GB2593558A - Axial-flow pump impeller design method based on axial distance - Google Patents
Axial-flow pump impeller design method based on axial distance Download PDFInfo
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- GB2593558A GB2593558A GB2012612.4A GB202012612A GB2593558A GB 2593558 A GB2593558 A GB 2593558A GB 202012612 A GB202012612 A GB 202012612A GB 2593558 A GB2593558 A GB 2593558A
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- 238000000034 method Methods 0.000 title claims abstract description 31
- 238000013461 design Methods 0.000 title claims abstract description 26
- 230000004323 axial length Effects 0.000 claims abstract description 26
- 230000008719 thickening Effects 0.000 claims abstract description 21
- 230000004048 modification Effects 0.000 claims description 47
- 238000012986 modification Methods 0.000 claims description 47
- 238000004364 calculation method Methods 0.000 claims description 6
- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 description 13
- 230000008901 benefit Effects 0.000 description 4
- 238000010276 construction Methods 0.000 description 4
- 238000012423 maintenance Methods 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000000903 blocking effect Effects 0.000 description 1
- 238000006243 chemical reaction Methods 0.000 description 1
- 238000011161 development Methods 0.000 description 1
- 230000018109 developmental process Effects 0.000 description 1
- 230000007613 environmental effect Effects 0.000 description 1
- 239000012530 fluid Substances 0.000 description 1
- 230000002262 irrigation Effects 0.000 description 1
- 238000003973 irrigation Methods 0.000 description 1
- 238000004519 manufacturing process Methods 0.000 description 1
- 238000000746 purification Methods 0.000 description 1
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Classifications
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D29/00—Details, component parts, or accessories
- F04D29/18—Rotors
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D3/00—Axial-flow pumps
- F04D3/005—Axial-flow pumps with a conventional single stage rotor
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D29/00—Details, component parts, or accessories
- F04D29/02—Selection of particular materials
- F04D29/026—Selection of particular materials especially adapted for liquid pumps
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D29/00—Details, component parts, or accessories
- F04D29/18—Rotors
- F04D29/181—Axial flow rotors
-
- G—PHYSICS
- G06—COMPUTING; CALCULATING OR COUNTING
- G06F—ELECTRIC DIGITAL DATA PROCESSING
- G06F30/00—Computer-aided design [CAD]
- G06F30/10—Geometric CAD
- G06F30/17—Mechanical parametric or variational design
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2240/00—Components
- F05D2240/20—Rotors
- F05D2240/30—Characteristics of rotor blades, i.e. of any element transforming dynamic fluid energy to or from rotational energy and being attached to a rotor
- F05D2240/301—Cross-sectional characteristics
-
- G—PHYSICS
- G06—COMPUTING; CALCULATING OR COUNTING
- G06F—ELECTRIC DIGITAL DATA PROCESSING
- G06F2113/00—Details relating to the application field
- G06F2113/08—Fluids
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- Engineering & Computer Science (AREA)
- General Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Physics & Mathematics (AREA)
- Geometry (AREA)
- General Physics & Mathematics (AREA)
- Theoretical Computer Science (AREA)
- Pure & Applied Mathematics (AREA)
- Computer Hardware Design (AREA)
- Evolutionary Computation (AREA)
- Mathematical Optimization (AREA)
- Mathematical Analysis (AREA)
- Computational Mathematics (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
Disclosed is an axial-flow pump impeller design method based on an axial distance, the method comprising the following steps: (1) on the basis of an axial-flow pump impeller axial length L design function L = l × sinβL, and according to given design parameters, i.e. a flow Q, a lift H, a rotating speed n and a specific speed ns, designed for an axial-flow pump, dividing sections at equal intervals from a hub of an impeller to an outer edge of the impeller, and determining the number of the sections and the number of blades by means of the specific speed ns; then, determining an airfoil chord length l and a blade angle βL of the impeller of the axial flow pump; (2) by taking the airfoil chord length l and the blade angle βL as benchmark coefficients, determining the diameter D of the impeller, the diameter dh of the hub, and a pitch t; and (3) selecting a 791 airfoil thickness variation rule for blade thickening. The method can effectively control the axial length of an impeller of an axial-flow pump.
Description
METHOD FOR DESIGNING AXIAL-FLOW PUMP IMPELLER BASED ON AXIAL DISTANCE
Technical Field
The present invention relates to the field of fluid machinery design, and in particular,to a method for designing an axial-flow pump impeller based on axial distance.
