CN110147608B - Fan blade-based heat dissipation synchronous pulley design method - Google Patents
Fan blade-based heat dissipation synchronous pulley design method Download PDFInfo
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Abstract
The invention discloses a fan blade-based heat dissipation synchronous pulley design method, and belongs to the field of mechanical transmission system design. The invention provides a fan blade-based heat dissipation synchronous pulley design method, which combines the design of a synchronous pulley with the design of a fan blade and provides a systematic design method suitable for the heat dissipation synchronous pulley under various working conditions. The synchronous belt wheel based on the fan blades can rotate by rotating to drive the blades to rotate when in work, airflow which directionally passes through the belt wheel is generated, the convective heat transfer of the belt wheel is enhanced, the friction temperature rise of the belt wheel and a belt is reduced, and the service life of the belt wheel and the belt is prolonged.
Description
Technical Field
The invention relates to a fan blade-based heat dissipation synchronous pulley design method, and belongs to the field of mechanical transmission system design.
Background
In mechanical transmission, the synchronous belt pulley has the advantages of accurate transmission ratio, no slip, constant speed ratio, stable transmission, low noise, high transmission efficiency and the like, and is widely applied to transmission devices of mechanical equipment such as automobiles, textiles, printing, chemical engineering, metallurgy, instruments and meters, petroleum, machine tools and the like. Synchronous pulley realizes high-efficient transmission with the tooth meshing of belt, and the friction between band pulley and the belt can produce a large amount of heats, makes the temperature of band pulley and belt all rise. High temperatures will reduce the life of the belt and also cause safety hazards to the operation of the transmission system. Unlike gear drives, pulley drives have difficulty dissipating heat from the drive using a coolant, and therefore, designing a heat dissipation scheme for synchronous pulley drives has always been a challenge. At present, the existing synchronous belt wheel heat dissipation scheme comprises the step of dissipating heat of a belt wheel by adopting an external air source, but the scheme is constrained by an integral mechanical system, the distribution of the belt wheel is complex in a large-scale transmission system, the effect is poor by adopting an external air source heat dissipation mode, and the installation difficulty of a fan is high. The other heat dissipation scheme is to improve the structural design of the synchronous belt wheel and realize heat dissipation by utilizing the structural characteristics of the synchronous belt wheel. The existing heat dissipation structure of the synchronous pulley comprises grooves formed in positions of the gear tooth surface of the pulley, heat dissipation holes formed in the positions of the gear tooth surface of the pulley and the like, the heat dissipation condition of the synchronous pulley can be improved to a certain extent by the structure, but generally, the grooves or holes are formed in a passive heat dissipation mode, the positions and the number of the grooves or the holes are limited due to the constraint of structural strength requirements, and the corresponding heat dissipation effect is limited. Therefore, by further improving the structure of the synchronous pulley, the efficient active heat dissipation type synchronous pulley is designed on the premise of meeting the basic transmission task, and the synchronous pulley has important value for prolonging the service life and improving the reliability of a synchronous pulley transmission system.
Disclosure of Invention
The invention aims to overcome the defects of the prior art and provides a fan blade-based heat dissipation synchronous pulley design method.
The working principle of the invention is as follows: on the basis of not changing the functions and the basic structure of a conventional synchronous belt wheel, a supporting structure in the shape of multiple fan blades is designed and used for connecting a central mounting ring and a gear outer ring, when the synchronous belt wheel works, the multiple fan blades on the belt wheel synchronously rotate, and fan blades are used for applying work to airflow, so that air near the synchronous belt wheel continuously passes through the belt wheel at a certain speed to flow, the convective heat transfer of the belt wheel is enhanced, and finally the heat dissipation and the temperature reduction of the belt wheel and a belt are realized.
In order to solve the technical problem, the invention provides a fan blade-based design method of a heat dissipation synchronous pulley, which specifically comprises the following steps:
(1) according to the transmission requirement, the type of the synchronous pulley is selected according to GB/T11361 and 2008, and the type parameters are selected as follows: the pitch, the tooth socket bottom width, the tooth socket depth, the tooth socket radius, the tooth root fillet radius, the tooth top fillet radius and the double pitch-top distance are used for determining the rated rotating speed of the belt pulley.
(2) According to the transmission and installation requirements, basic parameters of the synchronous belt pulley are designed: the number of teeth, tooth width, pitch diameter, gear half warp, design hold-in range wheel structural parameter: meridian chord length, blade tip outer radius, blade tip inner radius, blade root outer radius, blade root inner radius and blade lobe radius.
(3) The air flow through the synchronous pulley is estimated according to the cooling demand.
