Axial flow fan blade and axial flow fan

Abstract

The present invention provides an axial flow fan blade and an axial flow fan. The axial flow fan blade comprises: a hub and a blade. The installation angle β of the elementary-level airfoil and the relative radius #imgabs0# satisfy #imgabs1# the blade cascade density ρ and #imgabs2# satisfy #imgabs3# the forward bending angle θ and the relative radius #imgabs4# satisfy #imgabs5# the relative position z and the relative radius #imgabs6# satisfy the formula #imgabs7# z / (2R2)=e2#imgabs8#. Through the present invention, the fan blade can have a forward bending feature, improve the airflow morphology on the fan surface, improve the flow efficiency of the fan blade, and suppress the boundary layer separation phenomenon on the fan blade surface. Compared with the original technology, under the condition of the same static pressure (especially in the high-pressure area), the static pressure efficiency can be improved, the work efficiency and work capacity can be improved, the fan blade power can be reduced, and the fan blade noise can be reduced.

Description

Technical Field

[0001] The present invention belongs to the technical field of fans, and in particular relates to an axial flow fan blade and an axial flow fan. Background Art

[0002] The inlet of the fan cargo hold condensation duct is usually set in the upwind direction of the fan to utilize the oncoming high-pressure gas for internal heat exchange. The inlet of the cargo hold condensation duct is usually very small to reduce the flow of high-pressure gas from outside the aircraft into the aircraft cargo hold during flight. However, when the aircraft is on the ground, the heat exchange of the condensing unit requires the fan to drive the airflow. Because the inlet of the cargo hold condensation duct is extremely small, a large gas flow rate is generated here, which in turn leads to a large airflow loss (high static pressure is usually required to overcome the loss). Therefore, the fan cargo hold auxiliary cooling condensing unit requires a high-pressure, high-efficiency axial flow fan.

[0003] Since the axial flow fan in the prior art has low static pressure efficiency when working in the high-pressure area, resulting in low work capacity and high noise of the fan blades, the present invention studies and designs an axial flow fan blade and an axial flow fan. Summary of the Invention

[0004] Therefore, the technical problem to be solved by the present invention is to overcome the defect of low static pressure efficiency of axial flow fans in the prior art when working in the high-pressure area, resulting in low work capacity, thereby providing an axial flow blade and an axial flow fan.

[0005] The present invention provides an axial flow fan blade, comprising:

[0006] A hub and a blade, one end of the blade being connected to the hub and the other end extending radially outward, with the rotation axis of the axial flow fan blade as the center, the radius of the hub being R1, the radius of the radially outermost end of the blade being R2, and within the range of R1 to R2, a three-dimensional curved surface obtained by intercepting the axial plane at the radius R of the axial flow fan blade is a primitive level of the blade at the radius R, and the axial plane is parallel to the axis of the rotation axis and perpendicular to the radial direction of the axial flow fan blade;

[0007] The axial flow fan blade is formed by flattening two adjacent elementary levels at the same radius in the circumferential direction to form a two-dimensional plane, thereby forming a two-dimensional blade cascade. The line connecting the midpoints of the leading edge and the trailing edge of any elementary level forms the chord length L of the airfoil. The relative radius is is the ratio of radius R to blade radius R2,

[0008] The angle between the straight line where L is located and the rotation direction of the axial flow fan blade is the installation angle β of the elementary airfoil, and β is proportional to the relative radius. The relationship satisfies the functional relationship of formula ①. The distance between two adjacent two-dimensional blade cascades along the rotation direction is the blade spacing t. The ratio of the chord length L to the blade spacing t is the blade density ρ. ρ is related to the relative radius. The relationship satisfies the functional relationship of formula ②;

[0009] The stacking method of each element level is based on the center of gravity. The relative position of the center of gravity of each element level in the circumferential direction is represented by θ, θ is the forward bending angle, and the relative position of the center of gravity of each element level in the axial direction is represented by z. The forward bending angle θ is related to the relative radius. The relationship satisfies the functional relationship of formula ③, the relative position z and the relative radius The relationship satisfies the functional relationship between formulas ④ and ⑤:

[0010]

[0011] Among them: a3 = -37.5 to -37.0, a2 = 110 to 110.5, a1 = -131.0 to -129.0, a0 = 80.5 to 81.2;

[0012] b3=-0.82~-0.81, b2=2.81~2.82, b1=-3.55~-3.45, b0=2.1~2.2;

[0013] c3=-102.0~-101.0, c2=316~317, c1=-261.5~-259.5, c0=62.5~63.5;

[0014] d2=-0.76~-0.65, d1=0.83~0.93, d0=-0.3~-0.2;

[0015] e2=0.005~0.05, e1=0.01~0.05, e0=-0.04~-0.015.

[0016] In some embodiments, a3 = -37.3 to -37.1, a2 = 110.08 to 110.25, a1 = -130.0 to -129.5, a0 = 80.6 to 81.0;

[0017] b3=-0.815~-0.810, b2=2.810~2.817, b1=-3.52~-3.48, b0=2.11~2.18;

[0018] c3=-101.63~-101.57, c2=316.54~316.62, c1=-260.94~-260.84, c0=63.01~63.05;

[0019] d2=-0.712~-0.708, d1=0.84~0.94, d0=-0.27~-0.23;

[0020] e2=0.020~0.025, e1=0.030~0.033, e0=-0.026~-0.020.

[0021] In some embodiments, a3=-37.257193, a2=110.2038742642, a3=-37.257193, a2=110.2038742642, a1=-129.9148286048, a0=80.8610046620;

[0022] b3=-0.8128842148, b2=2.8149019095, b1=-3.50649509, b0=2.15179;

[0023] c3=-101.6105268506, c2=316.5893700873, c1=-260.886842,

[0024] c0=63.0365703544;

[0025] d2=-0.7105404664, d1=0.8856794513, d0=-0.2570622;

[0026] e2=0.0229574760, e1=0.0312583813, e0=-0.0242159;

[0027] Right now:

[0028] In some embodiments, the elementary-level airfoil is formed by a post-loading method.

[0029] In some embodiments, the airfoil bone line ML is a line formed by connecting positions in the primitive airfoil at equal distances from the two blade surfaces in the normal direction, and the maximum height Y of the airfoil bone line ML is max Corresponding X max The value is 0.53~0.63, and the maximum normal thickness of the blade δ max Corresponding X max The value is 0.25~0.35, and its relative thickness δ max The value of / L is 0.025-0.04, and the normal direction is the direction of a line perpendicular to the tangent line selected from a point on the leaf surface curve.

[0030] In some embodiments, the maximum height Y of the airfoil bone line ML max Corresponding X max The value is 0.58, and the maximum normal thickness of the blade δ max Corresponding X max The value is 0.32, and its relative thickness δ max / L takes the value of 0.037.

[0031] In some embodiments, the relative thickness δ of each elementary airfoil from the blade root R1 to the blade tip R2 is max / L is gradually reduced, where the relative thickness is the maximum thickness δ in the normal direction max The ratio to the chord length L, the normal is to select a point on the curve as a tangent, and then make a direction perpendicular to the tangent.

[0032] In some embodiments, the number of the blades is an odd number.

[0033] In some embodiments, the number of the blades is 7.

[0034] The present invention further provides an axial flow fan, comprising the axial flow fan blades as described in any of the preceding items, and further comprising a motor, wherein the motor drives the axial flow fan blades to rotate.

