CN107023515B - 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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CN107023515B
CN107023515B CN201710455803.XA CN201710455803A CN107023515B CN 107023515 B CN107023515 B CN 107023515B CN 201710455803 A CN201710455803 A CN 201710455803A CN 107023515 B CN107023515 B CN 107023515B
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point
circle
blade
trailing edge
bionical
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CN107023515A (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 category 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 6405 aerofoil profile of NACA, it is formed by connecting by multiple bionical units in space, the blade has periodical 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 intermediate position in section where two crestal lines is a bionical unit, the width and thickness at position is smaller than bionical two Location of ridge axis of unit among crestal line.The present invention can effectively control the temporal-spatial evolution process of laminar boundary layer or turbulent boundary layer, have lower sensibility to Reynolds number, axial flow blower can be made to all have 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 fields, and in particular to a kind of low noise axial fan Composite bionic airfoil fan.
Background technique
Noise pollution not only influences normal rest, study and the work of people, but also can seriously endanger human health, such as The diseases such as heart disease, hypertension are induced, and serious negative effect is generated to social economy.Airfoil type axial flow blower is industrial life Common fluid machinery in production and daily life, in the case where running at high speed, aerodynamic noise is considerably beyond mechanical noise, total It occupies an leading position in noise.The aerodynamic noise for reducing airfoil type axial flow blower is always the important of domestic and international research common concern Project.
Flowing control is one of hydromechanical Disciplinary Frontiers, and the one of flowing control field has been expedited the emergence of with bionic collision A 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.Based on the theory of bionical flowing control, domestic and international researcher in vane manufacturing corrugated leading edge or Trailing edge serrations structure is centainly playing inhibiting effect to its aerodynamic noise.But certain features of fluid biological body be in order to It adapts to from surrounding's flow field characteristic evolution that matrix shape determines, biomimetic features are to Reynolds number sensibility with higher.It is right For rotating machinery, there is preferable aeroacoustics performance only under the revolving speed of characteristic, under the conditions of very much, compares prototype Blade, often noise reduction even increasing the situation of aerodynamic noise these structures does not occur.Reduce denoising structure to the sensitivity of Reynolds number Property, make to all have low-noise characteristic under its full working scope, is the key that it is promoted and applied in engineering.
Summary of the invention
The purpose of the present invention is to provide the low noise acoustic axis of a kind of aeroperformance that can improve axial flow blower and acoustical behavior Flow fan composite bionic airfoil fan.
Blade of the invention has the feature of ridge-like structure surface B, sharp tooth trailing edge C and periodical concavity leading edge D.
The key feature points of each bionical unit A be trailing edge a point, trailing edge b point, trailing edge c point, leading edge d point, leading edge e point and Leading edge f point.
It is key feature line S2, cf curve is crucial that the ad curve of each bionical unit A, which is key feature line S1, be curve, 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, closing Maximum gauge at key characteristic curve S3 is δcf。
The straight length of ad two o'clock is Lad, the straight length of be two o'clock is Lbe, the straight length of cf two o'clock is Lcf。
Each bionical unit A is designed with II F of I E of crestal line and crestal line.
Blade inlet edge 2 is sequentially connected by blade root I 5 to leaf top I 6 by the inner concavity characteristic curve S4 of each bionical unit A in space Form, blade trailing edge 4 be sequentially connected by blade root II 8 to leaf top II 7 by the inner concavity characteristic curve S5 of each bionical unit A in space and At.
I characteristic point of blade root of blade inlet edge 2 is j point, and I characteristic point of leaf top of blade inlet edge 2 is i point.
II characteristic point of blade root of blade trailing edge 4 is g point, and II characteristic point of leaf top of blade trailing edge 4 is h point.
The straight length of j point and g point is Ljg, the straight length of i point and h point is Lih。
The bionical unit A is the part where II F of I E of crestal line and crestal line between section.
Low noise axial fan composite bionic airfoil fan design aerofoil profile used is repairing for NACA6405 aerofoil profile Change aerofoil profile.
The LihAnd LjgBetween relationship are as follows:
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 Relationship are as follows:
R2=0.5 (R1+R3).