(4) And respectively calculating the relative airflow angles of the inlet and the outlet at the three radius positions of the middle and the tip according to the air flow, the rated rotating speed of the belt wheel, the inner radius of the blade tip, the outer radius of the blade root and the meridian chord length, and designing blade arc type mean camber lines at the three radius positions according to the calculated relative airflow angles of the inlet and the outlet.
(5) The blade pitch arc lines at the three radius positions of the blade root, the blade pitch arc line at the middle and the blade tip generate blade profile thickness from an inlet to an outlet according to an equal thickness distribution rule, and the respective gravity centers of the blade profile thickness and the blade pitch arc line are stacked along the radius direction of the belt wheel to form the three-dimensional blade.
(6) And calculating the number of blades, generating complete synchronous pulley blades according to the equal-angle distribution of the number of blades in the 360-degree circumference of the synchronous pulley, and performing integral three-dimensional modeling on the pulley.
(7) And (3) performing structural strength verification and cooling performance verification on the impeller by adopting a test or computer numerical simulation mode, if the structural strength verification is unqualified, reselecting the outer radius of the blade root and the inner radius of the blade tip, returning to the step (2), if the cooling performance verification is unqualified, re-estimating the air flow of the synchronous pulley, returning to the step (3), and if both the two verifications are qualified, finishing the design.
Drawings
FIG. 1 is an isometric view of a fan blade based heat dissipating synchronous pulley;
FIG. 2 is a front view of a fan blade based heat dissipating synchronous pulley;
FIG. 3 is a meridional cross-sectional view of a fan blade based heat dissipating synchronous pulley;
FIG. 4 is a flow chart of a fan blade based heat dissipating synchronous pulley design.
FIG. 5 is a schematic view of a fan blade based cooling synchronous pulley blade speed triangle;
FIG. 6 is a schematic view of a fan blade based design of camber lines in a heat dissipating synchronous pulley blade;
FIG. 7 is a schematic view of a fan blade based heat dissipating synchronous pulley blade profile;
FIG. 8 is a fan blade based heat dissipating synchronous pulley blade root, blade, and blade tip profile stack up schematic;
fig. 9 is a fan blade based heat dissipating synchronous pulley three dimensional blade view.
Detailed Description
The present invention will be described in further detail with reference to the accompanying drawings.
As shown in fig. 1 and 2, a fan blade-based heat dissipation synchronous pulley is divided into four parts, namely a root circle (1), a blade (2), a tip circle (3) and a gear tooth (4), wherein the four parts are connected with each other integrally and can be manufactured by one-time casting or integral milling.
As shown in the meridian section view of the synchronous pulley in the radius direction in fig. 3, (7) is the rotation axis of the pulley, (6) is the rotation direction, when the pulley is in operation, cooling air flows through the impeller in the direction indicated by the arrow (5), (2) is the blade, (4) is the gear tooth, (8) is the inner radius of the blade root, (9) is the outer radius of the blade root, using RhExpressed as (10) the tip inside radius is RtExpressed as (11) the tip outer radius and (12) the lobe inner radius, RmIs shown, and
(13) the meridian chord length of the blade is represented by B.
As shown in fig. 4, the fan blade-based heat dissipation synchronous pulley design process of the present invention includes the following steps:
the method comprises the following steps: according to the transmission requirement, the type of the synchronous pulley is selected according to GB/T11361 and 2008, and the type parameters are selected as follows: the pitch, the tooth space bottom width, the tooth space depth, the tooth space radius, the tooth root fillet radius, the tooth top fillet radius and the double pitch-top distance are used for determining the rated rotating speed of the belt wheel.
Step two: according to the transmission and installation requirements, basic parameters of the synchronous belt pulley are designed: the number of teeth, tooth width, pitch diameter, gear radius, as shown in fig. 3, design synchronous pulley structural parameters: a root inner radius (8), a root outer radius (9), a tip inner radius (10), a tip outer radius (11), a lobe inner radius (12), and a blade meridian chord length (13).
Step three: the air flow through the synchronous pulley is estimated according to the cooling demand.
Step four: calculating inlet and outlet relative airflow angles of three radius positions of an inner radius of the blade tip, an inner radius of the blade tip and an outer radius of the blade root according to the air flow, the rated rotating speed of a belt wheel, the inner radius of the blade tip, the outer radius of the blade root and the meridian chord length of the blade, and designing blade camber lines of the three radius positions according to the inlet and outlet relative airflow angles of the three radius positions obtained by calculation, wherein the detailed calculation method comprises the following steps:
first, according to the formula:
q (lambda) is obtained by calculation in the formula
The unit of the estimated air flow in the third step is kg/m3,PtIs the total pressure of air in the working environment at the inlet of the belt wheel, measured in Pa, and if there is no measured value, the default parameter P is takent＝101325Pa，TtThe total temperature of the air in the working environment of the belt wheel inlet is measured in K, if no measured value is obtained, a default parameter T is takent＝300K，RhAnd RtAnd the blade root outer radius and the blade tip inner radius are respectively designed values in the second step. According to the formula:
λ is calculated, where k is constant and k is 1.4. According to the formula:
and calculating to obtain the inlet Mach number Ma.