[0035] The axial flow fan and the axial flow fan provided by the present invention have the following beneficial effects:

[0036] Based on the theory of aerodynamics, the present invention invents a high-efficiency axial flow fan blade structure, by respectively limiting ρ, β, θ and z and The relationship between the four expressions, namely, the four expressions, can make the fan blade have a forward bending feature, which can greatly improve the airflow morphology on the fan surface, improve the flow efficiency of the fan blade, and suppress the boundary layer separation phenomenon on the fan blade surface. Compared with the original technology, under the condition of the same static pressure (especially in the high-pressure area), it can improve the static pressure efficiency, thereby improving the work efficiency, improving the work capacity, reducing the fan blade power, and at the same time reducing the fan blade noise. The primitive-level airfoil of the present invention adopts a rear loading method, that is, limiting the maximum height Y of the airfoil skeleton line ML max Corresponding X max The value is between 0.53 and 0.63, and the maximum normal thickness of the blade δ max Corresponding X max The value is 0.25~0.35, and its relative thickness δ max / L takes a value of 0.025 to 0.04, so that the work done by the rear-loaded airfoil is mainly distributed in the rear half of the airfoil, that is, the curvature of the rear half of the airfoil will be relatively large (or relatively curved), which can improve the lift-to-drag ratio of the elementary airfoil and thus improve the efficiency of the wind blade. BRIEF DESCRIPTION OF THE DRAWINGS

[0037] Figure 1 This is a front structural diagram of the axial flow fan of the present invention;

[0038] Figure 2 is a side structural diagram of the axial flow fan of the present invention;

[0039] Figure 3 This is a front view of an existing axial flow fan blade;

[0040] Figure 4 This is a front view structural diagram of the axial flow fan blade of the present invention;

[0041] Figure 5 It is a confirmed structural diagram of multiple elementary levels of the axial flow fan blade of the present invention;

[0042] Figure 6 It is a schematic diagram of the structural parameters of the fan blade cascade of the present invention;

[0043] Figure 7 Schematic diagram of the forward bending angle of the center of gravity of the axial flow fan blade of the present invention;

[0044] Figure 8 is a schematic diagram of the axial relative positions of the axial flow fan blades of the present invention;

[0045] Figure 9 It is a parameter diagram of the elementary-stage rear-loaded airfoil of the axial flow fan blade of the present invention.

[0046] The reference numerals in the figures are as follows:

[0047] 1. Blades; 2. Hub; 3. Casing; 4. Motor. DETAILED DESCRIPTION

[0048] like Figure 1-9 As shown, the present invention provides an axial flow fan blade (preferably a high-efficiency axial flow fan blade for aviation), which includes:

[0049] A hub 2 and a blade 1, one end of the blade 1 is connected to the hub 2 and the other end extends radially outward. With the rotation axis of the axial flow fan blade as the center, the radius of the hub is R1, and the radius of the radial outermost end of the blade is R2. In the range of R1 to R2, the three-dimensional curved surface obtained by intercepting the radius R of the axial flow fan blade by the axial plane is the primitive level of the blade at the radius R, and the axial plane is parallel to the axis of the rotation axis and perpendicular to the radial direction of the axial flow fan blade (this is the definition of the primitive level, that is, any radius R is stretched along the axial direction of the fan blade to form a circular arc surface, and the three-dimensional curved surface contained in the closed curve where the circular arc surface intersects the fan blade surface is the primitive level S of the fan blade at the radius R).

[0050] The axial flow fan blades are formed by flattening two adjacent elementary levels at the same radius in the circumferential direction to form a two-dimensional plane, thus forming a two-dimensional blade cascade (that is, a three-dimensional blade cascade is formed by flattening the three-dimensional blade cascade along the circumference). Figure 6 The line connecting the midpoints of the leading edge and trailing edge of the airfoil of any of the primitive levels S forms the chord length L of the airfoil, and the relative radius It is the ratio of the radius R to the blade radius R2 (the leading edge of the airfoil is the radially outermost free end of the elementary airfoil, and the trailing edge of the airfoil is the end where the elementary airfoil is connected to the hub).

