first end ring (2), and the other ends of the blades are connected with the middle disc (3);
the blades are arranged between the second end ring (4) and the middle plate (3), one ends of the blades are connected with the second end ring (4), and the other ends of the blades are connected with the middle plate (3).
9. Impeller according to claim 8, characterized in that 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 offset with respect to the middle disc (3).
10. The impeller according to claim 7, characterized in that the angle between the tangent of the line at the inlet of the blade body (1) and the tangent of the impeller circumference is inlet mounting angle β b1, and that β b1 is 50 ° -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 b2 degrees, and beta b2 degrees is more than or equal to 5 degrees and less than or equal to 30 degrees.
11. A centrifugal fan comprising an impeller according to any one of claims 7-10.
12. A range hood comprising the centrifugal fan of claim 11.
13. A blade design method for designing a blade according to any one of claims 1 to 6, comprising the steps of:
determining a space curve equation of a circular arc pressure surface molded line of the blade;
Selecting a reference airfoil, and determining a space curve equation of the reference airfoil;
And converting the relative thickness distribution of the reference airfoil along the chord length, and 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 by using a space curve coordinate conversion method, thereby obtaining a space curve equation of the suction surface molded line of the blade.
14. The blade design method of claim 13, wherein determining the space curve equation of the circular arc pressure surface profile of the blade comprises the steps of:
determining a circular arc pressure surface molded line of the blade according to a forward bending blade design method of the multi-wing centrifugal impeller, wherein two end points of the pressure surface molded line of the blade are respectively a point A and a point B;
an XY rectangular coordinate system is established by taking the point A as an origin, wherein an X axis is arranged along the extending direction of the connecting line of the point A and the point B, and a space curve equation of the pressure surface molded line of the blade is calculated as The center point of the pressure surface molded line of the blade is O, and the coordinate of the O point is%）。
15. The blade design method of claim 14, wherein determining the space curve equation for the reference airfoil comprises the steps of:
Selecting a reference airfoil of the blade, scaling the reference airfoil according to chord length, placing the reference airfoil in an XY rectangular coordinate system, enabling the front edge endpoint of the reference airfoil to be positioned on a Y axis, enabling the rear edge endpoint of the reference airfoil to coincide with a point B, and converting a space curve equation of a suction surface molded line of the reference airfoil into The space curve equation for the pressure surface profile of the reference airfoil is f b (x).
16. The blade design method of claim 15, wherein converting the relative thickness profile of the blade along the chord length to the same relative thickness profile along the chord length as the reference airfoil, thereby obtaining a space curve equation for the suction side profile of the blade comprises the steps of:
the O point is taken as a straight line OE, the straight line OE is intersected with the pressure surface molded line of the reference airfoil at a point C, the straight line OE is intersected with the pressure surface molded line AB of the blade at a point D, the O point and the point A are taken as a straight line OA, and the included angle between the straight line OE and the straight line OA is Determining X-axis coordinate value of C pointAccording toAnd fb (X), determining the X-axis coordinate value asThe distance between the pressure surface profile of the reference airfoil and the suction surface profile of the reference airfoil, namely the length of the line segment CF;
Making the length of the line segment DE identical to the length of the line segment CF to determine the coordinates (x E,yE) of the E point;
through an included angle of connection All E points are determined to obtain the suction surface profile of the cross section of the blade and the space curve equation of the suction surface profile of the blade。
17. A method of designing a blade according to claim 16, wherein the equation of the space curve of the pressure surface profile of the bladeThe method comprises the following steps:
（）；
R b is the radius of the pressure surface line AB of the blade, θ is the center angle of the pressure surface line AB of the blade, ，；
The reference airfoil is a plano-convex airfoil, the straight line part in the pressure surface profile of the reference airfoil is overlapped with the X axis, and the length L AC of the line segment AC is =X-axis coordinate value of C point，=LAC = 】；
The length of the line CF isThe length of the line segment CF is equal to the length of the line segment CD to obtain the coordinate of the E point，）；
Wherein:，
LEC = 。
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CN114198324B (en) * 2021-12-10 2022-10-25 西安交通大学 Multi-element coupling centrifugal fan collector, centrifugal fan and preparation method of centrifugal fan collector
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