Background
Pump stations and gates are important parts in hydraulic engineering, environmental protection, urban water supply and drainage, enterprise water affairs and the like, where pumps are irrigation and drainage equipment, and gates are low-head hydraulic structures that regulate water levels and control flow. A conventional pump-gate is generally constructed in a manner of combining axial-flow water pumps with a gate, that is, arranging a gate in the middle of the cross-section of a river channel and arranging a water pump on each side of the gate. Such a pump-gate separation design results in that the discharge volume of the conventional pump-gate is much lower than actual needs; therefore, timely and effective flood diversion usually fails during flood season, and the efficiency of pollution control by river water exchange is far from being satisfactory. Meanwhile, this arrangement also limits the cross-section of the river channel and slows down the river flow, which is unfavorable to water exchange and circulation of inland rivers, fails to meet the requirements of the inland water ecological environment, and impairs the self-purification capacity of the rivers In a new integrated pump-gate, a pump unit is directly arranged on a gate, and the gate not only serves as a water blocking structure, but also as a supporting base of the water pump; therefore, the gate and the pump station are integrated. Compared with a conventional pump-gate, the integrated pump-gate has the following advantages: (1) since the pump is vertically installed on the gate, no additional pump room is needed, the cross-sectional area of the river is more than doubled when the gate is lifted, and the pump can significantly speed up water discharge when the gate is lowered; (2) only the power distribution room, water pump, gate, and flap valve are needed, the main plant does not need to be built, no auxiliary oil, water and gas systems are required, and it takes up a small area and is easy and rapid to construct; therefore, the investment in the construction work and electromechanical equipment of the pump station is lowered; (3) by mounting auxiliary facilities such as a level control system and an automatic gate control system, coordinated control of the whole system can be achieved, unattended and automatic control can be truly realized, and the manual maintenance cost at a later stage of the pump-gate is largely reduced.
The current design of integrated pump-gates mostly focuses on optimizing the gate structure and improving the forebay and afterbay flow state. The axial-flow pump functions as key power equipment of an integrated pump-gate and is generally directly selected from existing products. In fact, limited by the thickness of the gate, the integrated pump-gate requires the axial length of the axial-flow pump to be as short as possible. A greater axial length of the axial-flow pump leads to a thicker gate, which results in a significant increase of the design, manufacturing, operation, and maintenance costs of the integrated pump-gate and also a large decrease of the response speed of the gate. Thus, the existing axial-flow pump products cannot well meet the structural and performance requirements of the integrated pump-gate. Therefore, it is in urgent need of a simple and practical method for designing an axial-flow pump impeller based on axial distance, so that the hydraulic performance of the axial-flow pump can be ensured, and the axial length of the axial-flow pump impeller can be effectively controlled according to actual needs.
In view of the above, a method for designing an axial-flow pump impeller based on axial distance is proposed. In this method, an airfoil chord length / and a blade angle jk, of the axial-flow pump impeller are determined based on /,=/xsinjk and by using the capacity 0, head H, and rotary speed n according to actual needs; other design parameters such as impeller diameterD, hub diameter clh, and pitch t of the impeller are determined based on the airfoil chord length land the blade angle /IL of the impeller; finally, the thickness variation pattern of airfoil 791 is selected for blade thickening.
So far, no method for designing an axial-flow pump impeller based on axial length has been publicly proposed. The present invention provides a method for designing an axial-flow pump impeller based on axial distance.
Summary
The objective of the present invention is to provide a method for designing an axial-flow pump impeller based on axial distance, comprising the following steps: Sl: based on the axial length L=/xsinik of an axial-flow pump, and according to given design parameters of capacity 0, head if, rotary speed n, and specific speed 17s of the axial-flow pump, obtaining sections by division at an equal interval from the hub to the outer edge of the impeller, and determining the number of sections and the number of blades through the specific speed 'is; and then determining the airfoil chord length I and the blade angle& related to the axial length L of the axial-flow pump impeller; 52: when Li/L=0.95-I, where Li is the desired axial length and f is the axial length of the outermost section, determining the impeller diameter D, hub diameter di, and pitch t by using the airfoil chord length / and the blade angle /31_, of the axial-flow pump impeller as reference parameters; S3: selecting the thickness variation pattern of airfoil 791 for blade thickening with reference to the airfoil chord length /.
The technical solution of the present invention is as follows.
