CN115263807B - Coupling bionic air conditioner axial flow fan blade structure - Google Patents
Coupling bionic air conditioner axial flow fan blade structure Download PDFInfo
- Publication number
- CN115263807B CN115263807B CN202210805742.6A CN202210805742A CN115263807B CN 115263807 B CN115263807 B CN 115263807B CN 202210805742 A CN202210805742 A CN 202210805742A CN 115263807 B CN115263807 B CN 115263807B
- Authority
- CN
- China
- Prior art keywords
- blade
- axial flow
- flow fan
- air conditioner
- airfoil
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Active
Links
- 239000011664 nicotinic acid Substances 0.000 title claims abstract description 42
- 230000008878 coupling Effects 0.000 title claims abstract description 27
- 238000010168 coupling process Methods 0.000 title claims abstract description 27
- 238000005859 coupling reaction Methods 0.000 title claims abstract description 27
- 241000272168 Laridae Species 0.000 claims abstract description 19
- 230000010349 pulsation Effects 0.000 claims description 6
- 238000013461 design Methods 0.000 abstract description 8
- 238000000926 separation method Methods 0.000 abstract description 2
- 238000012544 monitoring process Methods 0.000 description 11
- 230000003068 static effect Effects 0.000 description 8
- 230000009467 reduction Effects 0.000 description 7
- 238000004364 calculation method Methods 0.000 description 4
- 230000009471 action Effects 0.000 description 2
- 238000009434 installation Methods 0.000 description 2
- 238000004519 manufacturing process Methods 0.000 description 2
- 238000000034 method Methods 0.000 description 2
- 238000004088 simulation Methods 0.000 description 2
- 208000024172 Cardiovascular disease Diseases 0.000 description 1
- 238000009825 accumulation Methods 0.000 description 1
- 238000004378 air conditioning Methods 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000011161 development Methods 0.000 description 1
- 230000004064 dysfunction Effects 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 230000002124 endocrine Effects 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 230000017525 heat dissipation Effects 0.000 description 1
- 230000001939 inductive effect Effects 0.000 description 1
- 230000004630 mental health Effects 0.000 description 1
- 210000005036 nerve Anatomy 0.000 description 1
- 230000008569 process Effects 0.000 description 1
- 238000012545 processing Methods 0.000 description 1
- 238000011160 research Methods 0.000 description 1
- 238000001228 spectrum Methods 0.000 description 1
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- 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
- F04D29/325—Rotors specially for elastic fluids for axial flow pumps for axial flow fans
-
- 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
- F04D29/386—Skewed blades
-
- 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
- F04D29/66—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
- 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
- F04D29/667—Combating cavitation, whirls, noise, vibration or the like; Balancing especially adapted for elastic fluid pumps by influencing the flow pattern, e.g. suppression of turbulence
-
- 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
- F04D29/68—Combating cavitation, whirls, noise, vibration or the like; Balancing by influencing boundary layers
- F04D29/681—Combating cavitation, whirls, noise, vibration or the like; Balancing by influencing boundary layers especially adapted for elastic fluid pumps
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F24—HEATING; RANGES; VENTILATING
- F24F—AIR-CONDITIONING; AIR-HUMIDIFICATION; VENTILATION; USE OF AIR CURRENTS FOR SCREENING
- F24F1/00—Room units for air-conditioning, e.g. separate or self-contained units or units receiving primary air from a central station
- F24F1/06—Separate outdoor units, e.g. outdoor unit to be linked to a separate room comprising a compressor and a heat exchanger
- F24F1/38—Fan details of outdoor units, e.g. bell-mouth shaped inlets or fan mountings
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F24—HEATING; RANGES; VENTILATING
- F24F—AIR-CONDITIONING; AIR-HUMIDIFICATION; VENTILATION; USE OF AIR CURRENTS FOR SCREENING
- F24F1/00—Room units for air-conditioning, e.g. separate or self-contained units or units receiving primary air from a central station
- F24F1/06—Separate outdoor units, e.g. outdoor unit to be linked to a separate room comprising a compressor and a heat exchanger
- F24F1/40—Vibration or noise prevention at outdoor units
Landscapes
- 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 discloses a blade structure of an axial flow fan of a coupling bionic air conditioner, which comprises a blade body, wherein the blade is in a sickle-shaped structure with wide outside and narrow inside and a three-dimensional space twisted structure; the front edge of the blade is provided with a double-wave structure, the double-wave structure can induce vortex generation, the momentum and energy exchange in the boundary layer is enhanced, and the separation of the boundary layer is further controlled, so that the aerodynamic noise source is reduced to reduce the aerodynamic noise; the blade airfoil is a section airfoil of which the distance between the simulated gull wing and the wing root is 40%, and the gull airfoil has the characteristics of high lift coefficient and high lift-drag ratio. Therefore, the coupling design is carried out by adopting the two structures of the blade front edge double-wave structure and the simulated gull wing, the pneumatic noise can be effectively reduced, and the high pneumatic performance of the axial flow fan is ensured.
