CN216478016U - Backward centrifugal impeller - Google Patents
Backward centrifugal impeller Download PDFInfo
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- CN216478016U CN216478016U CN202121612242.8U CN202121612242U CN216478016U CN 216478016 U CN216478016 U CN 216478016U CN 202121612242 U CN202121612242 U CN 202121612242U CN 216478016 U CN216478016 U CN 216478016U
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- centrifugal impeller
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Abstract
The utility model relates to a backward centrifugal impeller and a ventilator, which comprises a blade, a front disc and a rear disc, and is characterized in that a plurality of blades are fixedly arranged between the front disc and the rear disc, the cross section of each blade is in a crescent-shaped airfoil shape, the blade adopts the airfoil-shaped blade in a specific shape, the impact loss and the inlet impact noise of the blade channel at the inlet can be weakened, and the flowing state of airflow before entering the blade channel is improved.
Description
Technical Field
The utility model relates to the related field, in particular to a backward centrifugal impeller.
Background
The ventilator is a machine which increases the gas pressure and discharges the gas by depending on the input mechanical energy, generally, for the convenience of processing, the blade of the impeller of the centrifugal ventilator is usually made of metal plate, the section of the blade is of an equal thickness type, because the actual blade has a certain thickness, near the edge of the outlet of the blade, because the pressure of the working surface and the pressure of the non-working surface of the blade are different, the airflows at the two sides form a vortex and are continuously expanded in the confluence process, the main airflow is disturbed, and the pressure loss and the airflow noise are formed;
the ventilator gas forms an axial vortex opposite to the rotation direction of the impeller in the blade flow passage, so that the relative speed of the gas flow at the outlet of the impeller deviates instead of flowing out from the tangential direction of the point under the action of the axial vortex when the main gas flow flows from the inlet to the outlet of the blade passage when the gas flow flows through the passages among the blades, and the pressure is reduced;
when the ventilator is actually operated, the flow of the operating working point of the ventilator cannot be guaranteed to always operate at the designed flow, and thus the impact of the airflow and the blades can be generated.
SUMMERY OF THE UTILITY MODEL
The utility model aims to provide a backward centrifugal impeller, which solves the problems.
The utility model realizes the purpose through the following technical scheme: the utility model provides a backward centrifugal impeller, includes blade, front disc and back dish, its characterized in that, the front disc with fixed a plurality of blades that are equipped with between the back dish, the blade cross-section is the airfoil type of crescent shape.
Preferably, the shape of the inlet side head of the blade is smooth and circular arc instead of a right-angle sharp edge, so that the impact loss and the inlet impact noise at the inlet of the blade channel can be reduced, and the flow state of the airflow before entering the blade channel is improved.
Preferably, the shape of the outlet-side tail part of the blade is gradually reduced, and the thickness of the outlet-side tail part is the smallest thickness of the outlet-side tail part of the blade in the chord direction of the whole blade, so that the expansion degree of the airflow wake at the outlet edge of the blade can be weakened, and the outlet pressure loss and the outlet airflow noise can be reduced.
Preferably, the center point of the leading arc, i.e., the leading point of the blade profile, is m points, the center point of the trailing arc, i.e., the trailing point, is p points, the straight line segment "pm" is the chord length of the blade, the length is L, the main body parts of the upper arc and the lower arc are both on the upper side of the straight line segment "pm" of the chord length, the arc line "mep" is the center line of the crescent, the maximum camber point of the center line "mep" relative to the chord length line is e points, the maximum camber value is f, and the maximum thickness of the blade profile in the normal direction of the chord length is c.
Preferably, in the present invention, "mp" ═ L is the blade chord length.
As a preferable range of the present invention, the maximum relative thickness of the airfoil is in a suitable range:
in particular to
The appropriate range of the maximum relative camber of the blade profile is as follows:
in particular
Preferably, the middle main body section of the blade adopts an upper concave crescent-shaped airfoil shape, and the thickness of the middle part of the blade is larger.
Preferably, the vane midsection occupies a small portion of the flow area, but limits the development of axial swirl and the resulting flow losses to some extent.
Compared with the prior art, the utility model has the following beneficial effects: the blades of the utility model adopt airfoil-shaped blades with specific shapes, which can weaken the impact loss and the inlet impact noise when the blade channel is at the inlet and simultaneously improve the flowing state of airflow before entering the blade channel.