In Step S I, the airfoil chord length /and the blade angle /iL are determined through the capacity 0, head H, and rotary speed n by using the following calculation method: (1) determining the number of sections and the number of blades in the impeller design: dividing the axial-flow pump impeller into 4-6 sections, where the sections are obtained by division at an equal interval from the hub to the outer edge of the impeller; and determining the number of sections and the number of blades through the specific speed ns; Specific ii < 450 450 <n < 800 800 < its speed II, The number 4 5 6 of sections of the impeller Specific speed ns ns < 600 600 < ris < 850 850 < ns < 1500 The number of blades 5 4 3 (2) calculating the airfoil chord length / according to a lifting design method: determining the airfoil chord length ic through the airfoil chord length 1, of the outermost section; when the number of sections of the impeller is 6, the outermost section being the section 6; when the number of sections of the impeller is 5, the outermost section being the section 5; and when the number of sections of the impeller is 4, the outermost section being the section 4; 89.3 x a where a is a modification coefficient valued in the following method: The number of blades z 3 4 5 Modification coefficient a(6 4.2-6.3 6.3-8.9 8.9-I 0.2 sections) Modification coefficient a (5 3.4-5.8 5.8-7.6 7.6-9.4 sections) Modification coefficient a (4 2.8-5.5 5.5-7.3 7.3-8.9 sections) determining the airfoil chord length L of the airfoil section by using the following general formula: = a1 x where a, is a proportionality coefficient valued in the following table: -Section No. The number of sections 1 2 3 4 5 6 4 0.651-0.728 0.793-0.873 0.894-0.981 1 0.623-0.685 0.712-0.787 0.826-0.894 0.931-0.963 1 6 0.489-0.553 0.586-0.653 0.705-0.781 0.793-0.842 0.856-0.925 1 (3) calculating the blade angle /31_, according to the lifting design method: determining the blade angle fir., of the airfoil section through blade angle /11.,. at the outermost section; the blade angle flL,,, at the outermost section being calculated in the following method: vm1 = vm2 = TE X (0.276 -b) u= 0.00843 xj(7xn-xn 12.9 x H V112 - )62 = arctan U -vu, 11 + /32 fia, = 2 = arctan llmi Vm2 where Vmu is inlet meridional velocity; Vm2 is outlet meridional velocity; is is circumferential velocity; V-112 is component of rotation velocity; flu is inlet blade angle; outlet blade angle; b is a modification coefficient determined through the specific speed; Specific speed n, 0-380 380-610 610-930 930-1500 Modification 0.21-0.28 0.16-0.21 0.12-0.16 0.05-0.12 coefficient b (6 sections) Modification 0.19-0.24 0.13-0.19 0.08-0.13 0.03-0.08 coefficient b (5 sections) Modification 0.16-0.22 0.13-0.16 0.07-0.13 0.03-0.07 coefficient b (4 sections) determining the blade angle /ke of the airfoil section by using the following general formula: PLC = b1 x AAA, where b1 is a proportionality coefficient valued in the following table: Section No. The number of I 2 3 4 5 6 sections ' N 4 1.92-2.24 1.52-1.73 1.36-1.56 1 1.84-2.18 1.43-1.68 1.22-1.34 1.06-1.15 1 6 1.72-2.06 1.21-1.53 1.17-1.42 0.97-1.21 0.83-0.92 1 (4) the axial length L determining the axial length of the axial-flow pump impeller by means of L=fxsinjk; Li being the desired axial length; in, being the axial length of the outermost section; the allowable range of design errors being 5%, that is, 1:13:=0.95-I; if Li>/: and the error is greater than 5%, returning to Step (2) to increase the value of the modification coefficient a, or returning to Step (3) to increase the value of the modification coefficient h; if Li<L and the error is greater than 5%, returning to Step (2) to reduce the value of the modification coefficient a, or returning to Step (3) to reduce the value of the modification coefficient b.
In Step S2, the impeller diameter D, hub diameter dh, and pitch t are determined through the airfoil chord length I and the blade angle It: (1) the impeller diameter D determining the impeller diameter a of each section by using the following general formula: 10.5 + lgl, D, = cx K x the maximum diameter D". of the impeller being determined by using the following general formula: 10.5 + lglw D, = c x x where c is a proportionality coefficient, K is a modification coefficient, and their values are determined in the following tables: Section No. 1 2 3 4 5 6 Proportionality 0.5 0.64 0.76 0.98 coefficient c (6 sections) Proportionality 0.5 0.61 0.73 0.85 0.97 coefficient c (5 sections) Proportionality 0.5 0.53 0.57 0.69 0.82 0.93 coefficient c (4 sections) The number of 4 5 6 sections Modification 19.3-22.45 17.8-20.14 15.8-19.6 coefficient K (2) the diameter dh of the impeller hub dh = D x d where A, is the maximum diameter of the impeller, and the hub ratio d is determined through the specific speed ns + 3.87 x sin/3: when n.s. + 3.87 x sin/?L < 470, 0.58 < d < 0.64; when 470 < ?Ts + 3.87 x sin/IL < 720, 0.52 < d < 0.58; when 720 < n + 3.87 x sin/IL < 940, 0.44 < d < 0.52; when 940 < n + 3.87 x sin/IL < 1200, 0.36 < d < 0.44; when 1200 < its + 3.87 x sinflt 1500, 0.3 < d < 0.36; (3) the pitch / determining the pitch te of each section by using the following general formula: TI X D, t, -In Step S3, the thickness variation pattern of airfoil 791 is selected for blade thickening: (I) the maximum airfoil thickness 6,,,, mar = (0.012 -0.015) X D, X VT-i (2) adopting the thickness variation pattern of airfoil 791 for thickening with reference to the airfoil chord length 4 the thickness variation pattern of airfoil 791 being shown in the following table, where x is the distance away from the left edge of' the airfoil, and 6 is the airfoil thickness; x /1 0 0.05 0.075 0.1 0.2 0.3 0.4 0.5 0.6 6/5max 0 0.296 0.405 0.489 0.778 0.92 0.978 1.0 0.883 x/1 0.7 0.8 0.9 0.95 1.0 3/6",a" 0.756 0.544 0.356 0.2 0 (3) thickening: back-side thickening by using the profile as a working surface. The present invention has the following beneficial effects: (1) the method for designing an axial-flow pump impeller based on axial distance can be perfectly adapted to an integrated pump-gate with a small axial length; (2) compared with conventional design methods that adopt similar models for conversion and thus have low efficiency and poor adaptability, this method provides formulas capable of rapidly determining the dimensions of the axial-flow pump impeller, thereby achieving advantages of good adaptability, rapid calculation, and high efficiency; (3) the existing hydraulic design methods of axial-flow pumps mainly focus on ensuring the capacity and head, resulting in an excessively large axial length of the axial-flow pump; whereas, the provided design method can control the axial length of the axial-flow pump while ensuring the capacity and head; (4) the established method for designing an axial-flow pump impeller based on axial distance has advantages of short construction period and low construction cost; (5) the established method for designing an axial-flow pump impeller based on axial distance can break the bottleneck of the development of the integrated pump-gate; (6) with the construction of national hydraulic engineering, the update of national large, medium, and small-sized pump stations has increasingly higher requirements on parameters of the axial-flow pump; therefore, the present invention will achieve higher economic and social benefits.