[0051] The angle between the straight line where L is located and the rotation direction of the axial flow fan blade is the installation angle β of the elementary airfoil, and β is proportional to the relative radius. The relationship satisfies the functional relationship of formula ①. The distance between two adjacent two-dimensional blade cascades along the rotation direction is the blade spacing t. The ratio of the chord length L to the blade spacing t is the blade density ρ. ρ is related to the relative radius. The relationship satisfies the functional relationship of formula ②;

[0052] The stacking method (i.e. spatial arrangement method) of each element level is based on the center of gravity. The center of gravity of each element level can be represented as P1, P2, P3, P4, and P5 respectively. The relative position of the center of gravity of each element level in the circumferential direction is represented by θ, where θ is the forward bending angle. Figure 7 The relative position of the center of gravity of each element level in the axial direction is represented by z, see Figure 8 . Forward bending angle θ and relative radius The relationship satisfies the functional relationship of formula ③, the relative position z and the relative radius The relationship satisfies the functional relationship between formulas ④ and ⑤:

[0053]

[0054]

[0055] Wherein a3=-37.5~-37.0,a2=110~110.5,a1=-131.0~-129.0,a0=80.5~81.2;

[0056] b3=-0.82~-0.81, b2=2.81~2.82, b1=-3.55~-3.45, b0=2.1~2.2;

[0057] c3=-102.0~-101.0, c2=316~317, c1=-261.5~-259.5, c0=62.5~63.5;

[0058] d2=-0.76~-0.65, d1=0.83~0.93, d0=-0.3~-0.2;

[0059] e2=0.005~0.05, e1=0.01~0.05, e0=-0.04~-0.015.

[0060] Forward bend angle θ: First, select the line connecting the centroids of each element level of a blade in the fan blade, and its projection on the plane perpendicular to the direction of the fan blade rotation axis is shown in Figure 1. Figure 7 In the second step, draw a straight line L1 between the center of the circle and the elementary center of gravity P1 at the hub in the projection diagram. In the third step, take any half of R between the radius R2 of the wind blade and the radius R1 of the hub in the projection diagram (assuming the value is R2), and its corresponding elementary center of gravity is P5. Then draw a straight line L2 from the center of the circle and P5. The angle between L1 and L2 is the forward bending angle θ of the wind blade at the radius R.

[0061] Axial relative position Z: First, select the line connecting the center of gravity of each element level of a blade in the fan blade, and its projection parallel to the direction of the fan blade rotation axis is shown in Figure 2. Figure 8 In this figure, the direction of the rotation axis is used as a reference, and the elementary center of gravity point P1 at the hub is used as a benchmark. An arbitrary radius R is taken (assuming the value is R2). The elementary center of gravity corresponding to R is P5, and the axial distance between P5 and P1 is the axial relative position Z at the radius R.

[0062] Based on the theory of aerodynamics, the present invention invents a high-efficiency axial flow fan blade structure, by respectively limiting ρ, β, θ and z and The relationship between, that is, the four expressions, can make the fan blade have a forward bending feature, which can greatly improve the airflow pattern on the fan surface, improve the flow efficiency of the fan blade, and suppress the boundary layer separation phenomenon on the fan blade surface. Compared with the original technology, under the condition of the same static pressure (especially the high-pressure area), the static pressure efficiency can be improved, thereby improving the work efficiency, improving the work capacity, reducing the fan blade power, and reducing the fan blade noise.

[0063] Technical effects of this application:

[0064] Effect of the original plan

[0065]

[0066] Effects of the present invention

[0067]

[0068] Compared with the existing technology, the solution of the present invention can greatly improve the static pressure efficiency of the fan blades under the same static pressure (especially in the high-pressure area), and increase the working capacity of the fan blades in the high-pressure area by 7% to 8%. The improvement is particularly obvious in the high static pressure area, reaching 7.9 percentage points, and reducing noise by about 1dB / A.

[0069] In some embodiments, a3 = -37.3 to -37.1, a2 = 110.08 to 110.25, a1 = -130.0 to -129.5, a0 = 80.6 to 81.0;

[0070] b3=-0.815~-0.810, b2=2.810~2.817, b1=-3.52~-3.48, b0=2.11~2.18;

[0071] c3=-101.63~-101.57, c2=316.54~316.62, c1=-260.94~-260.84, c0=63.01~63.05;

[0072] d2=-0.712~-0.708, d1=0.84~0.94, d0=-0.27~-0.23;

[0073] e2=0.020~0.025, e1=0.030~0.033, e0=-0.026~-0.020.