Description
Technical Field
The invention relates to the technical field of fans, in particular to a blade structure of an axial flow fan of a coupling bionic air conditioner.
Background
With the continuous development of the economy and society, the air conditioning technology has also made remarkable progress. The air conditioner outdoor unit mostly adopts an axial flow fan for heat dissipation, and the axial flow fan is used as an important part of the air conditioner, and the air is directionally flowed under the action of the blades by virtue of the high-speed rotation action of the axial flow fan, so that the air conveying purpose is achieved. The increase in blade functioning corresponds to the increased turbulence created, which generally increases the aerodynamic noise of the fan, which has far exceeded the mechanical noise at high speeds, and is dominant in the total noise.
Noise pollution not only affects normal rest, study and work of people, but also seriously damages physical and mental health of human bodies, such as inducing nerve dysfunction, cardiovascular diseases, endocrine dyscrasia and the like. Therefore, people expect to reduce the pneumatic noise of the axial flow fan of the air conditioner without obviously affecting the pneumatic performance of the axial flow fan of the air conditioner, which is an important point of research at home and abroad in the technical field of the air conditioner at present.
The noise is mostly reduced by reducing the aerodynamic performance of the fan or the aerodynamic performance is improved without considering the increase of the noise, so that the noise of the fan is difficult to be reduced while the aerodynamic performance is enhanced. Some axial flow fans adopt bionic design to achieve the noise reduction effect, a drag reduction structure is arranged on the surface of a blade, or a rectifying structure which is easy to wear is arranged at the front edge of the blade, so that the structure is complex, the manufacturing cost is generally high, and large-scale application is difficult to realize.
Disclosure of Invention
The invention aims at solving the technical problems of the prior art and provides a coupling bionic air conditioner axial flow fan blade structure, wherein the coupling bionic air conditioner axial flow fan blade is designed by designing a double-wave structure at the front edge of the blade, and the blade wing profile is designed by adopting a section of the blade wing at 40% of the distance from the gull wing to the wing root, so that the aerodynamic noise of the fan can be effectively reduced, and the aerodynamic performance of the blade can be obviously enhanced.
In order to solve the technical problems, the invention adopts the following technical scheme:
the blade structure of the coupling bionic air conditioner axial flow fan comprises a blade body, wherein the blade is in a sickle-shaped structure with wide outside and narrow inside and a three-dimensional space twisted structure; the front edge of the blade is provided with a double-wave structure; the blade wing profile is a section wing profile of which the distance from the simulated gull wing to the wing root is 40%;
the double wave type structure comprises a large wave structure and a small wave structure, the small wave structure is designed on the large wave structure based on the large wave structure, the double wave type structure can play a role of rectification, so that the airflow speed on the surface of the blade is uniformly distributed, the interference on the airflow at the tail edge of the blade is reduced, the turbulence boundary layer pressure pulsation intensity on the surface of the blade is further reduced, the boundary layer stability is enhanced, and the aerodynamic noise caused by the boundary layer pressure pulsation is reduced;
the aerofoil section at the position 40% of the simulated gull wing distance from the wing root can effectively improve the aerodynamic performance of the blade;
the distribution formula of the upper surface of the profile line of the section airfoil at the position 40% of the simulated gull wing distance from the wing root is as follows: z is Z up ＝Z (c) +Z (t) The distribution formula of the lower surface of the contour line is as follows: z is Z low ＝Z (c) -Z (t) Wherein Z is up 、Z low Z is the coordinates of the upper and lower surfaces of the airfoil (c) Z is the mean camber line coordinate of the section of the airfoil (t) The thickness coordinate of the airfoil is c, and the chord length of the airfoil is c;
the mean camber line distribution formula is:wherein Z is (c)max Is the maximum value of the camber line distribution, c is the chord length of the airfoil, eta is the relative position coordinate of the chord length, S n Is a coefficient to be determined;
the airfoil thickness distribution formula is:wherein Z is (t)max For maximum thickness of mean camber line distribution, A n Is a coefficient to be determined;
the Z is (c)max The distribution formula of (2) is: z is Z (c)max /c＝0.14/(1+1.32ξ 1.4 )；
The Z is (t)max The distribution formula of (2) is: z is Z (t)max /c＝0.1/(1+3.545ξ 1.4 )；
Where ζ is the proportionality coefficient of the thickness distribution.