Brief Description of the Drawings
FIG. I is an axial sectional view of an impeller in Embodiment I. FIG. 2 is a sectional view of a blade.
FIG. 3 is a schematic view of airfoil thickening.
FIG. 4 is a flow chart of the present invention.
In the drawings, /-airfoil chord length, A-blade angle, D-impeller diameter, di-hub diameter, t-pitch, 1-section 1, 2-section 2, 3-section 3, 4-section 4, 5-section 5, x-distance away from the left edge of the airfoil, 6-airfoil thickness, 6,,",-maximum airfoil thickness.
Detailed Description of the Embodiments
Embodiment: In the design of an axial-flow pump, capacity 0=0.35 ms/s, head 11=6.72 m, rotary speed n=1450 r/min, and axial length L1=26 mm. The present invention is further illustrated below.
I. The airfoil chord length/and the blade angle A are determined through the capacity 0, head H, and rotary speed n by using the following calculation method: (I) determining the number of sections and the number of blades in the impeller design: 3.65 x n x 3.65 x 1450 x V0.35 ns -H3/4 = 6.723/ -7504 the number of sections of the impeller being 5 according to the following table: Specific speed ns ns < 450 450 < ns < 800 800 < ns The number 4 5 6 of sections of the impeller z=4 according to the following table: Specific speed ns. 0-600 600-850 850-1500 The number of blades 3 4 5 (2) the airfoil chord length / as for the airfoil chord length 15 of the section 5, a=6 according to the following table: The number of blades z 3 4 5 Modification coefficient a 3.4-5.8 5.8-7.6 7.6-9.4 89.3xa 89.3x6 V0.35 79.2 therefore, = X VQ - X = mm, as for the airfoil chord length 14 of the section 4, according to 14 = a1 x 15 = (0.931 -0.963) x /5, /4 = 0.951 x 15 = 0.951 x 79.2 = 75.3 mm; as for the airfoil chord length 13 of the section 3, according to 13 = a1 x 15 = (0.826 -0.894) x 15, 13 = 0.842 x 15 = 0.842 x 79.2 = 66.7 mm, as for the airfoil chord length /2 of the section 2, according to 12 = al x 15 = (0.712 -0.787) x 15 1 = 0.762 x /5 = 0.762 x 79.2 = 60.4 mm; as for the airfoil chord length /1 of the section 1, according to = a1 x /5 = (0.623 -0.685) x /5 /1 = 0.651 x /5 = 0.651 x 79.2 = 51.6 mm, (3) the blade angle fit.
as for the blade angle /11,5 of the section 5, since n = 750, b=0.1 according to the following table: Specific speed ns 0-380 380-610 610-930 930-1500 Modification 0.19- 0.13- 0.08-0.13 0.03-0.08 coefficient b 0.24 0.19
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VmlVm2 -7.23 m/s 7F X (0.276 -b) iv x (0.276 -0.1) u= 0.00843 xVVx 7 xn= 0.00843 x V0.35 xiv x 1450 = 22.72 m/s 12. 9 x H 12.9 x 6. 72 Vu2 = -3.82 m/s 22.72 Vnil 7.23 fli = arctan-u = arctan 22.72 = 17.65° U v-mv2u2 22.7 7.23 )32 = arctan -aretan 2 -3.82 -20.93° p _ 13,-F/3, 17.65+20.93 PL5 - -19.29'; 2 2 as for the blade angle AA of the section 4, according to 13f,4 = b1 x fln," = (1.06 -1.15) 21.60'; as for the blade angle 111.3 of the section 3, according to)3E3 = 1)1 x MA," = (1.22 -1.34) x fiL3 -1.31 x fiLs = 1.31 x 19.29 = 25.27'; as for the blade angle,61.2 of the section 2, according to 131,2 = bi x /3E, = (1.43 -1.68) 29.51'; as for the blade angle,6L2 of the section 1, according to /3Li = bi x /3E, = (1.84 -2.18) XJ3J,, = 2.02 x /3L, = 2.02 x 19.29 = 38.97'; (4) the axial length L L, = 1 x sim3L, = 79.2 x sin19.29° = 26.16 mm L, 26 0.99 L" 26.16 the error range being less than 5%, which meets the design requirement.