[0074] This is the preferred value range of multiple parameters in the above four relationship equations of the present invention, a3 is preferably -37.3 to -37.1, a2 is preferably 110.08 to 110.25, a1 is preferably -130.0 to -129.5, a0 is preferably 80.6 to 81.0; b3 is preferably -0.815 to -0.810, b2 is preferably 2.810 to 2.817, b1 is preferably -3.52 to -3.48, b0 is preferably 2.11 to 2.18; c3 is preferably -10 1.63 to -101.57, c2 is preferably 316.54 to 316.62, c1 is preferably -260.94 to -260.84, c0 is preferably 63.01 to 63.05; d2 is preferably -0.712 to -0.708, d1 is preferably 0.84 to 0.94, d0 is preferably -0.27 to -0.23; e2 is preferably 0.020 to 0.025, e1 is preferably 0.030 to 0.033, e0 is preferably -0.026 to -0.020;

[0075] It can further improve the airflow pattern on the fan surface, improve the flow efficiency of the fan blades, and inhibit the boundary layer separation phenomenon on the fan blade surface. Compared with the original technology, it can further improve the static pressure efficiency under the same static pressure (especially in the high-pressure area), improve the work efficiency, improve the work capacity, reduce the fan blade power, and further reduce the fan blade noise.

[0076] In some embodiments, a3=-37.257193, a2=110.2038742642, a1=-129.9148286048, a0=80.8610046620;

[0077] b3=-0.8128842148, b2=2.8149019095, b1=-3.50649509, b0=2.15179;

[0078] c3=-101.6105268506, c2=316.5893700873, c1=-260.886842,

[0079] c0=63.0365703544;

[0080] d2=-0.7105404664, d1=0.8856794513, d0=-0.2570622;

[0081] e2=0.0229574760, e1=0.0312583813, e0=-0.0242159;

[0082] Right now:

[0083] This is a further preferred value range for multiple parameters in the above four relationship equations of the present invention, which can further improve the airflow morphology on the fan surface, improve the flow efficiency of the fan blades, and suppress the boundary layer separation phenomenon on the fan blade surface. Compared with the original technology, under the condition of the same static pressure (especially in the high-pressure area), it can further improve the static pressure efficiency, improve the work efficiency, improve the work capacity, reduce the fan blade power, and at the same time further reduce the fan blade noise.

[0084] In some embodiments, the primitive-stage airfoil is formed using a rear-loading method. The primitive-stage airfoil of the present invention adopts a rear-loading method, so that the work of the rear-loaded airfoil is mainly distributed in the rear half of the airfoil. That is, the curvature of the rear half of the airfoil is relatively large (or relatively curved), which can improve the lift-to-drag ratio of the primitive-stage airfoil and thus improve the efficiency of the wind blade.

[0085] like Figure 9 In some embodiments, the airfoil bone line ML is a line formed by connecting positions in the primitive airfoil at equal distances from the two blade surfaces in the normal direction. The maximum height Y of the airfoil bone line ML is max Corresponding X max The value is 0.53~0.63, and the maximum normal thickness of the blade δ max Corresponding X max The value is 0.25~0.35, and its relative thickness δ maxThe value of / L is 0.025 to 0.04, and the normal direction is the direction of the line perpendicular to the tangent line selected from a point on the blade curve. The primitive-level airfoil of the present invention adopts a post-loading method, that is, the maximum height Y of the airfoil bone line ML is limited. max Corresponding X max The value is between 0.53 and 0.63, and the maximum normal thickness of the blade δ max Corresponding X max The value is 0.25~0.35, and its relative thickness δ max / L takes a value of 0.025 to 0.04, so that the work done by the rear-loaded airfoil is mainly distributed in the rear half of the airfoil, that is, the curvature of the rear half of the airfoil will be relatively large (or relatively curved), which can improve the lift-to-drag ratio of the elementary airfoil and thus improve the efficiency of the wind blade.