Further, the amplitude of the large wave structure is 5mm, the wavelength is 20.6mm, the amplitude of the small wave structure is 1mm, and the wavelength is 2.25mm.
Further, the undetermined coefficient S n Is given by S 1 ＝3.876，S 2 ＝-0.806，S 3 ＝0.771。
Further, the undetermined coefficient A n The value of (A) is A 1 ＝-15.245，A 2 ＝26.481，A 3 ＝-18.976，A 4 ＝4.623。
Further, the blade mounting angle is 26.55 degrees, and the difference between the inner diameter mounting angles is controlled to be +/-2 degrees.
Further, the connecting line of the center points of the blade profiles on each rotating radius of the blade is a three-dimensional curve, and the axial direction is upward parabolic.
Further, the chord length at the outer diameter of the blade is within 2.7 times of the chord length at the inner diameter, and the ratio of the chord length of each section of the blade to the curvature radius is controlled to be between 0.75 and 0.8.
The invention has the following beneficial effects:
(1) The double wave type structure is designed at the front edge of the blade, and is similar to a small-scale vortex generator, so that vortex generation can be induced to enhance momentum and energy exchange in the boundary layer, further separation of the boundary layer is controlled, and aerodynamic noise sources are reduced to reduce aerodynamic noise.
(2) The blade airfoil is designed based on the section of the gull wing, which is 40% away from the wing root, and compared with the traditional airfoil, the gull bionic airfoil has better aerodynamic performance due to the characteristics of high lift coefficient and high lift-drag ratio, and can obviously enhance the aerodynamic performance of the blade.
(3) The coupling design is carried out by adopting the two structures of the blade front edge double-wave structure and the simulated gull wing, so that the problem of overlarge airflow noise caused by the turbulence accumulation of airflow at the tail edge due to uneven flow speed distribution on the surface of the blade front edge is solved, and the high aerodynamic performance of the axial flow fan and the easy-processing property of the blade are also ensured.
Drawings
FIG. 1 is a schematic perspective view of a coupled bionic air conditioner axial flow fan blade structure of the present invention;
FIG. 2 is a schematic top view of a coupled bionic air conditioner axial flow fan blade structure according to the present invention;
FIG. 3 is a schematic front view of a coupled bionic air conditioner axial flow fan blade structure according to the present invention;
FIG. 4 is a schematic view of a double wave-shaped leading edge structure according to the present invention;
FIG. 5 is a schematic view of a 40% section airfoil configuration of an imitated sea-gull wing according to the present invention;
FIG. 6 is a schematic view of a partial cross-section of a coupled bionic air conditioner axial flow fan blade structure of the present invention;
FIG. 7 is a graph comparing static pressure-flow characteristics of an axial flow fan employing a coupled bionic air conditioner axial flow fan blade structure of the present invention with an original axial flow fan;
FIG. 8 is a graph comparing static pressure-efficiency characteristics of an axial flow fan employing a blade structure of a coupled bionic air conditioner axial flow fan of the present invention with that of an original axial flow fan;
FIG. 9 is a graph of 12 monitoring points of the aerodynamic noise simulation of an axial flow fan employing a coupled bionic air conditioner axial flow fan blade structure according to the present invention;
FIG. 10 is a graph of sound pressure level comparison of 12 monitoring points of an axial flow fan employing a blade structure of a coupled bionic air conditioner axial flow fan of the present invention with an original axial flow fan;
FIG. 11 is a graph showing the comparison of sound pressure level spectra of an axial flow fan with a 4 # monitoring point of an original axial flow fan, which is coupled with the blade structure of the axial flow fan of the bionic air conditioner;
the method comprises the following steps: 1. a hub; 2. a blade; 3. a double wave-like leading edge structure; 4. 40% of the simulated gull wing is provided with a section wing profile.
