CN107023515A - A kind of low noise axial fan composite bionic airfoil fan - Google Patents

A kind of low noise axial fan composite bionic airfoil fan Download PDF

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CN107023515A
CN107023515A CN201710455803.XA CN201710455803A CN107023515A CN 107023515 A CN107023515 A CN 107023515A CN 201710455803 A CN201710455803 A CN 201710455803A CN 107023515 A CN107023515 A CN 107023515A
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points
circle
trailing edge
blade
bionical
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CN107023515B (en
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张成春
王晶
鲍杨春
张秀梅
岳永丽
任露泉
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Jilin University
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Jilin University
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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
    • F04D29/00—Details, component parts, or accessories
    • F04D29/26—Rotors specially for elastic fluids
    • F04D29/32—Rotors specially for elastic fluids for axial flow pumps
    • F04D29/38—Blades
    • F04D29/388—Blades characterised by construction
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/26—Rotors specially for elastic fluids
    • F04D29/32—Rotors specially for elastic fluids for axial flow pumps
    • F04D29/38—Blades
    • F04D29/384—Blades characterised by form
    • 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

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)

Abstract

A kind of low noise axial fan composite bionic airfoil fan belongs to fluid machinery blade design and flow control technique field, composite bionic airfoil fan design proposed by the present invention aerofoil profile used is the modification aerofoil profile of the aerofoil profiles of NACA 6405, it is formed by connecting by multiple bionical units in space, the blade has periodicity indent leading edge, pointed tooth structure trailing edge and ridge-like structure surface characteristics, the pressure face and suction surface of blade are the space curved surface that multiple camber is constituted, the middle part in section where two crestal lines is a bionical unit, the width and thickness of crestal line middle part are smaller than the bionical Location of ridge axis of unit two.The present invention can be effective to the temporal-spatial evolution process of laminar boundary layer or turbulent boundary layer control, have relatively low sensitiveness to Reynolds number, axial flow blower can be made to be respectively provided with good aeroperformance and acoustical behavior under full working scope.