x 13f,5 /3L4 = 1.12 x,8L5 = 1.12 x 19.29 = x fiLs 13L2 -1.53 x fiLs = 1.53 x 19.29 = 2. The impeller diameter D, hub diameter dh, and pitch / are determined through the airfoil chord length land the blade angle /1L by using the following calculation method: (1) the impeller diameter D the impeller diameter 1)5 of the section 5: 10.5 + 1913 10.5 + 1g79.2 c x = 0.374 m = 374 mm Ds = x = 0.97 x 19 x the impeller diameter 1)4 of the section 4: 10.5 + 1914 10.5 + 1g75.3 C x x V0.35 = 0.327 m = 327 mm D4 X -0.85 x 19 the impeller diameter D3 of the section 3: 10.5 + 1913 10.5 + /g66.7 D3 C X X -0.73 x 19 x il0.35 = 0.280 m = 280 mm the impeller diameter 1)2 of the section 2: 10.5 + 1912 10.5 + /g60.4 D2=CX X1112= 0.61 x 19 x V0.35 = 0.233 m = 233 mm the impeller diameter Di of the section 1: 10.5 + 1911 10.5 + 1g51.6 = 0.5 x x,F2 = 0.5 x 19 x VO.35 = 0.191 m = 191 mm (2) the impeller hub diameter dh since ?Ls + 3.87 x sin& = 750 + 3.87 x sin38.58° = 752, d = 0.51 according to the following table: ns + 3.87 x sink'', 0-470 470-720 720-940 940-I 200 I 200-1500 Hub ratio d 0.58-0.64 0.52-0.58 0.44-0.52 0.36-0.44 0.3-0.36 dh = D1/4, x d = 374 x 0.51 = 191 mm; (3) the pitch t the pitch t5 of the section 5: 7T X Ds mx374 t5= = -294 mm the pitch t4 of the section 4: = 257 mm TE X D4 mx327 t4= the pitch 13 of the section 3: 7 X D3 7 X 280 t3 = -220 mm the pitch t2 of the section 2: 7 X D2 7 X 233 t2 = -183 mm the pitch ti of the section 1: 7 X Di 7 X 190 - 4 -149 mm 3. The thickness variation pattern of airfoil 791 is adopted for thickening with reference to the airfoil chord length /: (1) the airfoil thickness of the section 5 A. the maximum airfoil thickness 6,"" according to 6,,"" = (0.012 -0.015) x D5 X 07, Smax = 0.014 X D5 X -1,ifi = 0.014 x 0.374 x V6.72 = 0.01357 m = 13.57 mm B. adopting the thickness variation pattern of airfoil 791 for thickening with reference to the airfoil chord length I, the corresponding airfoil thickness being shown in the following table: x// 0 0.05 0.075 0.1 0.2 0.3 0.4 0.5 0.6 0 4.017 5.496 6.636 10.557 12.484 13.271 13.57 11.982 x/1 0.7 0.8 0.9 0.95 1.0 8 10.259 7.382 4.831 2.714 0 (2) the airfoil thickness of the section 4 A. the maximum airfoil thickness according to 6,na, = (0.012 -0.015) x D4 x, Smax = 0.014 x D. X 1,T1 = 0.014 x 0.327 xVC72 = 0.01187 m = 11.87 mm B. adopting the thickness variation pattern of airfoil 791 for thickening with reference to the airfoil chord length), the thickness variation pattern of airfoil 791 being shown in the following table: x// 0 0.05 0.075 0.1 0.2 0.3 0.4 0.5 0.6 6 0 3.514 4.807 5.804 9.235 10.920 11.609 11.87 10.481 x/1 0.7 0.8 0.9 0.95 1.0 6 8.974 6.457 4.226 2.374 0 (3) the airfoil thickness of the section 3 A. the maximum airfoil thickness 6,..na, according to 6,a, = (0.012 -0.015) x D3 X VW, 6max = 0.014 x D3 X = 0.014 x 0.28 x V6.72 = 0.01016 in = 10.16 mm B. adopting the thickness variation pattern of airfoil 791 for thickening with reference to the airfoil chord length the thickness variation pattern of airfoil 791 being shown in the following table: x// 0 0.05 0.075 0.1 0.2 0.3 0.4 0.5 0.6 6 0 3.001 4.114 4.968 7.904 9.347 9.936 10.16 8.971 x/1 0.7 0.8 0.9 0.95 1.0 6 7.112 8.128 9.144 9.652 10.16 (4) the airfoil thickness of the section 2 A. the maximum airfoil thickness according to 6mar = (0.012 -0.015) X D2 X VII, Smax = 0.014 X D2 X Vi? = 0.014 x 0.233 xVC72 = 0.00846 m = 8.46 mm B. adopting the thickness variation pattern of airfoil 791 for thickening with reference to the airfoil chord length), the thickness variation pattern of airfoil 791 being shown in the following table: x// 0 0.05 0.075 0.1 0.2 0.3 0.4 0.5 0.6 6 0 2.504 3.426 4.137 6.582 7.783 8.274 8.46 7.470 x/I 0.7 0.8 0.9 0.95 1.0 6 5.922 6.768 7.614 8.037 8.46 (5) the airfoil thickness of the section 1 A. the maximum airfoil thickness 6",", according to max = (0.012 -0.015) x x VU, 8",a" = 0.014 x x = 0.014 x 0.191 x V6.72 = 0.00219 m = 2.19 mm B. adopting the thickness variation pattern of airfoil 791 for thickening with reference to the airfoil chord length the thickness variation pattern of airfoil 791 being shown in the following table: x// 0 0.05 0.075 0.1 0.2 0.3 0.4 0.5 0.6 6 0 0.648 0.887 1.071 1.704 2.015 2.142 2.19 1.934 x/1 0.7 0.8 0.9 0.95 1.0 6 1.533 1.752 1.971 2.081 2.19 (6) thickening: back-side thickening by using the profile as a working surface.