Detailed Description
The invention will be described in further detail with reference to the accompanying drawings and specific preferred embodiments.
In the description of the present invention, it should be understood that the terms "left", "right", "upper", "lower", etc. indicate orientations or positional relationships based on the orientations or positional relationships shown in the drawings, are merely for convenience in describing the present invention and simplifying the description, and do not indicate or imply that the apparatus or element being referred to must have a specific orientation, be configured and operated in a specific orientation, and "first", "second", etc. do not indicate the importance of the components, and thus are not to be construed as limiting the present invention. The specific dimensions adopted in the present embodiment are only for illustrating the technical solution, and do not limit the protection scope of the present invention.
As shown in fig. 1-3, the blade structure of the coupling bionic air conditioner axial flow fan comprises a blade 2 body, wherein the blade 2 is a coupling bionic blade, the blade 2 is in a sickle-shaped three-dimensional space twisted structure with wide outside and narrow inside, and the front edge of the blade 2 is provided with a double-wave-shaped front edge structure 3; the connecting line of the blade profile central points on each rotating radius of the blade 2 is a three-dimensional curve, and the axial direction is upward parabolic; the chord length at the outer diameter of the blade 2 is within 2.7 times of the chord length at the inner diameter, and the ratio of the chord length of each section of the blade 2 to the curvature radius is controlled between 0.75 and 0.8.
The blades 2 are arranged on the hub 1 of the axial flow fan of the air conditioner, the installation angle of the blades 2 is 26.55 degrees, and the difference of the installation angles of the inner diameters is controlled to be +/-2 degrees.
The wing profile of the blade 2 is a section wing profile 4 of which the distance between the simulated gull wing and the wing root is 40%.
As shown in fig. 4, the double-wave-shaped leading edge structure 3 of the blade 2 comprises a large wave structure and a small wave structure, wherein the small wave structure is designed on the large wave structure on the basis of the large wave structure, and the amplitude of the large wave structure is 5mm and the wavelength is 20.6mm; the amplitude of the small wave structure is 1mm, and the wavelength is 2.25mm. The double-wave-shaped front edge structure 3 is similar to a small-scale vortex generator, can play a role in rectifying, enables the airflow speed on the surface of the blade to be uniformly distributed, reduces interference on airflow on the tail edge of the blade, and further reduces the turbulence boundary layer pressure pulsation intensity on the surface of the blade so as to enhance the stability of the boundary layer, thereby reducing aerodynamic noise caused by the boundary layer pressure pulsation. In addition, the double-wave-shaped front edge structure 3 is simple in structure, easy to process and low in manufacturing cost.
5-6, the aerodynamic performance of the blade can be effectively improved by the wing profile 4 with the section of the simulated gull wing 40% away from the wing root; the distribution formula of the upper surface and the lower surface of the profile line of the section airfoil 4 at the 40% distance from the fin root of the simulated seagull wing is as follows:
Z up ＝Z (c) +Z (t) ，
Z low ＝Z (c) -Z (t) ，
wherein Z is up 、Z low Z is the coordinates of the upper and lower surfaces of the airfoil (c) Z is the mean camber line coordinate of the section of the airfoil (t) The thickness coordinate of the airfoil is c, and the chord length of the airfoil is c;
the distribution formula of the camber line of the section airfoil profile at the 40% position of the simulated gull wing distance from the wing root is as follows:
wherein Z is (c)max Is the maximum value of the camber line distribution, c is the chord length of the airfoil, eta is the relative position coordinate of the chord length, S n For the undetermined coefficient (n=1, 2, 3), the value is S 1 ＝3.876，S 2 ＝-0.806，S 3 ＝0.771。
The airfoil thickness distribution formula is:wherein Z is (t)max For maximum thickness of mean camber line distribution, A n Is a coefficient to be determined (n=1, 2,3, 4); a is that 1 ＝-15.245，A 2 ＝26.481，A 3 ＝-18.976，A 4 ＝4.623。
Z (c)max The distribution formula of (2) is: z is Z (c)max /c＝0.14/(1+1.32ξ 1.4 )；
Z (t)max The distribution formula of (2) is: z is Z (t)max /c＝0.1/(1+3.545ξ 1.4 )；
Where ζ is the proportionality coefficient of the thickness distribution.
