CN217176965U

CN217176965U - Centrifugal impeller for turbine fan, turbine fan and integrated stove

Info

Publication number: CN217176965U
Application number: CN202122883336.5U
Authority: CN
Inventors: 李承鹏; 邓鹏飞; 龚东巧; 付成冲; 陆峰; 王帅
Original assignee: Haier Smart Home Co Ltd; Qingdao Haier Wisdom Kitchen Appliance Co Ltd
Current assignee: Haier Smart Home Co Ltd; Qingdao Haier Wisdom Kitchen Appliance Co Ltd
Priority date: 2021-11-23
Filing date: 2021-11-23
Publication date: 2022-08-12
Anticipated expiration: 2031-11-23

Abstract

The utility model relates to the technical field of household appliances, in particular to a centrifugal impeller for a turbine fan, the turbine fan and an integrated stove, the turbine fan of the utility model comprises a volute and a motor, and the centrifugal impeller comprises a basal disc, blades and an annular fixing piece; the basal disc is positioned in the volute and fixedly connected with an output shaft of the motor; blade one end and basal disc fixed connection, the quantity of blade sets up to a plurality ofly, and a plurality of blades are at the ascending evenly distributed of circumference of basal disc, the other end fixed connection of annular mounting and a plurality of blades, and wherein, the blade sets up to the unequal thickness blade to reduce the drag coefficient of blade, thereby reduce the noise that turbofan produced. Through setting up the blade into the blade of unequal thickness, when the blade was rotatory, the air when through the blade streamline structure of unequal thickness, reduced the resistance coefficient of air and blade, promptly, reduce the resistance between blade and the air, the noise of friction or stirring between greatly reduced blade and the air.

Description

Centrifugal impeller for turbine fan, turbine fan and integrated stove

Technical Field

The utility model relates to a domestic appliance's technical field specifically provides a centrifugal impeller and turbofan, integrated kitchen for turbofan.

Background

The integrated kitchen range is a kitchen appliance integrating various work of a range hood, a gas stove, a disinfection cabinet, a storage cabinet and the like, and has the advantages of space saving, good oil fume extraction effect, energy saving, low consumption, environmental protection and the like.

The existing integrated cooker adopts a working mode of near-suction and downward-discharge, wherein a volute of a turbine fan is arranged at the rear part of a lower module of the integrated cooker. In order to improve the oil smoke exhaust performance of the integrated cooker, the current main solution is to increase the diameter of the impeller of the turbofan to install more blades, or to increase the rotation speed of the motor of the turbofan to improve the air exhaust performance of the turbofan. Meanwhile, greater noise is generated in the exhaust process of the turbine fan, and the experience of using the integrated cooker by a user is influenced.

Accordingly, there is a need in the art for a new solution to the above problems.

SUMMERY OF THE UTILITY MODEL

The problem that the noise is too big is produced in order to solve the above-mentioned problem among the prior art, promptly for solving the centrifugal impeller rotation of current turbofan.

In a first aspect, the present invention provides a centrifugal impeller for a turbofan, the turbofan comprising a volute and a motor, the centrifugal impeller comprising: the basal disc is positioned in the volute and is fixedly connected with an output shaft of the motor; one end of each blade is fixedly connected with the base plate, the number of the blades is multiple, and the blades are uniformly distributed in the circumferential direction of the base plate; the annular fixing piece is fixedly connected with the other ends of the blades; wherein the blades are arranged as unequal thickness blades so as to reduce the drag coefficient of the blades, thereby reducing noise generated by the turbofan.

In the above-mentioned preferred technical solution of the centrifugal impeller for the turbo fan, the unequal-thickness blades are NACA0008 type unequal-thickness blades.

In the above preferred technical solution of the centrifugal impeller for the turbo fan, the end portions of the unequal-thickness blades are provided with noise reduction structures.

In the above-mentioned preferred technical solution of the centrifugal impeller for the turbo fan, the noise reduction structure is a tooth-shaped structure formed on the blades of different thicknesses.

In the above-mentioned preferred technical solution for the centrifugal impeller of the turbo fan, the tooth-shaped structure is provided as a triangular tooth.

In the above-mentioned preferred technical solution of the centrifugal impeller for the turbo fan, the noise reduction structure is a plurality of through hole structures formed on the unequal-thickness blades, and the plurality of through hole structures are uniformly distributed along the height direction of the unequal-thickness blades.

In the above-mentioned preferred technical solution of the centrifugal impeller for the turbo fan, the noise reduction structure is disposed at the non-windward end of the unequal-thickness blade.

In the above preferred technical solution for the centrifugal impeller of the turbo fan, an included angle between an extension line of a connecting line of the inner end and the outer end of the blade and a connecting line of the inner end of the blade and the center point of the base plate is 50 to 55 degrees.

In a second aspect, the present invention provides a turbofan, said turbofan comprising a centrifugal impeller for a turbofan as described in the above technical solution.

In a third aspect, the present invention provides an integrated cooking stove, comprising a turbofan according to the above technical solution.

As can be understood by those skilled in the art, the turbofan of the present invention includes a volute, a motor, and a centrifugal impeller, wherein the centrifugal impeller includes a base plate, a blade, and an annular fixing member; the basal disc is positioned in the volute and fixedly connected with an output shaft of the motor; blade one end and basal disc fixed connection, the quantity of blade sets up to a plurality ofly, and a plurality of blades are evenly distributed in the circumference of basal disc, the other end fixed connection of annular mounting and a plurality of blades, wherein, the blade sets up to the blade of not uniform thickness to reduce the resistance coefficient of blade, thereby reduce the noise that turbofan produced. Through such setting, be about to the blade and set up to the blade of not uniform thickness, when the blade was rotatory, the air when the streamline structure of blade of not uniform thickness, reduced the resistance coefficient of air and blade, promptly, reduce the resistance between blade and the air, the noise of the production friction or stirring between greatly reduced blade and the air has restrained the noise between blade and the air.

Further, the unequal-thickness blades are set to be NACA0008 type unequal-thickness blades. Through the arrangement, compared with other wing profiles, the NACA0008 has the advantages that the unequal-thickness blades of the wing profile structure have higher lift coefficient and lower resistance coefficient, the resistance between the blades and air is reduced, and the air exhaust capacity of the blades is improved.

Further, noise reduction structures are arranged at the end portions of the blades with different thicknesses. Through such setting, the structure of making an uproar falls can be broken up the air current that passes through the structure of making an uproar and become turbulent flow or torrent, reduces the noise that the blade slammed air output.

Further, the noise reduction structure is a tooth-shaped structure formed on the blade with different thicknesses. Through the arrangement, the whole air flow is scattered and divided by the blades through the tooth-shaped structure, and the probability of noise generated by air slapping the blades is reduced.

Further, the tooth-shaped structure is provided as triangular teeth. Through such setting, design simple structure, it is with low costs, be convenient for reduction in production cost.

Further, the noise reduction structure is a plurality of through hole structures formed on the blades with different thicknesses, and the through hole structures are uniformly distributed in the height direction of the blades with different thicknesses. Through such setting, design simple structure, it is with low costs.

Further, the noise reduction structure is arranged at the non-windward end of the blades with different thicknesses. Through the arrangement, the whole air flow is scattered and separated at the tail part of the blade, and the noise of the air flowing through the tail part of the blade is reduced.

Furthermore, the included angle between the extension line of the connecting line of the inner end and the outer end of the blade and the connecting line of the inner end of the blade and the central point of the base plate is 50-55 degrees. By such an arrangement, rotating the vanes provides an optimum amount of exhaust air.

Furthermore, the utility model discloses the turbofan and the integrated kitchen that further provide on above-mentioned technical scheme's basis owing to adopted foretell centrifugal impeller, therefore possess the technological effect that above-mentioned centrifugal impeller possessed, compare in current turbofan and integrated kitchen, the utility model discloses a noise of turbofan and integrated kitchen is littleer, and user experience is better.

Drawings

Preferred embodiments of the present invention are described below with reference to the accompanying drawings, in which:

fig. 1 is a schematic structural view of a turbofan according to the present invention;

fig. 2 is a schematic cross-sectional structural view of a centrifugal impeller of a turbo fan according to the present invention;

fig. 3 is a schematic structural view of the blades of the turbo fan of the present invention;

Fig. 4 is a schematic sectional structure view of the blade with different thicknesses of the present invention.

Fig. 5 is a data coordinate diagram of a cross-sectional curve of a NACA0008 airfoil of the present invention.

List of reference numerals:

1. a volute; 11. a centrifugal impeller; 111. a base plate; 112. blades of unequal thickness; 113. a ring-shaped fixing member; 1121. triangular teeth; 1122. and (5) clamping the column.

Detailed Description

Preferred embodiments of the present invention will be described below with reference to the accompanying drawings. It should be understood by those skilled in the art that these embodiments are only for explaining the technical principle of the present invention, and are not intended to limit the scope of the present invention.

It should be noted that in the description of the present invention, the terms "upper", "windward", "rear", "inner", "outer", etc. indicating directions or positional relationships are based on the directions or positional relationships shown in the drawings, which are only for convenience of description, and do not indicate or imply that a device or element must have a specific orientation, be constructed and operated in a specific orientation, and thus, should not be construed as limiting the present invention.

Furthermore, it should be noted that, in the description of the present invention, unless otherwise explicitly specified or limited, the terms "mounted," "connected," and "connected" are to be construed broadly, and may be, for example, fixedly connected, detachably connected, or integrally connected; they may be connected directly or indirectly through intervening media, or they may be interconnected between two elements. The specific meaning of the above terms in the present invention can be understood by those skilled in the art according to specific situations.

The problem of excessive noise caused by the rotation of the centrifugal impeller of the prior art turbo fans pointed out by the background art.

The inventor finds that the noise source brought by increasing the diameter of the impeller and increasing the rotating speed of the motor of the existing turbine fan is mainly aerodynamic noise generated when the fan rotates, and the noise intensity of the blades and air is reduced by reducing the friction between the blades and the air. The invention adopts NACA four-digit non-uniform-thickness airfoil blades as blades of a centrifugal impeller, wherein the NACA four-digit airfoil family is a low-speed airfoil series which is firstly established by the National aviation council (National Advisory Committee for Aeronautics, NACA for short), and compared with other airfoils, the airfoil structure has the characteristic of providing higher lift coefficient and lower drag coefficient. The code of each of the airfoils consists of four letters of "NACA" and a series of numbers, i.e., the NACA XYZZ form to represent the airfoil code, the "XYZZ" representing a four digit number meaning that the X position number represents the relative camber, the Y position number represents the maximum camber position, and the ZZ position number represents the relative thickness. For example, the present invention is represented by an airfoil of the NACA0008 type in the sense of having a relative camber of 0, a maximum camber position of 0 and a relative thickness of 8%. As the NACA series airfoil structure forms a data standard, corresponding airfoil section curve data can be obtained from a data standard library only according to digital airfoil codes according to actual needs.

The utility model discloses an adopt on the NACA0008 airfoil blade basis and optimize it, make centrifugal impeller when rotatory, reduce the resistance between air and the blade, the air is through streamline molding's airfoil surface, and air and blade resistance are little, have reduced the noise and have improved the volume of airing exhaust.

Specifically, as shown in fig. 1 and fig. 2, the turbofan of the present invention includes a volute 1, a motor (not shown in the figure), and a centrifugal impeller 11 disposed in the volute 1, wherein the centrifugal impeller 11 includes a base disc 111, blades, and an annular fixing member 113; wherein, the base disc 111 is positioned in the volute 1, and the base disc 111 is fixedly connected with an output shaft of the motor; one end and the base disc 111 fixed connection of blade, the quantity of blade sets up to a plurality ofly, and a plurality of blades evenly distributed is gone up in the circumference of base disc 111, and annular mounting 113 and the other end fixed connection of a plurality of blades, blade set up to unequal thickness blade 112 to reduce the drag coefficient of blade, thereby reduce the noise that turbofan produced.

Exemplarily, as shown in fig. 1, fig. 2 and fig. 3, the turbo fan of the present invention includes a volute 1 and a motor disposed in the volute 1, and the centrifugal impeller 11 includes 1 base disc 111, 60 blades and 1 annular fixing member 113. The center of the base disc 111 is provided with a fixing hole, after an output shaft of the motor passes through the fixing hole on the base disc 111, the base disc 111 is fixedly connected with the output shaft, 60 blades are uniformly distributed on the circumference of the base disc 111, wherein, as shown in fig. 3, two ends of each blade are provided with a clamping column 1122, clamping holes (not shown in the figure) are arranged on the circumference of the base disc 111 and the annular fixing part 113, the clamping column 1122 at one end of each blade is clamped with the clamping hole on the base disc 111, the clamping column 1122 at the other end of each blade is clamped with the clamping hole on the annular fixing part 113, and after the base disc 111 and the annular fixing part 113 are fastened, 60 blades are installed on the base disc 111 to form a centrifugal impeller 11.

It should be noted that the number of the blades is not limited to the above number, for example, the diameter of the centrifugal impeller 11 is increased, the number of the blades can be set to 70, or, for example, the diameter of the centrifugal impeller 11 is decreased, the number of the blades can be set to 50, and the adjustment and the change of the number of the blades do not deviate from the principle and the scope of the present invention, and all should be limited within the protection scope of the present invention.

Preferably, as shown in FIGS. 4 and 5, the non-uniform thickness blades 112 are configured as NACA0008 type non-uniform thickness blades 112.

Illustratively, as shown in fig. 5, since NACA0008 is a symmetric airfoil, the data for one curved edge of the NACA0008 airfoil is listed in table 1. Wherein c in table 1 represents a chord length (chord length of 1.00); x is the chord length coordinate (in x/c); y is the airfoil-to-chord distance (in y/c) corresponding to the x position. According to the curve data of the NACA0008, a section view of the airfoil, namely a figure 5, can be directly drawn, and according to actual needs, the airfoil structure of the blade with the actual size can be obtained by scaling the data of the curve edge of the NACA0008 airfoil in an equal proportion. The utility model discloses well adoption sets up c to 32 mm.

TABLE 1

Y axis coordinate (Y/c)	X axis coordinate (X/c)
		0.00084	1.0000
0.00537	0.9500
		0.00965	0.9000
0.01749	0.8000
		0.02443	0.7000
0.03043	0.6000
		0.03529	0.5000
0.03869	0.4000
		0.04001	0.3000
0.03961	0.2500
		0.03825	0.2000
0.03564	0.1500
		0.03121	0.1000
0.02800	0.0750
		0.02369	0.0500
0.01743	0.0250
		0.01263	0.0125
0.00000	0.0000

It should be noted that the unequal thickness blades 112 of the present invention are further optimized for the NACA0008 airfoil configuration. As shown in fig. 4, the blades 112 with different thicknesses of the present invention are blades formed by bending the NACA0008 airfoil to have a curvature.

Take centrifugal impeller 11 of the present invention as an example, set the diameter of base plate 111 of centrifugal impeller 11 to 28CM, set the length of unequal-thickness blades 112 to 15CM, and evenly set 60 unequal-thickness blades 112 in the circumferential direction of centrifugal impeller 11. Wherein, the unequal thickness blade 112 prepared according to table 1 is bent, as shown in fig. 4, the bending radius R is 22mm, the peak h after the bending of the linear distance at both ends of the unequal thickness blade 112 is 6.9mm, and the optimized NACA0008 wing-shaped unequal thickness blade 112 of the utility model is obtained.

Under the same condition, install the utility model discloses an optimize the centrifugal impeller 11 of the unequal thickness blade 112 of back NACA0008 airfoil and the impeller of ordinary equal thickness blade and exhaust the volume performance to such as table 2:

TABLE 2

By comparison, when the optimized NACA0008 airfoil type unequal thickness blades 112 are installed, the air discharge amount of the turbo fan in unit time is obviously higher than that of the ordinary equal thickness blades under the same revolution. Therefore, the unequal thickness blades 112 of the optimized NACA0008 airfoil can obviously improve the exhaust air volume of the impeller.

As shown in fig. 2, an angle a between an extension line of a line connecting an inner end and an outer end of the unequal-thickness blade 112 of the centrifugal impeller 11 and a line connecting the inner end of the unequal-thickness blade 112 and a center point of the base plate 111 is defined as an installation angle of the unequal-thickness blade 112, which is preferably set to 50 to 55 degrees.

It should be noted that, the installation angle of the unequal thickness blade 112 also influences the air discharge volume of the centrifugal fan, according to actual conditions, according to the diameter of the centrifugal impeller 11 and the installation quantity of the unequal thickness blade 112, the installation angle of the unequal thickness blade 112 can be flexibly adjusted to adapt to different air discharge volume modes, the installation angle of the blade can be set to 51 degrees, or the installation angle of the blade can also be set to 53 degrees, and further, or the installation angle of the blade can also be set to 54 degrees, and so on, and the adjustment and the change of the installation angle of the blade are not deviated the principle and the range of the present invention should be limited within the protection range of the present invention. Of course, it is preferable to set the installation angle of the blade to 53 degrees.

Preferably, as shown in FIG. 3, the ends of the non-uniform thickness blades 112 are provided with noise reducing structures.

Illustratively, as shown in fig. 3, one end of the unequal thickness blades 112 of the centrifugal impeller 11 of the present invention is provided with a noise reduction structure.

When the centrifugal impeller 11 rotates at a high speed, the end portions of the blades 112 with different thicknesses easily slap noise generated by air, and the noise reduction structure provided at the end portions of the blades 112 with different thicknesses can disperse and disturb the airflow, and at this time, the airflow direction generated by the blades 112 with different thicknesses and the air is changed and disturbed, thereby reducing or suppressing the intensity of the noise.

It should be noted that, in order to reduce the noise better, the noise reduction structure can be set up to be made by sound absorbing material or set up sound absorbing material at the structure surface of making an uproar that falls, can further improve the effect of making an uproar structure noise suppression like this on the whole, and this kind of adjustment and change to the material of the structure of making an uproar that falls is not skew the utility model discloses a principle and scope should all be injectd within the protection scope.

Preferably, the noise reducing structure is disposed at the non-windward end of the unequal thickness blades 112.

Illustratively, as shown in FIG. 2, the noise reducing structure of the non-uniform thickness blades 112 of the present invention is disposed at the non-windward end of the non-uniform thickness blades 112, i.e., outside of the non-uniform thickness blades 112. When the centrifugal impeller 11 rotates, an air pressure difference is generated between the center of the centrifugal impeller 11 and the outside, and at this time, air is sucked to the center of the centrifugal impeller 11 and then discharged through the non-windward ends (i.e., the tails) of the rotating unequal-thickness blades 112. Because the tangential velocity of the non-windward end of the unequal-thickness blade 112 is greater than the tangential velocity of the windward end of the inner unequal-thickness blade 112 during rotation, and the noise intensity generated by the non-windward end of the unequal-thickness blade 112 is greater than the noise intensity of the windward end, the noise reduction structure disposed at the non-windward end can better suppress aerodynamic noise when air is discharged out of the unequal-thickness blade 112.

It should be noted that, according to practical application scenario, unequal thickness blade 112 can set up the structure of making an uproar at the windward end, perhaps, unequal thickness blade 112 both ends all set up the structure of making an uproar, again perhaps, also can set up the structure of making an uproar on unequal thickness blade 112 windward side, and this kind is not skew to the adjustment and the change that set up the position of the structure of making an uproar that falls the utility model discloses a principle and scope all should be injectd within the protection scope. Of course, it is preferred to locate the noise reducing structure at the non-windward end of the non-uniform thickness blades 112.

In a preferred embodiment, as shown in FIG. 3, the noise reducing structure is a tooth-like structure formed on the unequal thickness blades 112.

Illustratively, as shown in fig. 3, along the length direction of the unequal-thickness blade 112, the noise reduction structure is a continuous tooth-shaped structure, wherein the tooth-shaped structure is provided as triangular teeth 1121, the number of the triangular teeth 1121 on the unequal-thickness blade 112 is 12, and the triangular teeth 1121 are uniformly distributed along the length direction of the unequal-thickness blade 112.

It should be noted that, the number of the above triangular teeth 1121 is not limited to the above situation, and according to the practical application length of the unequal-thickness blade 112, the number of the triangular teeth 1121 may be set to 8 or 16, and meanwhile, the angle of the triangle may also be adjusted according to the practical application condition, and the adjustment and the change of the tooth-shaped structure are not deviated.

In another preferred embodiment, the noise reducing structure is a plurality of through hole structures (not shown) formed on the unequal thickness blades 112, and the plurality of through hole structures are uniformly distributed along the height direction of the unequal thickness blades 112.

It should be noted that, a plurality of through-hole structures can set up to triangle-shaped, trapezoidal, circular or oval, as long as can leave the air on the blade 112 that does not vary in thickness when the blade 112 that does not vary in thickness, with the air current dispersion in disorder in order to reduce the noise the production intensity can, this kind is not skew with the change to through-hole structure the utility model discloses a principle and scope all should be injectd within the protection scope.

So far, the technical solution of the present invention has been described with reference to the preferred embodiments shown in the drawings, but it is easily understood by those skilled in the art that the scope of the present invention is obviously not limited to these specific embodiments. Without departing from the principle of the present invention, a person skilled in the art can make equivalent changes or substitutions to the related technical features, and the technical solutions after these changes or substitutions will fall within the protection scope of the present invention.

Claims

1. A centrifugal impeller for a turbofan comprising a volute and a motor, the centrifugal impeller comprising:

The basal disc is positioned in the volute and fixedly connected with an output shaft of the motor;

one end of each blade is fixedly connected with the base plate, the number of the blades is multiple, and the blades are uniformly distributed in the circumferential direction of the base plate; and

the annular fixed part is fixedly connected with the other ends of the blades;

wherein the blades are arranged as unequal thickness blades so as to reduce the drag coefficient of the blades, thereby reducing noise generated by the turbofan.

2. The centrifugal impeller for a turbo fan according to claim 1, wherein the unequal thickness blades are provided as NACA0008 type unequal thickness blades.

3. The centrifugal impeller for a turbo fan according to claim 1, wherein ends of the unequal thickness blades are provided with noise reduction structures.

4. The centrifugal impeller for a turbo fan according to claim 3, wherein the noise reduction structure is a tooth structure formed on the blades of unequal thickness.

5. The centrifugal impeller for a turbo fan according to claim 4, wherein said tooth-shaped structures are provided as triangular teeth.

6. The centrifugal impeller for a turbo fan according to claim 3, wherein the noise reduction structure is a plurality of through hole structures formed on the unequal thickness blades, the plurality of through hole structures being uniformly distributed in a height direction of the unequal thickness blades.

7. The centrifugal impeller for a turbo fan according to claim 3, wherein the noise reducing structure is provided at a non-windward end of the unequal thickness blades.

8. The centrifugal impeller for a turbo fan according to any one of claims 1 to 7, wherein an angle between an extension line of a line connecting the inner end and the outer end of the blade and a line connecting the inner end of the blade and the center point of the base plate is 50 to 55 degrees.

9. A turbo fan, characterized in that it comprises a centrifugal impeller for a turbo fan according to any one of claims 1 to 8.

10. An integrated cooker, characterized in that it comprises a turbofan according to claim 9.