Claims (4)
- Claims What is claimed is: 1. A method for designing an axial-flow pump impeller based on axial distance, characterized by specifically comprising the following steps: (5 1) based on a design function L=/xsinfiL of the axial length L of the axial-flow pump impeller, and according to given design parameters of capacity 0, head I-T, rotary speed n, and specific speed n, of an axial-flow pump, obtaining sections by division at an equal interval from the hub to the outer edge of the impeller, and determining the number of sections and the number of blades through the specific speed ns; and then determining the airfoil chord length land the blade angle /31, related to the axial length L of the axial-flow pump impeller; (52) when Li/L},=0.95-1, where Li is the desired axial length and L", is the axial length of the outermost section, determining the impeller diameter D, hub diameter c/11, and pitch t by using the airfoil chord length / and the blade anglek of the axial-flow pump impeller as reference parameters; (53) selecting the thickness variation pattern of airfoil 791 for thickening with reference to the airfoil chord length /.
- 2. The method for designing the axial-flow pump impeller based on the axial distance according to claim 1, characterized in that in Step 51, the airfoil chord length / and the blade angle /31. are determined through the capacity 0, head H, and rotary speed n by using the following calculation method: ( I) determining the number of sections and the number of blades in the impeller design according to the specific speed n5: dividing the axial-flow pump impeller into 4-6 sections, where the sections are obtained by division at an equal interval from the hub to the outer edge of the impeller; and determining the number of sections and the number of blades through the specific speed m; when the specific speed satisfies acc-450, the number of sections of the impeller being 4; when the specific speed satisfies 450 < n < 800, the number of sections of the impeller being when the specific speed satisfies 800 < ns, the number of sections of the impeller being 6; when the specific speed satisfies ns<600, the number of blades being 5; when the specific speed satisfies 600 < ns < 850, the number of blades being when the specific speed satisfies 850 < ns < 1500, the number of blades being 3; (2) calculating the airfoil chord length / according to a lifting design method: determining the airfoil chord length 1, of the airfoil section through the airfoil chord length 1,, of the outermost section; when the number of sections of the impeller is 6, the outermost section being the section 6; when the number of sections of the impeller is 5, the outermost section being the section 5; and when the number of sections of the impeller is 4, the outermost section being the section 4; 89.3 x a j-where a is a modification coefficient valued in the following method: when the number of sections is 6 and the number of blades z is 3, the modification coefficient a-4.2-6.3, when the number of sections is 6 and the number of blades z is 4, the modification coefficient when the number of sections is 6 and the number of blades z is 5, the modification coefficient a=8. 9-10. 2, when the number of sections is 5 and the number of blades z is 3, the modification coefficient when the number of sections is 5 and the number of blades z is 4, the modification coefficient r5.8-76, when the number of sections is 5 and the number of blades z is 5, the modification coefficient a-7.6-9.4, when the number of sections is 4 and the number of blades z is 3, the modification coefficient a =2. 8-5.5, when the number of sections is 4 and the number of blades z is 4, the modification coefficient a=5.5-7.3, when the number of secti is 4 and the number of blades z is 5, the modification coefficient (1-7.3-8.9, determining the airfoil chord length 1c of the airfoil section by using the following general formula: ic = a1 x Iw where al is a proportionality coefficient valued as follows: when the number of sections is 4, al of the section 1 being 0.651-0.728, al of the section 2 being 0.793 -0.873, al of the section 3 being 0.894-0.981, and al of the section 4 being 1, when the number of sections is 5, al of the section 1 being 0.623-0.685, al of the section 2 being 0.712-0.787, al of the section 3 being 0.826-0.894, al of the section 4 being 0.931-0.963, and al of the section 5 being 1, when the number of sections is 6, al of the section I being 0.489-0.553, al of the section 2 being 0.586-0.653, al of the section 3 being 0.705-0.781, al of the section 4 being 0.793-0.842, al of the section 5 being 0.856-0.925, and al of the section 6 being 1; (3) calculating the blade angle /IL according to the lifting design method: determining the blade angle //Lc of the airfoil section through the blade angle fiLw at the outermost section; the blade angle /11_,,, at the outermost section being calculated in the following method: vma. = vraz it x (0.276 -b) u = 0.00843 xj2xmx rt 12.9 x H vuz = ons vna = arctan Vm2 12 = arctan U via + )62 fix,w 2 where Vmt is inlet meridional velocity; V,,,2 is outlet meridional velocity; it is circumferential velocity; a, is component of rotation velocity; flu is inlet blade angle; outlet blade angle; b is a modification coefficient determined through the specific speed; in the case that the number of sections is 6, when the specific speed ns is 0-380, the modification coefficient b being 0.21-0.28; when the specific speed n, is 380-610, the modification coefficient b being 0.16-0.21; when the specific speed ns is 610-930, the modification coefficient b being 0.12-0.16; when the specific speed ns is 930-1500, the modification coefficient b being 0.05-0.12; in the case that the number of sections is 5, when the specific speed