The section wing profile is drawn according to the relative coordinates of the upper and lower surfaces of the section wing profile at 40% of the gull wing distance from the wing root as shown in fig. 5. The simulated gull wing has the characteristics of high lift coefficient and high lift-drag ratio, and has better aerodynamic performance compared with the traditional wing.
Example 1: in order to verify the aerodynamic performance of the axial flow fan adopting the coupling bionic air conditioner axial flow fan blade structure, CFD numerical calculation is carried out on the original axial flow fan without the coupling bionic blade design and the coupling bionic axial flow fan adopting the coupling bionic blade under five working conditions of static pressure 0Pa, 10Pa, 20Pa, 30Pa and 40Pa, and the aerodynamic performance simulation calculation results are shown in figures 7 and 8.
As can be seen from fig. 7 and 8, the flow and efficiency of the axial flow fan adopting the coupling bionic air conditioner axial flow fan blade structure of the invention are higher than those of the original axial flow fan without coupling bionic design, and under the working condition of static pressure 0Pa, the flow is improved by about 4.5%, and the efficiency is improved by 5.9%; under the working condition of static pressure 10Pa, the flow is improved by about 14.3 percent, and the efficiency is improved by 7.1 percent; under the working condition of the static pressure of 20Pa, the flow is improved by about 6.1 percent, and the efficiency is improved by 3.32 percent; under the working condition of static pressure of 30Pa, the flow is improved by about 12.7 percent, and the efficiency is improved by 2.52 percent; under the working condition of the static pressure of 40Pa, the flow is improved by about 14.2 percent, and the efficiency is improved by 3.55 percent. From this, it can be seen that, compared with the original axial flow fan of no coupling bionic design, the aerodynamic performance of the axial flow fan adopting the coupling bionic air conditioner axial flow fan blade structure is obviously enhanced.
Example 2: in order to verify the noise reduction performance of the axial flow fan adopting the coupling bionic air conditioner axial flow fan blade structure, on the basis of the calculation result of the embodiment 1, noise monitoring points are arranged on the circumference which is 1m away from the fan radius at intervals of 30 degrees, pneumatic noise numerical calculation is carried out, and 12 monitoring points are distributed as shown in figure 9.
Fig. 10 is a graph comparing sound pressure levels of 12 monitoring points of an axial flow fan adopting the coupling bionic air conditioner axial flow fan blade structure of the invention with that of an original axial flow fan adopting a non-coupling bionic design, and as seen from fig. 10, pneumatic noise of the axial flow fan adopting the coupling bionic air conditioner axial flow fan blade structure is obviously lower than that of the original axial flow fan adopting the non-coupling bionic design, sound pressure levels of monitoring points 1 to 12 are reduced, especially sound pressure level reduction of monitoring point 4 is most obvious, and the sound pressure level reduction of the monitoring points 1 to 12 can reach 18.83dB, and average total sound pressure level reduction of the monitoring points 1 to 12 can reach 9.1dB.
The sound pressure level spectrogram of the No. 4 monitoring point is shown in fig. 11, and it can be seen from the graph that the sound pressure level of the axial flow fan adopting the coupling bionic air conditioner axial flow fan blade structure is reduced in each frequency band, and the reduction of 20-4000Hz frequency band is most remarkable, which can reach 21.1dB. Therefore, the axial flow fan adopting the blade structure of the coupling bionic air conditioner axial flow fan can effectively reduce noise.
The preferred embodiments of the present invention have been described in detail above, but the present invention is not limited to the specific details of the above embodiments, and various equivalent changes can be made to the technical solution of the present invention within the scope of the technical concept of the present invention, and all the equivalent changes belong to the protection scope of the present invention.