Description

A kind of low noise axial fan composite bionic airfoil fan
Technical field
The invention belongs to fluid machinery blade design and flow control technique field, and in particular to a kind of low noise axial fan Composite bionic airfoil fan.
Background technology
Noise pollution not only influences the normal rest, study and work of people, but also can seriously endanger health, such as The diseases such as heart disease, hypertension are induced, and serious negative effect is produced to social economy.Airfoil type axial flow blower is industrial life The fluid machinery commonly used in production and daily life, in the case where running at high speed, its aerodynamic noise is considerably beyond mechanical noise, total Occupied an leading position in noise.The aerodynamic noise of airfoil type axial flow blower is reduced, is always the important of domestic and international research common concern Problem.
It is one of hydromechanical Disciplinary Frontiers to flow control, and the one of flowing control field has been expedited the emergence of with bionic collision Individual important research branch --- bionical flowing control, i.e., by imitating the peculiar function with study biology or organism, further The effect of enhancing flowing control.The theory controlled based on bionical flowing, domestic and international researcher in vane manufacturing corrugated leading edge or Trailing edge serrations structure, is necessarily serving inhibitory action to its aerodynamic noise.But, some features of fluid biological body be in order to Adapt to by surrounding's flow field characteristic that matrix profile is determined is evolved, biomimetic features have higher sensitiveness to Reynolds number.It is right For rotating machinery, there is preferable aeroacoustics performance only under the rotating speed of characteristic, under the conditions of a lot, compared to prototype Blade, often noise reduction the situation of increase aerodynamic noise even to these structures does not occur.Reduce sensitivity of the denoising structure to Reynolds number Property, make to be respectively provided with low-noise characteristic under its full working scope, be the key of its popularization and application in engineering.
The content of the invention
It is an object of the invention to provide a kind of aeroperformance that can improve axial flow blower and the low noise acoustic axis of acoustical behavior Flow fan composite bionic airfoil fan.
The blade of the present invention has ridge-like structure surface B, sharp tooth trailing edge C and periodicity concavity leading edge D feature.
Each bionical unit A key feature points are trailing edge a points, trailing edge b points, trailing edge c points, leading edge d points, leading edge e points and Leading edge f points.
Each bionical unit A ad curves are that key feature line S1, be curve is that key feature line S2, cf curve is crucial Characteristic curve S3, def curve is that inner concavity characteristic curve S4, abc curve is inner concavity characteristic curve S5.
Blade maximum gauge at key feature line S1 is δad, maximum gauge at key feature line S2 be δbe, close Maximum gauge at key characteristic curve S3 is δcf。
The straight length that 2 points of ad is Lad, the straight length that 2 points of be is Lbe, the straight length that 2 points of cf is Lcf。
Each bionical unit A is designed with the E of crestal line I and the F of crestal line II.
Blade inlet edge 2 is sequentially connected in space by each bionical unit A inner concavity characteristic curve S4 by blade root I 5 to leaf top I 6 Form, blade trailing edge 4 be sequentially connected by each bionical unit A inner concavity characteristic curve S5 in space by blade root II 8 to leaf top II 7 and Into.
The characteristic point of blade root I of blade inlet edge 2 is j points, and the characteristic point of leaf top I of blade inlet edge 2 is i points.
The characteristic point of blade root II of blade trailing edge 4 is g points, and the characteristic point of leaf top II of blade trailing edge 4 is h points.
The straight length of j points and g points is Ljg, the straight length of i points and h points is Lih。
Described bionical unit A is the part between section where the E of the crestal line I and F of crestal line II.
Described low noise axial fan composite bionic airfoil fan design aerofoil profile repairing for NACA6405 aerofoil profiles used Change aerofoil profile.
The LihAnd LjgBetween relation be：
Lih=(1.35~1.75) Ljg。
The key feature line S1 of the bionical unit A, key feature line S2, key feature line S3 are along perpendicular to paper side It is respectively I C1 of circle, II C2 of circle, III C3 of circle to the circle where projection, I C1 of circle, II C2 of circle, III C3 of circle are concentric circles, three's radius Relation be：
R2=0.5 (R1+R3).
Trailing edge a points, trailing edge b points, the trailing edge c points of the bionical unit A be respectively blade trailing edge 4 with I C1 of circle, II C2 of circle, Intersection point of III C3 of the circle edges perpendicular to the face of cylinder obtained by horizontal plane；Leading edge d points, leading edge e points and leading edge f points be respectively with circle I C1, Justify II C2, III C3 of circle along the intersection point perpendicular to the face of cylinder obtained by horizontal plane.