ns is 0-380, the modification coefficient b being 0.19-0.24; when the specific speed ns is 380-610, the modification coefficient b being 0.13-0.19; when the specific speed ns is 610-930, the modification coefficient b being 0.08-0.13; when the specific speed n, is 930-1500, the modification coefficient b being 0.03-0.08; in the case that the number of sections is 4, when the specific speed tit; is 0-380, the modification coefficient b being 0.16-0.22; when the specific speed ns is 380-610, the modification coefficient b being 0.13-0.16; when the specific speed ns is 610-930, the modification coefficient b being 0.07-0.13; when the specific speed ns is 930-1500, the modification coefficient b being 0.03-0.07; determining the blade angle Ac of the airfoil section by using the following general formula: filc = b1 x f364/ where b1 is a proportionality coefficient valued as follows: when the number of sections is 4, b1 of the section I being 1.92-2.24, 191 of the section 2 being 1.52-1.73, b1 of the section 3 being 1.36-1.56, and b1 of the section 4 being 1; when the number of sections is 5, b1 of the section 1 being 1.84-2.18, b1 of the section 2 being 1.43-1.68, b, of the section 3 being 1.22-1.34, b1 of the section 4 being 1.06-1.15, and b, of the section 5 being 1; when the number of sections is 6, b1 of the section 1 being 1.72-2.06, b1 of the section 2 being 1.21-1.53, b1 of the section 3 being 1.17-1.42, b1 of the section 4 being 0.97-1.21, b1 of the section 5 being 0.83-0.92, and b1 of the section 6 being 1; (4) determining the axial length of the axial-flow pump impeller by means of L=// sin,8L; Li being the desired axial length; in, being the axial length of the outermost section; the allowable range of design errors being 5%, that is, /4//,,=0.95-1; if L1>Lir and the error is greater than 5%, returning to Step (2) to increase the value of the modification coefficient a, or returning to Step (3) to increase the value of the modification coefficient h if Li<L,, and the error is greater than 5%, returning to Step (2) to reduce the value of the modification coefficient a, or returning to Step (3) to reduce the value of the modification coefficient b.
- 3. The method for designing the axial-flow pump impeller based on the axial distance according to claim 1 or 2, characterized in that in Step S2, the impeller diameter D, hub diameter di, and pitch t are determined through the airfoil chord length / and the blade angle /31_, by using the following calculation method: (1) the impeller diameter D determining the impeller diameter D, of each section by using the following general formula: 10.5 + lgl, D, -c x x the maximum diameter D". of the impeller being determined by using the following general formula: 10.5 + lglw D" -c x K x where c is a proportionality coefficient, K is a modification coefficient, and their values are determined as follows: when the number of sections is 4, the modification coefficient K being 19.3-22.45; the proportionality coefficient c of the section 1 being 0.5, the proportionality coefficient c of the section 2 being 0.64, the proportionality coefficient c of the section 3 being 0.76, and the proportionality coefficient c of the section 4 being 0.98; when the number of sections is 5, the modification coefficient K being 17.8-20.14; the proportionality coefficient c of the section 1 being 0.5, the proportionality coefficient c of the section 2 being 0.61, the proportionality coefficient c of the section 3 being 0.73, the proportionality coefficient c of the section 4 being 0.85, and the proportionality coefficient c of the section 5 being 0.97, when the number of sections is 6, the modification coefficient K being 15.8-19.6; the proportionality coefficient c of the section 1 being 0.5, the proportionality coefficient c of the section 2 being 0.53, the proportionality coefficient c of the section 3 being 0.57, the proportionality coefficient c of the section 4 being 0.69, the proportionality coefficient c of the section 5 being 0.82, and the proportionality coefficient c of the section 6 being 0.93; (2) the diameter di, of the impeller hub 4 = D x where kY4. is the maximum diameter of the impeller, and the hub ratio d is determined through the specific speed it5 + 3.87 x sinfiL: when it + 3.87 x sinflL < 470, 0.58 < d < 0.64; when 470 < n, + 3.87 x sinf3L < 720, 0.52 < d < 0.58; when 720 < ns + 3.87 x sin/IL < 940, 0.44 < d < 0.52; when 940 < ns + 3.87 x sin/IL < 1200, 0.36 < d < 0.44; when 1200 < rts + 3.87 x sin& < 1500, 0.3 < d < 0.36; (3) the pitch t determining the pitch te of each section by using the following general formula: 71-X D, t, -
- 4. The method for designing the axial-flow pump impeller based on the axial distance according to claim 1, characterized in that in Step S3, the thickness variation pattern of airfoil 791 is selected for thickening: (I) the maximum airfoil thickness 6,,,, 6","x = (0.012 -0.015) x D, x (2) adopting the thickness variation pattern of airfoil 791 for thickening with reference to the airfoil chord length 1, the thickness variation pattern of airfoil 791 being shown as follows, where x is the distance away from the left edge of the airfoil, and 6 is the airfoil thickness; when x// is 0, 6/6,,", being 0; when x/1 is 0.05,6/6,flaxbeing 0.296; when x// is 0.075, 6/6,"x being 0.405; when x// is 0.1,6/6,flaxbeing 0.489; when x/1 is 0.2, 6/6,na, being 0.778; when x// is 0.3, 6/6max being 0.92; when x// is 0.4, 6/6","x being 0.978; when x/1 is 0.5, 6/6".,", being 1.0; when x// is 0.6, 6/6max being 0.883; when x// is 0.7, 6/6max being 0.756; when x// is 0.8, 6/5max being 0.544; when x// is 0.9, 6/67llat being 0.356; when x// is 0.95, 6/6,,,,," being 0.2; when x// is 1.0,6/ömaxbeing 0; (3) thickening: back-side thickening by using the profile as a working surface.