Claims (7)
1. The utility model provides a coupling bionic air conditioner axial fan blade structure which characterized in that: the novel three-dimensional space twisted type wind turbine blade comprises a blade body, wherein the blade is of a sickle-shaped structure with a wide outer part and a narrow inner part; the front edge of the blade is provided with a double-wave structure; the blade wing profile is a section wing profile of which the distance from the simulated gull wing to the wing root is 40%;
the double wave type structure comprises a large wave structure and a small wave structure, the small wave structure is designed on the large wave structure based on the large wave structure, the double wave type structure can play a role of rectification, so that the airflow speed on the surface of the blade is uniformly distributed, the interference on the airflow at the tail edge of the blade is reduced, the turbulence boundary layer pressure pulsation intensity on the surface of the blade is further reduced, the boundary layer stability is enhanced, and the aerodynamic noise caused by the boundary layer pressure pulsation is reduced;
the aerofoil section at the position 40% of the simulated gull wing distance from the wing root can effectively improve the aerodynamic performance of the blade;
the distribution formula of the upper surface of the profile line of the section airfoil at the position 40% of the simulated gull wing distance from the wing root is as follows: z is Z up ＝Z (c) +Z (t) The distribution formula of the lower surface of the contour line is as follows: z is Z low ＝Z (c) -Z (t) Wherein Z is up 、Z low Z is the coordinates of the upper and lower surfaces of the airfoil (c) Z is the mean camber line coordinate of the section of the airfoil (t) The thickness coordinate of the airfoil is c, and the chord length of the airfoil is c; the mean camber line distribution formula is:wherein Z is (c)max Is the maximum value of the camber line distribution, c is the chord length of the airfoil, eta is the relative position coordinate of the chord length, S n Is a coefficient to be determined; the airfoil thickness distribution formula is: />Wherein Z is (t)max For maximum thickness of mean camber line distribution, A n Is a coefficient to be determined;
the Z is (c)max The distribution formula of (2) is: z is Z (c)max /c＝0.14/(1+1.32ξ 1.4 )；
The Z is (t)max The distribution formula of (2) is: z is Z (t)max /c＝0.1/(1+3.545ξ 1.4 )；
Where ζ is the proportionality coefficient of the thickness distribution.
2. The coupled bionic air conditioner axial flow fan blade structure of claim 1, wherein: the amplitude of the large wave structure is 5mm, the wavelength is 20.6mm, the amplitude of the small wave structure is 1mm, and the wavelength is 2.25mm.
3. The coupled bionic air conditioner axial flow fan blade structure of claim 2, wherein: the undetermined coefficient S n Is given by S 1 ＝3.876，S 2 ＝-0.806，S 3 ＝0.771。
4. The coupled bionic air conditioner axial flow fan blade structure of claim 3, wherein: the undetermined coefficient A n The value of (A) is A 1 ＝-15.245，A 2 ＝26.481，A 3 ＝-18.976，A 4 ＝4.623。
5. The coupled bionic air conditioner axial flow fan blade structure of claim 4, wherein: the blade mounting angle is 26.55 degrees, and the difference of the inner diameter mounting angles is controlled to be +/-2 degrees.
6. The coupled bionic air conditioner axial flow fan blade structure of claim 5, wherein: the connecting line of the blade profile central points on each rotating radius of the blade is a three-dimensional curve, and the axial direction is upward parabolic.