L in the bionical unit Aad、LbeAnd LcfBetween relation be：
Lbe=(0.85~0.95) × 0.5 (Lad+Lcf)。
δ in the bionical unit Aad、δbeAnd δcfBetween relation be：
δbe=(0.85~0.95) × 0.5 (δad+δcf)。
The inner concavity characteristic curve S4 of the bionical unit A is the B-spline curves I of leading edge d points, leading edge e points and leading edge f points； Bionical unit A inner concavity characteristic curve S5 is trailing edge a points, trailing edge b points, the B-spline curves II of trailing edge c points, B-spline curves I and B The specific dimensional parameters of SPL II are determined by claim 5 and claim 6.
The beneficial effects of the present invention are：
(1) under smaller rotating speed, after airflow passes composite bionic blade inlet edge, unstable T-S ripples are formed, boundary layer is not Separate, come off with " tubular " from blade trailing edge；Air-flow is flowed through after the wavy leading edge of blade, adjacent two ridge-like structures middle air flow There is equivalent reverse speed in the spanwise direction, limited by blade wall, normal velocity increase of the air-flow at the lowest point, resistance The formation of T-S ripples is stopped.Air-flow forms more regular " block whirlpool ", reduces and flow to whirlpool after sawtooth trailing edge comes off Open up to relevance.
(2) under moderate rotation, in the middle of suction surface side, the adjacent ridge-like structure of composite bionic blade surface two, air-flow exhibition Further increase to flow velocity, the lowest point wall reflection make under form higher normal velocity, accelerate boundary layer turn twist, subtract The pressure fluctuation that small boundary layer unstability is caused.In pressure surface side, surface ridge-like structure is to pneumatic gathering, to boundary layer Stabilization is played, the unstable Λ whirlpools formed during boundary layer transition are eliminated, laminar boundary layer is close to trailing edge Neighbouring rapid development from trailing edge into coming off after turbulent boundary layer.
(3) under larger rotating speed, composite bionic blade suction surface side, its surface ridge-like structure plays the work of gathering to fluid With.Pressure surface side, ridge-like structure surface accelerate boundary layer turn twist, the unstable pressure arteries and veins caused in wall boundary layer can be reduced It is dynamic.Air-flow is in pressure face after trailing edge comes off, and sawtooth trailing edge structures reduce the length for flowing to whirlpool and opened up to relevance, can reduce whirlpool Come off noise.
The present invention can be effective to the temporal-spatial evolution process of laminar boundary layer or turbulent boundary layer control, have to Reynolds number Relatively low sensitiveness, can make axial flow blower be respectively provided with good aeroperformance and acoustical behavior under full working scope.
Brief description of the drawings
Fig. 1 is composite bionic airfoil fan side view
Fig. 2 is that composite bionic airfoil fan key feature marks schematic diagram
Fig. 3 is the modification Curve of wing figure of NACA6504 aerofoil profiles
Fig. 4 is composite bionic airfoil fan characteristic point and characteristic curve schematic diagram
Fig. 5 is composite bionic airfoil fan front view
Fig. 6 is the enlarged drawing at the signified positions of G in Fig. 5
Fig. 7 is the enlarged drawing at the signified positions of H in Fig. 5
Fig. 8 is that bionical element characteristic linear dimension marks schematic diagram
Wherein：A. bionical unit B ridge-like structures surface C sharp tooths trailing edge D. periodicity concavity leading edge E. crestal lines I F. the leaf top II 8. of II 1. pressure face of crestal line, 2. blade inlet edge, 3. suction surface, 4. blade trailing edge, 5. blade root, I 6. leaf top I 7. Blade root II
Embodiment
Present invention is described below in conjunction with the accompanying drawings:
A kind of low noise axial fan composite bionic airfoil fan of the present invention, with ridge-like structure surface B, sharp tooth tail Edge C and periodicity concavity leading edge D feature.The pressure face 1 and suction surface 3 of whole composite bionic airfoil fan are imitative by 25-50 Raw unit A curved surface connect into and space curved surface, as shown in Figure 1 and Figure 2.
Each bionical unit A key feature points are trailing edge a points, trailing edge b points, trailing edge c points, leading edge d points, leading edge e points and Leading edge f points；
Each bionical unit A ad curves are that key feature line S1, be curve is that key feature line S2, cf curve is crucial Characteristic curve S3, def curve is that inner concavity characteristic curve S4, abc curve is inner concavity characteristic curve S5；
Blade maximum gauge at key feature line S1 is δad, maximum gauge at key feature line S2 be δbe, close Maximum gauge at key characteristic curve S3 is δcf；
The straight length that 2 points of ad is Lad, the straight length that 2 points of be is Lbe, the straight length that 2 points of cf is Lcf；
Each bionical unit A is designed with the E of crestal line I and the F of crestal line II；