Trailing edge a point, trailing edge b point, the trailing edge c point of the bionical unit A be respectively blade trailing edge 4 and circle I C1, circle II C2, III C3 of circle is along the intersection point perpendicular to the resulting cylindrical surface of horizontal plane；Leading edge d point, leading edge e point and leading edge f point be respectively with circle I C1, II C2 of circle, III C3 of circle are along the intersection point perpendicular to the resulting cylindrical surface of horizontal plane.
L in the bionical unit Aad、LbeAnd LcfBetween relationship are as follows:
Lbe=(0.85~0.95) × 0.5 (Lad+Lcf)。
δ in the bionical unit Aad、δbeAnd δcfBetween relationship are as follows:
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 point, leading edge e point and leading edge f point； The inner concavity characteristic curve S5 of bionical unit A is the B-spline curves II of trailing edge a point, trailing edge b point, trailing edge c point, B-spline curves I and B The specific size parameter of spline curve II is determined by claim 5 and claim 6.
The beneficial effects of the present invention are:
(1) under smaller revolving speed, after air-flow flows through composite bionic blade inlet edge, unstable T-S wave is formed, boundary layer is not It separates, is fallen off with " tubular " from blade trailing edge；After air-flow flows through the wavy leading edge of blade, adjacent two ridge-like structures middle air flow There is equivalent reversed speed in the spanwise direction, limited by blade wall surface, normal velocity of the air-flow at the lowest point increases, resistance The formation of T-S wave is stopped.After air-flow falls off from sawtooth trailing edge, more regular " blocky whirlpool " is formd, reduces and flows to whirlpool It opens up to relevance.
(2) under moderate rotation, among suction surface side, the adjacent ridge-like structure of composite bionic blade surface two, air-flow exhibition Further increased to flow velocity, the lowest point wall surface reflection make under form higher normal velocity, accelerate boundary layer turn twist, subtract Pressure fluctuation caused by small boundary layer unstability.In pressure surface side, surface ridge-like structure is to pneumatic gathering, to boundary layer Stabilization is played, eliminates the unstable whirlpool Λ formed during boundary layer transition, laminar boundary layer is close to trailing edge Neighbouring rapid development falls off at after turbulent boundary layer from trailing edge.
(3) under larger revolving speed, composite bionic blade suction surface side, surface ridge-like structure plays the work of gathering to fluid With.Pressure surface side, ridge-like structure surface accelerate boundary layer turn twist, can reduce wall boundary layer it is unstable caused by pressure arteries and veins It is dynamic.After pressure face falls off from trailing edge, sawtooth trailing edge structures reduce the length for flowing to whirlpool and open up to relevance air-flow, can reduce whirlpool Fall off noise.
The present invention can effectively control the temporal-spatial evolution process of laminar boundary layer or turbulent boundary layer, have to Reynolds number Lower sensibility can make axial flow blower all have good aeroperformance and acoustical behavior under full working scope.
Detailed description of the invention
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 profile
Fig. 4 is composite bionic airfoil fan characteristic point and characteristic curve schematic diagram
Fig. 5 is composite bionic airfoil fan main view
Fig. 6 is the enlarged drawing at G meaning position in Fig. 5
Fig. 7 is the enlarged drawing at H meaning position in Fig. 5
Fig. 8 is that bionical element characteristic linear dimension marks schematic diagram
Wherein: the bionical unit B ridge-like structure surface C sharp tooth trailing edge D. periodicity concavity leading edge E. crestal line I of A. F. 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. leaf top II 8. Blade root II
Specific embodiment
Present invention is described with reference to the accompanying drawing:
A kind of low noise axial fan composite bionic airfoil fan of the invention has ridge-like structure surface B, sharp tooth tail The feature of edge C and periodical concavity leading edge D.The pressure face 1 and suction surface 3 of entire composite bionic airfoil fan are imitative by 25-50 The curved surface of raw unit A connect into and space curved surface, as shown in Figure 1 and Figure 2.