[0086] In some embodiments, the maximum height Y of the airfoil bone line ML max Corresponding X max The value is 0.58, and the maximum normal thickness of the blade δ max Corresponding X max The value is 0.32, and its relative thickness δ max The value of / L is 0.037. This is a further preferred value range for the rear loading mode of the elementary-level airfoil of the present invention, which can further improve the lift-to-drag ratio of the elementary-level airfoil and further improve the efficiency of the wind blade.

[0087] In some embodiments, the relative thickness δ of each elementary airfoil from the blade root R1 to the blade tip R2 is max / L is gradually reduced, where the relative thickness is the maximum thickness δ in the normal direction max The ratio of the chord length L is the normal direction, which is the direction perpendicular to the tangent line drawn from a point on the curve. This can improve the lift-to-drag ratio of the elementary airfoil while effectively increasing the blade strength and further improving the blade efficiency.

[0088] In some embodiments, the number of the blades is an odd number.

[0089] In some embodiments, the number of blades is 7. The main protection part of the present invention is the three-dimensional structure of the axial flow fan blade. The number of axial flow fan blades is 7. Since the number of pole pairs of the motor carried by the fan blade is usually an even number, the use of an odd number of fan blades can effectively avoid the formation of a resonant frequency between the fan blade and the motor. Since using a smaller number of blades will increase the installation height, and too many blades will increase aerodynamic noise, after comprehensive consideration, the present invention preferably uses 7 blades. (Note: an odd number of blades can avoid resonance with the motor. In addition, under the same blade density, fewer blades can reduce the axial height of the fan blade. In addition, when the airflow passes through the leading edge of the blade and enters the blade channel, there will be a certain amount of airflow impact to form noise. A larger number of blades will worsen this type of noise.) See Figure 5The direction of rotation of the fan blade is counterclockwise (with the output shaft end of the motor as a reference).

[0090] The present invention also provides an axial flow fan, which includes the axial flow fan blades described in any of the above items, and also includes a motor 4 and a housing 3, wherein the motor 4 drives the axial flow fan blades to rotate. Figure 4 ) and the single arc midline of the airfoil structure results in low fan performance and efficiency in high-pressure / high-load areas. Based on aerodynamic theory, this invention invents a high-efficiency axial flow fan blade structure. This blade features a forward curvature, combined with a rear-loaded, high-efficiency airfoil. This significantly improves the airflow pattern on the fan surface, suppresses boundary layer separation on the blade surface, improves blade flow efficiency, and thereby reduces blade power and noise.

[0091] The above description is merely a preferred embodiment of the present invention and is not intended to limit the present invention. Any modifications, equivalent substitutions, and improvements made within the spirit and principles of the present invention shall be included within the scope of protection of the present invention. The above description is merely a preferred embodiment of the present invention. It should be noted that those skilled in the art can make various improvements and variations without departing from the technical principles of the present invention, and such improvements and variations shall also be considered within the scope of protection of the present invention.