Blade inlet edge 2 is sequentially connected in space by each bionical unit A inner concavity characteristic curve S4 by blade root I 5 to leaf top I 6 Form, blade trailing edge 4 be sequentially connected by each bionical unit A inner concavity characteristic curve S5 in space by blade root II 8 to leaf top II 7 and Into.
The characteristic point of blade root I of blade inlet edge 2 is j points, and the characteristic point of leaf top I of blade inlet edge 2 is i points.
The characteristic point of blade root II of blade trailing edge 4 is g points, and the characteristic point of leaf top II of blade trailing edge 4 is h points.
The straight length of j points and g points is Ljg, the straight length of i points and h points is Lih。
Part between section where the bionical unit A refers to the E of the crestal line I and F of crestal line II.
Composite bionic airfoil fan design aerofoil profile used is the modification aerofoil profile of NACA6405 aerofoil profiles, and its Curve of wing is as schemed Shown in 3.Lower surface I shown in figure is respectively intended to build the pressure face 1 and suction surface 3 of each bionical unit with upper surface II. Take aerofoil profile chord length ccNon-dimensional length is 1, and the dimensionless coordinate fitting curve representation formula of its upper and lower surface is divided into formula And formula (2) (1)：
Composite bionic airfoil fan root leading edge point g and trailing edge point j air line distance LjgWith vane tip leading edge point h and tail Edge point i air line distance LihThe relation of (shown in Fig. 4) is：
Lih=(1.35~1.75) Ljg (3)
The key feature line S1 of the bionical unit A, key feature line S2, key feature line S3 are along perpendicular to paper side It is respectively I C1 of circle, II C2 of circle, III C3 of circle to the circle where projection, as shown in Fig. 5~Fig. 7.I C1 of circle, II C2 of circle, III C3 of circle are Concentric circles, the relation of three's radius is：
Trailing edge a points, trailing edge b points, the trailing edge c points of the bionical unit A be respectively blade trailing edge 4 with I C1 of circle, II C2 of circle, Intersection point of III C3 of the circle edges perpendicular to the face of cylinder obtained by horizontal plane；Leading edge d points, leading edge e points and leading edge f points be respectively with circle I C1, Justify II C2, justify intersection point of the III C3 edges perpendicular to the face of cylinder obtained by horizontal plane, as shown in Figure 8.
L in the bionical unit Aad、LbeAnd LcfBetween relation be：
Lbe=(0.85~0.95) × 0.5 (Lad+Lcf) (4)
δ in the bionical unit Aad、δbeAnd δcfBetween relation be：
δbe=(0.85~0.95) × 0.5 (δad+δcf)(5)
The inner concavity characteristic curve S4 of the bionical unit A is the B-spline curves I of leading edge d points, leading edge e points and leading edge f points； Bionical unit A inner concavity characteristic curve S5 is trailing edge a points, trailing edge b points, the B-spline curves II of trailing edge c points, B-spline curves I and B The specific dimensional parameters of SPL II are determined by formula (3)~(5).
First, composite bionic blade Application Example 1 on axial flow blower
Airfoil type axial-flow fan blade (aerofoil profile is the amendment aerofoil profile that aerofoil profile proposed by the present invention is NACA6405 aerofoil profiles) is straight Footpath is 215mm, works as Lih=1.75Ljg,Lbe=0.95 × 0.5 (Lad+Lcf), δbe=0.95 × 0.5 (δad+δcf) when, special The aeroperformance tested on fan test table shows, under tetra- voltage modes of 13V, 16V, 20V, 24V, and its startup power is maximum Reduction by 2.51%, static pressure efficiency improves 1.53%.According to standard GB/T/T2888-2008《Blower fan and Roots blower noise Measuring method》, application specific acoustic test equipment test result shows that its noise overall sound pressure level maximum can reduce 4.14dB.
2nd, composite bionic blade Application Example 2 on axial flow blower
Airfoil type axial-flow fan blade (aerofoil profile is the amendment aerofoil profile that aerofoil profile proposed by the present invention is NACA6405 aerofoil profiles) is straight Footpath is 215mm, works as Lih=1.55Ljg,Lbe=0.9 × 0.5 (Lad+Lcf), δbe=0.9 × 0.5 (δad+δcf) when, in special wind The aeroperformance tested on machine testing stand shows, under tetra- voltage modes of 13V, 16V, 20V, 24V, its startup power maximum drop Low by 3.52%, static pressure efficiency improves 3.09%.According to standard GB/T/T2888-2008《Blower fan and Roots blower noise are surveyed Amount method》, application specific acoustic test equipment test result shows that its noise overall sound pressure level maximum can reduce 3.25dB.
3rd, composite bionic blade Application Example 3 on axial flow blower
Airfoil type axial-flow fan blade (aerofoil profile is the amendment aerofoil profile that aerofoil profile proposed by the present invention is NACA6405 aerofoil profiles) is straight Footpath is 215mm, works as Lih=1.35Ljg,Lbe=0.85 × 0.5 (Lad+Lcf), δbe=0.85 × 0.5 (δad+δcf) when, special The aeroperformance tested on fan test table shows, under tetra- voltage modes of 13V, 16V, 20V, 24V, and its startup power is maximum Reduction by 3.68%, static pressure efficiency improves 3.79%.According to standard GB/T/T2888-2008《Blower fan and Roots blower noise Measuring method》, application specific acoustic test equipment test result shows that its noise overall sound pressure level maximum can reduce 2.35dB.