Secondly, according to the formula:
calculating to obtain the static temperature T of the inlet airsIn the formula (I), wherein,Ttfor the total temperature of the air in the working environment at the pulley inlet, according to the formula:
calculating a speed of sound a, where R is a constant, and R is 287J/(kg · K), according to the formula: the inlet airflow axial velocity C is calculated as a × Ma, as shown in fig. 5 (14), and the inlet airflow axial velocity (14) is parallel to the inlet airflow velocity (5).
Then, according to the formula:
calculating the radius RiPeripheral velocity U of the air flowiWherein N is the rated rotation speed of the belt wheel and the unit is R/min, Rh，Rm，RtRespectively substituted into formula to replace RiCalculating to obtain the airflow circumferential speed U of three radius positions of blade root, blade leaf and blade tiph，Um，Ut，UiShown in fig. 5 (17), and in fig. 5 (14) and (17) are perpendicular to each other, according to the triangular geometric relationship:
the radius is calculated to be RiInlet gas flow angle beta of1i(19) In degrees and radius RiA circumferential speed difference Δ W ofiIs shown in FIG. 5 (18), by taking Δ Wi＝0.2UiAccording to the formula:
the radius is calculated to be RiOutlet air flow angle beta of2i(20) In degrees according to radius RiInlet gas flow angle beta of1i(19) And a radius RiOutlet air flow angle beta of2i(20) Respectively draw a radius of RiHas an inlet gas flow direction (16) and a radius RiThe calculation is repeated three times to obtain the inlet airflow angle and the outlet airflow angle of the three radius positions of the blade root, the blade leaf and the blade tip respectively, and the three radii of the blade root, the blade leaf and the blade tip are drawnThe inlet airflow direction and the outlet airflow direction of the location.
Finally, the calculated inlet airflow angles (19), inlet airflow directions (16), outlet airflow angles (20) and outlet airflow directions (15) of the three radius positions of the blade root, the blade tip and the blade tip are plotted according to the formula shown in FIG. 6:
respectively calculating the radius (22) of a mean camber line at three radius positions of a blade root, a blade leaf and a blade tip, wherein B is the meridian chord length (13) of the blade, and beta1iIs a radius RiAt an inlet gas flow angle (19), beta2iIs a radius RiThe outlet flow angle (20) of (A) as shown in FIG. 6, finally describes the mean camber line (21) of the blade at three radial positions of the root, the leaf and the tip.
Step five: as shown in fig. 7, the blade profile (25) is drawn by the blade mean camber line of three radius positions of the blade root, the blade tip and the blade tip from the inlet to the outlet according to the equal thickness distribution rule, and the method is as follows: the radius of the thickness circle (23) is designed to be (24), the thickness circle (23) is moved along the camber line (21) of the blade, and a track line formed by the outer contour of the thickness circle after the movement is the blade outer shape (25). Finding the center of gravity of the blade according to the formula:
the center of gravity length (28) is calculated, in which thetaiIs a radius RiThe included angle (26) of the mean camber line is measured in degrees, the included angle (27) of the gravity center is half of the included angle of the mean camber line, and the position of the gravity center (29) of the blade can be determined according to the length (28) of the gravity center and the included angle (27) of the gravity center. As shown in fig. 8, the gravity centers (29) of the blade profiles at three radial positions of the root blade profile (30), the leaf blade profile (31) and the tip blade profile (32) are stacked along the radial direction of the pulleys, and finally the complete blade shown in fig. 9 is obtained.
Step six: calculating the number of blades according to the formula:
calculating to obtain the number of the blades, wherein: rtIs the inner half of the blade tipDiameter, beta1tInlet airflow angle, beta, at the inner radius of the blade tip2tAnd the outlet airflow angle at the inner radius position of the blade tip is the meridian chord length (13) of the B blade. And according to the number of the blades, the blades are distributed in the 360-degree circumference of the synchronous pulley according to equal angles to generate complete synchronous pulley blades, and the whole three-dimensional modeling of the pulley is carried out.