Claims

1. An axial flow fan blade, characterized in that: include: A hub (2) and a blade (1), one end of the blade being connected to the hub and the other end extending radially outward, with the rotation axis of the axial flow fan blade as the center, the radius of the hub being R1, the radius of the radially outermost end of the blade being R2, and within the range of R1 to R2, a three-dimensional curved surface obtained by intercepting the radius R of the axial flow fan blade by an axial plane is a primitive level of the blade at the radius R, and the axial plane is parallel to the axis of the rotation axis and perpendicular to the radial direction of the axial flow fan blade; The axial flow fan blade is formed by flattening two adjacent elementary levels at the same radius in the circumferential direction to form a two-dimensional plane, thereby forming a two-dimensional blade cascade. The line connecting the midpoints of the leading edge and the trailing edge of any elementary level forms the chord length L of the airfoil. The relative radius is is the ratio of radius R to blade radius R2; The angle between the straight line where L is located and the rotation direction of the axial flow fan blade is the installation angle β of the airfoil of the elementary level, and β is related to the relative radius. The relationship satisfies the functional relationship of formula ①. The distance between two adjacent two-dimensional blade cascades along the rotation direction is the blade spacing t. The ratio of the chord length L to the blade spacing t is the blade density ρ. ρ is related to the relative radius. The relationship satisfies the functional relationship of formula ②; The stacking method of each element level is based on the center of gravity. The relative position of the center of gravity of each element level in the circumferential direction is represented by θ, θ is the forward bending angle, and the relative position of the center of gravity of each element level in the axial direction is represented by z. The forward bending angle θ is related to the relative radius. The relationship satisfies the functional relationship of formula ③, the relative position z and the relative radius The relationship satisfies the functional relationship between formulas ④ and ⑤: Wherein a3=-37.5~-37.0,a2=110~110.5,a1=-131.0~-129.0,a0=80.5~81.2; b3=-0.82~-0.81, b2=2.81~2.82, b1=-3.55~-3.45, b0=2.1~2.2; c3=-102.0~-101.0, c2=316~317, c1=-261.5~-259.5, c0=62.5~63.5; d2=-0.76~-0.65, d1=0.83~0.93, d0=-0.3~-0.2; e2=0.005~0.05, e1=0.01~0.05, e0=-0.04~-0.

015.

2. The axial flow fan blade according to claim 1, characterized in that: a3=-37.3~-37.1, a2=110.08~110.25, a1=-130.0~-129.5, a0=80.6~81.0; b3=-0.815~-0.810, b2=2.810~2.817, b1=-3.52~-3.48, b0=2.11~2.18; c3=-101.63~-101.57, c2=316.54~316.62, c1=-260.94~-260.84, c0＝63.01～63.05； d2=-0.712~-0.708, d1=0.84~0.94, d0=-0.27~-0.23; e2=0.020~0.025, e1=0.030~0.033, e0=-0.026~-0.

020.

3. The axial flow fan blade according to claim 2, characterized in that: a3=-37.257193, a2=110.2038742642, a1=-129.9148286048, a0=80.861004 6620; b3=-0.8128842148, b2=2.8149019095, b1=-3.50649509, b0=2.15179; c3=-101.6105268506, c2=316.5893700873, c1=-260.886842, c0＝63.0365703544； d2=-0.7105404664, d1=0.8856794513, d0=-0.2570622; e2=0.0229574760, e1=0.0312583813, e0=-0.0242159; Right now:

4. The axial flow fan blade according to claim 1, characterized in that: The elementary-level airfoil is formed by a post-loading method.

5. The axial flow fan blade according to claim 4, characterized in that: The airfoil bone line ML is a line formed by connecting the positions of the primitive airfoil at equal distances from the two blade surfaces in the normal direction. The maximum height Y of the airfoil bone line ML is max Corresponding X max The value is 0.53~0.63, and the maximum normal thickness of the blade δ max Corresponding X max The value is 0.25~0.35, and its relative thickness δ max The value of / L is 0.025-0.04, and the normal direction is the direction of a line perpendicular to the tangent line selected from a point on the leaf surface curve.

6. The axial flow fan blade according to claim 5, characterized in that: Maximum height Y of the airfoil bone line ML max Corresponding X max The value is 0.58, and the maximum normal thickness of the blade δ max Corresponding X max The value is 0.32, and its relative thickness δ max / L takes the value of 0.

037.

7. The axial flow fan blade according to claim 4, characterized in that: From R1 to R2, the relative thickness of each elementary airfoil is max / L is gradually reduced, where the relative thickness is the maximum thickness δ in the normal direction max The ratio to the chord length L, the normal is to select a point on the curve as a tangent, and then make a direction perpendicular to the tangent.

8. The axial flow fan blade according to any one of claims 1 to 7, characterized in that: The number of the blades is an odd number.

9. The axial flow fan blade according to claim 8, characterized in that: The number of the blades is 7.

10. An axial flow fan, characterized in that: The axial flow fan blade comprises the axial flow fan blade according to any one of claims 1 to 9, and further comprises a motor (4), wherein the motor (4) drives the axial flow fan blade to rotate.

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