The key feature points of each bionical unit A be trailing edge a point, trailing edge b point, trailing edge c point, leading edge d point, leading edge e point and Leading edge f point；
It is key feature line S2, cf curve is crucial that the ad curve of each bionical unit A, which is key feature line S1, be curve, 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, closing Maximum gauge at key characteristic curve S3 is δcf；
The straight length of ad two o'clock is Lad, the straight length of be two o'clock is Lbe, the straight length of cf two o'clock is Lcf；
Each bionical unit A is designed with II F of I E of crestal line and crestal line；
Blade inlet edge 2 is sequentially connected by blade root I 5 to leaf top I 6 by the inner concavity characteristic curve S4 of each bionical unit A in space Form, blade trailing edge 4 be sequentially connected by blade root II 8 to leaf top II 7 by the inner concavity characteristic curve S5 of each bionical unit A in space and At.
I characteristic point of blade root of blade inlet edge 2 is j point, and I characteristic point of leaf top of blade inlet edge 2 is i point.
II characteristic point of blade root of blade trailing edge 4 is g point, and II characteristic point of leaf top of blade trailing edge 4 is h point.
The straight length of j point and g point is Ljg, the straight length of i point and h point is Lih。
Part where the bionical unit A refers to II F of I E of crestal line and crestal line between section.
Composite bionic airfoil fan design aerofoil profile used is the modification aerofoil profile of NACA6405 aerofoil profile, and Curve of wing is as schemed Shown in 3.Lower surface I shown in figure is respectively intended to construct 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 upper and lower surfaces is divided into formula (1) and formula (2):
The linear distance L of composite bionic airfoil fan root leading edge point g and trailing edge point jjgWith vane tip leading edge point h and tail The linear distance L of edge point iihThe relationship of (shown in Fig. 4) are as follows:
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 relationship of three's radius are as follows:
Trailing edge a point, trailing edge b point, the trailing edge c point of the bionical unit A be respectively blade trailing edge 4 and circle I C1, circle II C2, III C3 of circle is along the intersection point perpendicular to the resulting cylindrical surface of horizontal plane；Leading edge d point, leading edge e point and leading edge f point be respectively with circle I C1, II C2 of circle, III C3 of circle are along the intersection point perpendicular to the resulting cylindrical surface of horizontal plane, as shown in Figure 8.
L in the bionical unit Aad、LbeAnd LcfBetween relationship are as follows:
Lbe=(0.85~0.95) × 0.5 (Lad+Lcf) (4)
δ in the bionical unit Aad、δbeAnd δcfBetween relationship are as follows:
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 point, leading edge e point and leading edge f point； The inner concavity characteristic curve S5 of bionical unit A is the B-spline curves II of trailing edge a point, trailing edge b point, trailing edge c point, B-spline curves I and B The specific size parameter of spline curve II is determined by formula (3)~(5).
One, 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 profile) is straight Diameter is 215mm, works as Lih=1.75Ljg,Lbe=0.95 × 0.5 (Lad+Lcf), δbe=0.95 × 0.5 (δad+δcf) when, dedicated The aeroperformance tested on fan test table shows that under tetra- voltage modes of 13V, 16V, 20V, 24V, startup power is maximum 2.51% is reduced, static pressure efficiency improves 1.53%.According to standard GB/T/T2888-2008 " blower and Roots blower noise Measurement method ", application specific acoustic test equipment test result shows that its noise overall sound pressure level maximum can reduce 4.14dB.
Two, 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 profile) is straight Diameter is 215mm, works as Lih=1.55Ljg,Lbe=0.9 × 0.5 (Lad+Lcf), δbe=0.9 × 0.5 (δad+δcf) when, in dedicated wind The aeroperformance tested on machine testing stand shows that under tetra- voltage modes of 13V, 16V, 20V, 24V, startup power maximum drops Low 3.52%, static pressure efficiency improves 3.09%.According to standard GB/T/T2888-2008, " blower 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.
Three, 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 profile) is straight Diameter is 215mm, works as Lih=1.35Ljg,Lbe=0.85 × 0.5 (Lad+Lcf), δbe=0.85 × 0.5 (δad+δcf) when, dedicated The aeroperformance tested on fan test table shows that under tetra- voltage modes of 13V, 16V, 20V, 24V, startup power is maximum 3.68% is reduced, static pressure efficiency improves 3.79%.According to standard GB/T/T2888-2008 " blower and Roots blower noise Measurement method ", application specific acoustic test equipment test result shows that its noise overall sound pressure level maximum can reduce 2.35dB.