Drawings
FIG. 1 is a schematic structural diagram of an embodiment of the present invention;
FIG. 2 is a schematic view of the blade of FIG. 1 according to an embodiment of the present invention;
FIG. 3 is a schematic diagram of the overall appearance of the product in FIG. 1 according to the embodiment of the present invention;
FIG. 4 is a static pressure comparison graph of a comparative prototype according to a first embodiment of the present invention;
FIG. 5 is a graph comparing the static pressure efficiency of a comparative prototype to that of a comparative prototype according to the first embodiment of the present invention;
FIG. 6 is a static pressure comparison graph of example two of the present invention and a comparison sample machine two;
FIG. 7 is a graph comparing the static pressure efficiency of the second embodiment of the present invention with that of the second comparative sample.
Detailed Description
The utility model will be further described with reference to the accompanying drawings in which:
a backward centrifugal impeller is shown in figures 1-7 and comprises blades 11, a front disc 12 and a rear disc 13 and is characterized in that a plurality of blades 11 are fixedly arranged between the front disc 12 and the rear disc 13, and the cross sections of the blades 11 are crescent-shaped airfoil shapes.
Preferably, the shape of the inlet side head of the vane 11 is smooth arc shape without a sharp edge, so that the impact loss and inlet impact noise at the inlet of the vane passage can be reduced, and the flow state of the air flow before entering the flow passage of the vane 11 can be improved.
Preferably, the shape of the outlet-side tail of the blade 11 is gradually reduced, and the thickness of the outlet-side tail is the smallest thickness of the whole blade 11 in the chord direction, so that the expansion degree of the airflow wake at the outlet edge of the blade 11 can be weakened, and the outlet pressure loss and the outlet airflow noise can be reduced.
Preferably, the center point of the leading edge of the blade profile, i.e., the center point of the head arc, is m, the center point of the trailing edge, i.e., the center point of the tail arc, is p, the straight line segment "pm" is the chord length of the blade 11, the length is L, the main body parts of the upper arc and the lower arc are both on the upper side of the straight line segment "pm" of the chord length, the arc line "mep" is the center line of the crescent, the maximum camber point of the center line "mep" relative to the chord length line is e, the maximum camber value is f, and the maximum thickness of the blade profile in the normal direction of the chord length is c.
Preferably, in the present invention, "mp" ═ L is the chord length of the blade 11.
As a preferable range of the present invention, the maximum relative thickness of the airfoil is in a suitable range:
in particular
The appropriate range of the maximum relative camber of the blade profile is as follows:
in particular
Preferably, the middle main body section of the blade 11 is of a wing shape with a concave crescent shape, and the middle part of the blade 11 has a larger thickness.
Preferably, the vane 11 occupies a small part of the flow area in the middle, but limits the development of axial vortices and the resulting flow losses to some extent.
In use, the section of the blade 11 of the first embodiment and the second embodiment is a crescent-shaped airfoil, the main dimensions of which are shown in fig. 1, and the main data are shown in the following table:
vane exit diameter Φ D for example one and comparative sample one2Are all phi 226.6mm, the number of the blades is 7, and the blades of the comparison model I are arc-shaped blades with equal thickness and the blades of the embodiment IThe blade is a crescent-shaped airfoil-shaped blade, and the diameter phi D of the blade inlet of the prototype I is compared with that of the blade of the prototype I1Is 130.8mm phi, and the inlet diameter phi D of the vane of the first embodiment1Phi is 151.9 mm;
the embodiment is based on a comparison model I, the fan blade is formed by improving the shape of the blade, namely the original conventional uniform-thickness arc-shaped blade is improved into a crescent-shaped wing section with a concave bottom, and other main dimensions of an impeller and a ventilator are kept unchanged.
The ratio of the maximum camber of the blade midline to the blade chord length of the first embodiment is as follows: f/L is 0.068;
the diameter ratio of the chord length of the vane to the outlet of the first embodiment is as follows: L/D2＝0.356；
The blade installation angle of the first embodiment is 42.18 degrees;
the diameter ratio of the inlet and the outlet of the blade in the first embodiment is as follows: d1/D2＝0.672；
The performance curves of example one and comparative sample one are compared and shown in FIGS. 4-5; the main performance parameters for the highest efficiency operating point are compared as shown in the following table:
| rotating speed (r/min) | Air volume (m)3/h) | Static pressure (Pa) | Static pressure efficiency (%) | |
| Comparison prototype 1 | 2500 | 720 | 300.8 | 57.92 |
| Example one | 2500 | 720 | 309.8 | 61.97 |
Under the working condition of the same air quantity, the static pressure of the first embodiment is improved by 9Pa and the static pressure efficiency is improved by 4.05 percent compared with that of the first comparative sample machine;
vane exit diameter Φ D for example two and comparative sample two2Phi 263.4mm, 7 blades, the second sample machine, the second embodiment, and the second sample machine1Is phi 159.1mm, the inlet diameter phi D of the vane of the second embodiment1Phi 177.8 mm;
the second embodiment is formed by improving the shape of the blade on the basis of comparing with the second embodiment, namely the original conventional uniform-thickness arc-shaped blade is improved into a crescent-shaped airfoil shape with the concave bottom, and other main sizes of an impeller and a ventilator are kept unchanged;
the ratio of the maximum camber of the blade midline to the blade chord length of the second embodiment is as follows: f/L is 0.07;
the diameter ratio of the chord length of the vane to the outlet of the second embodiment is as follows: L/D2＝0.372；
The blade setting angle of the second embodiment is 42.45 °;
the diameter ratio of the inlet and the outlet of the blade in the second embodiment is as follows: d1/D2＝0.675；
The performance curves of example two and comparative sample two are compared and shown in FIGS. 6-7; the main performance parameters for the highest efficiency operating point are compared as shown in the following table:
under the working condition of the same air volume, the static pressure of the second embodiment is improved by 54.8Pa and the static pressure efficiency is improved by 2.32 percent compared with that of the second comparative sample machine.
The foregoing illustrates and describes the principles, general features, and advantages of the present invention. It will be understood by those skilled in the art that the present invention is not limited to the embodiments described above, which are described in the specification and illustrated only to illustrate the principle of the present invention, but that various changes and modifications may be made therein without departing from the spirit and scope of the present invention, which fall within the scope of the utility model as claimed.
Claims (6)
1. The backward centrifugal impeller comprises blades, a front disc and a rear disc and is characterized in that a plurality of blades are fixedly arranged between the front disc and the rear disc, the cross section of each blade is a crescent-shaped airfoil shape, the head of the inlet side of each blade is smooth and circular-arc without a right-angle sharp edge, the tail of the outlet side of each blade is gradually thinned, and the thickness of the tail of each blade is the minimum thickness of the whole blade in the chord length direction.
2. The backward centrifugal impeller according to claim 1, wherein the leading edge point of the blade profile, i.e., the midpoint of the head arc, is set to m, the trailing edge point, i.e., the midpoint of the tail arc, is set to p, the straight line segment "pm" is the chord length of the blade, the length is L, the main portions of the upper arc and the lower arc are located on the upper side of the straight line segment "pm" of the chord length, the arc "mep" is the center line of the crescent, the maximum camber point of the center line "mep" relative to the chord length line is set to e, the maximum camber value thereof is set to f, and the maximum thickness of the blade profile in the normal direction of the chord length is set to c.
3. A backward centrifugal impeller according to claim 2, wherein "mp" = L is the vane chord length.
4. A backward centrifugal impeller according to claim 3 wherein the profile has a suitable range of relative thicknesses
(ii) a Proper range of relative camber of blade profile
。
5. The backward centrifugal impeller of claim 4 wherein said blade intermediate body section is of a concave crescent shape, said blade intermediate section being thicker.
6. A backward centrifugal impeller according to claim 5 wherein the vane midsection limits the development of axial vortices and the resulting flow losses.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202121612242.8U CN216478016U (en) | 2021-07-15 | 2021-07-15 | Backward centrifugal impeller |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202121612242.8U CN216478016U (en) | 2021-07-15 | 2021-07-15 | Backward centrifugal impeller |
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| CN216478016U true CN216478016U (en) | 2022-05-10 |
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| CN202121612242.8U Active CN216478016U (en) | 2021-07-15 | 2021-07-15 | Backward centrifugal impeller |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113864231A (en) * | 2021-07-15 | 2021-12-31 | 浙江科贸智能机电股份有限公司 | Backward centrifugal impeller and ventilator |
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2021
- 2021-07-15 CN CN202121612242.8U patent/CN216478016U/en active Active
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113864231A (en) * | 2021-07-15 | 2021-12-31 | 浙江科贸智能机电股份有限公司 | Backward centrifugal impeller and ventilator |
| CN113864231B (en) * | 2021-07-15 | 2024-06-14 | 浙江科贸智能机电股份有限公司 | Backward centrifugal impeller and ventilator |
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