Claims (7)

1. a kind of low noise axial fan composite bionic airfoil fan, it is characterised in that：The key feature of each bionical unit (A) Point is trailing edge a points, trailing edge b points, trailing edge c points, leading edge d points, leading edge e points and leading edge f points；The ad curves of each bionical unit (A) It is that key feature line S2, cf curve is that key feature line S3, def curve is inner concavity feature for key feature line S1, be curve Line S4, abc curve are inner concavity characteristic curve S5；Blade maximum gauge at key feature line S1 is δad, in key feature line S2 The maximum gauge at place is δbe, maximum gauge at key feature line S3 be δcf；The straight length that 2 points of ad is Lad, 2 points of be Straight length be Lbe, the straight length that 2 points of cf is Lcf；Each bionical unit (A) is designed with crestal line I (E) and crestal line II (F)；Blade inlet edge (2) by each bionical unit (A) inner concavity characteristic curve S4 space by blade root I (5) to leaf top I (6) successively It is formed by connecting, blade trailing edge (4) is by the inner concavity characteristic curve S5 of each bionical unit (A) in space by blade root II (8) to leaf top II (7) it is connected in sequence；The characteristic point of blade root I of blade inlet edge (2) is j points, and the characteristic point of leaf top I of blade inlet edge (2) is i points, The characteristic point of blade root II of blade trailing edge (4) is g points, and the characteristic point of leaf top II of blade trailing edge (4) is h points；
The straight length of 1.j points and g points is Ljg, the straight length of i points and h points is Lih。
2. the low noise axial fan composite bionic airfoil fan as described in claim 1, it is characterised in that：Described bionical list First (A) is the part between section where crestal line I (E) and crestal line II (F).
3. the low noise axial fan composite bionic airfoil fan as described in claim 1, it is characterised in that：It designs used Aerofoil profile is the modification aerofoil profile of the aerofoil profiles of NACA 6405.
4. the low noise axial fan composite bionic airfoil fan as described in claim 1, it is characterised in that：The LihAnd LjgIt Between relation be：
Lih=(1.35~1.75) Ljg。
5. the low noise axial fan composite bionic airfoil fan as described in claim 1, it is characterised in that：The bionical unit (A) key feature line S1, key feature line S2, key feature line S3 distinguishes along perpendicular to the circle where paper direction projection For I (C1) of circle, II (C2) of circle, III (C3) of circle, I (C1) of circle, II (C2) of circle, III (C3) of circle are concentric circles, the relation of three's radius For：
R2=0.5 (R1+R3).
6. the low noise axial fan composite bionic airfoil fan as described in claim 1, it is characterised in that：The bionical unit (A) trailing edge a points, trailing edge b points, trailing edge c points is respectively blade trailing edge (4) with I (C1) of circle, II (C2) of circle, III (C3) of circle along hanging down Directly in the intersection point on the face of cylinder obtained by horizontal plane；Leading edge d points, leading edge e points and leading edge f points are respectively and I (C1) of circle, circle II (C2), intersection point of III (C3) of the circle edges perpendicular to the face of cylinder obtained by horizontal plane；L in the bionical unit (A)ad、LbeAnd LcfBetween Relation be：
Lbe=(0.85~0.95) × 0.5 (Lad+Lcf)
δ in the bionical unit (A)ad、δbeAnd δcfBetween relation be：
δbe=(0.85~0.95) × 0.5 (δad+δcf)。
7. the low noise axial fan composite bionic airfoil fan as described in claim 1, it is characterised in that：The bionical unit (A) inner concavity characteristic curve S4 is the B-spline curves I of leading edge d points, leading edge e points and leading edge f points；The inner concavity of bionical unit (A) Characteristic curve S5 is trailing edge a points, trailing edge b points, the B-spline curves II of trailing edge c points, B-spline curves I and B-spline curves II it is specific Dimensional parameters are determined by claim 5 and claim 6.
CN201710455803.XA 2017-06-16 2017-06-16 A kind of low noise axial fan composite bionic airfoil fan Active CN107023515B (en)