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| Application Number | Priority Date | Filing Date | Title |
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| CN201910113073.4A CN109763995B (en) | 2019-02-13 | 2019-02-13 | Axial flow pump impeller design method based on wheel base |
| PCT/CN2019/077064 WO2020164168A1 (en) | 2019-02-13 | 2019-03-06 | Axial-flow pump impeller design method based on axial distance |
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| GB202012612D0 GB202012612D0 (en) | 2020-09-30 |
| GB2593558A true GB2593558A (en) | 2021-09-29 |
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| CN103994095A (en) * | 2014-04-29 | 2014-08-20 | 江苏大学 | Designing method of multiphase mixed transportation axial flow pump impeller |
| CN105805043A (en) * | 2016-04-07 | 2016-07-27 | 西安理工大学 | Design method for nonadjustable axial flow pump impeller with characteristic of long blades and short blades |
| RU2606290C1 (en) * | 2015-10-22 | 2017-01-10 | Владимир Николаевич Кудеяров | Centripetal impeller pump for transfer of heated non-uniform by density liquids |
| CN108223424A (en) * | 2017-11-30 | 2018-06-29 | 河海大学 | A kind of vertical-type axial-flow pump pumps section |
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| CN101629583A (en) * | 2009-06-23 | 2010-01-20 | 江苏大学 | Methods for calculating and thickening profile of impeller vane of axial flow pump |
| CN201539437U (en) * | 2009-06-23 | 2010-08-04 | 江苏大学 | High-efficiency axial-flow pump impeller |
| CN103696983B (en) * | 2013-12-31 | 2017-03-01 | 江苏大学 | A kind of Double-way axial flow impeller of pump Optimization Design |
| CN103925234B (en) * | 2014-04-10 | 2016-05-25 | 江苏大学 | A kind of wear-resistant axial-flow pump impeller method for designing |
| CN104005983B (en) * | 2014-05-07 | 2016-08-31 | 江苏大学 | A kind of higher specific speed axial-flow pump impeller three operating point method for designing |
| CN204061320U (en) * | 2014-07-28 | 2014-12-31 | 北京新安特风机有限公司 | A kind of axial-flow blower single plate blade structure |
| CN105443433A (en) * | 2015-12-08 | 2016-03-30 | 合肥工业大学 | Design method for cavitation-resistance axial flow pump impeller |
| CN105626574B (en) * | 2015-12-25 | 2018-01-30 | 江苏大学 | A kind of high-lift axial-flow pump impeller Hydraulic Design Method |
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2019
- 2019-02-13 CN CN201910113073.4A patent/CN109763995B/en active Active
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Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103994095A (en) * | 2014-04-29 | 2014-08-20 | 江苏大学 | Designing method of multiphase mixed transportation axial flow pump impeller |
| RU2606290C1 (en) * | 2015-10-22 | 2017-01-10 | Владимир Николаевич Кудеяров | Centripetal impeller pump for transfer of heated non-uniform by density liquids |
| CN105805043A (en) * | 2016-04-07 | 2016-07-27 | 西安理工大学 | Design method for nonadjustable axial flow pump impeller with characteristic of long blades and short blades |
| CN108223424A (en) * | 2017-11-30 | 2018-06-29 | 河海大学 | A kind of vertical-type axial-flow pump pumps section |
| CN109236726A (en) * | 2018-07-31 | 2019-01-18 | 江苏大学镇江流体工程装备技术研究院 | A kind of higher specific speed axial-flow pump impeller angle of outlet and Thickness Design Method |
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| CN109763995A (en) | 2019-05-17 |
| WO2020164168A1 (en) | 2020-08-20 |
| GB202012612D0 (en) | 2020-09-30 |
| GB2593558B (en) | 2022-08-10 |
| CN109763995B (en) | 2020-08-28 |
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