Claims (6)

1. a kind of low noise axial fan composite bionic airfoil fan, it is characterised in that: blade inlet edge, rear have pointed knot Structure, surface have ridge-like structure, for accelerating boundary layer to turn to twist, and Shedding Vortex are divided into " bulk ", to effectively reduce The exhibition of Shedding Vortex reduces aerodynamic noise to relevance；Composite bionic airfoil fan is sequentially connected by multiple bionical units in space It forms, two neighboring bionical unit is respectively formed a leading edge pointed structures, a rear pointed structures and a ridge-like structure； The key feature points of each bionical unit (A) are trailing edge a point, trailing edge b point, trailing edge c point, leading edge d point, leading edge e point and leading edge f point ；It is key feature line S2, cf curve is key feature that the ad curve of each bionical unit (A), which is key feature line S1, be curve, Line S3, def curve is that inner concavity characteristic curve S4, abc curve is inner concavity characteristic curve S5；Blade is maximum at key feature line S1 With a thickness of δad, maximum gauge at key feature line S2 be δbe, maximum gauge at key feature line S3 be δcf；Ad two The straight length of point is Lad, the straight length of be two o'clock is Lbe, the straight length of cf two o'clock is Lcf；Each bionical unit (A) Equipped with crestal line I (E) and crestal line II (F)；Blade inlet edge (2) is by the inner concavity characteristic curve S4 of each bionical unit (A) in space by leaf Root I (5) is connected in sequence to leaf top I (6), and blade trailing edge (4) is by the inner concavity characteristic curve S5 of each bionical unit (A) in space It is connected in sequence by blade root II (8) to leaf top II (7)；I characteristic point of blade root of blade inlet edge (2) is j point, blade inlet edge (2) I characteristic point of leaf top be i point, II characteristic point of blade root of blade trailing edge (4) is g point, and II characteristic point of leaf top of blade trailing edge (4) is H point；The straight length of j point and g point is Ljg, the straight length of i point and h point is Lih。
2. low noise axial fan composite bionic airfoil fan according to claim 1, it is characterised in that: the bionical list First (A) is the part where crestal line I (E) and crestal line II (F) between section.
3. low noise axial fan composite bionic airfoil fan according to claim 1, it is characterised in that: it designs used Aerofoil profile is the modification aerofoil profile of 6405 aerofoil profile of NACA.
4. low noise axial fan composite bionic airfoil fan according to claim 1, it is characterised in that: the LihAnd LjgIt Between relationship are as follows:
Lih=(1.35~1.75) Ljg。
5. low noise axial fan composite bionic airfoil fan according to 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 relationship of three's radius Are as follows:
R2=0.5 (R1+R3).
6. low noise axial fan composite bionic airfoil fan according to claim 1, it is characterised in that: the bionical unit (A) trailing edge a point, trailing edge b point, trailing edge c point is respectively blade trailing edge (4) and I (C1) of circle, II (C2) of circle, III (C3) of circle along vertical Directly in the intersection point on the resulting cylindrical surface of horizontal plane；Leading edge d point, leading edge e point and leading edge f point are respectively and I (C1) of circle, circle II (C2), III (C3) of circle is along the intersection point perpendicular to the resulting cylindrical surface of horizontal plane；L in the bionical unit (A)ad、LbeAnd LcfBetween Relationship are as follows:
Lbe=(0.85~0.95) × 0.5 (Lad+Lcf)
δ in the bionical unit (A)ad、δbeAnd δcfBetween relationship are as follows:
δbe=(0.85~0.95) × 0.5 (δad+δcf)。
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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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
GB201818839D0 (en) * 2018-11-19 2019-01-02 Cambridge Entpr Ltd Foils with serrations
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CN112623187B (en) * 2020-12-30 2022-11-29 吉林大学 Detachable and replaceable wing-shaped trailing edge device and manufacturing method thereof
CN112963515B (en) * 2021-04-26 2021-09-10 吉林大学 Hydraulic torque converter blade modeling method based on quasi-uniform B-spline curve
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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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