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CN108980101A (en) * 2018-08-02 2018-12-11 江苏大学镇江流体工程装备技术研究院 A kind of bionic blade based on shark surface drag reduction technology
CN109281866A (en) * 2018-12-07 2019-01-29 泰州市罡阳喷灌机有限公司 The bionic blade of liquid-ring type self priming pump
CN112623187A (en) * 2020-12-30 2021-04-09 吉林大学 Detachable and replaceable wing-shaped trailing edge device and manufacturing method thereof
CN112963515A (en) * 2021-04-26 2021-06-15 吉林大学 Hydraulic torque converter blade modeling method based on quasi-uniform B-spline curve
WO2021180559A1 (en) * 2020-03-10 2021-09-16 Ebm-Papst Mulfingen Gmbh & Co. Kg Fan and fan blades
CN113573978A (en) * 2018-11-19 2021-10-29 吕本帅 Airfoil with tooth profile
CN114412834A (en) * 2022-03-31 2022-04-29 佛山市南海九洲普惠风机有限公司 Composite bionic wing-shaped blade and axial flow fan impeller
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CN203532325U (en) * 2013-09-27 2014-04-09 杭州微光电子股份有限公司 External rotor axial flow fan with blades having bionic characteristic
CN104100570A (en) * 2014-07-09 2014-10-15 德意电器股份有限公司 Bionic impeller for exhaust hood
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CN203532325U (en) * 2013-09-27 2014-04-09 杭州微光电子股份有限公司 External rotor axial flow fan with blades having bionic characteristic
CN104100570A (en) * 2014-07-09 2014-10-15 德意电器股份有限公司 Bionic impeller for exhaust hood
CN205423320U (en) * 2016-03-22 2016-08-03 浪潮集团有限公司 Be applied to fan of making an uproar that falls of server

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CN108980101B (en) * 2018-08-02 2023-07-04 江苏大学镇江流体工程装备技术研究院 Bionic blade based on shark surface drag reduction technology
CN108980101A (en) * 2018-08-02 2018-12-11 江苏大学镇江流体工程装备技术研究院 A kind of bionic blade based on shark surface drag reduction technology
CN113573978A (en) * 2018-11-19 2021-10-29 吕本帅 Airfoil with tooth profile
CN113573978B (en) * 2018-11-19 2024-03-26 吕本帅 Airfoil, noise reduction device, turbine, aircraft, watercraft and cooling fan
CN109281866A (en) * 2018-12-07 2019-01-29 泰州市罡阳喷灌机有限公司 The bionic blade of liquid-ring type self priming pump
CN109281866B (en) * 2018-12-07 2023-09-15 泰州市罡阳喷灌机有限公司 Bionic blade of water ring type self-priming pump
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WO2021180560A1 (en) * 2020-03-10 2021-09-16 Ebm-Papst Mulfingen Gmbh & Co. Kg Fan and fan blades
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