Step seven: and (3) performing structural strength verification and cooling performance verification on the impeller by adopting a test or computer numerical simulation mode, reselecting the inner radius of the blade tip and the outer radius of the blade root if the structural strength verification is unqualified, returning to the step two, if the cooling performance verification is unqualified, re-estimating the air flow of the synchronous pulley, returning to the step three, and if the two-week verification is qualified, finishing the design.
The foregoing is only a preferred embodiment of this invention and it should be noted that modifications can be made by those skilled in the art without departing from the principle of the invention and these modifications should also be considered as the protection scope of the invention.
Claims (1)
1. A fan blade-based heat dissipation synchronous pulley design method comprises the following steps: (1) according to the transmission requirement, the type of the synchronous pulley is selected according to GB/T11361 and 2008, and the type parameters are selected as follows: pitch, tooth's socket bottom width, tooth's socket degree of depth, tooth's socket radius, tooth root fillet radius, tooth top fillet radius, twice pitch-top distance, confirm the rated rotational speed of band pulley, (2) according to transmission and installation demand, design synchronous pulley basic parameter: the number of teeth, tooth width, pitch diameter, gear half warp, design hold-in range wheel structural parameter: meridian chord length, blade tip outer radius, blade tip inner radius, blade root outer radius, blade root inner radius and blade root middle radius, (3) according to cooling requirements, predicting air flow passing through a synchronous pulley, (4) according to the air flow, the rated rotating speed of the pulley, the blade tip inner radius, the blade root outer radius and the meridian chord length, respectively calculating the relative airflow angles of an inlet and an outlet of three radius positions of a fan blade root, a middle and a tip, according to the calculated relative airflow angles of the three inlet and the outlet, designing blade arc type middle arcs of the three radius positions, (5) enabling the blade middle arcs of the three radius positions of the blade root, the middle and the tip to generate blade profile thickness according to the equal thickness distribution rule from the inlet to the outlet, and stacking the respective gravity centers of the blade arc type middle arcs along the radius direction of the pulley to form a three-dimensional blade, (6) calculating the number of the blades, according to the equal angle distribution in the 360-degree circumference of the synchronous pulley, generating a complete synchronous pulley blade, carrying out integral three-dimensional modeling on the pulley, (7) carrying out structural strength verification and cooling performance verification on the impeller by adopting a test or computer numerical simulation mode, if the structural strength verification is unqualified, reselecting the outer radius of the blade root and the inner radius of the blade tip, returning to the step (2), if the cooling performance verification is unqualified, re-estimating the air flow of the synchronous pulley, returning to the step (3), and if both verifications are qualified, finishing the design.
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| CN115081123A (en) * | 2021-03-16 | 2022-09-20 | 广东博智林机器人有限公司 | Synchronous belt transmission type selection method and device, electronic equipment and storage medium |
| CN114184066B (en) * | 2021-12-14 | 2025-05-06 | 蚌埠市和平乳业有限责任公司 | Heat exchange type dairy product cooling device |
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| CN102945292A (en) * | 2012-09-24 | 2013-02-27 | 西安理工大学 | Method for determining wing-shaped oblique-flow cooling fan of automobile engine |
| JP2014240685A (en) * | 2013-06-11 | 2014-12-25 | 株式会社リコー | Gear design support method, program and device |
| CN206159420U (en) * | 2016-11-16 | 2017-05-10 | 福建双延兴业传动科技股份有限公司 | Synchronous pulley with self -cooling effect |
| CN107269583A (en) * | 2017-07-21 | 2017-10-20 | 哈尔滨工业大学 | A kind of super/transonic speed axial fan designs method based on high-order moment |
| CN206785971U (en) * | 2017-06-03 | 2017-12-22 | 福建双延兴业传动科技股份有限公司 | A kind of cooling type synchronous pulley |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| US6856941B2 (en) * | 1998-07-20 | 2005-02-15 | Minebea Co., Ltd. | Impeller blade for axial flow fan having counter-rotating impellers |
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Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102945292A (en) * | 2012-09-24 | 2013-02-27 | 西安理工大学 | Method for determining wing-shaped oblique-flow cooling fan of automobile engine |
| JP2014240685A (en) * | 2013-06-11 | 2014-12-25 | 株式会社リコー | Gear design support method, program and device |
| CN206159420U (en) * | 2016-11-16 | 2017-05-10 | 福建双延兴业传动科技股份有限公司 | Synchronous pulley with self -cooling effect |
| CN206785971U (en) * | 2017-06-03 | 2017-12-22 | 福建双延兴业传动科技股份有限公司 | A kind of cooling type synchronous pulley |
| CN107269583A (en) * | 2017-07-21 | 2017-10-20 | 哈尔滨工业大学 | A kind of super/transonic speed axial fan designs method based on high-order moment |
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