7. The coupled bionic air conditioner axial flow fan blade structure of claim 6, wherein: the chord length at the outer diameter of the blade is within 2.7 times of the chord length at the inner diameter, and the ratio of the chord length of each section of the blade to the curvature radius is controlled between 0.75 and 0.8.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210805742.6A CN115263807B (en) | 2022-07-08 | 2022-07-08 | Coupling bionic air conditioner axial flow fan blade structure |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210805742.6A CN115263807B (en) | 2022-07-08 | 2022-07-08 | Coupling bionic air conditioner axial flow fan blade structure |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN115263807A CN115263807A (en) | 2022-11-01 |
| CN115263807B true CN115263807B (en) | 2023-12-22 |
Family
ID=83764577
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202210805742.6A Active CN115263807B (en) | 2022-07-08 | 2022-07-08 | Coupling bionic air conditioner axial flow fan blade structure |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN115263807B (en) |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2005282491A (en) * | 2004-03-30 | 2005-10-13 | Mitsubishi Fuso Truck & Bus Corp | Program and method for preparing aerofoil profile |
| KR20070107877A (en) * | 2006-05-04 | 2007-11-08 | 주식회사 에어로네트 | Multi sectioning design method for axial fan |
| CN107023515A (en) * | 2017-06-16 | 2017-08-08 | 吉林大学 | A kind of low noise axial fan composite bionic airfoil fan |
| CN108180169A (en) * | 2018-02-09 | 2018-06-19 | 广东美的厨房电器制造有限公司 | Fan and micro-wave oven |
-
2022
- 2022-07-08 CN CN202210805742.6A patent/CN115263807B/en active Active
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2005282491A (en) * | 2004-03-30 | 2005-10-13 | Mitsubishi Fuso Truck & Bus Corp | Program and method for preparing aerofoil profile |
| KR20070107877A (en) * | 2006-05-04 | 2007-11-08 | 주식회사 에어로네트 | Multi sectioning design method for axial fan |
| CN107023515A (en) * | 2017-06-16 | 2017-08-08 | 吉林大学 | A kind of low noise axial fan composite bionic airfoil fan |
| CN108180169A (en) * | 2018-02-09 | 2018-06-19 | 广东美的厨房电器制造有限公司 | Fan and micro-wave oven |
Non-Patent Citations (2)
| Title |
|---|
| 史继拓 ; 华欣 ; 王宏伟 ; 吴克超 ; .基于仿海鸥翅翼构型的机翼气动性能分析.机械科学与技术.2017,(第S1期), * |
| 基于仿海鸥翅翼构型的机翼气动性能分析;史继拓;华欣;王宏伟;吴克超;;机械科学与技术(第S1期) * |
Also Published As
| Publication number | Publication date |
|---|---|
| CN115263807A (en) | 2022-11-01 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN108386383B (en) | Cross bionic blade combining carangid body and bird wing and preparation method thereof | |
| CN110360150B (en) | Wind wheel, centrifugal fan and air conditioner indoor unit | |
| CN107061329A (en) | A kind of axial flow blower | |
| CN111120401A (en) | Multi-wing centrifugal ventilator blade design method based on NACA wing profile | |
| WO2021063050A1 (en) | Fan and axial-flow impeller | |
| CN103122872B (en) | Axial fan | |
| CN106762824A (en) | Axial flow blower 3 d impeller with leaf vein texture and sea-gull type splitterr vanes | |
| CN205173055U (en) | Low noise that trailing edge is buckled does not have spiral case fan wheel | |
| CN115263807B (en) | Coupling bionic air conditioner axial flow fan blade structure | |
| CN203130602U (en) | Cross-flow fan for air conditioner, cross-flow blower and air conditioner | |
| CN203584898U (en) | Low-noise high-efficiency central air conditioner outdoor machine cooling axial-flow fan | |
| CN110285094B (en) | Curved sweep type blade for axial flow fan | |
| CN108953222B (en) | Centrifugal impeller | |
| CN207004919U (en) | Axial flow blower 3 d impeller with leaf vein texture and splitterr vanes | |
| CN216589274U (en) | Axial flow fan blade, fan assembly, air conditioner outdoor unit and air conditioner | |
| CN114909325A (en) | Low-noise axial flow fan blade and axial flow fan | |
| CN214404094U (en) | Wind wheel and fan | |
| CN205638999U (en) | Blade area wing section guide plate and stator have bionical tail edge's axial fan | |
| CN114607641A (en) | Axial fan's stator structure and axial fan | |
| CN210660731U (en) | Mining local axial-flow fan with V-shaped blade tip structure | |
| CN106837867A (en) | Axial flow blower 3 d impeller with leaf vein texture and splitterr vanes | |
| CN102979764A (en) | Axial flow fan blade and fan | |
| CN213511350U (en) | Axial flow wind wheel and air conditioner | |
| CN202418036U (en) | Axial flow fan and air conditioner with same | |
| CN205779899U (en) | Centrifugation blade, outer rotor blower fan and air-conditioner |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant |