CN106939902B - Energy-saving straight-wall front and rear disk variable-curvature curve element ternary impeller and centrifugal fan adopting same - Google Patents
Energy-saving straight-wall front and rear disk variable-curvature curve element ternary impeller and centrifugal fan adopting same Download PDFInfo
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Abstract
The utility model provides an energy-saving straight wall preceding, back plate variable curvature curve element ternary impeller, includes front disc, blade, back plate and reel, and front disc and back plate are straight wall structure, and the blade is the variable curvature curve element ternary distortion blade, promptly: the front disc and the rear disc of the fan impeller still adopt a straight wall structure of a traditional fan, the original binary blade is replaced by a ternary blade with variable curvature curve elements, and the curvature of the blade in the blade height direction of an inlet of the fan impeller is adjusted, so that the blade force exerted on airflow by the blade can properly balance the centrifugal inertia force when the airflow is changed from the axial direction to the radial direction when the impeller rotates, and the violent change of the speed of the airflow at the inlet is weakened; the invention also claims a centrifugal fan using the ternary impeller; the invention eliminates the adverse effect of small-radius turning inertia force through the variable-curvature curve element ternary impeller blade force, adopts the traditional structure of the straight-wall front disk and the straight-wall rear disk, designs the variable-curvature curve element ternary impeller of the straight-wall front disk and the straight-wall rear disk, and realizes the energy-saving effect of the fan ternary impeller.
Description
Technical Field
The invention belongs to the technical field of radial and mixed flow type turbo machinery, relates to equipment such as a centrifugal fan, a blower, a compressor and the like, and particularly relates to an energy-saving straight-wall three-element impeller with variable curvature curve elements of a front disk and a rear disk and a centrifugal fan (fan, blower and compressor) adopting the impeller.
Background
Since the general theory of subsonic and supersonic three-element flow of axial flow, radial flow and mixed flow type turbomachines was published in the United states in the last fifties of the century by professor Wu Zhong Hua in China, the three-element flow turbomachines are widely applied in the field of high-end energy equipment along with the rapid development of computer technology. At present, the straight line element ternary impeller of the American NREC is widely adopted in the field of radial and mixed turbomachinery at home and abroad, and mainly comprises a front disc 1, blades 2, a rear disc 3, a volute 4, an air suction pipe 5 and the like, wherein the blades 2 are straight line element ternary blades. The straight line element ternary impeller is formed by the following rule, in particular to the constitution of a ternary twisted blade central plane of the impeller: the manufacturing drawing only gives the x, y and z coordinates of two space curves at the top end and the root part of the blade, a group of space straight lines are obtained from equal parameter corresponding points of the two space curves, the space curved surface formed by the group of space straight lines is the blade central plane of the straight line element ternary impeller, and the American NREC is called as an 'arbitrary space straight line element ternary impeller'. It is obvious that the direction of the group of spatial straight lines is basically vertical to the curves of the front disk and the rear disk (because the front disk and the rear disk cannot be concentric arcs, a common normal line does not exist, and the front disk and the rear disk cannot be strictly vertical), and because of this, when the impeller rotates, the blade force generated by the blades 2 on the air flow in the inlet area of the impeller is also basically vertical to the normal inertial force generated when the air flow is changed from the axial direction to the radial direction (figure 2), and the inertial force is just the reason for generating the violent speed change in the height direction of the blades. In order to overcome the adverse effect of severe speed change caused by normal inertia force when the airflow at the inlet of the impeller is converted from axial direction to radial direction, a meridian (meridian) flow channel with a large turning radius is required to be adopted, a front disk (Shroud)1 and a rear disk (Hub)3 of the impeller are required to be bent (shown in figure 1), and the energy consumption of the straight line element ternary impeller is reduced by 5-10 percent compared with that of a conventional binary impeller.
The straight line element ternary impeller needs to adopt a meridian flow channel with a large turning radius, and the bent front disc and the bent rear disc greatly improve the manufacturing cost. For the fields of large, medium and low speed fans, such as sintering, dust removal, boiler blowing, induced draft fans and the like, in consideration of cost, the shell, the front disk and the rear disk of the impeller are all in metal plate structures, and the traditional structure (figure 3) of the front disk and the rear disk with straight walls is still used, wherein the traditional structure comprises a front disk 1, blades 2, a rear disk 3, a shaft disk 4 and the like, and the blades 2 are binary blades. The straight-wall front and rear disk structure greatly limits the application of the straight-element ternary impeller in the field of low-end fans, and only can adopt the traditional binary blades (figure 4) with the flow direction being bent and the height direction not being twisted. Because the quantity of the low-end fans is large and wide, a great amount of energy waste of China is caused.
Disclosure of Invention
In order to overcome the defects of the prior art, the invention aims to provide an energy-saving straight-wall three-element impeller with variable curvature curve elements of a front disk and a rear disk and a centrifugal fan adopting the impeller, so that the drastic change of the speed of airflow at an inlet is greatly weakened, and the energy-saving and consumption-reducing effects of the three-element impeller are realized; meanwhile, the limit condition that the American NREC straight line element ternary impeller can be designed only by having a large enough turning radius of a meridian channel is overcome.
In order to achieve the purpose, the invention adopts the technical scheme that:
the energy-saving type straight-wall three-element impeller with the variable-curvature curve elements on the front disk and the rear disk comprises the front disk, blades, the rear disk and a shaft disk, wherein the front disk and the rear disk are of a straight-wall structure, and the blades are three-element twisted blades with the variable-curvature curve elements. Namely: the front and back disks of the fan impeller are still in the traditional fan straight wall structure, and the original binary blades are replaced by the ternary blades with variable curvature curve elements.
The three-element twisted blade with the variable curvature curve elements is characterized in that the blade has twist in the height direction and the flow direction, and the curvature of the blade in the blade height direction of the impeller inlet is different from the curvature of the blade at the rest positions.
The curvature of the vanes in the height direction of the inlet of the impeller is adjusted, so that the vanes exert a vane force F on the airflow when the impeller rotatesbCan properly balance centrifugal inertia force F when the airflow is converted from axial direction to radial directioniThereby attenuating the drastic change in velocity of the air stream at the inlet.
The design method of the blade comprises the following steps:
desired velocity profile along the meridian flow line m for a given blade tip, root
I.e. relative speed of air flow in the impeller
And the airflow flowing angle, namely the blade mounting angle beta, satisfy the following relational expression:
wherein, WθRepresenting tangential component velocity, W representing airflow relative velocity, the value of β is:
and because:
wherein r is the radius from the arc blade to the rotating shaft, the angular coordinate value theta of the blade is obtained by the following integral expression:
the projection of the blade top and blade root space streamline s on the meridian plane, i.e. the meridian streamline m, is the front and rear disk type lines m ═ f (r, z), thereby obtaining the blade top space streamline thetasAnd the blade root thetahThe spatial streamline formula of (a) is as follows:
θs＝f(rs,zs)
θh＝f(rh,zh)
and taking the isoparametric points of the blade top and the blade root space streamline as two end points of the variable curvature curve elements of the space twisted blade, and giving the expected distribution value of the curvature of each curve element along the quasi-orthogonal line q, thereby obtaining the whole space curved surface.
And according to the obtained curved surface of the blade, a flow analysis method on the opposite flow surface of a cross-disk cover of a centrifugal or mixed-flow compressor is adopted to carry out ternary flow design on the straight-wall front and rear disk variable-curvature curve element centrifugal fan.
The invention also claims a centrifugal fan adopting the energy-saving straight-wall front and rear disk variable-curvature curve element ternary impeller.
Compared with the prior art, the invention has the following beneficial effects:
1) the drastic change of the speed of the airflow at the inlet is greatly weakened, and the effects of energy conservation and consumption reduction of the ternary impeller are realized. Three-element blade with variable curvature and curve elements, the blade force F applied to the airflow by the blade when the impeller rotatesbCan properly balance the centrifugal inertia force F when the airflow is converted from the axial direction to the radial directioni(as shown in fig. 7 and 8), the drastic speed change of the airflow at the inlet is greatly weakened, and the energy-saving and consumption-reducing effects of the ternary impeller are realized.
2) The limit condition that the three-element impeller of the NREC in the United states can be designed only by having a sufficient meridian passage turning radius is overcome. It is conceivable that the effect of the invention is difficult to achieve without abandoning the design condition that the profile of the ternary impeller blade is required to be a ruled surface.
3) The limitation that the straight line element ternary impeller can only be used when turning radiuses of a front disk (Shroud) and a rear disk (Hub) of the impeller are increased to a sufficient degree is avoided, and the efficient and energy-saving ternary impeller can be used only under the structural condition of the traditional binary centrifugal fan with the front disk and the rear disk of a straight wall (non-curved) by changing the curvature curve element ternary twisted blade.
By adopting the straight-wall front and rear disc variable-curvature curve element ternary impeller centrifugal fan, the energy-saving and consumption-reducing effects of the centrifugal ternary impeller are realized, the energy consumption is expected to be reduced by 5-10% compared with the traditional centrifugal fan and the air blower, and the cost is reduced by more than 50% compared with the curved-wall straight-line element ternary impeller.
Drawings
Fig. 1 is a schematic diagram of a linear element ternary impeller structure in the prior art (a circumferential view, namely a meridian view).
Fig. 2 is a schematic structural view (axial view, i.e., a view of a surface of revolution) of a linear element ternary impeller in the prior art.
Fig. 3 is a schematic structural view (circumferential view, i.e., meridional view) of a straight-wall front and rear disk binary impeller in the prior art.
Fig. 4 is a schematic structural view (axial view, i.e., a view of a surface of revolution) of a straight-wall front and rear disk binary impeller in the prior art.
Fig. 5 is a schematic structural view (circumferential view, i.e., meridian view) of a three-element impeller with straight-wall front and rear disks and variable curvature curve elements according to the present invention.
Fig. 6 is a schematic structural view (axial view, i.e. revolution surface view) of a three-element impeller with variable curvature curve elements of a straight-wall front disk and a straight-wall rear disk of the invention.
FIG. 7 is a schematic view of the inlet area of the ternary impeller with straight wall front and back disk variable curvature curve elements of the present invention showing the air flow stress (meridian plane).
FIG. 8 is the schematic view of the inlet area of the three-element impeller with variable curvature curve elements of the front and rear straight walls of the invention showing the airflow stress (revolution surface). Fb-blade force; fi — Normal inertial force; w-relative velocity of air flow; omega-impeller rotation angular velocity.
FIG. 9 is a schematic design of the aerodynamic portion of the blade.
FIG. 10 is a schematic view of a single suction plate housing and rotor structure.
Fig. 11 is a schematic view of the structure of the double-suction plate housing and the rotor.
Detailed Description
The embodiments of the present invention will be described in detail below with reference to the drawings and examples.
The invention provides an energy-saving straight-wall front and rear disk variable-curvature curve element ternary impeller centrifugal fan, which is characterized in that under the structural limit condition of the traditional low-end fan of the straight-wall front and rear disks, by utilizing a 'direct proposition pneumatic design method' independently developed by the inventor for a long time, the limit condition of a straight-line element blade of an American NREC ternary impeller is abandoned, and a variable-curvature curve element ternary impeller (as shown in figures 5 and 6) is designed, wherein the variable-curvature curve element ternary impeller comprises a front disk 1, blades 2, a rear disk 3, a shaft disk 4 and the like, and the blades 2 are variable-curvature curve element ternary blades.
The three-element twisted blade with variable curvature curve elements is characterized in that the blade has twist in the height and flow direction, and the curvature of the blade in the height direction of the inlet blade of the impeller is different from the curvature of the blade at the rest position. The curvature of the vanes in the height direction of the inlet of the impeller is adjusted, so that the vanes exert a vane force F on the airflow when the impeller rotatesbCan properly balance centrifugal inertia force F when the airflow is converted from axial direction to radial directioniThereby attenuating the drastic change in velocity of the air stream at the inlet. The specific design method of the blade is as follows:
1. given the desired velocity profile along the meridian streamline m for the blade tip, root
As shown in FIG. 9, the relative velocity of the air flow in the impeller
And the airflow flowing angle, namely the blade mounting angle beta, satisfy the following relational expression:
in FIG. 9, WθDenotes the tangential component velocity, W denotes the relative velocity of the air flow, WrDenotes the radial component velocity, WmThe projection of the relative speed W on the meridian plane, and omega is the rotation angular speed of the impeller;
therefore, the distribution of the blade mounting angle beta along the space streamline s can be obtained, namely the value of the beta is as follows:
and because:
wherein r is the radius from the arc blade to the rotating shaft;
the blade angular coordinate value θ can thus be obtained by the following integral:
the space streamline s of the blade top and the blade root is projected on the meridian plane, namely the meridian streamline m is the front and back disk type line m ═ f (r, z), and finally the following results are obtained: the space streamline of the blade top and the blade root are respectively as follows:
θs＝f(rs,zs)
θh＝f(rh,zh)
2. using the isoparametric points of the blade top and blade root space streamline as two end points of the variable curvature curve element of the space twisted blade, and giving the expected distribution value of the curvature of each curve element along the quasi-orthogonal line q
Thus, the entire spatial curved surface θ is known as f (m, q).
3. After the coordinate values of the curved surface of the blade are obtained, Katsanis is adopted, and T is flowed by Wuzhonghua ternary flowMean span disc cover S developed by kinetic theory2mFlow surface analysis (reference: [ Katsanis, T "application of arbitrary quasi-orthogonal line method in calculating turbomachinery meridian flow analysis" TN D2546, NASA, Cleveland, Ohio,1964]) The analysis problem of the blade profile and the pneumatic design of the ternary impeller can be solved. The invention adopts the flow analysis (positive proposition) of a centrifugal or mixed flow compressor across the opposite flow surfaces of a disk cover, which is further developed by Katsanis, T (reference document: turbine compressor specialty, computational mathematics specialty, "flow analysis (positive proposition) of a centrifugal or mixed flow compressor across the opposite flow surfaces of a disk cover," West An university of traffic newspaper 3, 1976) to carry out ternary flow analysis and design of a straight-wall front and rear disk variable curvature element centrifugal fan.
In the invention, the smaller turning radius can be realized by the static air guide pipe in front of the impeller.
Referring to fig. 10 and 11, the implementation of the present invention includes:
a high-efficiency energy-saving straight-wall front and rear disc variable-curvature curve element ternary impeller centrifugal fan is characterized in that in the traditional single-suction (figure 10) and double-suction (figure 11) sheet metal casings of the original low-intermediate-speed and medium-low-pressure centrifugal fan, the traditional structure that a main shaft is sleeved with a shaft disc and front and rear straight disc binary (circular arc) blades to weld an impeller rotor is adopted, and the binary circular arc blades are only required to be changed into the variable-curvature curve element ternary blades, so that the problems that a large amount of energy is wasted by the binary impeller, and the energy conservation and the environmental protection are not facilitated under the traditional low-end fan structure and material using conditions are solved. At this time, except that the three-element blade with variable curvature curve elements needs to adopt a design and a manufacturing process different from those of the traditional low-end fan, the structures, materials and manufacturing processes of other parts of the air inlet chamber, the casing and the rotor are kept unchanged. The profile design of the ternary blade with variable curvature curve elements is implemented according to the parts 1 and 2 in the pneumatic design method in the embodiment, and the analysis of the ternary impeller internal flow field is carried out according to the method in the part 3. After the blade unfolding and hot press forming die is programmed by a computer and is finished by a numerical control cutting machine and a three-coordinate numerical control milling, the hot press forming twisted blade is welded with the front and the rear disks of the straight wall to form the three-element blade impeller with the variable curvature curve elements of the front and the rear disks of the straight wall. The rest procedures of the fan are the same as those of the traditional centrifugal binary fan.
The above description is only an embodiment of the present invention, and not intended to limit the scope of the present invention, and all modifications of equivalent structures and equivalent processes, which are made by using the contents of the present specification and the accompanying drawings, or directly or indirectly applied to other related technical fields, are included in the scope of the present invention.
Claims (5)
1. The utility model provides an energy-saving straight wall preceding, back plate variable curvature curve element ternary impeller, includes front disc, blade, back plate and reel, front disc and back plate are straight wall structure, its characterized in that, the blade is variable curvature curve element ternary distortion blade, variable curvature curve element ternary distortion blade is that the blade all has the distortion in height and flow direction, and the blade is different with the curvature of other positions in the high direction of impeller import blade.
2. The energy-saving type straight-wall ternary impeller with variable curvature curve elements of the front disk and the rear disk as claimed in claim 1, wherein the curvature of the blades in the height direction of the inlet blades of the impeller is adjusted so that the blades exert a blade force F on the airflow when the impeller rotatesbCan properly balance centrifugal inertia force F when the airflow is converted from axial direction to radial directioniThereby attenuating the drastic change in velocity of the air stream at the inlet.
3. The energy-saving straight-wall three-element impeller with variable curvature curve elements of the front disk and the rear disk as claimed in claim 1, wherein the design method of the blades is as follows:
given the desired velocity profile along the meridian streamline m for the blade tip, root
I.e. relative speed of air flow in the impeller
And the airflow flowing angle, namely the blade mounting angle beta, satisfy the following relational expression:
wherein, WθRepresenting the tangential component velocity, W representing the relative velocity of the air flow, the value of β is:
and because:
wherein r is the radius from the arc blade to the rotating shaft, the angular coordinate value theta of the blade is obtained by the following integral expression:
the projection of the blade top and blade root space streamline s on the meridian plane is meridian streamline m, i.e. front and rear disk type lines m ═ f (r, z), so that the blade top space streamline theta can be obtainedsAnd the blade root thetahThe spatial streamline formula of (c) is as follows:
θs＝f(rs,zs)
θh＝f(rh,zh)
and (3) taking the isoparametric points of the blade top and the blade root space streamline as two end points of the variable curvature curve element of the space twisted blade, and giving the expected distribution value of the curvature of each curve element along the quasi-orthogonal line q, thereby obtaining the whole space curved surface.
4. The energy-saving straight-wall three-element impeller with variable-curvature curve elements of the front disk and the rear disk is characterized in that the three-element flow design of the straight-wall three-element impeller with variable-curvature curve elements of the front disk and the rear disk is carried out by adopting a flow analysis method on the opposite flow surfaces of a cross disk cover of a centrifugal or mixed-flow compressor according to the obtained curved surfaces of blades.
5. A centrifugal fan using the energy-saving straight-wall three-element impeller with front and back disks of variable curvature curve elements as claimed in claim 1.
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| CN107559235B (en) * | 2017-09-07 | 2024-03-19 | 佛山市南海九洲普惠风机有限公司 | Fan blade and impeller of ternary torsion fan |
| CN107642491B (en) * | 2017-11-02 | 2024-03-12 | 洛阳北玻三元流风机技术有限公司 | Ternary fluidization centrifugal fan for cooling motor car and high-speed rail traction transformer |
| CN107917102A (en) * | 2017-11-10 | 2018-04-17 | 佛山市南海九洲普惠风机有限公司 | A kind of axial wheel |
| CN107989823B (en) * | 2017-12-26 | 2023-12-01 | 北京伯肯节能科技股份有限公司 | Impeller, centrifugal compressor, and fuel cell system |
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| CN1147662C (en) * | 2002-08-23 | 2004-04-28 | 西安交通大学 | Design method of radial and mixed flow cylinder face secant element three-dimensional impeller |
| CN104613006A (en) * | 2014-12-10 | 2015-05-13 | 张凤荣 | Wing sectional material combination type turbine centrifugal impeller |
| CN204692190U (en) * | 2015-02-04 | 2015-10-07 | 浙江理工大学 | A kind of vane diffuser with deviated splitter vane |
| CN205618428U (en) * | 2016-03-02 | 2016-10-05 | 云南贵鼓风机有限公司 | Impeller of centrifugal fan |
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Effective date of registration: 20220909 Address after: 261500 Haomai Industrial Park, 5655 Kangcheng street, Gaomi Economic Development Zone, Weifang City, Shandong Province Patentee after: HIMILE MECHANICAL MANUFACTURING Co.,Ltd. Address before: 15a-318, Maike center, No. 12, Jinye Road, Zhangba street, high tech Zone, Xi'an, Shaanxi 710076 Patentee before: Xi'an Shangjin Siyuan Turbine Technology Research Institute Co.,Ltd. |
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| PE01 | Entry into force of the registration of the contract for pledge of patent right |
Denomination of invention: Energy saving straight wall front and rear disc variable curvature curve element three-dimensional impeller and centrifugal fan using this impeller Granted publication date: 20220722 Pledgee: China Construction Bank Corporation Gaomi sub branch Pledgor: HIMILE MECHANICAL MANUFACTURING Co.,Ltd. Registration number: Y2024980023256 |